teofflioi - defense technical information center 2.3 debris separation 2-13 ... 4.8.9 communication...
TRANSCRIPT
#
iH CO
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r
TW-LX-12 3/000/00
TEOffliOI RAH ^
(TM Series)
This document was produced by SOC in performance af AF 19(628)-l646t System.496L
Space Track for Elect onic Systems Division, AFSC.
ORBITAL ANALYST
HANDBOOK
k May 196J+
SYSTEM
DEVELOPMENT
CORPORATION
45 HARTWELL AVE.
LEXINGTON
MASSACHUSETTS
0
COMMAND CONTROL DIVISION
CORPORATE OFFICES Santa Monica. Caiifornia
A 1159 IX 7/63
lk August 1964 A Page B Blank
TM-LX-I23/OOO/OOB
MOnHCATIOM Tl TM-LX-123/OOO/OO, "Orbital
Analyst Handbook," dated 4 May 1964
Syitim Dovolopmont Corporation/2500 Colorado Ava./Santa Monica, California
APPROVED
R. E. FergUöfcn
Modified Pages
A and B
CURRENT MODIFICATION
Notes and Filing Instructions
Remove pages A and B, dated 1 July 1964 and insert pages A and B, dated l4 August 1964.
Remove pages 4-33 ar*d. k-^k, dated 4 May 1964 and insert pages 4-33 through k-^kY, dated lk August 1964
•CUMULATIVE LIST OF MODIFICATIONS-
Modified Pages
i-iv 3-1, 3-2 3-35, 3-36 4-7, 4-8 4-9 4-33 thru 4-34Y 5-1 5-3, 5-fc 5-9 thru 5-12 5-27 thru 5-64
Modification Number and Date
A (l July 1964) New pages A (l July 1964) New pages A (l July 1964) New pages A (l July 1964) New pages A (1 July 1964) Errata B (14 August 1964) New pages A (l July 1964) New page A (l July 1964) New pages A (l July 1964) New pages A (l July 1964) New pages A (1 July 1964) New tab
1 July ±96h i TM-LX-123/OOO/OQA
TABLE OF CONTENTS
Page Table of Contents i
Section 1. INTRODUCTION 1-1
Section 2. TASKS 2-1
2.1 DOMESTIC LAUNCH 2-3 2.1.1 Check List 2-3 2.1.2 Task Description 2-4
2.2 FOREIGN LAUNCH PROCESSING ,. .. 2-9 2.2.1 Check List , 2-9 2.2.2 Task Description. 2-10
2.3 DEBRIS SEPARATION 2-13 2.3.1 Check List 2-13 2.3.2 Task Description 2-1 k
2.4 PROXIMITY DETERMINATION 2-15 2.1.1 Check List 2-15 2.4.2 Check List 2-15 2.4.3 Task Description. 2-l6 2.4.4 Task Description 2-l6
2.5 ELEMENT MAINTENANCE 2-17 2.5.1 Check List 2-17 2.5.2 Task Description 2-l8
2.6 DECAY PREDICTION 2-21 2.6.1 Check List 2-21 2.6.2 Task Description 2-22
Section 3. PROCEDURES 3-1
3.1 NOMINAL ELEMENT SET DETERMINATION 3-3 3.1.1 General.. , 3-3 3.1.2 Domestic Launch Information 3*3 3.1.3 Foreign Launch Information 3-7
3.2 INITIAL ELEMENT SET DETERMINATION 3-9 3.2.1 General 3-9 3-2.2 Foreign Launch Information 3-9
3.3 SYSTEM SEAIC FILES UPDATE 3-11 3-3-1 General 3-11 3.3.2 Foreign Launch 3-11 3.3.3 Domestic Launch 3-12 3.3.4 Satellite Maintenance 3-12 3-3-^ SEAI Tape Files Maintenance 3-13
»v
1 July x96k ii IM-LX-123/OOO/0OA
Page
3-4 OBSERVATION ASSOCIATION 3-15 3.4.1 General 3-I5 3.4.2 Gross Association 3-15 3.4.3 Routine Association 3-15 3.4.4 Special Association 3-l6
3.5 ELEMENT CORRECTION 3-19 3.5.1 General 3-19 3.5.2 Complete Correction - Anomalistic Data 3-19 3-5-3 Partial Correction (Time equation only) -
Nodal Data 3-19
3.6 SENSOR TASKING. 3-21 3-6*1 General. 3-21 3.6.2 USAF Sensors 3-21 3.6.3 NAVSPASUR Sensors. 3-21
3.7 BULLETIN GENERATION 3-23 3.7.1 General 3-23
3.8 LOOK ANGLE GENERATION 3-25 3.8.1 General 3-25 3.8.2 Anomalistic Data 3-25 3.8.3 Nodal Data 3-25
3.9 ELEMENT SET ADJUSTMENT 3-27 3.9.1 General 3-27 3.9.2 Foreign Launch Data 3-27 3-9-3 Domestic Launch Data 3-27 3.9.4 Unusual Orbital Data 3-27
3.10 OBSERVATION SELECTION 3-29 3*10.1 General 3-29 3.10.2 Initial Observations 3-29 3.10.3 Element Set Variations 3-29 3.10.4 Observations on an Unusual Orbit 3~30 3.10.5 Observations on Associated Bodies 3-30 3-10.6 Unidentified Observations 3-30
3.11 DECAY PREDICTION 3-33 3.11.1 General. . . 3-33 3.11.2 Initial Decay Indications 3-33 3.H.3 Final Decay Indications 3-33
3.12 ELEMENT CONVERSION 3-35 3.12.1 General. 3.35
I July 1964 iii TM-LX-I23/0OO/OQA
Section 4. PROGRAMS 4-1
4.1 EXECUTIVE AREA 4-3 4.2 ASSOCIATION AREA 4-5 4.2.1 RASSN 4-7 4.2.2 OBSSEP 4-17 4.2.3 REDUCT 4-19 4.2.4 Other 4-27
4.3 ELEMENT DETERMINATION AREA 4-31 4.3.1 ESPOD 4-33 4.3.2 IOANGLE , 4-35 4.3.3 IOHG 4-4l 4.3.4 IORF 4-47 4.3.5 LOCVEC 4-53 4.3.6 ROC 4-57 4.3.7 SEAI 4-61 4.3.8 SGPDC 4-65 4.3.9 SPIRDEC 4-71 4.3.10 SPWDC 4-73 4.3.11 XROADS 4-89 4.3.12 Other 4-97
4.4 OBSERVATION ACQUISITION AREA 4-99 4.4.1 BNSCHED 4-101 4.4.2 BLTNSGP 4-105 4.4.3 GLASGP 4-111 4.4.4 GRNTRK 4-115 4.4.5 LAP 4-119 4.4.6 OBSERV 4-127 4.4.7 PSR 4-133 4.4.8 SYSBULL 4-137 4.4.9 XYZLA 4-147 4.4.10 Other 4-151
4.5 INTERPLANETARY AREA 4-153 4.5.1 HELIO 4-155 4.5.2 MUNENDC 4-169 4.5.3 NEAR 4-179
4.6 SPECIAL PURPOSE AREA 4-187 4.6.1 RESPLT 4-189 4.6.2 Other 4-193
1 July 196U iv IM-LX-123/OOO/OQA
Page
4.7 1620 COMPUTER PROGRAMS 4-197 4.7.1 Jacchia II Satellite Decay Prediction 4-199 4.7.2 King-Hele/Findley Decay Prediction... 4-203 4.7.3 l620 Launch 4-205
4.8 STANDARD SYSTEM INFORMATION 4-209 4.8.1 PCS Sequence. , 4-211 4.8.2 Schedule Tape Operation 4-213 4.8.3 Observation Card Format 4-217 4.8.4 Satellite Number Card Format 4-221 4.8.5 Sensor File Card Format 4-223 4.8.6 Element Set File Card Formats 4-225 4.8.7 Acquisition File Card Format 4-237 4.8.8 Information File Card Format 4-239 4.8.9 Communication File Card Format 4-243 4.8.10 SEAI File Deletion Card Format 4-245
Section 5- APPENDICES 5-1
5.1 FORMS 5-3
5.2 MISCELLANEOUS. 5-11 5.2.1 Conversion Factors 5-13 5.2.2 Modified Julian Days - 1964, 5-17 5.2.3 Oblate Spheriodal Earth Model 5-19 5.2.4 Right Ascension of Greenwich," 0 Jan, 000C£ 5-21 5.2.5 Satellite Elevation and Slant Range 5-23 5..?. 6 Semi-Major Axis Vs. Period 5-25 5.2.7 Mathematical Constants 5-28 5.2.8 Formulas 5-30 5.2.9 Minutes and Seconds to Degrees 5-33
5.3 OBSERVATION REPORT FORMATS 5-35 5.3.1 Standard A Format. 5-35 5.3.2 Station 315 Old Format 5-38 5.3.3 Hoiloman AFB Format, 5-40 5.3.4 Moonwatch Format. .. . .. 5-I1I 5.3.5 SAO Baker-Nunn 5-43 5.3.6 SATEV Format. •" 5-45 5.3.7 SATOF Format 5-48 5.3.8 SATUG Format 5.5O 5.3.9 Trinidad Format 5-52 5.3.10 SYNCOM II Format 5-5U 5.3.11 681/682 Format 5-56 5.3.12 Millstone Format 5-58 5.3.13 Code Tables 5-60
5.4 GLOSSARY. . 5-63
h May 1964 1-1 TM-LX-123/OOO/OO (Page 1-2 Blank)
Section 1
INTRODUCTION
This handbook has been prepared to provide 4«t-Aero&paee Control -Squadron ^ADO)
personnel assigned to the Orbital Analyst position in SPACETRACK with detailed
procedures and standardized methods for accomplishing their assigned tasks in
satellite processing.j These tasks are:
a. Domestic Launch
b. Foreign Launch
c. Debr's Separation
d. Proximity Determination
e. Element Maintenance
f. Decay Prediction
Each task represents a major orbital problem. A check list for each problem
is provided. The required steps leading to the solution of the problem are
identified. Analyst procedures are described and cross-referenced to per-
tinent tasks. Computer programs which support the orbital analyst are or-
ganized by functional area and detailed with respect to their use, input
options and formats, and output format. Other system programs not of primary
interest to the analyst are identified and briefly discussed. Standard
system card formats, the system tape requirements, and the operating modes
are described in detail. Aids, charts, graphs, and other material which
assist in job performance are to be found in the appendix.
f k May 1964 2-1
(Page 2-2 Blank)
Section 2
TM-LX-123/OOO/OO
TASKS
The analyst is responsible for solving a variety of orbital problems. These
may occur independently or in numerous combinations. There are six such
problems, each constituting a task. Each task is described at two levels of
detail. The Check List identifies the major requirements of the task, and the
task description identifies a workable set of procedures which will suffice
for task accomplishment in a majority of cases. Each of the procedures is
referenced to a more detailed description of its use in the Procedures section
of this document.
The following tasks are described:
Task Page
1. Domestic Launch 2-3
2. Foreign Launch 2-9
3. Debris Separation 2-13
k. Orbital Proximity Determination 2-15
5. Element Maintenance 2-17
6. Decay Prediction 2-21
I
2.1 DOMESTIC LAUNCH
k May I96U 2-3 TM-LX-123/000/00
2.1 DOMESTIC LAUNCH
2.1.1 Check List
2.1.1.1 Satellite classification
2.1.1.2 Pre-launch information
2.1.1.3 Pre-launch folder:
a. 1ACS Form 31
b. Calculated element set
c. Computed element set
d. Nominal bulletin
e. Nominal look angles
f. Launch nemo
g. Launch messages
2.1.1.1* Lift-off time
2.1.1.5 Sensor notification
2.1.1.6 Adjusted element set ( Q , T )
2.1.1.7 Sensor notification
2.1.1.8 SPADATS object number
2.1.1.9 International code name
2.1.1.10 Released bulletin and look angles
2.1 DOMESTIC LNJJ':CH
2-4 TM-LX-123/000/00
2.1.2 Task Description
2.1.2.1 Determine security classification of satellite.
2.1.2.2 Gather the following pre-launch information and initiate Form 31, to include:
a.
b.
c.
d.
e.
f.
g.
h.
i.
Nominal number
Day of Launch
PA = anomalistic Period (in ddys), or
a = semi-major axis
i = inclination
e = eccentricity
¢. = injection latitude l.
Aw = injection longitude i
Time from lift-off to injection
j. Direction of satellite motion at I: northerly or southerly
2.1.2.3 Manually calculate a nominal element set (procedure 3.1), as follows: a.
b.
Calculate w :
sin u = sinoj0~ s:i.n i (N.); sin (180°-u) = ( s.)
sin j¢~ sin i
w0 = u, (¢i is +); w0
~ 360°-u, (¢1 is -).
::ct~ Ta1!0] if o0 ~ ~0 ~ 90°, then o0 ~ ~ ~ 90°
cot~- /80j" )SA=: f.] cot [?a; l8oj; if 90° < : 0 ~ 180°,
M0
-:o E - Qe MPA
t,. t = 360°
then 90° < ~ ~ 180° 2
c.
2-5 -
2.1 OOMESTIC LAUNCH
TM-LX-123/000/00
~ Time of lift-off (in days) + Time from lift-off to injection (in days). -i
T0
T1
(in days)- 6.t
NOTE: Nominal time of lift-off is assumed to occur at OOOOZ hours
on the doy of launch.
Calculate 0 (wi~h 9 0 0 (1964)
ER ·=
cos
t.H 0
'l ,,
90
[T0
X 1.00273791)
0 6.t X 3f0 ,
\ ± !::,\ wi
e,~ - '·w J'l' -0 -·
- EH
Determine C fro:n ec~entrlci ty vs. perigee plot (Fig. 2-1); where perigee
hei~ht (q) (in earth radii) = a (1-e).
2.1.2.;> Cor::pute a no:t~nal element set (procedure 3.1) using the 1620 launch
program.
2.1.2.5 Compare the ncminal element sets and make the necessary corrections
on -:!1e :::even-~a:r<l element set cards output by the 1620 program.
2 .1.~:. 6 Build <-l special SEAIC tape for the launch (procedure 313L.uaing ti.Je
2.1.2.7 Gcnerutc a bullotlli (procedure 3.7) and look angles (procedure 3.8)
usir:l', the BLTNGG? and GI.ASGP programs ( OCS 17). The security classification
'~.:: U:c look m:G;lc::c i:~ thr: h.i ~:l1er of the classification of the sennor or the
satcl.ll te. The secc::ri.ty classification of the bulletin is the same as that
'~ the satcllJ tr:~. In::;ur•:' epJJropdate sensor tasking.
2.1 DOt•tE~·nc lAUNCH
2-6 TM-LX-123/000/00
2 .1.2 .8 E.xamine the bulletin and look angles far errors and release through
the P~ajec~/Sensor Branch.
2.1.2.9 Rece1ve actual lift-off time.
2.1.2.10 Hotify the ~:;.::n::;ors by phone of the time of their first pass, immedi-
ately afte~· l"!..ft-off and j'~st prior to acquisition.
2.1.2.11 C&lct<late T0
and o0
, as follows:
a. Calculute T0
: I~crcase nominal T0
by lift-off time (in days).
c. Calculate o0 : Re-calculate 00
using T0
.
2 .1.2 .12 Update the :wminol element set to reflect actual 00
and T0
.
2.1.2.13 Correct the :1ominal element set using reported observations.
2 .1.2 .13 .1 If the LnHtal observations are identHied with the satellite .•
and if they sufficiently represent the orbit of the satellite, correct the
nor::.i.nal element set (procedure 3· 5) usln~ the SGPOC program. This is usually
done after t~o or three revolutions o: data have been received.
2.1.2.13.2 If insuffi2ient taggeu observations are rece1ved:
a. Fro:-:1 BHEHS sen:;._.~s :.o separete all observations on the 410 tape
'\-Jithin the expe.:::"ted sensor ac_quisit1on times from the_balance, us1ng
~~he HAP, ORCON and OBSSEP programs; nssoc1ate the observation on the
!:ich-pnority R-tapc· uith oll element sc:t.=; in theE-file (procedure
3.1!), usi.ng the RP.~3SN pr·ogram; generate observat1on cards, using the
SR'f!.ffiG progrom; retrievr:- all unascociated observation cards manually.
b. Fro~:1 o'.:.hcr sensors - r'f'trieve all possibly associated observation
c. f,r.;soclate the olJscrvaL:e;r . .: (procedure 3.4) w1th the nominal element
::.;ct, c.:c:::nc 1~~1r.~ PJ\~~::;H pr:Jgrorn 1n the SC!!'I'P mocle with lenient assoc.iat.ion
2.1 DOMESTIC LAUNCH
k May 196^4 2-7 TM-LX-123/000/00
e. If the DC fails, compute an initial element set (procedure 3-2) using
IOHG, etc., or manually adjust the nominal elements (procedure 3*9)
as warranted;
f. Correct the element set again (procedure 3-5) using the SGPDC program.
2.1.2.14 If the DC is successful:
a. Change the initial and final revolution on the seventh card of the
element set.
b. Ujdate the E, A and I files on the SEAIC tape (procedure 3*3) using
the SEAI program.
c. Publish a bulletin (procedure 3-7) and look angles (procedure 3*8)•
2.1 DOMESTIC UmCB
k May 196h 2-8 •W-IJC-I23/OOO/OO
C TERM
U M J- -t Urn. . Ä _ _J m --g H- -€ '1 - 7 » l ». rw •jr h # 1 1
• 1
.4 .* >| —1—r "**—t 4 w f
f > <> f .r 41 4
V > f
-1 t. r
A f q& — t * 4
* *
~t * t J f I 9 J If
69 f
1— r #
1 1 f 4) r ^U b f f w
X 2 1 w 1 1 '
3 £ J $ 8 I * f t
• ~r t # 36: E * f
1 t i 1 * _j L • f f i 1 1
30- 1 1 1 f
• f
30 J ± f ^ f • (XIO ) § 1 NO SUPPORTING DATA
I FOR e>o.3
1 MASS AREA NOT CONSIDERED
1 j 1 1
£ 1 [~ _J
a 1 i I | i
*^ IS - 1 J * J Mi
^ 1 It s - 1 it s _ t i t Jt r 1
t A X X i s
- —
—|— —
JiSG CR I 10
KX> 450 «00 750 900 1060 1200 i960 f§M EARTH RAOll |
95« 1 KM
»s.S 2870 3*2.7 4784 574 0 668.7 765.4 8610 95671
2.2 FOREIGN LAUNCH
4 May 1964 2-9 TM-LX-12 3/000/00
2.2 FOREIGN LAUNCH PROCESSING
2.2.1 Check List
2.2.1.1 Discrimination
2.2.1.2 Observation selection
2.2.1.3 Element set determination
2.2.1.4 Nominal element set adjustment (T and Qn)
2.2.1.5 Initial element set evaluation
2.2.1.6 Element set correction
2.2.1.7 Nominal element set evaluation
2.2.1.8 SEAIC update
2.2.1.9 Trial bulletin
2.2.1.10 Sensor tasking
2.2.1.11 Released bulletin and look angles
~·'OREIGH LAUNCH
2-10 TM-LX-123/000/00
;~ .2 .2 Tasl: Description
:~ .:?. .2 .l C'J:npare ::.ni tlal fan data with Beam Projection charts for d5.scrimin-
2.2.:?.;2 Exa:r.ine i.ni.tial observations for a major trend (procedure 3.4 and
3.10) ancl remove those observations which deviate from such a trend. Retain
"Jw de,;·~ute cl:ser-<"ations for use in determining the possible existence of
'J ') 0 J ._ • c. • c_ • _; Ii' the :I.ni tial obsenrations are fan data, compare them with the
2.2 .2 .L I}2te1·mine :·rom the RADINT charts comparison if any of the nominal
elc~ent sets can be used to represent the initial fan data (procedure 3.1).
2.2.2.5 If one of t:·,e t.or~inal element sets represents the initial fan data,
clpdate Tc·· and Or ba::.;ed on assumed lift-off time (see appropriate folder). I ()
2.2.2.6 If none of ".::he nominal element sets represents the initi:<Jl ffn data,
rnan:.:ally calculate m1 cle:nent set using the initial fan datu and sele~ed
i~fcrmation (procedure 3.1).
2 .:~ .2 .7 If the lni. ~,jnl '~;1Jservations arc trac!-:er dat.13, compute an :i.ni tial
ele:nent set (rrocedure ·-:;.2) using thFO IOHG progre:!:.
~~.2.2.8 If the ·in~t-i.c:1 -.;bservations are telernet!-J data, compute an initial
cler:er;t :::et; (prc,c,~dure 3.2) using the IOANGLE prol!r~nn.
2.:2 .2 .9 r:· ~~he in:i -tial cLscrrutions are e;eocentric rectangular coordinates
a~d velcclty data, comp~te an initial element SE~ (procedure 3.2) using the
2.2.2.1C If ~~e inlt~al ocscrvutions are simply two or more isolated radar
:.': xe::: J :·!·z_r~: t!:e c~a::;c c.r cL ~·::·e r·r;;,~ ::;tations Dwl/cr on the same or different
:··:::·.-ch:·~ic.:J~:, ·c,:::v;t:•: :1!1 .:::~ t~iul clement GeL (p~·ucedurc 3.2) using the IORF
2.~~.2.11 C::·n,,_.•, ~;;;c L<>:::~rwl clu!lcnt set (procedure 3.)) usine; the initial
4
•
2.2 FOREIGN LAUNCH
k May 1964 2-11 TM-LX-123/OOO/OO (Page 2-12 Blank)
a. A t
b. At range
c. A 0
d. Aß range
e. Perigee height
f. Period
g. Drag
2.2.2.13 If* any of the elements is unacceptable, correct the element set
(procedure 3«5)> using additional observations in the SGPDC program.
2.2.2.14 If the DC fails, treat the satellite as an element maintenance
problem.
2.2.2.15 If the DC is successful, evaluate the element set for acceptability,
2.2.2.16 When all the elements are acceptable, add the element set to the
System SEAIC files and the SEAIC tape (procedure 3.3) using the Special SEAIC
program. A bulletin (procedure 3*7) and look angles (procedure 3*5) will be
generated automatically, as well as a trial bulletin.
2.2.2.17 Examine the trial bulletin for acceptability.
2.2.2.18 Insure appropriate sensor ^asking (procedure 3-6).
2.2.2.19 Release the bulletin and look angles through the DSSO.
2.3 DEBRIS SEPARATION
2.3.1 Check List
2.3.LI Corrected main element set
2.3.1.2 Selected debris observations
2.3.1.3 Debris element set(s)
2.3.1.4 SEAIC update
2.3.1.5 Sensor tasking
2.3.1.6 Released bulletin and look angles
2.3 DEBRIS SEPARATION
k May I96U 2-13 TM-LX-123/OOO/OO
..... ? - . _;
DE~1 !iiS SEPARATION
2-14 TM-LX-123/000/00
2.~.2 To3k DescriPtio~
~.j.2.l c,~rrcct ~he r:min eler.:er.t set (procedure 3.5) 1sing the most recent
.!. ~ .. :'::.2 Select :fn)r:: nll associated observations (procedure 3.10) those which
::.::;:: ~-q.!··-·~3e:·,:, debris pi-::c.::s :-ather than the rnain body.
:?.3.2.~ .·_,:;,c~iate t!;e:~ debris observations with the main element set (procedure
~:.:~) .• ·_;::;·L;,:~ the REDUCT p·c:13:-3r:: or the RASSN program ir: the SCHTP mode.
").j.2.'· Exa:;,ine the residu:J.ls to identify groups of c..bservatic,ns which may
:2r:stit~te r.:~jor trc~ds related to debris objects (prncedure 3.10).
~::.3.2.5 r-~c:d:.:.fy the :::ni!': element set (procedure 3.5) (•,dth a temporary identi-
:~icatic;; nu:::ber), ucinc; eosh group of selected debris observations in the
:=~?OC !)rs;l·a:-::, pr•:;du::::.::.:.c a debris element set for eac!: debris object.
').3.2.C E t!-:e DC i'~J:.L_. :r.•Jlify ·~he m&in element set (procedure 3.5) using
· · ,, L:::e res..:.duals r·:· ':!-Je debris observations in the SYSBULL program, rro-
;~. 3.2. 7 C:.<1!1f:e t!1e ter:r;or<3Q' identification number t.L the next usable
sa'• ~ ~tr;; nt:::.t.e!·, ~:Jsslc·: <:::-1<:' pror.er IntermrUonal CCYJe: suffix,and add the
r• -., ... __ ele::.er-:t set 2r.r1 ''!~I~rupriDte acquisitio:-, and. infurmation data to the
:;:;s'.:e:~ !"~E!IIC :·~ lc; :.J~:d t:v~ CEAIC tupc ( fil'OCCdU!'e 3. 3) using the SEAl rrograrn.
2.3.2.9.1 I~ ~he uet~i~ ~s fro:: a furelcn satellite, generHte a bulletin
( r:-':C'''durc :, . '() ur.d l cDi: U'''~lr:·~ (procedure 3. 8) using the BLTHSGP and GIASGP
release &s soon as
~. ; [. ., ( ..
FFCXIMITY DE7SRM
May 1964 2-15, TM-LX-I23 OCC X
2.4 PROXIMITY DETERMINATION
2.4.1 Check List - for orbits related to each other
2.4.1.1 Observation association
2.4.1.2 Element set correction
2.4.1.3 Initial proximity computation
2.4.1.4 Final proximity computation
2.4.1.; Proximity determination
2.4.2 Check List - for orbits related to a given point and
2.4.2.1 Initial proximity computation
2.4.2.2 Element set correction
2.4.2-. 3 Final proximity computation
2.4.2.4 Proximity determination
2.)j
PROXTIHTY DETERrv1
2-16 'IM-LX-123/000/00
2.4.3 Task Description -for orbits related to each other.
2.4.3.1 Associate all ol,servations (procedure 3.4) with one element set usin~ tl:e Pv-'\SSN program in the SCHTP mode.
2.!+.3.2 Examine all residuals to identify groups of observations (procedure
3.10) which may constitute major trends related to different orbits.
2.4.3.3 Determine an element set for each orbit (procedures 3.2 or 3.5)
2.1L3.1J. Correct each element set (procedure 3.5) with epoch time being the
ti.me of nodal crossing for the revolution on which closest estimated proxi-
!:l:i. ty ~Jccurred.
2.11-.3.5 Compute the time_. distance and positions of closest proximity using
the XROADS program, with the time range equal to the span of time durin~
vhich closest estimated proximity occurred.
2.4.3.6 Examine the XROADS program output for the nmallest proximity dintance.
•
2.4.3.7 Recompute the time, distance a~d positions of closest proximity using I the points of smallest proximity distance in the XROADS program and as small
a time range as is reas::mable and meaningful. This rrny be repeated until the ~ .. ··· ·
analyst achieves the desired level of estimation a~curacy.
2.4.3.8 Determine fror:l the final XROADS output the point, time and distance
of closest proximity.
2.l+.h Task Descrlntion -for orbits related to a given point and time.
2.1:.h.l Compute nll satellite :p::Jsitions relative to a given tjme and
c:eneratc.: a Position Situation Heport usine; the PSR program.
2.4.4.2 Exami~e the Position Situation Report to determine those satellites
·,rithin ::.he reqt~lred range '.)f the given point.
2.4.1:.3 Correct each elemr:nt set (procedure 3.5) using the SGPDC program
2.!1.4.14 Rcc::;myn;te eac:1 satellite position for the revolution on which the
s2.tc~!2.ite L; cloce:~t to the given point and time usinc; the GRNTRK program.
2.i,.h.r; D·:.:~,ermlne from the cmtput of the GRNTRK program those satellites
· .. ;[t.!~:n U:r-• ,,~rlui.red ranr:e of the given point and tjmP.
'
2-17
2.5.1 Check List
') " ' "1 .-_.) . . l. ~- Element set correction
?.).1.2 SEAIC up:la te
?.~.1.3 Bulletin, look angle generation
Sensor tasking
2.).1.) Element set correction
SEAIC u:;xia te
2.').1.7 Return satellite to DSSO
?.').1.2- Unidentified observation association
Element set correction
Observetion reduction
Eler:1ent evaltm t ion
~.: .1.12 Ele:nen-:. ndjttstrnent
L~ast squares correction
Bulleting, look angle generation
Release b'JlJ.et:in and/or look angles
2.5 ELEMENT MArnT
TM-LX-123/000/00
EI_J:,~NT ~1ATI!1'
2-18 TM-LX-123/000/00
2.~.2 Task Description
2.~.2.1 Sufficient Observations
I:f' sufficient ob::;ervat:Lons are available, correct the last good element set
(procedure 3.)), using selected observations (procedure J;W) in the SGPDC
pro~ra!n.
2.).2.2 If the DC fails, evaluate the element set as in 2.5.2.11 below.
2.5.2.3 If the DC partially corrects the elements, re-evaluate the observa
tions o.nd c:nn}Xlre the input elements with the output elements from the DC.
CCJrrect the better element set again (procedure 3.5) using the re-selected
n:;servntions in the SGPDC program. This may be repeated as long as the
SGPDC program o.ppears to improve the elements.
2.).2.1+ If the DC is successful, up:latethe System SEAIC files (procedure
3.3) usinr; tLe SEAI proc;ram. The element set may be assigned the next
:.l~=c:bl;o; nu:nber ac ·:::2.taloc;ue elements, or may be Identified alphanumerically
~ts test, ele::-:ent::::. 'rc·.;:;t clements are considered less valid than catalogue
Generc\te a b.ll.letln (procedure 3.7) and look angles (procedure 3.8)
H Gppr:Jpriate usir;~~ '-~:·.:: BLTNSGP and/or the GLASGP programs, OCS 17, or, if
n d-tcrrn cxJ.~;ts_, the GLA? proc;rum.
I:1:3ure appropriate sensor to.sking (procedure 3.6).
2.5.2.1 If additional observations are returned by the tasked sensors,
cc)!'rec:t the ele:ae!lt ce-:. (procedure 3.5) using the selected and additional
obc•-.:r·n '~ icm::: Lr: tbr.:> SGPDC pror~rat:J.
2.5,.2.0 TJ:p'lute the Sy:::tem SEAIC files (procedure 3.3) using the SEAI program.
Ii' te:;t element::: ·,rere used they must be deleted and the old cataloc;ue elements
rcpla.::·~d wit}: tile n,_c•,.r element set. Maintain the satellite until. it can be
re'~urned ~.o the DSSO for rc_)qtine proce::::;sing.
;:'.).~'.9 Insuffl~Lcut cJb:;ervations
r:· :-;ufi'~ci"':n'.; cJb:-;':~r·.'rJtions are unav3ilable, associate the_...unidentified obser-
·;i, tl :;::~; in :).'~' :jy::::;i_err, (procedure 3. 1,) with the lact good element set using the
RASSIJ p!·:=·r~n:r:: in the SCHTP mode. The association parameters should have wide
'
'
•
2-19 (Page 2-20 Blank)
2.5 ELEMENT MAINT
TM-LX-123/000/00
? ~1"2"10 Con·cct t!1l: element set using the SGPDC program as in 2.5.2.1 above.
c: .. ~;-2.11 T.! sufficient obscr·vations are--still unavailable, or if-for some
other renc;cn t!1e DC f'uilc•, reduce all observations (procedure 3.4) against the
best elcn;cnt :::'-c·~ u.s i n,:s the REDlTC'J' program. An examination of past element sets
~~:3y ~·c·:c:<Jl tl:l' bcginrHJW ·Jf the r:Lsparity between the observations and the
2. ';. 2 12 E~:o~;nnr> tl•P r,~.:;idu<.Jl:, outp.1t by the REDUCT program to determine the
2.'~ 2.'i3 lf tlx cler:H'tJ''' :Jffp·tE<l by the time equation appear valid, reselect
t~:~· ,,i,sc:·•::Jt lOtJ': ( pr,··c:~•_,rr· -~· 10; El'Jd/or manually adjust one or more of the
~·c:·::1i1~rw clc:::c-n::s (;j:·r:::'Crllll'C' j 9! •o fac:ilitate successful differential cor-
:·c-\,' ·_.! ~~·:··u• '-"w~ -.'.'(; -.~ ·, fn· 11··•·JtP o :;ucccssful DC, generate a delta t
l'C'-'C]~,·: .• -::.:, :;J.u~. ( prcw,_·d~J:·~c" 3 lO~ of the residuals output by the REDUCT
the, "'quat1on des-~r.i bing the plot and the
r
~'. L· DECAY PREDICTION
2.'~.~ .J Kinc;-Hc-1e/F.inJle:; estimate
2.(.1.~ Decay f8lder.
n. Satellite c~urncteristics
~~. ~3GPDC ~_,utput
Sens~r tuskln~ messn~es
BulJetins released
2-21
2.6 DECAY PREDICTION
TM-LX-123/000/00
"' Jd.Ul t v:. lYV:)lu~~ion, period vs. revolution or period vn. day plots
l:~nt;-Hele/Flndl~::':,', Jucchi.u and other program predictions
2.'. 1.•. Ob.:.·~·vnt::·::m :,.,:·· -~,-:1atl.cm nnd element c::Jrrection
.xi. ·:~-. :·c::Jhtt:ion oc- period vs. day plot
~;.:~.1 .lC1 L'-'c.::t ~:q_llCll''=''-; ::orrection, bulletin and look angles
2.~.1.12 Delt~ t vs. r~v~lution plot
DECAY PREDICTIOn
2-22 'l'M-LX-123/000/00
2.6.2.1 Estimate the decay day (procedure 3.11) using King-Hele/FindJey
prosrn~n.
~.G.2.2 When the period is 90 minutes or less, initiate a decay folder on
the ~atellite, '~o include.
~,. Sa.tellite ~haracteristics: tumble ratA, motion, size, shape and mass.
b. SGPDC ou Lput from a 90-minute period to decay
All ~;ens'Jr tasking messages
d. B~Jlletin:::: released from a 90-minute period to decay
e. Lo'Jk anrles relea~ed from a 90-minute period to decay
.. -'-.
g.
D•::Lta t ·;s. revolution and period vs. revolution or period vs. day plot:~ .
Y.lnc-Eelc/Findlcy, Jacchla and uther proc;rarn predictions
Final decay message
2J,.2.j Correct tbe latest elernent set (procedure 3.5) uslr
l
2-23
2.6 DECAY PREDICTION
TM-LX-123/000/00
~.2.10 ~-."he:; the DC fails, attempt to correct the elements (procedure 3.5)
the REDUCT-SYSBULL-GLAP program sequence .
.. :?.12 1·~an~:ally r::e~e-:-atc a delta t vs. revolution plot (procedure 3.11).
<::' 1~. l.:lctJ • ::e s•·n~:c:'' syct.e~ fails to acquire the satellite in successive
.. ;~ 11. r;xn:~:l!1e ~-:~:· ~)'U!'lC·'.iS ~Je~;uy pr12dictions and, when they ogree, deter-
1· !--:8!1\~·Jl ~~lot ;f pcrLc;d vc. rcvolut1on and/or period vs. day ..
,. 'l'~:~c Sl an l;c• .. wecr. t!w la:jt cbservntion reportP.d and the first pre-
1 July 1964 3-1 TM-LX-123/00C/0QA
Section 3
PROCEDURES
A variety of procedures are utilized to sclve orbital determination problems.
They appear in various tas^s and in various combinations. A procedure may or
may not involve the use of computer program support, and the fashion in which
it is used may vary from task to task or from program to program. The re-
lationship between the procedures and the six tasks described in Section 2
is shown in Figure VI-
VIA fnllnui me
9
i:
ii
I 12
llowing procedures are included in this section:
Procedures
Nominal element set determination
Initial element set determination
System Sensor, Element, Acquisition, Information
and Ccmmunication (SEAIC) files update
Observation association
ELement c orre c t ien
Ser.scr tasking
Bullet i n genera ti on
Lee/, angle generation
Element se*. ad *uctnent
Ofcser\'ation selection
Decay predict:~n
El e me n t C: nv e r s i en
Page
3-3
3-9
3-11
3-15
3-19
3-21
3-23
3-25
3-27
3-29
j -j.
3-35
1 July 1964 3-2 IM-IX-I23/OOO/OQA
Procedures Tasks*
Title 1 2 i 6
1
2,
3-
6.
7. 8.
9 10.
11.
12.
Nominal element set determination
Initial element set determination,
SEAIC files update.
Observation association.
Element correction.
Sensor tasking.
Bulletin generation.
Lock angle generation.
Element set adjustment.
Observation selection.
Decay prediction
Eleme nt c cnver s i on.
X X
XX X
XXX X
X X X X X X
X X X X X X
XXX XX
XXX XX
XXX XX
XX X
X X X X X
Figure 3-1
Procedures and Related Tasks
*-*: i: te: Task titles:
D:mescic Laune:
2. Foreign Launch
Decrts Sera rat:
Proximity Dete:
Element Mai-nte:
Decay Predict:
;.na
t
I i
3-3
.1 ;;O!·UNAL Ern·IEHT SET DETERHNATION
.:!..l General
3.1 NOMINAL EUMENT
TM-LX-123/000/00
~c~inal element set is generated from predicted orbital values in order to
:c·o·:ide look ant;les to sensors so that the satellite can be tracked. Nominal
'cer.-:ents are determined t,efore each domestic launch and may be required for
::casional foreign launches for which iniUal observations are insufficient.
1e r;::):::inal ele:r:ent set should contain values for the following orbital
a. Epoch year
b. PA = anomalistic period, a semi-~ajor axis or q = perigee distance
c. i = inclination
d. e = eccentricity
e. epoch time
argument of perigee
right ascensic.n
C = drag
.1.2 Domestic Latmcn Information
ni.onal Aeronauti~s and Space Administration (NASA) or Space Systems Division
·~sD) c·:~ the U. S. Air Force usu~lly supply pre-launch information before every
' ~ ' ...... ' ~. ~ .... _ .. -- ~ ..
. l.~~ .l I!:.f-U.t
c. : (m<:::Js·.n·ed ccuntercloc;<:·.,.ise from the equator, east of the ascending
~, = l~~itude of injection (I)
x~. = lo~c!tude ~est cf ~njection
Di:·r;r·•.:m: c: c;G~~(:llit~ :::otion at I: ncrtherly or southerly
3-l NOI<lHiAL ELEME'I>JT
3-h TM-LX-123/000/00
Any ~~et of porarr.eters which define an orbit (e.g., position and velocity
vee :.or·s) :-nay be used in place of P A, i and e, with the proper formulas.
3.1.2 2 Processing
Ur:cn receipt of pre-launch information on a domestic launch, determine a set
of nomi:1ul elements in the standard format by manual calculation and by using
the I .. B,M" 1620 Computer Launch program. The two nominal element sets are
co:npared and, if they do not agree, the disparities should be analyzed and
adJusted.
3-1.2.2.1 To calculate the Argument of Perigee (w ) on revolution zero: 0
a. Calculate the distance (u) in the orbit from injection to the
closest ascending node (actual or theoretical):
Gin ¢. sin u = . .
1, if the direction of satellite motion ut I is northerly. s.1n 1
sin ¢1
sin i. ' if the direction of satelllite motion at I is
southerly ..
r.~. Culculate the Argument of Perigee (w ) measured from the theoretj cul 0
escend:i.ng node nn rrc:volution zero to the lJCrigee point in the direction
of satellite ~1oti.un:
w u, if T "'·; :n the northern hemisphere. 0
w c I is in the southern hemisphere.
NOTE: Pr.::l·:icco i.:::; ascumed to occur at I.
3.1.2.2.2 To colcul~Jte the Urne (T0
) of the satellite's imaginary passage
E ~ 90°, then 0° s:- s: 90°
2
~0 - 180~~-·-= cot --.---- ---
L 2 l + e'
9oo < E 2
$ 180°
t
3-5
n. Cnlculutc tl~e Menn Anomaly (M):
3.1 NOMINAL ELEMENT
TM-LX-123/000/00
There are 57.3 u~grec: per radian.
Calculate the t irno difference C:~t) between T and the time of 0
i !ljecU on ( T~ ) ; .L
t.t
I • ) d. Calculate 'l'. \ 1r1 duys since 1 January : l
rp ~i 'rl.me of lL:ft-off (in duys since 1 January) + Time from lift-off
to injection (in fractions of a day)
NOTE: If time from lift-off to injection is given in seconds,
divide Ly 86,400.
HOTE: Nom:i n:1l Umc of lift-off is assumed to occur at OOOOZ on the
dny uf luunch.
~. CalcuJate T : ('
(.; :,_; rll i -
~.:.. .. .::.~!.:> T,) c:~J.lc\:lute t!K· l'ight ascension (O )on revolution zero, (measured 0
~·us::,;u:·d frc,7:: t!w '.'enwl e'1uinox to the ascending node):
:". CulL'uLtc th: rlr:::ht uscension of zero longjtude (Greenwich) at
'I' (;,'r, ), '<.'ith r·.',:!Jt usc:cnston of zero longitude ut OOOOZ on urn
"·o , J:.m1.w r-y, l96h ( G
0) = 98 '(4077.
Gn ~·1 rn
10
= G • 0 Umes the fractional port of (T
0 · 1.00273791)]
L. ~o.JcuJ:Jtt:• t:;.:; :Lr:·erence in longitude (t::.A.) between injection
>.,:u·i 'J1Yle (;\., ) und the closest ascending node (actual or theoretical), \,.
r::c.:J~•.;~·cd ~n ~~ ;Jest\·mrd di rectJon from Greenwlch:
. . . '-. . .) J;., ) . - u)
3-6 TM-LX-123/000/00
Calculate the lonu;itude of the theoretical ascending node
!·evolu tlon zero:
A 1.; = A ± t:.\ - ER
0 ""i
IJOTE: 0
The Gigns of t:.>.. and 360 can be determined from the following
table, where P = prograde and R = retrograde satellite motion,
und N == northern hemisphere and S = southern hemisphere injection
latitude. Addition or subtraction of 360°, where indicated in
the table, will not change the value of (>... ± t:.>..- ER) wi
c. Calculate 0 : 0
()
N
s
p
Jj).. 360°
+
- +
3.1.2.2.1, Dcterr::ine the denc: term (C):
~
iiA ~60°
-- +
a. Enter the C-te r::, ]·let (Figure 3-2) \·rl th peric:ee heic;ht a Love the
b. Read tlle C-~cr·m lJO.c:e ~1umher from 1 to 0 (left to right) bet'\.,2en the
two appropriate cont8urs.
Read the C-terr:~ ezv,ncnt number· (to the base 10) between the two
rJ!T·rq,y·iatc ccmtou:·;_; :1~: the top of t-.he plot. -G
Fer exo.,:Jl')le. :if c = •J.2 and ER " 1.03, C " -O.c( x 10 . If e = 0.08 and ER - • • - r -e .
1.06, c;, -0.0 x 10 or -1.0 x 10 . The fractional part of the peri,zce
3-7
3·1 NOMINAL ELEMENT
TM-LX-123/000/00
F1··~"-laur:ch ~nfcnr:ution on foreign launches is usually unavailable. However,
i.ni tic:l obscnru~~ions m·ty come from three types of sensors.
3.1.3.1 Inrut
o. Ruda:· fan dutu: t Lme, uzimuth, elevation, range and range rate
(optional)
t:. 'I'rucker- duta: time, azimuth, elevation, range and range rate
c. Telc:netry data: time, azimuth and elevation
') l . • " j· ..• ) •• :. Pl·ocessl.nc
If te1.ero.etr:r or tracker datu ure received on a foreign launch, an initial
n}cr;!r~nt set. i:..; computed (procedure 3.2). If radar fan data only are received,
:~.er:'::Jlly [e!leratc un ele:!:ent set.
f::·::·c r:~'(' s:.;Yer~<l rredetcrrn:Lned element sets ·which have been computed from
:·:·,··:>:·~::;::·en;:,:"- lmmches. These :-:Jay be used as nominal element sets for
:;.tccl'•:di:•c l:.~u:·::::!le:~. Attempt to associate initial fan data with fan data
:: I'l'ev~ m:s lau:iches t() .:_'~1c ~li tate selection of one of the nominal elerr.~nt
::;··~:..;. r:::· t::e in.:.ti:Jl dJserv~ltions do associate, use the selected nominal
•2.~ .. c:·~e:1~ c:r~t c:r:t.i.l udd~ t..ionul observations are received. If the additional
(:,··:~··:u•.:o:ls ·_u:;s('c[:.:tc closely -..:it.h the nt'rninul element set (procedure 3.4),
i~; ::: ::..':: .. r-:~cto::d (;:roceclure 3 5). Other\-lise, the additional observations
~:::c·Jld !;e •.;:.~ed tc' cGr::pc.;.te Dn iniUul element set (procedure 3.2).
·,r:-:en r.~F~ L1~ tlul :·em dc1ta duc·s not associate with any historical data,
u~.~>.c:::pt tc, c~Jlculu~.:rc~ un .inJ.ti~,l element set (procedure 3.2) using the
:::: t~ul fur; dota and ether <.r:ailul!le information.
3-8 ~-LX-123/000/00
I .. -e -e -7 -8 -e -10 j.• ' " •• .18 .4 .2
., 50
• ~ • ~-
I I# ,~ t' , _4 l•
,; ,.. "'!" #'
J: ' I#~ .,#. Lf' ,
11 ,_. Lll"' t--
45
; I ~ , • ~ ' _. ,! I#-
40
II : ; ·f-
• I • ~· I I 4
' • I• I ~ ; • ~-• I • . ..
--1-J II I I ~--~~-I --, -- -
3 " I I I • • • I
I NO SUPPORTING DATA FOR e>0.3
MASS AREA NOT CONSID£REO 2 5
I I
2
Ell X 10
I I f. - ,_-
0 i
I
I I ' 5 I I 1\ ~ l
' 0 l " I 1\ ..
I 1 I' \ l 1\.
-l-t- 1\ ~ "'- --
I' I
- ---;---j -- -!-- i ___ L _..J~-- -~~- -- ._. ----I-- -~~ -f- - --- f-5 LH II\ -~ 1'-
' t--- -~-- ~- ·-t- !t.. .. . ~ 0 -~-t-r-1-t-t +-- ~ ' --f-.- ~-I-
4 1~0 :'100 -.~o 600
9~.6 19U 287.0 382.7
~ 900 EARTH RADII
478.4 ~74.0
KILOMETERS
FIGURE 3·-2
C-- TERM GRAPH
10!10 1200
669.7 765.4
15~
8610
-i
r-
"(X
9567
'
'
3-9
3.2 INITIAL ELEHEN'l'
TM-LX-123/000/00
"'~ llJJ'I'IAL ELD1ENT SET DETERMINATION
J\:; ] ::: t l:JJ ele:'!ent sc:t is deterr:-lined from initial observations in order to
;:·,.·:ide ~co!-·. unt:les to sc~1sors so that the satellite can be tracked. This
.:; .. :: .;~ Fcrclr~n Launch lr.f'ormation
:;:,,: :.l:.il. c.h•.:en·o-:;lons ~'Jn foreign launches usually come from three types of
~·. 2. :~. l Ir~pu t
a. R:Jdar i'an datu: time, azimuth_. elevation 1 range and range rate
(optionul)
lc. Tr~1cker datu: time azimuth_. elc=vation 1 range and range rate
Tc· J.er:1et r:·: d:1tu: time, az.>:mth and elevation
~.2.2.2 Processing
1Jr c·r: r·ec~elpt c,f radc.n· 1 :_,n dut:, ur, u foreie:;n launch, uttempt to associate the
ir:[r;i.o.J. fun datu i-:i:!; :··m cl:Jta o:1 pre•:ious foreign launches (procedure 3.1).
L' tl':.e lr.i ~iuJ ubsec/Jtlu:L dl: r:ut ussoc:iute, attempt to calculate an initial
c.ll.:~~cnt :~ct. u~:~ng !.he iLl :.:<.d ctJo.;erYutions und other selected information.
111n proceJur0 for this ~alculati~n follows as closely as possible the procedure
.. ' ~. cJe:::ent set based on U.S pre-luunch information
(I!'(•~c:d.:,:·,c 3 1). L·lC'l-: of ('V~! lett! inforrrution, however, rnuy require that a
:_, :.,:Jreign lsunch, the _!ni tial Qrbi t by
::r·t·: ·, .. :,_~:!;: :; (TC:Ir.) i'l'' :'t',:'~' 1 •• •.1:;cd to compute the ini.t.al]_ e.lement set.
~C,iW :T' :r;·u::, :Jsc:_; U:n••- trlree-dir:-:ensionu.l fixes fror:r one sensor to
The })ro~:;ram uutomat.icully uses all remaining
::;r;:"::t'-~.m:' 1J: dlf'1'er·e::t:u.lly C(irrcc:t thut element set (by the Simplified
_:; .. ~·
I:'HTIAL ELfl·1ENT
3-10 TM-LX-123/000/00
lJpcn receipt of telemetry data on a foreign launch, the l_nitial Orbit from
Angular Fixes (IOANGLE) program is used to compute the initial element set.
Three angular position fixes from one sensor are used in the computation
and the remaining o18ervations are t.:.tilized in a differential correction.
:S::.sically the same methods as in the IOHG program are employed for both
nler~ient set computation and differential correction.
lf or.ly geocentric rectangular coordinates and velocity data are available
on n lntmch, the Rade.r Orbit _Qomputation (ROC) program is used to compute
the initial elerr,ent set. No differential correction is included in this
program.
If t\-:o or more radar fixes only are available on a launch, nse the Initial
Orbit from InC:ependent Radar Fixe~- (IORF) program to compute the initial
element set. These fixes may be isolated radar hits which come from
different stations or which occur during different revolutions. Differential
correction is not included in this pr,)gramo •
•
3-11
SYSTE!·1 S:Et\IC FILES UPDATE
General
3·3 SEAIC UPDATE
TM-LX-123/000/00
Scr.~;u:· .• Ele~r,ent, Acqui sit Lon, Information and Communi. cation data are maintained
on .:.:ll sutellites carried by the SPACETRACK Center. This data is maintained
C'n r;unch;d ~ards in t!Je System SEAIC files. It is also stored on the SEAIC
::are :'or most satellites, because many of' the programs accept SEAIC tape
:nl:·uts. Tne SEAI Tape FJ le Maintenance program is used to add, modify or
delete ::nformation from the SEAIC tape.
3· 3.2 Foreir:n Inunch
Upon establishine; the first acceptable element set on a foreign launrh,
-+::he E, A and I files on the satellite are added to the SFAIC tape to
:aci litate ':-he generation of a bulletin and look angles. The Special
?o1·e:i gn SEAI 'D::lpe File Maintenance program is used because it includes a
p·r•dete:·:r:lned ncquisi ticn o.nd information file especially designed for
3· 3·2 .l Input
Classi~ic.:Jtion
D.
L'J. unc h :J reu
d. FLl\Sii tj 1_llletin indicator (optional)
E• - . Set•:lll tc t:n:m::;mi. t tine; indlcu tor ( optionul)
j. -~ .2 .2
'~::: G1cr·: ~~-~ Fore i r::n SEAI Tape F.i le ~!aintenance program addn the E, A and I
L le:; tc ~}!e SEAIC tape and automatically enters the bulletin and look
:,::,-1,:~ ;:~ene~·at.iO!t pr·ocedure::; (procedures 3·7 and 3.8). A and I-file cards
s::~~Jld :)e 1~l'1C':'led :..:o <:;hot the information on the SFAIC Tape is also in the
~.. -.. ) .... SEATC UPDATE
3.3.:, Dome~tic Launch
3-12 TM~LX-123/000/00
Upon c:c:.ermin::ttion of u nominal element set on a domestic launch, request that
a sr;edo.l SEAIC tape be built. This specio.l tape is used until after the
satellite is l:J.unched and an acceptable element set determined.
3·3·3-1 Input
a.
b.
" ,_ . d.
Sensor ciata
Nomin~l Element Set
Acquisition data - usually from the Operations Division
Information data - usually from the Operations Division
Satellite Maintenance
After a reliable element set for any satellite has been determined, the
element set is maintained in the System SEAIC files. Subsequent changes to
the clement sets are rna de mH.nually or automa. tic ally, depending on the stability
o1' the satellite :md the reliability of the element set.
~. 3. 1~ .1 Input
u. Elene:-.:t se-t
h. J\cqu"i~;:i tion dat:~
c. Inf'orm:rt.ion datu
3. 3. 4.? Prcc~es~~ ir.g
:;:_;:- tho:: '2le:;;cnt set is cor:::ectcd by the ~implif ied ~eneral Perturbation
Ephcr:1e:r:ic wi~;h Di:·:·erentLal Correction (SGPDC) program in the automatic
r~wde .• the ne".-1 c:lc:;;ent cet ;:ill be stored on the SEAIC tape in place of the
old el(~r::ent :3et provitled convergence occurs on all six elements and the
d:n1g tcr;:! (procedure 3.5). Otherwise, the old element set remains on the
SEAIC tape. If the SGPDC program is used in the Schedule Tape mode, the
SE/\.J Tape File l·h ir:t•:T'.ancc program is used to update the SEAIC tape (pro
C(:clm·c 3. 3).
3-13 (Page 3-14 Blank)
2· ).) SFAI Tnpe Files ?4aintenance
3-3 SEAIC UPDATE
TM-LX-123/000/00
Additions ~nd or deletions may be made to th~ S-file, E-file, A-file and
I-:".:.les using the SEA.I Tape File Maintenance program with the appropriate
S, E .. A or I-file card or the SE....\I File Deletion card.
3-15
3.4 OBSERVATION ASSOC
'IM-LX-123/000/00
0~: serv0tl ens re;::el\·ed ty the SPACEI'RACK Center must be associated with a
sa'.;•:ll:i te be::'orc they ':un l.Je used to correct the element set describing that
sa~~ell~ te ..
3.L~ .2 {}1·oss Association
Tr:e cr::;ss associet:i.on of observations with a satellite is accomplished by
1denti2'yir;g those cbservuticns which fall in a srecified time span. The
Ll :::e SIBn is usu2lly t.hut during which the satellite is expected to be
·,;_::,~:in the acquis:! ti or. ce;pabili ty of the sensor which returned the
Assc.'c~:: cltioL cr_L teriCJ - e.g., time span
;,;,- :: J.wrce ::::Jsses of J:Jtn :l:·e received, as from BME'wS, the Observation
')r<.'C!:·atic:: (03SSEP) l':·c;:r~:r~. is used to separate the observations into two
c~·~:c<rs ac~cord ::::~ ·Jc ~~::e t.ir::.e span indicated. The OBSSEP program outputs
·>~ .:::~;e:'".~l\,~;:::; fullir.c ;.:.i.~Jli.:: the time span on a high priority Beport tape
(R-~;:J!'E:) ::.;r:d t:;c,se :·alljnc: ::utslde the time span on a low priority R-tape.
exu~ined ~ist;ally.
~.4._ Rc~tjne Assuc:~~lu~
proc:ram is used to accomplish the routine
OI3~.iERVATION ASSOC
3-16 TM-LX-123/000/00
'fhc RASSN progTam nuy be run i.n the automatic or the Schedule Tape mode.
In the autom:1LJ.c modG the program attempts to associate all observations
with all satellites on the SEAIC tape. In the Schedule Tape mode the program
attempts to associate all observations with thost:: satellites for l'lhich
element sets are input.
The pro~:p:am assigns one of three levels of associatton to each observation and
iC.cntii'ie::> the sr1tellite with which it is associated. The levels of association
are Associ:ltecl (Ra), Doubtful (Rd) and Unassociated (Ru).
3.1~.4 Special Association
Special as~;ociation of observations with a satellite may bE: requi.red whenever ... , . ~-
--~. ·:·· '· ' L-.:' -:-·n·~~ctPrP -; n the RASSN program are too open or too restricted
:·or ~ccuratc ~ssociation to occur.
:1.. Ob:~ervation data
b . Sensor da t:.l.
c. Element data
d. Assoeia-::.ion parameters
3.l.4.2 Processing
Eitter the P.ASSN or the Reduction (REDUCT) program may be used to achieve
associ,ltion under special conditions.
The RASSN program, run in the Schedule Tape mode, requ:l.resspecification of
the numerical values of the as~·:)C:lation pn.ramet•~rs (time, right ascension,
height, vector magnitude and beta). The program tags each observation as
associated or unussucint0d.
'l'Lc REDUCT procr:1m ro::~duc:cs obr;crvations back to the last nodal crossing and
cor.1putc:; the n:s ldu~1l diff'r~rcnces between the observations and the elements
ln tenns of' time .. right ascension and height. The program then identifies
those ob:::crvattons whose residuals fall within one of several sets of tolerancP
limits contairwt.l ln Lhe program. 'l'he limits are spec 1f'ied each time the program
:! :.: run.
h May 1964 3-17 (Page 3-18 Blank)
3 .1~ OBSERVATION ASSOC
TM-LX-123/000/00
TI1e rcciduals output by the RASSN or REDUCT program may be used to further
refine the association levels of the observations (procedure 3.10).
r
3-19
ELFJ.ffiNT CORRECTION
General
3·5 ELFME\~ CORP~CTION
TM-LX-123/000/00
T!1c pur}'o~:f> ·,·,f clement c~orrection is to refine on element set, making use
o:· ulJ::>er:uticns recei•Jetl since the preceding correction, so that the resultant
:5·').2 Co~rmlete Correction - anor~mlistic data
rJt:d the druc terrn .
') (, ') "l _). ) • L_ • ......__ .Input
L ~ Sensor du tt.1
'J'r.c_· ~)Cl-DC IH'C'I~' alii u.., '-''~: .. :1 ~"' t.u tlifferent:i.ally correct all of the six orbital
~·Jr;:ncn~~s Dnd the drag parameter" In case the attempt to converge on these
sc•:ey; I-'arumeter:::: fn.i L;. the program automatica1ly tries to converge on a
fci.;er nu~nber. The Pl',J[::ram is de signed to handle most satellites having
ZC:!''• tl· :1c<lcrute cecentr.iclty Secular variations due to the earth bulge
~1nd at~.:ospher:Lc drnc are accmmted for directly. The perturbations due to
:;r>Jcn· nJd.!.:lti on I'ressures and gravity fields of the oun and moon are neglected
:n-.DJyt,Lcullyj howc·:er, any long 1~erm effects of theoe perturbations are
; :wlurJed ir: the elemr~nt curn~etions obtained by the least squares error
J !', cc,c;s. The SGPDC program does not compute the first derivative (D) of
::-.,. j Lu·tiul Corre~-~tion ( 'l'ime equation only)-nodal data
F:t~"-: ~d c ·~··!Tee U e-n or un element ::;et corrects only those parameters affecting
~"::" ;_~::::e c;:' cru:~s:nf~ ~-he ascending node: T0
, P, C, and D (the first
ELE'·!ETiT CORR.F.CTtofJ
3-20 TM-LX-123/000/00
a. Elemc~nt set.
L:. Time~ residt;o.l:::: ot specific revolutions
OrJer of the ·~quo.:.icm to be fit- linear_. quadratic or cubic
:" ! -. ) ') _, •• / 1 _) • t.... P:rocess:i.ng
'I'n·-; S-tstcm ~ullc:~~ 1 n (SYSBUT.JL) program may be used to correct an element set
tJcforc prod\h ~~lf: :J bullcti n. The program computes a least squares fit to
tr;r; tJ r~1'" t' l.~;a 1 Lor~ l'r"m time residual inputs. Tnese resldual values usually
co:nc f'!-·m thr:; out};ut nr thr.; REDUCT program (prot':::lt,:'f:' j.l+) and the order of
t!v· e tuatim: i.::: deterrnl ned by examination of the t:i;1:·: residuals plotted aga1nst
t·nf·~ir revolution ntl!nl~er (p-r·.:Jcedurr! 3.10).
•
3-21
Gene r·ol
3.6 SENSOR TASKING
TM-LX-123/000/00
A : :· i c !'j :,y fer ' :>,~C1",< n,• u partl cular sntelli te and the amount of data to be
:·r·I ~)rt,c:J :~,:<y Lc c.: pee i Li.cd l:.:y Jnsurln13 that the proper sensors are tasked at
~.t 0 USAF Scn~trs
T::•_::·c: :,~·-::~ t,!;n::e r•rl or_! t:; levels rmd three data levels.
1
3
Datu Su!'f'Jx
A
., '-
c
1
Meaning
Observations on emergency or extremely high priority space events.
High priority observation5---0n selected satellites.
Routine observations on selected satellites.
Send all possible position data from the time of ocquisi tion until the object passes beyond the sensor capability.
Send all position data obtainable during u perlod not to exceed 3 minutes
Send best single observation.
Meaning
All observations referenced to applicable receiver stations ore reported by telephone and followed by an "Immediate" precedence message as soon as possitle.
All observations refe~enced to applicable receiver stations ore reported by "l-'rlority" precedence message as soon us possible.
SEJiSOR 'I'ASKING
Tasking Categorv
5
3-22 TM-LX-123/000/00
Meaning
All multi-station observations referenced to Kickapoo site and all single observations referenced to applicable receiver stations are reported by "Routine" precedence message every 8 hours.
Same as Category 3: every 24 hours.
Same as Category 3: excluding single observations, every 2L~ hours.
Categories l, 2, and 3 are in effect tne same as tne presentCategory lJ 2,
and 3 used with USAF Sensors wnen applied to new foreign launcnes (Category 1)
and new domestic launches (Category 2). ~nerefore, all pre-printed message
f'c:::1ns ·will inclur1 <:? SPASUR as addressee on the initial alert messages from
NORAD SPADATS for both foreign and domestic launcnes. Suffixes A, B, and C
do not api1ly to NAVSPASUR and tney have been advised to disregard tne suffix
on multiple addressed messages.
Categories 1~. and 5 will b<: prirnarlly used by tne Data Control/Sensor Brancn
wnen assigning routine rnontnly tasking ~nrougn NORAD SPADATS. However, sensor
tasking may be cnanged, on rc1utine t;yrpe satellites, to Category 4 or 5 wnen
appLcable.
•
'
3-23 (Page 3-24 Blank)
3. 7 BULLETin GENERATION
3-7 BLTN GENERATION
TM-LX-123/000/00
l1 bulleti!1 ( eJ:hemerl s) contains predicted satellite position information.
Future satellite positions ore extrapolated from an element set best
!'it: inc the current rmd pust satellite observations.
3. ·r .1.1 Input
a. Element set
j.'i.l-2 Processinc;
'Y:1c~·e a~·e two methods 0f c;eneroting a bulletin. Normally the ~u_!le_!:i,!! with
~:irniJlificd Qeneral l:erturbntions (BLTNSGP) program is used to generate
a bulletin. If the SYSBULL program is used to correct the element set, it
,,,. ~ 11 r~·oduce a bulleU n automatically, and unlike BLTNSGP, will use the D
te2·r:c. TI1e BLTNSGP program uses anomalistic data, whereas the SYSBULL program
uses r:cdal data.
:1. A:J. element se:. at ~.he tirne of crossing the ascending node for the
Position ar:c: time oi' C!"ossing an ascending node for all revolutions
Pcsi-:.i.un, :lrre m:J }v_:lt·:-Jt at consecutive latitudes covering one
J~ chldl t.i.on_. the BLTNSGP f'rogrnm prepares a modified description of the
orb~tal clements, which is used for special prediction purposes as specified
: :; t}:c Inte!"·na~"ional _Qeuphyslcal Year ( IGY) World Wide Code for Satellite
3.8 LA GENERATION
i h May 196U 3-26 TM-LX-123/C00/C0
3.8.3.1 Input
a. Sensor data
b. Element set
c. Acquisition data
3.8.3.2 Processing
Tne GLAP program will compute a set of acquisition coordinates for eacn
satellite and the associated sensors. Tne program computes look angles
for general acquisition purposes.
3-9 ELEMENT ADJUST
k May 196h 3-27 "" 'm-LX-123/OOO/OO (Page 3-28 Blank)
3.9 ELEMENT SET ADJUSTMENT
3.9.1 General
When excessively large residuals exist, manual adjustment of the affected
element value may provide for a successful differential correction uping
routine procedures.
3.9-2 Foreign Launch Data
If the initial observations are insufficient to compute or calculate an
initial element set, or if the initial observations will not associate with
any of the nominal element sets, adjust one or more of the element values in
the closest nominal element set on a trial basis, and attempt to associate the
initial observations with this adjusted nominal element set.
3*9.3 Domestic Launch Data
Following a domestic launch the nominal elements (fin and T~) are manually
adjusted to reflect the actual lift-off time.
3.9^ Unusual Orbital Data
It is sometimes difficult to maintain a reliable set of orbital elements
on a satellite with an unusual orbit. Observations may no longer be received
or the elements may not converge on the observations available in a differential
correction (procedure 3 5)> Occasionally all but one or two of the elements
converge on the observations, indicating that the observations are reliable
but that one or more of the element values may be in error. Adjust the
apparently erroneous element values and attempt to attain convergence on all
the elements in another differential correction.
3-10 OBS SELECTION
k May 1964 3-29 TM-LX-123/OOO/OO
3.10 OBSERVATION SELECTION
3-10.1 General
Removal of doubtful or erroneous observations from a group of data will
usually facilitate a more accurate differential correction. Particular
observations are often selected from those available because they reflect
a major trend, evenly represent an entire orbit or indicate a different
but associated orbit.
The methods of observation selection are manual. In clear-cut cases, identify
observations by a visual examination of the hard copy produced by one of the
association programs. Otherwise plot the observations on a graph, in terms
of their deviations in observation time (delta t) or right ascension (HQ)
from predicted values, as a function of revolutions. The groupings of
residuals may reveal the source of a problem in the maintenance of reliable
elements. The output of the REDUCT program 'procedure 3-M is often used
to provide the data for such a graph.
3.10.2 Initial Observations
Initial observations on a newly launched satellite usually reflect a major
trend. Elimination of those observations which deviate from such a trend
tends to improve the computed element set. (procedure 3*2)
3.10.3 Element Set Variations
Observations on a satellite often reflect a slight change in the orbit of
the satellite by their general trend- A review of delta t vs. revolution usin^
all the observations sometimes indicates a break in the general trend. If
earlier observations (prior to the trend change) are eliminated, the most
recent element set can be differentially corrected (procedure 3*5) using
only the recent observations, which represent the latest changes in the orbit.
3.10 OBS SELECTION
h May 196U 3-30 TM-LX-123/OOO/CO
3-10.4 Observations on an Unusual Orbit
Satellites having unusual orbits often reflect one or more of the following:
a. High eccentricity
b. Low inclination
c. Small radar cross-section
d. Perigee in soutnern nemispnere
e. Large period
f. Small period (e.g., approacning decay)
g. High drag
n. Element set errors
When a satellite has an unusual orbit, sensor coverage is generally marginal.
Thus the observations reported often represent a few unequally distributed
points in the satellite orbit. A group of selected observations, evenly
representing tne entire satellite orbit, usually provides a better correction
of the element set.
3.10.5 Observations on Assocv ated Bodies
When part of tne main body of a satellite breaks off or is separated in
the form of debris, tne debris observations are often not as numerous as
the larger body observations. However, debris observations are usually
received about tne same time as tne main body observations, and may associate
partially or completely witn the main body element set. Debris observations
deviate mainly in tneir time residuals and, for a particular piece, tnese
deviations are consistent. Tne use of only debris observations in differentially
correcting tne main body element set provides an element set on the debris
object. The main body element set before correction is retained to represent
the main body of tne satellite.
3.10.6 Unidentified Observations
Occasionally tnere are too few observations associated with an element set
to provide for ade4uate correction of the element set. Some of the un-
identified observations in tne system, wnicn did not associate witn tne
3-10 OBS SELECTION
h May 1964 3-31 TM-LX-123/000/00 (Page 3-32 Blank)
element set using routine procedures, may in fact represent the satellite.
Observations received during a particular time period over a specific sensor
may be selected manually or by use of the OBSSEP program. Next, they are
associated with those observations which do not associate with any other sate]lite,
and then examined for possible association with a given element set.
iy
3.11 DECAY PREDICTION
k May 196U 3-33 TM-LX-123/OGO/OO
3.11 DECAY PREDICTION
3.11.1 General
A satellite is removed from the system when it has reentered the earth's
atmosphere or is no longer in orbit. Decay predict.-'on is seldom exact, so
several methods should be used simultaneously.
3.11.2 Initial Decay Indications
The Duty Space Surveillance Officer (DSSO) usually forecasts satellite
decay by a period check. The satellite is then transferred to the Analysis
Division for maintenance until it has decayed.
3.11.^.1 Input
a. Element set
b. Probable decay indication:
1. Period less than 90 minutes or
2. Decrease in period and eccentricity, and elements that hold for
only a fev days.
3.H.2.2 Processing
Determine a probable decay day by running the King-Hele/Findley program with
the element set, or by examining the results of the last King-Hele/Findley
run on this element set, which the DSSO initiated before transferring the
satellite to the Analysis Division. A revclution vs. day plot is generated
to substantiate the King-Hele/Findley predictions.
3.H.2.3 Output
The King-Hele and Findley routines both predict a decay day.
3.H.3 Final Decay Indications
The approach of final decay is indicated by the period, the rate of change
of the period and the satellite characteristics (tumble rate, motion, size,
shape and mass). Maintenance of the satellite requires greater attention
especially when decay appears to be less than ICO revolutions away. Care-
flil selection of observations may substantially improve the element set.
3-11 DECAY PREDICTION
h May 196k 3-34 OM-LX-123/OOO/OO
3.H.3.I Input
a. A graph of tne difference between predicted and reported observation
time for each revolution (delta t vs. revolution.)
b. A graph of the period for eacn revolution (period vs. revolution or day)
c. Satellite cnaracteristics - tumble rate, motion, size, snape and mass.
3.11.3-2 Processing
There are four metnods of predicting decay:
a. Run the Jacchia program using tne periods and corresponding
revolution.
b. Manually extrapolate the period on the period vs. revolution or day
graph, and compare tne results witn tnose of the Jacchia program.
c. Examine tne delta t vs. revolution graph for a break in tne curve.
This curve usually becomes cubic in snape and, just before final
decay, the rate of decrease of delta t increases so snarply as to
deviate from a cubic curve and approacn a logaritnmic curve.
d. Identify that time span between the last observation reported and
the first predicted observation not reported. Tnis is only as reliable
as the element set used to generate tne look angles for *,ne sensors.
Usually all four metnods are used, and Jaccnia may even be run several times
using different sets of periods, to determine a predicted range of revolutions
within wnicn to expect final decay. If results of tne various methods agree,
the analyst may conclude tnat final decay nas occurred wn^n tne first tasked
sensor fails to report an observation. Otnerwise tne analyst may wait until
several tasked sensors nave failed to observe tne satellite.
Occasionally satellites decay snortly after launcn or are deorbited. Time
for decay prediction is not available and tne time of decay is often reported
by an outside agency.
After final decay nas been concluded, initiate tne final decay message and
remove the satellite from tne SEAIA files.
3.12 ELEMENT CONVERSION
lJuly 1964 3-35 lM-LX-]23/000/00A
f)
3.12 ELEMENT CONVERSION
3.12.1 General
Elements received from external agencies (NASA, 659^-th Aerospace Test Wing,
Sunnyvale, NAVSPASUR) must be converted to a form useable by SPACETRACK.
The procedure for making the necessary adjustments is outlined below.
It should be noted that epoch times shown are not necessarily for a nodal
crossing as used by SPACETRACK, but are usually defined for some arbitrary
point in the orbit. The epoch time is measured at some point beyond perigee
and the satellite position at epoch is given by the mean anomaly, M.
3.12.1.1 Input
a. Orbital element set.
3.12.1.2 Processing
First, determine the time from perigee to the next nodal crossing. This is
dme by subtracting the argument of perigee (üu)from 36O . Figure 3~3 *s a
geographical representation of the problem.
atellite
point of ascending nodal crossing
M = mean anomaly from the message
u) B argument of perigee
perigee
v = the angle between perigee and nodal crossing (360°-^ )
Figure 3"3
3.32 ELEMENT CONVERSION
Uuly 1964 3-36 IW-LX-123/OOO/uOA
Let the quantity obtained above equal v, and, by substituting in equation 1,
determine the eccentric anomaly, E.
/,\ _ e + cos v , , . .j. \X) cos E = •— , where e = eccentricity 1 + e cos v *
Calculate the mean anomaly, M by equation (2):
(2) H « E . e sin E (57-3°),
Then, by substitution in (3) determine M , (total change in mean motion from old epoch to new epoch) * (3/ M=M - M, M = mean anomaly from the message
The time of the epoch in the message may now be changed to the time of the
ascending node by using equation (4) and (5). Mt (4) At = -rrzo P., P. = anomalistic period from the message
(5) T = T + At, T = nodal epoch time
T - message epoch time m
The right ascension of the ascending node at T must now be corrected, using
the right ascension (Q) to calculate a new right ascension (d ).
(6) 0 = Q + Ö At, where: Q = right ascension from message.
0 = right ascension of nodal crossing.
0 = right ascension motion.
Since the argument of perigee is given for a nodal crossing on SPACETRACK
elements the argument of perigee on the message must be changed by equation (7)
(T) W = UÜ + ti)At, where u> = new argument of perigee, o o CO = argument of perigee from the message.
U) = argument of perigee motion.
Next, perigee distance and semi-major axis must be converted into earth radii.
Finally, a new epoch revolution number should be calculated. This can be
obtained from an old bulletin, or from the time equation (8).
(8) T = TQ + PNAN + C (A N)2 + D (A N)3
r m- LX-12 3/000/00
r
4 May 1964 4-1 (Page 4-2 Blank)
Section 4
PROGRAMS
The programs in the B-2 System are organized into six functional areas:
a. Executive
b. Association
c. Element Determination
d. Observation Acquisition
e. Interplanetary
f. Miscellaneous
A seventh group consists of programs for use on the 1620 computer.
Card and deck input formats are specified and outputs described for the
programs most frequently used by the analyst. Tfte purposes of the less
used programs appear at the end of their appropriate functional area.
Following the program sections are descriptions of OCS sequences, Schedule
Tape requirements and standard card formats.
.
4 May 1964 4-3 TM-LX-123/OOO/OO (Page 4-4, Blank)
4.1 EXECUTIVE AREA
The executive area of the B-2 System is composed of a real-time subsystem
(BMEWS and INTPROC), a non-real-time subsystem (EXECM0D1, SYMOCT, EXECM0D2,
and EXECM0D3), and an initialization subsystem (BSTARTUP and BRSTART). The
real-time executive subsystem providet for BMEWS DIP backup while the non-
real-time executive subsystem provides control for the Space Track programs.
There are two modes of operating the B-2 System:
a. Interruptable - Space Track and BMEWS DIP backup
b. Non-interruptable - Space Track only
The BSTARTUP program is used to initialize the B-2 System when running in
the interruptable mode. The BRSTART program is used to re-start the system
when a machine malfunction has occurred in the real-time area of core. The
INTPROC program provides v,he capability to interrupt a Space Track program
and perform BMEWS DIP backup, and then return to the interrupted program
without loss of data. The BMEWS program provides duplicate backup for the
BMEWS DIP processor, under the control of the INTPROC program.
The primary non-real-time executive program is EXECM0D1, which contains the
basic routines that are required for operator control of the Space Track
System. The EXECM0D2 program provides control of OCS and Schedule Tape
runs, including program environment and system tape control. EXECM0D3 is
the Schedule Tape executive program. It is used for converting control
cards and data cards stored on the schedule tape, and for storing them in
core in a format acceptable to the othe^ system programs. It also transfers
data from the prestored schedule tape to a dato input tape when data for a
manual program is interpreted. After the data cards have been converted,
control is returned to EXECM0D2 where the specified program is read in and
operated. The SYMOCT program converts mnemonic octal corrections from a
prestored tape to a format acceptable to the central computer. The program
operates as a closed subroutine of the EXECM0D1 program.
*
h May 19& 4-5 -M-LX-123/OOO/OO (Page k-6 Blank)
4.2 ASSOCIATION AREA
The Association area includes the input conversion programs (MAP and ORCON),
the association sequence prr^rams (RASSN, RTPJUG, SRTMRG and SRCHEK), another
association program (REDUCT) and observation file maintenance programs (OFURGE,
OBSSEP, SRADU, RUMOV, PRINTER, GOODER and OBSEND).
r
»
RASSN
IJuly 1964 4-7 TM-LX-I23/OOO/OOA
4.2.1 REPORT ASSOCIATION - RASSN
4.2.1.1 Purpose
The RASSN program associates each of the observations with the element set
as Associated (Ra), Doubtful (Rd) or Unassociated (Ru). The classification
is based on a comparision of the residuals against specified criteria.
These criteria are specified by the Analyst when in the Schedule Tape Kode.
In the Automatic Mode, the criteria are contained within the program with
the following values:
At = 2 min.
RA = Not tested.
AH = Not tested.
VM = 1000 km.
e = .2°
4.2.1.2 Input
4.2.1.2.1 Automatic Mode - in an OCS sequence
a. Observations from the R-tape.
b. Element sets from the E-file tape.
c. Sensor coordinates from the S-file tape.
d. OCS Toggle number = Desired OCS sequence.
4.2.1.2.2 Schedule Tape Mode (Toggle 24 On)
Deck Column Position Card type Number Punch
1 Schedule Tape Card
2 Job Card
3 Remarks Card
4 Program ID Card
1-6 SPSJ0B
9-13 RASSN
RASSN
1 July 1964 4-Ta IM-LX-123/000/OQA
(Page 4-7b Blank)
Deck Column Position Card type Number Punch
17 0 = Element Set cards, S-file and R-tape
inputs.
1 = Observation cards, S-file and E-file
inputs.
2 = Parameter card, Satellite Number card
and S-file, E-file and R-tape inputs.
3 = Element Set cards, Observation cards,
and S-file tape inputs.
k = Parameter card and S -file, E-file and
R-tape inputs.
5 = Parameter card, Observation cards and
S-file and E-file tape inputs.
6 = Parameter card, Element Set cards,
Observation cards and S-file tape inputs
7 = Parameter card, Element Set cards and
S-file and R-tape inputs.
18 0 = Sorted/Merged, Hardcopy and residual
cards output.
1 = Sorted/No Merge, Hardcopy and residual
cards output.
2 = No Sort/No Merge, Hardcopy output.
3 = No Sort/Merged, Hardcopy output.
80 J = Card type.
RASSN
1 July 196k 4-8 IM-LX-123/OOO/OQA )
Deck Column Position Card Type Number Punch
Parameter Card
1-8
9-16
17-24
25-32
33-40
80
Delta T limit (max. = l440 min.)
Delta RA limit (max. = 3^0°)
Delta H limit (max. = 6378 km.)
Vec. Mag. limit (max. = 10 km.)
Beta limit (max. = 90°)
P = Card type
NOTE: Any unspecified limit (blank cols.) is assumed to contain its
maximum value.
6 Data Cards:
a. Input Option 0:
(l) Element Set cards
b. Input Option 1:
(l) Observation cards
c. Input Option 2:
(1) Parameter card
(2) Satellite Number card
d. Input Option 3"
(1) Element Set cards
(2) Observation cards
J
- • . -
t
Deck Position Card
Column Ttype .Number Punch
e.€. Input Option k:
(l) Parameter card
f.*. Input Option 5:
(1) Parameter card
(2) Observation cards
Input Option 6:
(1) Parameter card
(2) Element Set cards
(3) Observation cards
h. * Input Option 7:
(1) Parameter card
(2) Element Set cards
7 End of Case Card
8 End of Job Card
9 End of Schedule Tape Card
10 Blank Card
4.2.1-3 Output
RASSN
k May 1964 4-9 IM-LX-123/OOO/OO
k.2.I.3.I Normal RASSN
The ordering of the printed output from RASSN may be made in two forms, sorted
and unsorted. For sorted output associated (Ra) and doubtfully associated (RD)
observations are printed first and listed in the order received from the
R-tape. The unassociated observations are printed in the second section
of printout in chronological order. In the unsorted form, all reports are
output in the order processed.
The quantities printed are:
1. association status (STATUS)
1 = Ra for radar report
2 = Rd for radar report
3 = Ru for radar report
RASSN
h May 1964 4-10 TM-LX-123/OOO/OO
k - Ra for angles only report
5 = Rd for angles only report
6 = Ru for angles only report
7 = Ra for range rate report*
8 = Ru for range rate report*
2. tag (association made by sensor - OSAT)
3. sensor number (STAT)
k. observation time (last digit of year, month, day, hour, minutes,
seconds and hundredths of seconds YYM DD KHMMSS.SS)
5. association number (satellite number with which the observation has
been associated; blank for Ru's - NSAT)
6. message number (if present; MSGNO)
7. revolution number and element set number (Ra & Rd only; REV EL)
The remaining quantities vary with the type of association status and are
as shown below
STATUS QUANTITIES PRINTED
1 U &t, vector magnitude, ß, time since epoch
2 Uo, &t, vector magnitude, ß, Ap> Ah, AA cos h, time since epoch ;
3 0, \, H, A, h, p, sidereal time
k U, > At, , vector magnitude, ß, time since epoch ho n
5 U, , At, , vector magnitude, (3, time since epoch, A6 and Aa j ho n
cos 6, or Ah and A-A c°s h
6 6 and a or h and A
7 Ap, tag = association number, time since epoch
8 P
* currently not used
RAGSN
k May 1964 4-11 TM-LX-123/OOO/OO
• -
where U = argument of lPtitude
&t = observed minus predicted difference in time (minutes)
Victor Magnitude = magnitude of vector distance between observed
and predicted positions (km)
ß = "out of plane"angle
p = range
p = range rate *
Ap = observed minus predicted range
h = elevation
Ah = observed minus predicted elevation
6 = declination
A6 = observed minus predicted declination
or = right ascension
Aa cos 6 = observed minus predicted right «ascension
A = azimuth
AA cos h = observed minus predicted azimuth
At, = At computed from elements
AU. = AU computed from elements ho o
If on the same observation there are two or more doubtful assoceticns, they
are printed in the output. The best doubtful, based on the lowest vector
magnitude, is marked with an asterisk next to association status. A tagged
observation whose tag is changed in processing is shown first as a doubtful
association with a question mark next to association status. As many
residuals as have been computed are printed; those not computed at the time
of untagging are shown as zero.
SAM
PLE
PR
INT
OU
T,
RA
SSN
T
OSA
T
STA
T
YMM
DD
HH
MM
SS.S
S D
T
U
BE
TA
VE
C-M
AG
D
RA
NG
D
EL
EV
DA
CO
SH
TI-
TO
A
MIN
D
EG
DEG
K
M
KM
DEG
DEG
D
AY
S T
NSA
T
OB
SN
M
SGN
O
RE
V
EL
U
S
DE
LH
D
EL
RA
1 OO
O
32
8 1+
01
19 2
1303
7 A
2 68
1
2841
3 13
10
24
3 00
0
32
9 40
1 19 2
1295
1-98
28
412
2 00
0
32
9 ^0
1 1
9 21
1756
.42
f^8
2839
6 13
301
6
2*00
0
32
9 40
1 19 2
1141
0.30
23
6
2838
5 13
563
47
2 00
0
32
9 40
1 19 2
1141
0.30
54
2 28
385
1268
0
7
4 00
4
03
3 40
1 19
0312
10.9
2 00
4 29
249
0
0000
2613
1 2S
7
5';0
04
0
4l
401
l8
1455
25-2
4 29
252
00
000
0 29
7
4 00
4
041
401
18 1
4552
5.24
57
3 29
252
0000
0 16
38
10
2?02
8
345 4
01
18
1300
53-5
4 29
242
0000
0 0
117
3 02
8
34
5 40
1 18
1300
53.5
4 29
242
0000
0 5?0
8l
0
29
401
18 0
5445
2.18
29
204
00
000
0 14
6
6 0
8l
0
29
401
18
0544
52.1
8 29
204
00
000
-.56
84 -.
13
..01
65
-.0
7
..43
85
-01
--5
7
85
-31
.03
107
-.03
.00
94
-.05
-.05
125
-.6
0
.00
0
-.0
0
.00
3
7-3
.28
274
111
191
293 13
11
208
0
7359
-7.6
.0
•173
-1
1
.6
•293
.0
.0
.0
PAG
E
1
AL
T
RA
NG
E
EL
EV
AZ
IM
KM
RM
DEG
DEG
LA
T
LO
NG
SID
.T
RR
AT
DR
R
DEG
DEG
H
H M
M
M/S
M/S
.81
-.1
2
1.5
6
-.5
7.8
5
.2
18.
72
1.3
3
582.
O
2
12
8.8
6.8
346.
1 80.5
184.8
1
9 26
-1.3
-2
.8
.82
41.7
8
.0
13.7
7
75
2.9
IIO
5.O
39-4
1.49
.0
46.7
179.
2 8
25
23
.2
7
8.9
6
.40
I M k
-3.3 2
6?.
7
1 K 1 ts o
o
RASSN
k May 1964 4-13 lM-LX-123/OOO/OO
4.2.1.3.2 SRCHEK
Normally the SRTMRG and SRCHEK programs are automatically run immediately
after RASST^ so the SRCHEK output is included here. The quantities printed
are:
1. Satellite number and name.
2. Epoch date and time (year, month, day, hour, minutes, seconds,
thousandths of seconds).
3. Element number.
4. RMS value and RMS limit.
5. Delta T and mean delta T (of Ra's in last 5 days).
6. Number of observations from date and time, to date and time
7. Predicted date and time at which delta T will reach or exceed
.8 minutes (.8 DELTA T). A minus sign after the date indicates
that the satellite will not reach .8 minutes prior to bulletin
expiration. A plus sign indicates that the sate^.ite will exceed
.8 minutec before the elements expire. Eleven X's will be printed
for satellites with less than 5 observations or when the slope of
the least square fit is zero.
8. Number of blocks on the SRADU tape being utilized for observations on
the satellite and where they are located.
9. Number of Ra's since epoch and in the last two days.
4.2.1.3.3 SATTB from SRCHEK
A Satellite Table (SATTB) is also produced by the SRCHEK program. This table
contains those satellites which require an SGPDC run. Specific information
for each satellite is printed:
1. Indicators, listed in order of priority
a. Minus (-) - bulletin/element expiration date is within 36 hours
of expiration.
b. Plus ( + ) - RMS exceeds RMS limit for t:ie satellite.
c. Plus L (+L) - No Ra's within the last two days.
d. Plus T (+T) - Mean £t of all Ra's for last five days exceeds .4
minutes.
e. I suffix - an automatic run has been generated.
RASSN
k May 1964 k-lk TM-UC-123/OOO/OO
2. RMS value
3. Number of observations
k. Delta T
SAMPLE PRINTOUT, SRCHEK SATTB
SATTB- LIST OF SATELLITES WHICH NEED ELEMENTS CORRECTED
SATELLITE NO. RMS NO. OF OBS. T - TO
+L 059 2k 5 12.2 -I 08l 8 2 •9 +L 188 0 0 6.7 +L 194 38 6 29.2 +L 195 6 1 18.2 +L 196 15 2 26.1 +L 205 0 0 k.O +L 239 0 0 13.9 +L 273 26 1+ 17.0 +L 322 96 12 9.h +L 359 0 0 .8 +T 378 179 22 39.1
4.2.1.3.1+ Analyst RASSN
If a parameter card is used in input with input options 5 or 6 (Analyst
RASSN) the RASSN output will be presented in a slightly different format
although the content is the same. All of the associations within the limits
specified will be printed in the doubtful format to allow printing of all
residuals. The last line for each observation will be in the unassociated
format to allow printing of the observational data.
h May 1964
e 4-15
Page 16 blank) IM-DC-12 3/000/00
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ft- nn -4 4» •- «ft 9) »4 «9 M • ft« ft* -J ft- -» -J »4 rJ 9» J hi •» -J •- •>• Ul < «* • 5
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4 May 1964 4-17 TM-LX-123/000/00 (Page 18 blank)
4.2.2 OBSERVATION SEPARATION - OBSSEP
4-2.2.1 Purpose
The OBSSEP program separates the observations on a R-tape into two groups,
generating two new R-tapes. The separation is based on observation time.
Those observations falling within the specified time slice(s) will be Dlaced
on a "high priority" R-tape, and all others on a "low priority" R-tape.
4,2,2.2 Input
Each time slice is specified by the analyst and input via the i'lexowriter:
a. Hour, minute, month, day and year of start t.'rae.
b. Hour, minute, month, day and year of stop time.
4,2.2 3 Output
No program printout is generated by this program.
REDUCT
k May 1964 4-19 TM-LX-12 3/000/00
4.2.3 NODAL CROSSING REDUCTION - REDUCT
4.2.3.1 Purpose
The REDUCT program reduces observations to the last nodal crossing, computes
residual differences betveen the observations and an element set and compares
the differences against specified tolerance limits. There are three sub-
sections in the REDUCT program.
a. General - for visual, radar and/or Baker-Nunn observations
b. Doppler - for doppler observations
c. Direction Finder - for direction finder observations
Residuals Computed by Various Program Sections
Program Section Time Residual Right Ascension
Residual Height Residual
Visual Radar Baker-Nunn Doppler Direction Finder
X X X X X
X X X
X
Tolerance Codes and Corresponding Values
Right Ascension 1 Code Time (days) (degrees) Height (km)
Blank-» 0 j .002 20 200 1 1 5 500 1 2 .003 360 10000 3 .002 36O 10000 4 .001 36O 10000
1 5 .003 5 300 6 .05 2-5 200
REDUCT
k May 1964 1+-20 TM-LX-123/OOO/OO
4.2.3.2 Input - Schedule Tape Mode (Toggle 24 On)
Deck Position Card Type
Column Number Punch
1
2
3
k
Schedule Tape Card
Job Card
Remarks Card
Program ID Card
17-19
25-30
31-35
Parameter Card
RUN
REDUCT
,DATA
1 0 = Special sensor tape (not the S-file tape)
input
1 = Sensor cards input
3 0 = Use interim tape and check residuals vs.
tolerance limits
1 = No interim tape and no check of residuals
vs. tolerance limits
8 0 = Identified observations processed against
associated element set only
1 = All observations processed as unknowns
9 0 = Hardcopy output
1 = Hardcopy and TTY output
10 0 = Re-reduction, with open tolerance limits,
of unassociated observations
1 = No re-reduction of unassociated observations
11 0 = Compute perigee distance
1 = Use perigee distance from element set
Element Lead Card
8 7 = Card type
Element Set Cards (max. =25 sets)
Sensor Lead Card (unnecessary with special sensor tape)
8 8 = Card type
REDÜCT
ns
k May 196i+ 4-21 TM-LX-123/OOO/OO
Deck Column Position Card Type Number Punch
9 Sensor Cards (max. = 750 sensors)
10 Observation Lead Card
7 0 (or Blank) = Tolerance Code 0
1 = Tolerance Code 1
2 = Tolerance Code 2
3 = Tolerance Code 3
k = Tolerance Code h
5 = Tolerance Code 5
6 = Tolerance Code 6
8 8 = Card Type
NOTE. The tolerance limits for a group of observations may be changed by
preceding the observation cards with another Observation Lead card
11 Observation Cards (no limit)
12 Blank Card
13 End of Input Card
79 9 = Card type
Ik End of Data Card
15 End of Job Card
16 End of Schedule Tape Card
17 Blank Ca-d
4.2.3-3 Output
h.2.3«3-1 Satellite Inventory
Output begins with the satellite inventory. Seven groups, composed of
satellite number and element number, are printed per line.
k.2 3-3«2 Observation Output
Observation output will occur in three formats depending on which part of
the program has done the reduction.
REDUCT
k May 1964 k-22 TM-LX-123/OOO/OO
4.2.3.3.2.I General Reduction Output
1. Observation identification number
a. Satellite number
b. last digit of year of observation
c. month, day, hour, minutes, seconds, hundredths of seconds (ID)
2. Epoch revolution number (N)
3. Argument of latitude (U)
k. Time of nodal crossing (T sub N)
5. Time residual in days (DELTA T)
6. Latitude of subsatellite point (PHI S)
7. Longitude of subsatellite point (LS)
8. Right ascension of ascending node in degrees (RA N)
9. Right ascension residual (DEL RA)
10. Height in kilometers (H (KM))
11. Height residual (DEL H) - zero for B-N or VIS.
12. Obs type (TYPE) - VIS for visual
RDR for radar
B-N for Baker-Nunn
13. Element Number (ELM)
14. Station number (STA)
15. Optional $ - implies obsei'vation time precedes epoch by more than
h days.
00
REDUCT
4 May 1964 4-2 3 TM-LX-123/OOO/OO
4.2.3-3*2.2 Direction Finder Reduction (not currently used)
1. Identification (same as for general reduction)
2. Epoch revolution (N)
3. Time of nodal crossing (T SUB N)
4. Time residual (DELTA T)
5. Elevation in degrees (H)
6. Slant range in kilometers (s)
7. Height in kilometers (H (KM))
8. Element number (ELBA)
9. Station number (STA)
4.2.3«3-2.3 Doppler Output (not currently used)
1. Identification (same as for general reduction)
2. Epoch revolution (N)
3. Computed time of nodal crossing (T SUB N)
4* Time residual (DELTA T)
5« Arc distance in nautical miles from station to subsatellite point (D)
6. Elevation in degrees (H)
7. Slant range in kilometers (S)
8. Element number (ELM)
9. Station number (STA)
4.2.3'3-3 Explanatory Comments
Miscellaneous informative comments may be interspersed for observations. These
always appear with the ID information. Some of the more significant comments
are:
1. UNTAGGED UOS REDUCED W/0 TOLERANCES
All observations which follow have previously appeared as untagged
UO's, and have now been re-reduced with large tolerances.
2. U0 S FOLLOW
All observations which follow on the page did not correspond to any
satellite whose elements are stored in the catalog.
REDUCT
k May 196k 4-2^ TM-LX-123/OOO/OO
3. UNKXXXXX***XXX
The next observation is an unknown. The message number is given. If
the observation was a known observation which was treated as an un-
known, the satellite number is also given.
REDÜCT
k May 196b U-25 Page 26 blank)
TM-DC-123/000/00
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4 May 1964 4-27 IM-LX-123/OOO/OO
4,2.-4 OTHER
The following programs in the Association area are seldom used by the analyst.
A brief description of each program is given.
4.2.4.1 GOODER
The GOODER program is used when the SRCHEK program indicates that there are
satellites out of order on the SRADU tape. The program generates a new SRADU
tape restoring the satellites to their proper order.
4.2.4.2 MAP
MAP is a program designed to assemble DMNI data into input observation messages
in a format acceptable to ORCCN. The DMNI input tapes are generated in real-
time by INTPROC or off-line with the 410 Recorder, The DMNI tapes currently
contain only the high-speed data from BMEWS; however, the MAP program is
designed to process both high-speed and teletype data. The only data currently
assembled by MAP are BMEWS Q-point (penetrations of the BMEWS fans) messages.
All other data, including incomplete messages and improper formatted messages,
is discarded.
The DMNI dump tapes are processed in the order in which they were generated.
A left-over message table is maintained by MAP to prevent loss of data be-
tween successive DMNI tapes»
4.2»4„3 OESEND
The OBSEND program produces teletype and/or hard copy outputs from observations
on the SRADU tape. The program is used for transmitting observations to the
backup facility at Hanscom. The program allows for output!ng selected satellite
observations or all observations on the SRADU tape.
4.2 4.4 OPURGE
The OPURGE program it, used to purge observations from the SRADU tape. The
program operates in four modes as follows
a. Mode one - delete all observations for a specific satellite.
4 May 1964 4-28 TM-LX-123/OOO/OO
b. Mode two - delete only those observations requested by satellite and
sensor number.
c. Mode three - delete individual observations as specified by satellite
and observation number
d. Mode four - delete all observations prior to an input time and satellite
number.
4.2.4.5 ORCON
The purpose of ORCON is to decode, edit, and store sensor observations. The
observation reports are in a variety of formats and may be received via tele-
type, or digital data link (BMEWS). All observations of various types received
via the several communications systems are converted to one standard format
and stored on an R-tape. Error checking is performed and observations in
error are not stored on the R-tape; however, they are recorded on the system
output tape so corrective action can be taken.
4.2.4.6 PRINTER
The PRINTER program is an observation editing program. It converts the
observations on the R-tape to a readable format. The program is presently
used after the operation of ORCON to determine if all input data (especially
BMEWS Q-point messages) has been converted. The program will also convert
the information on the DMNI dump tapes to a readable format. This option
is especially useful in the checkout of certain programs and in error
correction
4.2.4.7 RTPJUG
The function of the RTPJUG program is to transfer all unprocessed observations
from the R-tape to a scratch tape so they can be processed later by RAGGN.
The console interrupt mode would be used only if a high priority run is
required during the operation of RAGGN.
RTPJUG is run as a result of
a. A console interrupt during the operation of RAGGN, or
b- As a manual program when a machine malfunction occurs during the
operation of RAGGN
4 May 1964 4-29 ^-LX-123/OOO/OO
(Page 30 blank)
4.2,4 08 RUMOV
The RUMOV program transfers the unassociated observations from the SRADU
tape to an R-tape for reprocessing by RASSN.
4.2.U„9 SRADU
The SRADU program generates a SRADU tape from standard observation cards. The
program first builds a RADU tape and then calls in the SRTMRG program vhich
sorts the RADU tape and builds the SRADU tape«
4.2.4.10 SRCHEK
The SRCHEK program is normally run automatically after SRTMRG in the association
sequence. However, the program can be run in the manual mode. The program is
used to:
a. determine if errors exist on the SRADU tape
b. furnish a satellite table (SATTB) of those satellites whose elements
need updating
c. describe the observational status of each satellite on the SRADU
tape (e.g., RMS, mean At, number of Ra's received in last five days, etc.)
4.2.4.11 SRTMRG
The SRTMRG program is normally run automatically after the operation of RASSN.
However, it can be run as a manual program if tape errors are encountered.
Its main functions are to:
a. Sort all newly associated observations (stored on RADU tapes) and
merge these observations onto the system observation tape (SRADU tape.)
bo Produce observation cards from the newly associated observations.
These cards are used for running programs in the schedule tape mode
and for system backup files
c. Purge those observations from SRADU tape that are not useful in the
differential correction function.
k May 196^ b-31 TM-LX-12 3/000/00 (Page 32 blank)
i+,3 ELEMENT DETERMINATION AREA
The Element Determination area includes the initial orbit computation
programs (IOHG, IORF, IOANGLE, and ROC), the differential correction
programs (SGPDC, SPWDC and ESPOD), the maintenance and summary programs
(SUM, SEAI, HANSEL, MSGV, LOCVEC, XROADS and CCOE), and the decay pre-
diction program (SPIRDECB).
(
#
ESPOD
14 August 1964 4-33 TM-LX-123/OOO/OOB
4.3,1 ELECTRONIC SYSTEMS PRECISION ORBIT DETERMINATION - ESPOD ''
4.3.I.I Purpose
The ESPOD program differentially corrects a given element set (first updating
the elements to a later epoch on option) and computes predicted satellite
positions. It can further differentially correct a given set of constant
biases in range, azimuth/right ascension, elevation/declination, range rate,
sensor longitude, sensor latitude, sensor height, and time for several sensors.
The differential correction is accomplished using a weighted least squares fit
to the observations. The trajectory and ephemeris computations use a special
perturbations Cowell formulation, where the whole force field is integrated.
The (optional) update of the elements to a later epoch uses a simplified gen-
eral perturbations formulation. Various statistical quantities are calculated
and output to aid the analyst in determining the degree of validity of the re-
sults. ESPOD may be used for orbits of any eccentricity (including elliptic,
parabolic, and hyperbolic types) provided the earth is the primary force center
Perturbations due to the moon and sun are accounted for by using ephemeris
tapes of these bodies. Several atmospheres are available on option.
4.3.12 Input - Schedule Tape Mode only (Toggle 24 On)
Deck Column Position Card Type Number Punch
1 Schedule Tape Card
2 Job Card
1. The write-up for the ESPOD program input has been furnished by the 496L SPO.
ESPOD
Ik August 19ft 4-35A TM-LX-123/000/0OB
Deck Column Position Card Type Number Punch
3 Remarks Card (optional)
h Program ID Card
17-19 RUN
25-29 ESPOD
30-34 ,DATA
5 Job Description Card
1-3 JDC = Card type
h-J Satellite Number (rt. adj.)
8-17 Satellite Name (optional)
l8-29 Header to be printed on output (optional)
30 0 = COLD START
1 = CONDITIONED START (i.e. results generated (on Tape 7 by previous
2 = CONDITIONAL START (ESPOD runs are input (on Tape 7-
31 0 = Neither observations nor sensors are input
in any way except by a previous Tape 7.
1 - Either observations and/or sensors are in-
put in the deck or on SRADU or SEAI tapes.
32 0 - Do not print sensor locations.
1 = Print sensor locations.
33 Q - Do n°t print observations.
1 = Print observations.
3^- 0 = No sensor cards are in input deck.
4
ESPOD
14 August 196k 4-33B TM-LX-I23/OOO/0OB
Deck Column Position Card Type Number Punch
3^- 1 = Sensor cards are in input deck (These will
supplement or override sensor data from
SEAI tape).
35 0 = Obtain observations from SRAIÜ tape.
1 = Obtain observations from observation cards
in input deck.
36 0 = Do not print the constants used in ESPOD.
1 = Print the constants used in ESPOD.
37 0 = Use seven-card element set from input deck
or E-file, or use IGTYP card in input deck,
or previous Tape 7«
1 = Use elements stored by a PRDCT card on an
immediately preceding ESPOD run.
kl 0 = Do not differentially correct.
1 = Differentially correct (i.e. use ESPODDC).
T k2 0 = A-priori A A matrix not input.
T 1 = A-priori A A matrix input (SMAT cards).
1+3 0 = Do not punch (A A)" matrix.
1 = Punch (A A) matrix each iteration.
(UPMAT cards)
T kk 0 = Do not punch A A matrix.
rp 1 = Punch A A matrix each Iteration (SMAT cards)
I
ESPOD
Ik August 196U k-^C TM-LX-123/000/00B
Deck Position Card Type
Column Number Punch
k$ 0 = Print the u, v, w residuals.
1 = Print the s, t, w residuals.
2 = Print sensor latitude, longitude, height
residuals (i.e. how much sensor must be
"moved" to make calculated orbit coincide
with observation)
k6 0 = Retain "proven" elements for use in the
calculation of the predictions. ("Proven"
elements are those which were used to cal-
culate the trajectory and residuals of the
very last iteration).
1 = Retain "new" elements for use in the cal-
culation of the predictions ("new" elements
are those which were predicted by the very
last iteration, but which have not been
used for the calculation of residuals).
k*f 0 = Normal differential correction on same
elements each iteration.
1 = Calculate velocity correction to minimize
the RMS of the time residuals, but do not
apply the correction.
2 - Calculate velocity correction to minimize
the RMS of the time residuals, and apply
the correction on first iteration.
C I
ESPOD
14 August 1964 4-33D TM-LX-123/000/0OB
Deck Column Position Card Type Number Punch
51 0 = Do not calculate predictions or epnemeris.
1 = Calculate predictions/epnemeris (i.e., use
ESPODEPH)
52 0 = DAC cards are not present in input deck.
1 = DAC cards are present in input deck.
53 0 = Do not generate an XYZ ephemeris tape.
1 = Generate an XYZ ephemeris tape on Tape 10
for the program XYZLA, writing all ephemeris
points on output Tape 11 as well.
2 = Generate an XYZ ephemeris tape on Tape 10
for the program XYZLA, writing only first
and last ephemeris points on output Tape 11.
55 0 = Do not output the updated statistical
quantities.
1 = Output the updated statistical quantities
(i.e. those associated with the points of
the ephemeris).
56 0 = Do not punch the updated covariance matrix
T inverse (A A matrix, SMAT cards).
1 = Punch the updated covariance matrix inverse.
NOTE: Zeros and blanks are equivalent for Cols. 30-80.
NOTE: All cards between the JDC and ENDPR cards may be in any order.
ESPOD
Ik August 1964 <-33E TM-LX-123/000/0OB
Deck Column Position Card Type Number Punch
Remarks Card (optional)
1-2 01 = Card number.
5-7 REM
10-72 (As desired). These remarks are printed on the
ESPOD output, but are not typed on the flexowriter
Initial Conditions Card #1 (omitted if seven-card element set is in
the input deck or is obtained from the SEAI tape).
1-2 01 = Card number.
3-4 Differential Correction Iteration Number (op-
tional)
5-9 ICOND = Card type.
10-23 * Initial value of Right Ascension (deg) (or
longitude east (deg) ) or X (km).
29-42 * Initial value of Declination (deg) or Y (km).
48-61 * Initial value of Flight Path Angle (deg) or
Z (km).
67-80 * Initial value of Azimuth of Velocity Vector
(deg) or X (km/sec).
Initial Conditions Card #2 (omitted if seven-card element set is in
the input deck or is obtained from the SEAI tape).
1-2 02 = Card number.
3-4 Differential Correction Iteration Number
(optional).
NOTE: ^-tcrisk means i;se decimal poine somewhere in field.
ESPOD
* Ik August 1964 ),
-t •
Deck Column Position Card Type Number Punch
-W TM-LX-I23/OOO/OOB
ter
»).
»).
5-9 ICOND = Card type.
10-23 * Initial value of geocentric range (km) or Y
(km/sec).
29-42 * Initial value of magnitude of velocity vector
(km/sec) or Z (Km/sec).
Initial Time Card #1 (omitted if seven-card element set is in the
input deck or is obtained from the SEAI tape).
(This card gives the time associated with Initial Conditions, i.e.
epoch).
1-2 01 = Card number.
5-9 ITIME = Card type.
10-23 * Last two digits of year plus decimal point.
29-^2 * Month of year (one or two digits plus decimal
point).
48-61 * Day of month (one or two digits plus decimal
point).
67-80 * Hour of day (one or two digits plus decimal
point).
Initial Time Card #2 (omitted if seven-card element set is in the
deck or is obtained from the SEAI tape).
1-2 02 = Card number.
5-9 ITIME = Card type.
NOTE: Asterisk means use decimal point somewhere in this f4.eld.
ESPOD
Ik August 1964 »+-33G TM-LX-123/0OO/0OB
Deck Column Position Card Type Number Punch
10-23 * Minutes of hour (one or two digits plus decimal
point).
29-1+2 * Seconds of minute (one or two digits plus deci-
mal point plus decimal fraction of second).
Initial Conditions Type Card (omitted if seven-card element set is
in input deck or is to be obtained from SEAI tape.)
1-2 01 = Card number.
5-9 ICTYP = Card type.
10-23 * 1.0 = Initial Conditions are right ascension,
declination, flight path angle, azimuth
of velocity vector, magnitude of geocentric
range, magnitude of velocity vector,
(i.e. ADBAHV).
2.0 * Initial Conditions are: east longitude,
declination, flight path angle, azimuth
of velocity vector, magnitude of geocentric
range, magnitude of velocity vector.
(i.e. A DBARV) • * •
3.0 -~ Initial conditions are XYZXYZ
12 Drag Parameter Card (Car. be omitted if drag is negligible.
Must be input if DC is on Cd ä/2M).
NOTE: Asterisk means use decimal point somewhere in this field.
ESPOD
Ik August 196h U-33H TM-LX-I23/OOO/OOB
Deck Column Position Card Type Number Punch
1-2 01 = Card number.
3-k Differential correction iteration number
(optional).
5-8 DRAG.
10-23 * Initial value of Cd A/2M (in square meters/
kilogram)
where Cd = Coefficient of Drag (approx. 2.2)
A = Cross-sectional area of satellite.
M = Mass of satellite.
29-^2 * Initial value of K.
U8-6l * Blank or 0.0 = No drag variation
1.0 = Drag variation model is
K (| cos5 I - £) (day-night)
2.0 = Drag *ariation model is
K (]Mo ) (secular)
6T-8O * 1.0 = Use ARDC 1959 Static Atmosphere
2.0 - Use Paetzold/ARDC 1959 Dynamic Atmosphere
Blank or 0.0 or 3-0 = Use C0ESA 1962 Static
Atmosphere
U.O = Use C0ESA I962 Dynamic Atmosphere.
NOTE: An asterisk means use decimal point somewhere in this field.
NOTE: APF 10 cards must be input if a dynamic atmosphere is used.
ESPOD
lU August 196U U-33I TM-LX-I23/OOC/OOB
Deck Column Position Card Type Number Punch
NOTE: Trailing floating point fields may be left blank, but no in-between
floating-point fields may be left blank (fill with 0.0 if not used).
13 Bounds Parameter Card(s) (-'.These cards input if and only if one
wishes to override the nominal values
of bounds which are built into ESPOD^.
(The bounds appear in one-to-one corres-
pondence and order as the one-punch flags
on the CAT1 and CAT2 cards).
1-2 Bounds Card Number (e.g. 01, 02, 03, etc.)
3-^ Differential Correction Iteration Number
(optional)
5-8 BNDS = Card type.
10-23 * Maximum value of change between iterations
of a differential correction variable (i.e.
initial condition, drag, drag variation, or
bias).
29J+2 * (same as cols. 10-23 but for another variable).
U8-61 * (Same as cols. 10-23 but for still another
variable).
67-80 * (Same as cols. 10-23 but for still another
variable).
NOTE: Asterisk means use decimal point somewhere in this field.
,)
I \
ESPOD
11+ August 196U 4-33J TM-LX-I23/OOO/OOB
Deck Column Position Card Type Number Punch
NOTE: As many ENDS cards may be used as are necessary to specify the
required number of bounds. The last ENDS card may have several
trailing blank fields. For example, only one bound might appear
on the last ENDS card.
NOTE: Units of the bounds are the same as the units of the variables
corresponding to the bounds.
Category One Differential Correction Variables Card
NOTE: If a differential correction is to be performed (i.e. col. kl of
JDC card has one punch) and if both CAT1 and CAT2 cards are omitted,
ESPOD automatically differentially corrects the six ADBARV variables
If a differential correction is to be performed only on Category 2
variables (biases), or if no differential correction is to be per-
formed at all (i.e. col. kl of JDC card is blank or zero), then omit
CAT1 card.
1-2 01 = Card number.
5-8 CAT1 - Card type.
10 0 = Do not differentially correct Alpha
(Right Ascension).
1 = Differentially correct Alpha (Right
Ascension.
11 0 = Do not differentially correct Delta
(Declination).
1 - Differentially correct Delta (Declination)
ESPOD
Ik August 1964 4-33K TM-LX-123/000/0OB
Deck Column Position Card Type Number Punch
12 0 = Do not differentially correct Beta
(Flight Path Angle).
1 = Differentially Correcc Beta (Flight Path
Angle).
13 0 = Do not differentially correct Az
(Azimuth of Velocity Vector).
1 = Differentially correct Az (Azimuth of
Velocity Vector).
Ik 0 = Do not differentially correct R
(Magnitude of geocentric range vector).
1 = Differentially correct R
(Magnitude of geocentric range vector).
15 0 = Do not differentially correct V
(Magnitude of velocity vector).
1 = Differentially correct V
(Magnitude of velocity vector).
16 0 = Do not differentially correct Cd A/2M.
1 = Differentially correct Cd A/2M.
17 0 = Do not differentially correct K
(Drag variation parameter).
1 = Differentially correct K
(Drag variation parameter).
ESPOD
14 August 1964 4-33L TM-LX-123/000/00B
Deck Column Position Card Type Number Punch
Number of DC Iterations Card (if this card is omitted, ESPOD assumes
a maximum of five DC iterations).
1-2 01 = Card number.
5-9 NITER = Card type.
10-23 * Maximum number of differential correction
iterations (integral number plus decimal point).
Weighting Parameter Card(s) (input if and only if one wishes to
supplement or override the weighting parameters
which are already built into ESPOD).
1-2 Sigma Type Number (in the Master Sigma or
Sensor Type List, or as associated by an
STYPE card). (Number may range between 01
and 60).
5-9 SIGMA = Card type.
10-23 * Standard Deviation in Range (km) (Right Ascen-
sion of Field Reduced BN) expected for sensor(s)
associated with the Sigma Type Number.
29-42 * Standard Deviation in Azimuth (degrees)
(Declination of Field Reduced BN) expected
for the sensor(s) associated with the Sigma
Type Number.
NOTE: Asterisk means this field must have decimal point somewhere in it.
ESPOD
11* August 1964 fc-33N TM-LX-123/OOO/OOB
Deck Column Position Card Type Number Punch
48-61 * Standard Deviation in Elevation (degrees)
(Right Ascension of Precision Reduced BN)
expected for the sensor(s) associated with
the Sigma Type Number.
67-80 * Standard Deviation in Range Rate (km/sec)
(Declination of Precision Reduced BN) expected
for the sensor(s) associated with the Sigma
Type Number.
Sensor Type and Parameter Card(s)
(input if and only if one wishes to supplement
or override the sensor weighting types and
parameters which are already built into ESPOD)
1-2 Sensor Type and Parameter Card Number
(e.g. 01, 02, 03,...)
5-9 STYPE = Card type.
10-13 Sensor Number.
14-15 Sigma Type (i.e. weighting type) to be associ-
ated with the sensor in columns 10-13. (Two
digits, no decimal).
l6-19 Gross Outlier Rejection parameter (Gs)
for the sensor in columns 10-13. (Right
adjusted, no decimal point).
NOTE: Asterisk denotes use of decimal point somewhere in this field.
ESPOD
;> Ik August 1964 -33N TM-LX-123/OOO/OOB
Deck Position Card Typo
Column Number Punch
20 0 or blank = Do not apply refraction correction
to measurements of sensor in columns 10-13.
1 = Apply refraction correction to sensor in
col. 10-13.
21-23 N (mean surface value of refractivity * 10 ) s
for the sensor in columns 10-13, (not required
if col. 20 is blank).
29-32 Sensor Number.
33-34 Sigma Type (i.e. Weighting Type) to be associated
with sensor in col. 29-32 (two digits, no decimal)
35-33 Gross Outlier Rejection parameter (Gs) for the
sensor in col. 29-32 (right adjusted, no decimal
point).
39 0 or blank = Do not apply refraction correction
to measurements of sensor in col. 29-32.
1 = Apply refraction correction for sensor in
col. 29-32.
40-42 N (mean surface value of refractivity • 10 ) s
for the sensor in columns 29-32; (not necessary
if col. 39 is blank).
48-51 Sensor Number
52-53 Sigma. Type (i.e. Weighting Type) to be associ-
ESPOD
Ik August 1964 4-350 TM-LX-123/000/0OB
Deck Column Position Card Type Number Punch
ated with the sensor in col. 48-51 (two digits,
no decimal).
54-57 Gross Outlier Rejection parameter (Gs) for the
sensor in col. 48-51 (right adjusted, no decimal).
58 0 or blank = Do not apply refraction correction
to measurements of sensor in col. 48-51.
1 = Apply refraction correction for sensor in
col. 48-51.
59-61 N (Mean Surface Refractivity ' 10 ) for sensor s
in cols. 48-51- (Not required if col. 58 is
blank).
67-70 Sensor Number.
71-72 Sigma Type (i.e. Weighting Type) to be associ-
ated with the sensor in col. 67-70 (two digits,
no decimal).
73-76 Gross Outlier Rejection parameter (Gs) for the
sensor in col. 67-70 (right adjusted, no decimal).
77 0 or blank = Do not apply refraction correction
to measurements of sensor in col. 67-70.
1 = Apply refraction correction for sensor in
col. 67-70.
78-80 Ns (Mean Surface Refractivity • 10 ) for sensor
in cols. 67-70. (Not required if col. 77 is blank)
Ik). §
ESPOD
Ik August 1964 4-33P TM-LX-.123/O0O/OOB
Deck Column Position Card Type Number Punch
NOTE: Only those fields which one wishes to supplement or override need to
be input. The Gross Outlier Rejection parameter causes observations
to be rejected as follows:
Reject Range Observation if Range Residual >G (standard devia- \ > " s
tion in range for this sensor).
Reject Azimuth Observation if I (Azimuth Residual) cos Elevation
^> G (standard deviation in Azimuth for this sensor) s
Reject Elevation Observation if I Elevation residual > G (stand- I I s
ard deviation in Elevation for this sensor).
Reject Range Rate Observation if Range Rate Residual >G (stand- I 1 s
ard deviation in range rate for this sensor).
Reject Right Ascension Observation if | (Right Ascension Residual)
cos 0
sensor).
Reject Declination Observation if I (Declination Residual)
(standard deviation in declination for this sensor).
Category Two Differential Correction Variables Card(s) (Biases)
(Omitted if no DC to be done on Category Two Variables).
1-2 Category Two Card Number (e.g. 01, 02, 03,etc.)
5-8 CAT2
10-13 Sensor Number
Ik 0 = Do not differentially correct RANGE BIAS
for this sensor.
> G (standard deviation in right ascension for this
> Gs
ESPOD
Ik August 1964 4-33Q TM-LX-123/OOO/OOB
Deck Position Card Type
Column Number Punch
1 = Differentially correct RANGE BIAS for this
sensor.
15 0 = Do not differentially correct AZIMUTH BIAS
for this sensor.
1 = Differentially correct AZIMUTH BIAS for
this sensor.
16 0 = Do not differentially correct ELEVATION
BIAS for this sensor.
1 = Differentially correct ELEVATION BIAS for
this sensor.
17 0 = Do not differentially correct RANGE RATE
BIAS for this sensor.
1 = Differentially correct RANGE RATE BIAS for
this sensor.
18 0 = Do not differentially correct RIC3iT ASCEN-
SION BIAS for this sensor.
1 - Differentially correct RIGHT ASCENSION BIAS
for this sensor. (Must be optical sensor).
19 0 = Do not differentially correct DECLINATION
BIAS tor this sensor.
1 = Differentially correct DECLINATION BIAS for
this sensor. (Must be optical sensor).
•* '
ESPOD
Ik August 196^ 4-33R TM-LX-123/OOO/OOB
Deck Column Position Card Type Number Punch
20 0 = Do not differentially correct TIME BIAS for
this sensor.
1 = Differentially correct TIME BIAS for this
sensor.
21 0 = Do not differentially correct this sensor's
LATITUDE BIAS.
1 = Differentially correct this sensor's LATI-
TUDE BIAS.
22 0 - Do not differentially correct this sensor's
LONGITUDE BIAS.
1 = Differentially correct this sensor's LONGI-
TUDE BIAS.
23 0 = Do not differentially correct this sensor's
HEIGHT BIAS.
1 = Differentially correct this sensor's HEIGHT
BIAS.
29-32 Sensor Number.
33-42 Information identical with Column Numbers Ik
through 23.
48-51 Sensor Number.
52-6l Information identical with Column Numbers ik
through 23.
67-70 Sensor Number.
ESPOD
Ik August 1964 4-33S TM-LX-I23/OOO/OOB
Deck Column Position Card Type Number Punch
Y1-Ö0 Information identical with Column Numbers 14-23•
NOTE: Any number of CAT2 cards may be used. However, only the last CAT2
card may have trailing blank fields. That is, there must be four
sensors per CAT2 card except for the last CAT2 card, which may have
any number between one and four).
Bias Estimate Card(s) (initial Value of Biases). (Omitted if no
differential correction is being performed on any Category Two
Variables (Biases). If a D.C. is being done on any biases, ESPOD
will automatically make initial bias estimates of zero if this card
is omitted).
1-2 Bias Estimate Card Number (e.g. 01, 02, 03, etc.)
3-4 Differential Correction Iteration Number (op-
tional).
5-9 BISES - Card Type.
10-23 * Initial value of a bias.
29-1+2 * Initial value of another bias.
h -6l • Initial value of still another bias.
67-80 * Initial value of still another bias.
NOTE: Asterisk means use decimal point somewhere in this field.
NOTE: Any number of BISES cards may be used. However, only the last BISES
card may have trailing blank fields. That is, there must be four
bias initial values per BISES card except for the last BISES card,
which may have any number between one and four. The initial values
I
ESPOD
Ik August. 1964 4-33T TM-LX-123/000/0OB
Deck Column Position Card Type Number Punch
of the biases should be listed in one-to-one correspondence and order as
the one-punch flags on the CAT2 card(s).
20 S-matrix Card(s) (a-pricri A A matrix) (optional input)
1-2 S-matrix card number (e.g. 01, 02, 03...)
3-i+ Differential Correction Iteration Number
(optional).
5-8 SMAT - Card type.
10-23 * Value of an element of the S-matrix.
29-^2 * Value of an element of the S-matrix.
U8-6l * Value of an element of the S-matrix.
6T-8O * Value of an element of the S-matrix.
NOTE: An asterisk indicates a floating point field.
NOTE: As many S-matrix cards (sequentially numbered) as are necessary to
completely give the matrix are input. As the matrix is symmetric,
only the upper triangular elements are input. They are input in
the following order: the top row from left to right, the second
row from left to right beginning r the second element, the third
row from left to right beginning at the third element, etc.
NOTE: If the S-matrix is input, col. ^2 of the JDC card must have a one-
punch.
NOTE: If the JDC card has a one-punch in col. kh, S-matrix cards corre-
sponding to epoch will be punched out in the correct format after each
< •
ESPOD
14 August 1964 4-33U TM-U-123/0OO/OOB
Deck Column Position Card Type Number Punch
iteration. If the JDC card has a 1 in col. 56, S-matrix cards
corresponding to each ephemeris point will be punched.
NOTE: If S-matrix cards are input, then CATl and CAT2 cards (punched to
indicate the respective variables of the SMAT cards) must also be
input.
T -1» 21 Covariance Matrix Card(s) (a-priori (A A) ) (optional input)
1-2 Covariance Matrix Card Number (e.g. 01, 02,
03,...).
3-4 Differential Correction Iteration Number
(optional).
5-9 UPMAT = Card type.
10-23 * Value of an element of the a -priori (A A)
matrix.
T -1 24-42 * Value of an element of the a-priori (A A)
matrix.
T -1 48-6l * Value of an element of the a-priori (A A)
matrix.
T -1 67-80 * Value of an element of the a-priori (A A)
matrix.
NOTE: An asterisk indicates a floating point field.
NOTE: As many covariance matrix cards are input (sequentially numbered) as
are necessary to completely give the matrix. Restrictions: The
maximum covariance matrix size is 8 x 8. ü covariance matrix entered
- \
ESPOD
Ik August 1964 h-33V TM-LX-123/OOO/oOB
Deck Column Position Card Type Number Punch
by UPMAT cards may only contain Category One variables. A CATl card
(punched to indicate the respective variables appearing on the
UPMAT cards) must be input whenever UPMAT cards are input.
NOTE: As the covariance matrix is symmetric, only the lower triangular
part of the matrix is input. They are input in the following order:
the first element of the first row, the first two elements of the
second row from left to right, the first three elements of the third
row from left to right, etc.
Zonal Harmonic Card (if this card is omitted, ESPOD assumes a stand-
ard set: J2, J , J^).
1-2 01 = Card Number.
5-9 ZONAL = Card type.
10 0 = Do not include Jp in the earth gravitational
potential model.,
1 = Include Jp in the earth gravitational
potential model.
11 0 = Do not include J .
1 = Include J-.
12 0 = Do not include J. .
1 - Include «L .
13 0 - Do not include J..
1 = Include J^.
ESPOD
Ik August 1964 ^-33W TM-LX-123/000/00B
Deck Column Position Card Type Number Punch
14
15
16
17
13
19
20
0 = Do not include «L-.
1 = Include J,-.
0 = Do not include J?.
1 = Include J-.
0 = Do not include JQ.
1 = Include Jo.
0 = Do not include Jq.
1 = Include Jq.
0 = Do not include J
1 = Include J-.~.
0 = Do not include- I
1 = Include J, .
0 = Do not include J
10'
11 •
12
1 = Include J 12-
NOTE: Values of J , J ,, J,0 must be input on 99 cards.
Sectorial Harmonics Card (if this card is omitted, no sectorial
harmonics are included).
1-2 01 = Card number.
5-9
10
SECTR = Card type.
0 = Do not include jf in the earth gravita-
tional potential model.
1 = Include JZ in the earth gravitational
potential model.
ESPOD
Ik August 196U ^-33X TM-LX-123/OOO/0OB
Deck Column Position Card Type Number Punch
11 0 = Do not include Jr.
3 1 = Include J::.
k 12 0 = Do not include J. .
k 1 = Include J, .
4
13 0 = Do not include £.
1 = Include J^.
Ik 0 = Do not include J>.
1 = Include J>.
Tesseral Harmonics Card (if this card is omitted, no tesseral
harmonics are included).
1-2 01 = Card number.
5-9 TESSR = Card type.
10-11 Value of tt- and m respectively means include
K>i„ the term J v ±7 in the earth's gravitational 1
potential model.
13-lk Value of np and mp respectively means include
the term J <«*>. "2
l6-17 Value of n and nu respectively means include
the term J '"V. n3
19-20 Value of n, and m. respectively means include
the term J ^"V. nk
ESPOD
Ik August 1964 -1-J3Y TM-LX-123/OOO/OOB
Deck Column Position Card Type Number Punch
22-23 Value of n^ and m respectively means include
the term J ^K n5
29-30 Value iv and nv respectively means include the
term J 'm6'. n6
32-33 Value of n? and nu respectively means include
the term J w'.
35-36 Value of no and mn respectively means include
the term J 'm8'. n8
38-39 Value of nQ and mq respectively means include
(m ) the term J K 9J.
n9
41-42 Value of n r and m,A respectively means include J-vJ iu
the term J ^m10'. nio
48-49 Value of n , and DL. , respectively means include
the term J *mll'. nll
51-52 Value of n p and m respectively means include
the term J 'm12'. n12
54-55 Value of n and m respectively means include
the term J 'm13'. nl3
ESPOD
Ik August 1964 '4-337. TM-LX-I23/OCO/OOB
Deck Column Position Card Type Number Punch
57-58 Value of n , and m , respectively means include
the term J ^\kK nlk
NOTE: Any or all of the following fourteen terms may be chosen:
(1) (2) (1) (2) (3) (1) (2) (3) T (4)
(1) T (2) T (3) T CM T (5) o
J^ , JV , J/: J Jf. > Jf. • Subscripts and superscripts
not punched on the TESSR card will be excluded from the geopotential
model. Values of J through «Lr must be entered on 99 cards.
New Constants Card (This card used if and only if one wishes to
override any particular constant in ESPOD with
a new value for a particular run.)
1-2 99 = Card type.
5-9 Location number of the constant (right
adjusted) (obtained from the master list).
10-23 * Value of the new constant whose location is
given in col. 5-9»
2^-28 Location number of a constant (right adjusted).
29-42 * Value of the new constant whose location is
given in col. 24-28.
1+3-47 Location number of a constant (right adjusted)
48-61 * Value of the new constant whose location is
given in col. 43-47*
62-66 Location number of a constant (right adjusted)
NOTE: Asterisk means decimal point must appear somewhere in field.
ESPOD
Ik August 1964 4-34 TM-LX-123/000/0OB
Deck Column Position Card Type Number Punch
67-80 * Value of the new constant whose location is
given in col. 62-66.
NOTE: Unneeded fields may be left blank.
Standard Element Set (with blank, 1 or 2 in col. 68 of Card 7).
Updating Elements Parameter Card (This card used if and only if
one wishes to update a seven-
card element set to a different
epoch).
1-2 01 = Card number.
5-9 DNREV = Card type.
10-23 * 1.0 = Update the seven-card element set to a
specified time given in days and fractions
of days in cols. 29-42*.
2.0 = Update the seven-card element set a
specified number of revolutions past
the epoch of the element set, the number
being given in col. 29-42* (this number
may be fractional).
3.0 - Update the seven-card element set to a
specified revolution number given in
col. 29-42*.
-1.0 = Update to the time of the last observation
NOTE: An asterisk denotes a field which must contain a decimal point.
s
ESPOD
14 August 1964 4>34A TM-LX-123/OOO/OOB
Deck Column Position Card Type Number Punch
29-42 * Days and fractions to which to update, or
Number of revolutions to update past epoch,
or Revolution Number to which to update, or
Blank (if update to time of last observation).
NOTE: Elements on cards are not updated unless a DNREV card is present.
Elements from the E-file are updated to the time of the last
observation unless a DNREV card is present.
Delete Residuals Card(s) (These cards used if and only if one wishes
to delete particular residuals from con-
sideration in all iterations of a run).
1-2 Delete Residual Card Number (e.g. 01, 02, 03...).
5-9 DELET = Card type.
10-l6 * Beginning Residual Number
17-23 * Ending Residual Number
29-35 * Beginning Residual Number
Causes deletion for all included numbers
Causes deletion for all included
36-42 * Ending Residual Number _l numbers.
48-54 * Beginning Residual Number
55-0I * Ending Residual Number
67-73 * Beginning Residual Number
74-80 * Ending Residual Number
NOTE: More than one of these cards may be used. Unneeded fields should
be left blank.
NOTE: Asterisk indicates a floating point field.
Causes deletion for all included numbers.
Causes deletion for all included numbers.
• -..... i
ESPOD
Ik August 196h U-3UB IM-LX-123/OOO/OOB
Deck Position Card Type
Column Number Punch
Dynamic Atmosphere Parameter Card(s) (Omitted if a dynamic atmosphere is
not used).
1-2 Dynamic Atmosphere Parameter Card Number
(e.g. 01, 02, etc.)
5-9 APF10 - Card type.
10-13 * Day number in the year.
14-18 * Value of Ap for the day in col. IO-.13.
19-23 * Value of F10 for the day in col. 10-13.
29-32 * Day number in the year.
33-37 * Value of Ap for the day in col. 29-32.
38-1*2 * Value of F10 for the day in col. 29-32.
1*8-51 * Day number in the year.
52-56 * Value of Ap for the day in col. 1*8-51.
57-61 * Value of P.0 for the day in col. 1*8-51.
67-70 * Day number in the year.
71-75 * Value of Ap for the day in col. 67-70.
76-80 * Value of F10 for the day in col. 67-70.
NOTE: Asterisk denotes a floating point field.
NOTE: 30 is maximum number of sets of one value of Ap and one value of
F,0 which may be entered. Thus there can never be more than eight
APF10 cards.
NOTE: If days are omitted between two day numbers, a linear interpolation
is done.
*
ö Ik Auguct 196^ U-3^C
ESPOD
TM-LX-123/OOO/OOB
I
Deck Column Position Card Type Number Punch
Ephemerls Specification Card(s)
1-2 Ephemerls Specification Card Number
(01, 02, 03, 0*0.
5-9 DEIffT = Card type.
10-23 * Value (in minutes of step size beJ^een
successive calculated positions).
29-1+2 * Time (in minutes) since epoch of the last point
of the calculated positions at the step size
given in col. 10-23.
48-61 * Value (in minutes) of another step size between
successive calculated positions.
67-80 * Time (in minutes) since epoch of the last
point of the calculated positions at the step
size given in col. 48-61.
NOTE: A maximum of four Ephemerls Specification cards may be used.
NOTE: The step size may be negative, Indicating an ephemerls calculated
backwards in time.
30 Prediction Specification Card
1-2 01 = Card number.
5-9 PRDCT = Card type.
NOTE: An asterisk indicates a floating-point field.
\ I
-SPOD
.
Ik August 196^ k-5kv TM-LX-123/000/00B
Teck Column Position Card Type Number Punch
10-23 * Time (in days and fractions of days) of first
prediction point,
29-U2 * Time (in days and fractions of days) of second
prediction point.
1+8-61 * Time (in days and fractions of days) of third
prediction point.
67-80 * Time (in days and fractions of days) of fourth
prediction point.
NOTE: Only one PRDCT card may be used in any run; i.e. the maximum number
of specific prediction times is four.
NOTE: Unneeded time of prediction fields may be left blank.
Time Step Specification Card (if this card is omitted, ESPOD uses
a variable time step size in the numeri-
cal integration).
1-2 01 = Card number.
5-9 TSTEP = Card type.
10-23 * Time step size (in minutes) to be used through-
out the numerical integration.
Maximum Time Specification Card (if this card is omitted, ESPOD will
automatically disregard observations
which are more than ten days from epoch).
NOTE: An asterisk denotes a floating-point field.
Ik August 19& ^-3^E
ESPOD
TM-LX-I23/OOO/OOB
)•
Deck Column Position Card Type Number Punch
1-2 01 = Card number.
5-8 TMAX = Card type.
10-23 * Maximum time in days and fractions from epoch
for which observations are to be used. (Obser-
vations are disregarded if more than this number
of days from epoch)..
Radiation Pressure Parameter Card (This card is only for radiation
pressure perturbations).
1-2 01 = Card number.
5-9 RABPR = Card type.
10-23 * Effective Area of satellite in square meters.
29-1*2 * Mass of satellite in kilograms.
End Preliminary Data Card
5-9 ENDPR = Card type.
Standard SPADATS Observation Cards (Not required if no DC is to be done).
NOTE: If observation cards are input, col. 31 of the JDC card must have a
one-punch. If there are less than 65O observations, they may be in
any temporal order; if more than 65O, they must be in descending
time order. There is no maximum limit to the number of observations.
End Observations Card (Required only if observation cards are input).
5-9 ENDOB = Card type.
NOTE: An asterisk denotes a floating-point field.
E3P0D
Ik August 196U *f-3^F TM-LX-I23/OOO/OOB
Deck Column Position Card Type Number Punch
Standard SPADATS Sensor Cards
(Standard SPADATS Sensor cards)
(input if and only if one wishes to override or
supplement the sensor file on the SEAI tape).
(if sensor cards are input, columns 31 a^d 3^ of the
JDC card must have a one-punch).
End Sensor Card (This card is input if and only if sensor cards are
input).
5-9 ENDSN = Card type.
N End Data Card (Last card of all ESPOD decks).
5-9 ENDAT = Card type.
N+l End of Data Card
N+2 End of Job Card
N+3 End of Schedule Tape Card
N+4 Blank Card
Ik August I96U -34G
ESPOD
TM-LX-123/OOO/OüB
U.3.I.3 Output
The program provides output on both hard copy and punched cards.
4.3.I.3.I Program Printout
Part 1: Lists the input cards, with the columns of the printout corre-
sponding exactly with the columns of the cards.
Part 2: General
a. Type of observations.
b. Satellite number and name.
c. Type of program run (e.g. COLD START or NON-COLD START).
d. Right ascension of Greenwich at 2^00 on day of epoch
(AIPHA G ZERO).
e. Epoch uime of the program run.
f. Initial conditions.
X - Position vector (km).
Y - Position vector (km).
Z - Position vector (km).
XDOT - Velocity vector (km/sec).
YDOT - Velocity vector (km/sec).
ZDOT - Velocity vector (km/sec).
Geocentric
Inertial
Cartesian
Coordinates
ALPHA - Right ascension (deg).
DELTA - Declination (deg).
BETA - Flight path angle (deg).
A - Azimuth (deg).
R - Range (km).
V - Velocity (km/sec).
Geocentric
Inertial
Spherical
Coordinates
ESPOD
Ik August 1964 1,-3411 TM-LX-123/ooo/OOB
CDA/2M (optional) - Atmospheric drag parameter (meters /
kilogram).
Part 3: Program Constants (optional).
Part h: Sensor Information (printed if Part 3 iß requested).
1. SENSOR NO. - Sensor number.
2. SIGMA TYPE - Standard deviation category applied to the
sensor.
3. RANGE/RA(FR) - Standard deviation in range/standard devia-
tion in right ascension for a field-reduced observation from
a Baker-Nunn camera.
h. AZ/DEC(FR) - Standard deviation in azimuth/standard devia-
tion in declination for a field-reduced observation from a
Baker-Nunn camera.
5. EL/RA(PR) - Standard deviation in elevation/standard devia-
tion in right ascension for a precision-reduced observation
from a Baker-Nunn camera.
6. ROT/DEC (PR) - Standard deviation in range rate/standard de-
viation in declination for a precision-reduced observation
from a Baker-Nunn camera.
7. GSUBS - Gross outlier editing criterion for the observations
in terms of N sigma.
8. REFR. FIAG - Refraction correction indicator (l = applied,
0 = not applied).
9« NSUBS = Refraction index for the time of interest.
ESPOD
-wK 1^ August 196k k~$a TM-Lx-123/oco/ooB
I
Part 5: Observe 1. ion Type
1. Ii) - Sensor number.
2. T-TO - Time of observation (inin. from epoch).
3. YR, MN, DAY, HR. MIN, SEC - Time observation (Greenwich time)
h. R - Range (tat),
5. A - Azimuth (deg).
6. EL - Elevation (deg).
7- R DOT - Range rate (km/sec).
8« HA - Hour angle (deg), in lieu of azimuth.
9. D - Declination (deg), in lieu of elevation.
Part 6: Sensor Locations
1. ST. NO, - Sensor number.
2. LAT. - Sensor latitude north (deg).
3. LONG. - Sensor longitude west (deg).
K. ALT. - Sensor altitude (meters).
Part 7: Residuals Print
1. ID - Sensor number.
2. DATE - Time of the observation from which the residuals
were obtained.
3. N - Residual number.
4. RANGE KM - Range residual (km).
5« AZ,HA DBG. - Azimuth/hour angle residual (deg).
6. EL,DC DBG. - Elevation/declination residual (deg).
1
ESPOD
ik August 196k 4-3'a TM-LX-123/000/00B
7. RDOT KM/SEC - Range rate residual (km/sec).
8. U KM (see notes) - Up component of the position residual
(km) collinear with and positive in the same direction as
the radius vector.
9. V KM (see notes) - Down component of the position residual
(km), orthogonal to the radius vector, in the orbit plane,
positive in the direction of motion.
10. W KM (see notes) - Cross component of the position residual
(km), normal to the orbit plane and positive in the direc-
tion of the angular momentum vector to complete a right-
handed coordinate system.
11. VM KM - Magnitude of the position residual or displacement
vector (km).
12. DEL T MIN - Time separation of computed and measured posi-
tions (min), assuming Keplerian mean motion.
13• U DEG - Argument of latitude (deg), angle from the ascend-
ing node to the radius vector.
Ik. BETA DEG. - Residual angle between the measured position
vector and the computed orbit plane.
NOTE: One of three symbols may appear following any numerical value, indica-
ting deletion of the residual from further calculations:
* = DEIETE input deletion.
G = Gross outlier deletion.
K = KRMS test deletion.
ESPOD
Ik Augudt 1964 k-3& TM-Dc-123/ooo/ooß
NOTE: U KM, V KM, and W KM may be optionally replaced by normal, tangential
and cross-directional components of a vector describing the displace-
ment of the observed with respect to the computed position:
S KM - Vector component (km), orthogonal to the velocity vector
and in the orbit plane, forming a right-handed coordinate
system with T and W.
T KM - Vector component (km), collinear with and in the same direc-
tion as the velocity vector.
W KM - Vector component (km), normal to the orbit plane and in the
same direction as the angular momentum vector.
NOTE: U KM, V KM and W KM may be optionally replaced by components of a
vector describing the displacement of the sensor which would be re-
quired to reduce the residual to zero.
ST. IAT DEG - Geocentric north latitude displacement (deg).
ST. LONE DEG - East longitude displacement (deg).
ST. HT KM - Height displacement (km above mean equatorial sea level).
Part 8: Estimates of Mean and Standard Deviations by Sensor and Type.
1. ST. ID. - Sensor number.
2. R - Range values (km).
3* A,HA - Azimuth or hour angle values (deg).
h. E,D - Elevation or declination values (deg).
5. RDOT - Rar^ü rate values (km/sec).
6. MEAN - Arithmetic mean.
7. ESTD - Estimated standard deviation (one sigma) of the mean.
8. NA/NR - Number of observations accepted/number of observations
rejected«
.
ESPOD
Ik August 1964 4-34L TM-LX-123/OöD/OOB
Part 9* Curve Fit Iteration Summary
1. Category 1 variables:
AIPHA - Right ascension (deg).
DEITA - Declination (deg).
BETA - Fli#it path angle (deg).
AZ - Azimuth to inertial velocity vector (deg).
R - Radius vector from geocenter (km).
V - Velocity vector magnitude (km/sec).
CDA/2M - Drag parameter (meters /kilogram).
K - Drag variation (secular option: meters /kilogram/day;
.periodic option: meters /kilogram.
2. DEI/TA - the corrections applied to each variable.
3» OLD - Numerical values from the previous iteration.
4. NEW - OID + DELTA.
5. SIGMA - The uncertainty in each variable, computed from the
covariauce matrix.
6. BOUNDS - The constraints epplied to the changes which the
program is allowed to make to the variables.
7« Category 2 variables:
R - Range (km).
A,HA - Azimuth or hour angle (deg).
E,D - Elevation or declination (deg).
RDOT - Range rate (km/sec).
LAX - Sensor north latitude (deg).
V
1
o lk August 196^ U-^M
ESPOD
TM-LX-123/OOO/OOB
IfNG - Sensor east longitude (deg).
ALT - Sensor altitude (meters).
T - Time (sec).
8. EELTA, OLD, NEW, SIGMA, BOUNDS - same as for Category 1
variables.
9. Convergence statement.
10. Bounds statement.
11. CURRENT RMS - Current root-mean-square of the residuals.
12. PREDICTED RMS - The RMS predicted for the next iteration.
13. BEST RMS - The best RMS so far in the curve fit run.
lk. DELTA V - The velocity correction based on the delta t fit.
15. RMS DEL T - Current root-mean-square of the time residuals.
16. PREDICTED RMS DEL T - The RMS predicted for the next itera-
tion,
IT- Correlation matrix, with rowb and columns numbered to
correspond to the Category 1 variables.
18. Covariance matrix, with rows and columns numbered to corre-
spond to the Category 1 variables.
19. Run termination statement.
Part 10: Trajectory (or Ephemeris)
1. Date and Greenwich mean time for the data.
2. Time from epoch (min).
3. Time from January 0 of the year of epoch (days).
v
:' •
ESPOD
Ik August 19& k-$kX TM-LX-I23/OOO/OOB
k. X, Y, Z, XDOT, YDOT, ZDOT - Components of the position (km)
and velocity (km/sec) vector in geocentric inertial Cartesian
coordinates. It is a right-handed orthogonal system where
the X axis is in the direction of the vernal equinox and
the Z axis is in the direction of true north. Coordinates h
are true as of 0#0 day of epoch.
5. Polar spherical position and velocity coordinates (ADBARV):
ALFA - Right ascension (deg).
DI/TA - Declination (deg).
BETA - Flight path angle (deg), positive downward from the
local vertical.
AZ - Azimuth of the velocity vector (deg).
R - Range (km).
V - Magnitude of the velocity vector (km/sec).
6. ALT - Height (km).
7. LAT - Geodetic north latitude (deg).
8. LONE - East longitude (deg).
9. Classical osculating elements:
SMA - Semimajor axis (km).
ECC - Eccentricity.
INC - Inclination (deg).
NODE - Right ascension of the ascending node (deg).
OMG - Argument of perigee (deg).
M - Mean anomaly (deg).
x^-jtzBrna
o
ESFOD
Ik August 1964 k-3kO TM-LX-123/OOO/oOB
10. UX, UY, UZ - Direction cosines of the position in Cartesian
coordinates, with axes directed as in the XYZ system.
11. RPVX, RPVY, RPVZ - Components in Cartesian coordinates of a
vector in the orbit plane which is orthogonal to the position
(r) and angular momentum (h) vectors.
12. AIAT - Argument of latitude (deg), equals the sum of the
argument of perigee and the true anomaly.
13» TAU - Time until the next ascending nodal crossing (min.
from epoch).
lU. PRD - Osculating orbital period (min).
15« Indeterminacy free elements:
l/A - Inverse of the semimajor axis (E.R.). 1
D - Scalar product of position and velocity vectors (E.R.?),
equals (R-R)-f-\f/^ .
16. APOG - Apogee distance (km), above a mean equator.
17• PRG - Perigee distance (km), tbove a mean equator.
18. ELUPSE or HYPERBOLA - Orbit's conic form.
19. XVM, YVM, ZVM, XD\M, YDVM, ZDYM - Selenocentric position
(km) and velocity (km/sec) coordinates, true as of 0*0 day
of epoch.
20. XVS, YVS, ZVS, SDVS, YDVS, ZDVS - Heliocentric position (km)
and velocity (km/sec) coordinates, true as of 0*0 day of
epoch.
21. DVIM - Distance from the vehicle to the selenocenter (moon)
(km).
•
ESPOD
Ik August 1964 k-j>k¥ TM-LX-I23/0OO/OOB
22. DVFS - Distance fron ',ne vehicle to the heliocenter (sun)
(km).
In addition to the above items, the following are optional:
23. ORBIT PLANE SIGMA AND RHO MATRIX - A matrix of standard
deviations (diagonal terms) and correlation coefficients
(off-diagonal terms) related to the UVW Orbit Plane coordin-
ates :
U - Position vector (up) component (km) in the direction of
and collinear with the radius vector.
V - Position vector (down) component (km) in the direction
of motion and orthogonal to the radius vector in the orbit
plane.
W - Position vector (cross) component (km) normal to the
orbit plane in the direction of the angular momentum vector
to complete a right-handed coordinate system.
UDOT - Velocity vector of U.
VDOT - Velocity vector of V.
WDCT - Velocity vector of W. p
CDA/2M - Drag parameter (meters /kilogram).
or
K - Drag variation parameter (for secular option: meters /
kilogram/day; for periodic option: meters /kilogram).
2k. EIGENVECTORS OF U, V, W COVARIANCE MATRIX - Direction cosine
components with respect to the U, V, W axes for the orthogonal
axes of the error ellipsoid defined by the covariance matrix.
.
14 August 1964 4-34Q OM-LX-123/OOO/OOB
2$. SQUARE ROOTS OF THE EIGENVALUES - Represent the lengths of
the orthogonal semi-principal axes of the error ellipsoid.
26. TO ALIGN U, V, W WITH Cffi PRINCIPAL AXES - A series of
ordered rotations which will reposition an observer, facing
initially in the positive V direction, to a new orientation
facing along the error ellipsoid's nearest principal axis:
YAW RIGHT - (deg).
PITCH DOWN - (deg).
ROLL CLOCKWISE - (deg).
27. POLAR SI04A AND RHO MATRIX - A matrix of standard deviations
(diagonal terms) and correlation coefficients (off-diagonal
terms) related to the Polar Spherical coordinates: ALPHA,
DELTA, BETA, AZ, R AND V.
28. CARTESIAN SIGMA AND RHO MATRIX - A matrix of standard devia-
tions (diagonal terms) and correlation coefficients (off-
diagonal terms) related to the geocentric inertial Cartesian
coordinates: X, Y, Z XDOT, YDOT, ZDOT.
4.3.I.3.2 Punched Cards
The program provides punched card output in three formats.
Part 1: Seven-card Element Set
The program provides OID or NEW osculating elements, as requested in col. 46
of the JDC card.
Part 2: Solution Parameters
The program provides a record of data from a run in a format identical with
ESPOD
Ik August 196k 4-3UR TM-LX-123/OOO/OOB
selected input card formats, for use in subsequent input decks. The data are
grouped by iteration, and each output card contains the iteration number in
cols. 3-U. The output cards can be read by referring to the corresponding
input cards: ICOND, ERAG, MSES, ENDS. ICTYP, ITBiE, SMAT, UPMAT.
Part 3: DAC Parameters
The program automatically provides the second and third card of a 3-card DAC
set when DAC cards are input to supply the desired update times. The first
card must be provided by the Analyst before using this output as input to
another program (see Message Header card for the GIPAR program). The output
cards can be read by referring to the corresponding input cards.
# ll August 196U l*-j4S
ESPOD
IM-DC-I23/OOO/OOB
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•
4 May 1964 4-35
IGANGLE
OM-LX-123/OOO/OO
4.3.2 INITIAL ORBIT DETERMINATION FROM ANGULAR FIXES - lOANGLE
4.3.2.1 Purpose
The lOANGLE program computes an element set describing a satellite orbit from
three angular position fixes from the same sensor on the same revolution (e.g.,
telemetry data). The element set is then differentially corrected using
additional observations.
4.3.2.2 Input - Schedule Tape Mode only (Toggle 24 On)
Deck Position Card I*ype
Column Number Punch
Schedule Tape Card
Job Card
Remarks Card
Program ID Card
1-6
9-15
IT
18
80
Parameter Card 1
1-3
4-6
7
8
9-18
SPSJ0B
lOANGLE
0 = Parameter card, Observation cards and
S-file tape inputs.
2 = Parameter card, Observation cards and
Sensor cards inputs
0 = Hardcopy and punched cards output
J = Card type
Satellite number
Element set number
0 = Circular approximation only
1 = Circular approximation and elliptical
sector-to-triangle approximation
0 • No differential correction
1 = Differential correction
Satellite name
IOANGLE
..
4 May 1964
Deck Fosition Card type
4-36 ÜM-UC-12 3/000/00
Column Number Punch
23-36
41-48
80
Parameter Card 2
24-36
67
6
T
8
9
80
End of Case Card
End of Job Card
End of Schedule Tape Card
Blank Card
Epoch revolution (floating point)
Minimum time between observations in the
initial orbit computation
F = card type
Final revolution (floating point)
0 = Correct the inclination
1 = Do not correct the inclination
P = Card type
4.3.2.3 Output
Program printout consists of four parts.
4.3.2.3.1 Part 1
The first part contains:
1. For each input observation; obs number, sensor identification, obs
date, and observed angles.
2. Preliminary elements using the circular approximation input option:
a. M12, the geocentric angle between the observations in radians
b. semi-major axis in earth radii (A)
c. inclination indegrees (INCL)
d. node in degrees (NODE)
e. period in minutes (P (MIN))
f. a , a components (AXNO, AYNO)
g. components of angular momentam vector (HXO, HYO, HZO)
h. mean longitude in degrees (LO)
•
IOANGLE
k May 1964 4-37 TM-LX-123/OOO/OO
3. or, elements using first circular and then the sector-to-triangle
method (input option):
a. semi-major axis in earth radii (A)
b. eccentricity (E)
c. inclination in degrees (i)
d. node in degrees (NODE)
e. argument of perigee in degrees (OMEGA)
f. time of nodal passage in minutes (TN)
g. period in minutes (P (MIN))
h. a , a , components (AXNO, AYNO)
i. components of angular momentum (HXO, HYO, HZO)
j. mean longitude (LO)
4.3.2.3-2 Parts 2-4
Parts 2-4 of the printed output contains the differential correction with
further observations and corresponds to Parts 1-3 of the SGPDC program (see
section 4.3.8.3).
*
.-.-•
•
SAM
PLE
PR
INT
OU
T, I
OA
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LE
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T
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NG
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TE
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N
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A
NG
LES
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09
15
40
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9
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246
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84.3
161
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A)
2 03
7 6
01
20
91
54
04
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11
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468
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A)
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09
15
40
57
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3
54
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95
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NO
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TN
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24
82
84
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34
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11
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62
67
92
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90
83
72
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3
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YN
O
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O
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O
HZO
LO
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90484257-2
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682224961-1
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35
70
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3
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RB
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LES
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LY
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TE O
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O
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RV
ATI
ON
O
BSE
RV
ED A
NG
LES
1 02
9 6
40
22
10
15
01
5.5
68
70.1
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DE
C)
32
8.5
25
4
(RA
)
2 02
9 6
40
22
10
14
21
3.0
07
53.2
261
(
DE
C)
2?6
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(R
A)
3 02
9 6
40
22
10
13
44
3.1
58
17.7
143
(
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M12
A
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L
NO
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1
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3
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3
OB
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NO
A
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O
HX
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HY
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HZO
LO
1 .0
00
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48
89
61
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1
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80554359+
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4 May 1964 4-4l TM-LX-123/OOO/OO
4.3.3 INITIAL ORBIT BY HERRICK-GIBBS - IOHG
4.3.3.1 Purpose
The IOHG program computes an element set describing a satellite orbit from three
or mere three-dimensional fixes from the same sensor on the same revolution
(e.g., tracker data). The element set is then differentially corrected using
additional observations.
4.3.3.2 Input - Schedule Tape Mode only (Toggle 24 On)
Deck Position Card type
Column Number Punch
1 Schedule Tape Card
2 Job Card
3 Remarks Card
4 Program ID Card
1-6
9-12
17
18
80
5 Program Card 1
1-3
6
8
9-18
36
79
80
SPSJ0B
IOHG
0 = Parameter card, Observations cards and
S-file tape inputs.
0 = Hardcopy and punched cards output
J - Card type
Space Track number
Element Set number
1 = Corresponding Element card number
Object name (optional)
Epoch revolution
1 = Second, next to last and median observa-
tions used in orbit computation
2 = Third* second to last and median observa-
tions used in orbit computation
P = Card type
IOHG
k May 1964 k-k2 IM-LX-I23/OOO/OO
Deck Position Card Type
Column Number Punch
8
9
10
11
12
Parameter Card 2
8
9-22
80
Parameter Card 3
8
29
36
67
k - corresponding Element card number
C-term
P = Card type
7 = Corresponding Element card number
Initial revolution number
Final revolution number
0 = Correct all elements
1 = Set the I-stop
2 = Set the C-stop
k = Correct mean motion
80 P = Card type
Data cards:
a. Parameter card
b. Observation cards (min. = 3 from one sensor, in order of in-
creasing time)
End of Case Card
End of Job Card
End of Schedule Tape Card
Blank Card
4.3.3.3 Output
The program printout contains h parts.
4.3.3.3.1 Part 1
Part 1 contains the following information
1. Satellite name and number
2. Element set number
3. Time of epoch
' .. I
I 0
IOHG
4 May 1964 4-43 IM-LX-123/OOO/oo
4. SPACETRACK elements (initial orbit)
a. Revolution number
b. Serai-major axis, a (earth radii)
c. Eccentricity, e
d. Inclination, i (degrees)
e. Node, Q (degrees)
f. Omega, w (degrees)
g. Drag, CQ (day/rev^)
h. Perigee altitude (statute mi.)
i. Anomalistic period, Pa (min.)
5. N, M elements
a. Revolution number
b. Mean longitude, L (radians)
c. A , A components xn7 yn d. Angular momentum components (H , H , H )
x y z
4.3.3.3.2 Parts 2-4
Parts 2-4 of the printout correspond to parts 1-3 of the SGPDC printout
(see section 4.3.8.3).
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IORF
4 May 1964 4-47 •JM-U-123/OOO/OO
4.3.4 INITIAL ORBIT DETERMINATION FROM INDEPENDENT RADAR FIXES - IORF
4.3-4.1 Purpose
The IORF program computes an element set describing a satellite orbit from two
or more radar fixes, which may come from different stations or occur during
different revolutions. The element set is then differentially corrected using
additional observations.
4.3.4.2 Input - Schedule Tape Mode only (Toggle 24 On)
Deck Column Position Card Type Number Punch
1 Schedule Tape Card
2 Job Card
3 Remarks Card
k Program ID Card
1-6 SPSJ0B
9-12 IORF
IT 0 = Pa 0 = Parameter card, Observation cards and S-
file tape inputs.
2 = Parameter card, Observation cards and
Sensor cards inputs.
18 0 * Hardcopy and punched cards
80 J - Card type
Parameter Card 1
1-3 Satellite number
4-6 Element set number
9-18 Satellite name
23-36 Epoch revolution
79 0 - No differential correction
1 = Differential correction
80 P = Card type
NOTE: All inputs are right-adjusted.
IORF
4 May 1964 4-48 TM-IÄ-123/OOO/OO
Deck Column Position Card Type Number Punch
6 Parameter Card 2
9-22 Drag term, C. (days); if unknown, use zero
23*24 M, maximum number of solutions desired
24-36 e^ (min.), magnitude of the difference between
the computed and observed times between the
two positions.
37-48 Q, (km.), distance of the third position fix
from the computed orbit
49-60 m, number of parts into which to divide the
interval between minimum p and maximum p
80 P = Card type
NOTE: If blank, the program assumes M = 1.0, e = .001 min., e, = 100km.
and m = p0.
7 Parameter Card 3
23-36 Predicted revolution number (see DC output)
67 0 = Correct the inclination
1 = Do not correct the inclination
80 P = Card type
8 Data Cards:
a. Input Option 0:
(l) Observation cards
b. Input Option 2:
(1) Observation cards
(2) Sensor cards
9 End of Case Card
10 End of Job Card
11 End of Schedule Tape Cord
12 Blank Card
IORF
k May 1964 k-k9 TM-LX-123/OOO/OO
4.3.4.3 Output
Printout of this program contains 4 parts.
4.3.4.3.1 Part 1
The first part contains:
1. Observations to be used
a. observation numbers
b. time of observations to thousandths of seconds
c. x, y, z and r in earth radii
2. Initial elements
a. semi-major axis in earth radii
b. eccentricity
c. inclination in degrees
d. node in degrees
e. omega in degrees
f. T , time of first node after T , days since 1950
g. L., longitude of first observation in degrees
h. a , a , xn yn'
i. angular momentum components (H , H , H )
j. T , time of first observation, days since 1950
k. revolutions between observations
i. perifocal distance (q) earth radii
1. semi-latus rectum (p) earth radii
m. mean angular motion (x.) radians/min
n. a drag coefficient (c")
4.3.4.3.2 Parts 2-4
Parts 2-4 of the printout correspond to parts of the SCPDC printout (see
section 4.3.8.3).
• A*¥
I INITIAL
ORBIT
DETERMINATION. P-ITERATION METHOD
DTeTMiTQ 17,
1963
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MANUAL RUN
i 8
f*
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LOCVEC
h May 196k 4-53 TM-LX-123/OOO/OO
4.3.5 LOCKHEED VECTOR COORDINATES - LOCVEC
4.3.5.I Purpose
The LOCVEC program computes the predicted position and velocity of a satellite
for the Satellite Control Facility (SCF) from a seven-card element set. The
output is a special binary teletype tape which is used as an input to the CDC
computer at SCF.
4.3.5„2 Input - Schedule Tape Mode (Toggle 24 On)
Deck Column Position Card Type Number Punch
1 Schedule Tape Card
2 Job Card
3 Remarks Card
4 Program ID Card
17-19 RUN
25-30 LOCVEC
31-35 ,DATA
Request Card (max. = 500, requires one for each element set)
1-3 SPADATS object number (optional)
9 First digit of STOsatellite number, or
9 = SPADATS number used
10-12 Satellite number (las
13-20 Satellite name
21-24 Country of origin
6 End Request Deck Card
8 Any of the digits 1-9
7 Element Set Cards (max. = 500 sets)
8 Blank Card
9 End of Data Card
10 End of Job ^ard
11 End of Schedule Tape Card
12 Blank Card
* H iunnyvale Track Ceiiter -= Satellite Control Facility
LOCVEC
h May 1964 k-^k TM-LX-123/OOO/OO
4.3.5.3 Output
There are two output lines printed for each satellite. The order is the same
as that of the request deck. Each line contains:
1. Satellite number
2. Sunnyvale Tracking Center number, or if preceded by 9, the SPACETRACK
number
5. Element number
k. Month, day, hour of epoch
5. Seconds since start of epoch month
6. Epoch revolution
'7. x, y, z coordinates in feet
8. Velocity components in feet per second
ft
1>
SAM
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PRIN
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11
6 91
16
37
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Y/DOT
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5090
69
65
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ROC
4 May 1964 4-57 TM-LX-123/000/00
4.3.6 RADAR ORBIT COMPUTATION -ROC
4.3*6.1 Purpose
The ROC program computes an initial orbit from a radar track or from geo-
centric rectangular coordinates and velocities. There is no differential
correction of the computed element set.
4.3.6.2 Input - Schedule Tape Mode (Toggle 24 On)
Deck Position Card Type
Column Number Punch
1 Schedule Tape Card
2 Job Card
3 Remarks Card
4 Program ID Card
17-19
25-27
28-32
5 Parameter Card
1-3
6-17
18-35
41
42
6 Data Cards:
a. Input Option 1:
(1) Sensor cards
(2) Observation cards
b. Input Option 2:
(l) Rectangular Coordinate cards
1-14 x (km.), including decimal point
15-28 y (km.)- including decimal point
RUN
ROC
,DATA
Number (odd) of observation cards to be input
(from 3-999); required only for input option 1
Satellite name
Date of computation
1 = Element cards output
1 = print x, y, z, x, y and z for the mean
of the observations
ROC
h May 1964 4-58 TM-LX-12 3/000/00
Deck Column Position Card Type Number Punch
?9-4? z (knu)j including decimal pcint
43-46 Year of epoch
(2) Velocity Component cards
1-14 x (km./sec.), including decimal point
14-28 y (km./sec.), including decimal point
29-42 z (km./sec), including decimal point
43-56 Day of year of observation (in days and
fractions), including decimal point
7 End Card
79 9 = Card type
8 End of Data Card
9 End of Job Card
10 End of Schedule Tape Card
11 Blank Card
3.6.3 Output
Program printout consists of the normal Radar Orbit Computation plus one extra
option.
4.3.6.3.I Normal Printout
The normal printout contains:
1. Satellite name and number.
2. Semi-major axis (km and earth radii).
3. Period (P in days)-
4. Perigee and apogee (in km and earth radii).
5o Right ascension of ascending node (deg.)
6. Argument of perigee (degrees).
7. Time of last perigee pasb (days).
8. Time of last nodal crosing (days).
9- Radius vector (km).
10. Velocity (km/sec).
11. inclination (degrees). p
12. Eccentricity (e) and e .
ROC
h May 1964 4-59 TM-LX-123/000/00
4.3.6.3.? Optional Output
The optional printout contains the geocentric rectangular coordinates (x, y, z) and
the velocity components with the time of the observation.
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SEAI
4 May 1964 4-61 TM-LX-123/OOO/OO
4.3.7 SEAI TAPE FILE MAINTENANCE - SEAI
4.3.7.1 Purpose
The SEAI program generates a new SEAI tape or modifies an existing SEAI tape
by replacing, adding or deleting data.
4.3.7.2 Input - Schedule Tape Mode (Toggle 24 On)
The SEAI program may be run in the Regular or the Special input mode. The
Special input mode is used exclusively to add an element set to the SEAI
files on a foreign launch. Toggle 47 On = Build new SEAI tape. Toggle 47
Off = Update old SEAI tape.
4.3.7.2.1 Regular Input Mode (Toggle 44 Off)
Deck Column Position Card Type Number Punch
1 Schedule Tape Card
2 Job Card
3 Remarks Card
1« Program ID :ard
17-19 RUN
25-28 SEAI
29-33 .DATA
5 Sensor Card (optional)
6 Element Set Cards (optional)
7 Acquisition Card (optional)
8 Information Card (optional)
9 Delete Card (optional)
10 End Card
1-3 END
11 End of Data Card
12 End of Job ( :ard
13 End of Schedule Tape Card
14 Blank Card
SEAI
4 May 1964 4-62 TM-LX-123/OOO/0O
4.3.7.2.2 Special Input Mode (Toggle 44 On)
Deck Column Position Card type Numb*r Punch
1 Schedule Tape Card
2 Job Card
3 Remarks Card
4 Program ID Card
17-19 RUN
25-28 SEAI
29-33 ,DATA
5 Parameter Card
1 U, BL
NOTE:
U, Blank = Unclassified
E = Unclassified EFTO
C = Confidential
F = Confidential/NoForn
S = Secret
N = Secret/NoForn
2 D = Deferred
R = Routine
P = Priority
0 = Immediate
Z = Flash
3 K *• Launch area
T, Blank = Launch area
4 Z = Send flash bulletin to DIA/CIIC
Used only when launch deviates from nominal inclination by 5 degrees
or more, or when launch area appears to be other than K or T.
5
80
T, Blank = Transmitting
N » Non-transmitting
P = Card type
SEAI
k May 196k 4-63 (Page h-6k Blank)
Deck Position
Column Card Type Number Punch
6 Element Set Cards
7 End Card
1-3 END
8 End of Data Card
9 End of Job Card
10 End of Schedule Tape Card
11 Blank Card
4.3.7.3 Output
ra-LX-123/ooo/oo
No printed output is generated by this program except for rejected input cards
SGPDC
k May 1964 k-65 1M-IX" 123/000/00
4.3.8 SIMPLIFIED GENERAL PERTURBATIONS 2MFHEMERIS WITH DIFFERENTIAL
CORRECTION - SGPDC
4.3.8.1 Purpose
The SGPDC program computes the best fitting orbit (in the least squares sense)
to a set of observations. All or any of the six elliptical elements and the
drag parameter may be corrected. The program converges on ss many parameters
as possible.
4.3.8.3 Input
4.3.8.2.1 Automatic Mode - in an OCS sequence
a. Observations from the SRADU tape.
b. Sensor coordinates from the S-file tape.
c. Satellite numbers from the SATTB tape.
d. Corresponding element sets from the E-file tape.
e. OCS Toggle number = Desired OCS sequence.
4.3.8.2.2 Schedule Tape Mode (Toggle 24 On)
Deck Column Position Card Type Number Punch
1 Schedule Tape Card
2 Job Card
3 Remarks Card
4 Program ID Card
1-6 SPSJ0B
9-13 SGPDC
IT 0 = Satellite Number cards, S-file, E-file
and SRADU tape inputs
1 = Satellite Number and Observation cards and
S-file and E-file tape inputs
2 = Observation Number and Element Set cards
and S-file and SRADU tape inputs
3 = Element Set and Observation cards and S-
file tape inputs.
NOTE: When using Element Set Cards: cols. 23-36 of the 7th card should be
blank and col. 67 of the 7th card should specify the desired correction
When using the E-file tape: + , -, E or N must be input by flexowriter.
SGPDC
h May 1964 k-66 TM-LX-123/OOO/oo
Deck Column Position Card Type Number Punch
h = Satellite Number and Observation Number
cards and S-file, E-file and SRADU tape
inputs
l8 0 = Hardcopy and punched cards output
1 = Angle residuals in degrees
80 J = Card type
5 Data Cards:
a. Input Option 0:
Satellite Number cards
b. Input Option 1:
Satellite Number cards
Observation cards
c. Input Option 2:
Observation Number cards
Element Set cards
d. Input Option 3:
Element Set cards
Observation cards
e. Input Option k:
Satellite Number cards
Observation Number cards
6 End of Case Card
7 End of Job Card
8 End of Schedule Tape Card
9 Blank Card
SGPDC
I k May 196U U-67 TM- DC-12 3/000/00
k.3.8.3 Out Fat
Printout from the program contains three separate parts.
4.3.8.3.I Part 1
The first part is the differential correction residuals and contains the
following quantities for each case:
1. Tag and sensor number
2. Time of observation to hundredths of seconds
3. Association status (RA)
k. Rejection indicator (Rj) - asterisk indicates rejection of at least
one residual. The residual rejected will appear with an asterisk also.
5. Range residuals (km)
6. Right ascension and declination residuals (km.) or azimuth
7« Elevation residuals (km.)
8. Range rate residual (km/sec)
9. Vector magnitude (km.)
10. Delta t (minutes)
11. Mean latitude (u)
12. Out-of-plane angle (BETA)
if.3.8.3.2 Part 2
Part 2 contains corrective quantities «nd elements as follows:
RMS and RMS2
&X./H (mean angular velocity)
Aa , Aa (components of a) xn' yn -
AU, (mean latitude)
Changes in node, inclinetion and drag term
Corrected elements (if they are corrected) revolution number, case number,
L, To, a, e, i, Q, uu, C , perigee altitude, Pft. O A
I+.3.8.3.3 Part 3
Part 3 is a summaiy sheet which contains in addition to a printout like
Part 2 old RMo values, old elements, rate of change of omega and node,
and summary notes.
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SPIREEC
4 May 1964 4-71 TM-LX-123/OOO/OO
» r 4.3.9 SPIRAL DECAY - SPIRDECB
(Page 4-72 Blank
(The input and output information for the SPIRDECB program will be included
in this document when the program becomes operational.)
r
j
SPWDC
k May 19Ö* 4-73 TM-LX-123/OOO/OO
4.3.10 SPECIAL PERTURBATIONS WITH WEIGHTED DIFFERENTIAL CORRECTION - SPWDC
4.3•10.1 Purpose
The SPWDC program corrects a given element set and computes predicted satellite
positions. The differential correction is accomplished using a least square
fit of observations which have been weighted by the Observation Weighting pro-
gram (OBSWGT). The emphemeris and prediction computations use a special
perturbations variation of parameters formulation. This requires that only
the perturbations in the elements be integrated at each integration step
instead of the whole force field as is required by an Encke method. All
integrations are numerical and can take place in either a backward or forward
direction. The perturbations included are:
a. Earth Bulge
b. Drag (1962 NASA atmosphere)
c. Radiation pressure
There are two types of prediction:
a. By time in which the start time, number of points and time between
points are specified.
b. By station pass, in which a closest point of approach (CPA) point
and points on either side of the CPA point are computed.
4.3.10.2 Input - Schedule Tape Mode Only (Toggle 24 On)
Deck Column Position Card Type Number Punch
1 Schedule Tape Card
2 Job Card
3 Remarks Card
h Program ID Card
1-6 SPSJ0B
9-14 OBSWGT
IT 0 = Pa 0 == Parameter cards, Satellite Number cards,
and S-file, E-file and SRADU tape inputs.
SPWDC
h May 19& k-Jk TM-LX-123/OOO/OO
Deck Column Position Card Type Number Punch
17 1 - Parameter cards, Element Set cards, and
(cont'd) s-file and SRADU tape inputs
2 = Parameter cards. Satellite Number cards,
Sensor cards, and E-file and SRAEU
tape inputs
3 = Parameter cards, Sensor cards, Element
set cards and SRADU tape inputs
k = Parameter cards, Observation cards,
Satellite Number cards, and S-file
and E-file tape inputs
5 = Parameter cards, Observation cards,
Element Set cards and S-file tape inputs
6 = Parameter cards, Observation cards, Sensor
cards, Satellite Number cards and E-file
tape inputs
7 = Parameter cards, Observation cards, Sensor
cards and Element Set cards inputs
8 = Parameter cards, Element Set cards and S-
file tape inputs
9 = Parameter cards, Satellite Number cards,
and S-file and E-file tape inputs
18 0 = Hardcopy and punched cards output
5 OBSWGT Parameter Card
1-5 SPWDC
9-11 Satellite number (optional)
12 0, Blank = Weighting Tape input
1 = Use Sensor Weighting Data in OBSWGT Weight
file
79 0, Blank = Use Observation weights in SPWDC
1 = Do not use observation weights in SPWDC
80 P - Card type
SPWDC
h May 19& 4-75 TM-DC-123/OCO/OO
Deck Column Position Card Type Number Punch
6 Vehicle Characteristic Card (required only for DC option)
1-42 Remarks
43-52 Diameter of Satellite (in meters)
53-62 Mass of satellite (in kilograms)
63-72 Reflectivity
79 2 = Parameter card number
80 P = Card type
NOTE: If the Vehicle Characteristic card is omitted, the program assumes
Mass = 10.0 kg., Diameter =1.0 meters and Reflectivity =1.0.
7 Differential Correction Parameter Card (required only for DC)
1 Blank = Variable At integration
1 = Fixed At integration
2-11 Delta t (min.), plus (+) or minus (-)
12 0 = Do not compute bulge perturbation
1 = Compute bulge perturbation
13 0 = Do not compute drag perturbation
1 - Compute drag perturbation
Ik 0 = Do not compute radiation pressure
perturbation
1 = Compute radiation pressure perturbation
15 0, Blank = New epoch is revolution in cols.
16-29 of this card
1 = New epoch is time in cols. 16-29 of this
card
2 = New epoch is time of last observation
l6-29 Time (days) since 1 Jan., or
Absolute revolution number, or
Blank if col. 15 of this card has a 2 punch
30 0, Blank = Do not correct n
1 = Correct n
SF/DC
4 May 1964 4-76 TM-LX-^ 3/000/00
Deck Position Card Type
7 (Cont'd)
Column Number Punch
31
32
33
*
35
36
0, Blank = Do not correct a _T ' xN 1 = Correct a
xN 0, Blank = Do not correct a
yN 1 = Correct a
yN 0, Blank = Do not correct U 0 1 = Correct U 0
37
38
39
0, Blank = Do not correct 0
1 = Correct Q
0, Blank = Do not correct i
1 = Correct i
0, Blank = Do not correct m
1 = Correct m
Maximum number of correction
0, Blank = n is not the only first pass
correction
1 = n is the only first pass correction
0 = No Aq check
1 = Aq check
NOTE: Cols. 38 and 39 are used only if 6 or 7 elements are corrected.
Maximum Aq (km.)
Absolute maximum azimuth, elevation and range
residuals (in kilometers)
Absolute maximum range rate residual (in
kilometers/second)
RMS multiplier
0, Blank = No residual output
1 = First and last residual output
2 = All residuals output
3 = Parameter card number
P = Card type
40-47
48-55
56-63
64-71
72
79
80
SPWDC
4 May 1964 4-77 M-IX-123/OOO/OO
Deck Column Position Card Type Number Punch
8 Absolute Error Parameter Card
1-10 aT (Absolute Error criteria)
11-20 a a x
21-30 a J a y
31-40 a a z
41-50 au h x
51-60 ah y
61-TO ah z
79 4 = Parameter card number
80 P = Card type
NOTE: If the Absolute Error card is omitted, the program assumes 7 P>
a. = 10 , a = a = 10 '*
9 Relative Error Parameter Card
1-10 r, (Relative Error criteria )
11-20 r a x
21-30 r J a y
31-40 r a z
41-50 r. 11 x
51-61 r
61-70
h y
rh z
79 5= Parameter card number
80 P = Card type
SPWDC
k May 1964 k-j8 m-LX-123/OOO/OO
Deck Column Position Card Type Number Punch
10 Time Prediction Parameter Card 1 (Prediction-by-time option only)
1 Blank = Variable At integration
1 = Fixed At integration
2-11 Delta t (min.); Plus (+) or minus (-)
12 0 = Do not compute bulge perturbation
1 = Compute bulge perturbation
13 0 = Do not compute drag perturbation
1 = Compute drag perturbation
Ik 0 = Do not compute radiation pressure
perturbation
1 = Compute radiation pressure perturbation
16 Print option - sum the desired options:
1 = Print t} T, r
2 = Print t} a, e, i, Cl, ti>, U
k = Print T, </>, \ , h
17 0, Blank = No binary tape output
1 = Binary tape output
18 0, Blank = Do not compute prediction reliability
1 = Compute prediction reliability (must have
weighted 6 or 7 element DC including the
drag term)
19 0, Blank = Do not punch r, t
1 --- Punch r, t
79 6 -- Parameter card number
80 P - Card type
11 Time Prediction ParameLer Card 2 (prediction-by-time option only)
1-12 Time (in days) since 1 Jan.
13-20 Delta t (min.)
21-24 Number of output points
79 7 - Parameter card number
80 P = Card type
SPVDC
h May 1964 4-79 TM-IX-123/OOO/00
Deck Column Position Card type Number Punch
12 Station Pass Prprtirt.ion Parameter Card 1 (Prediction-by-stati on
option only)
1 Blank = Variable At integration
1 = Fixed At integration
2-11 Delta t (min.)
12 0 = Do not compute bulge perturbation
1 = Compute bulge perturbation
13 0 = Do not compute drag perturbation
1 = Compute drag perturbation
14 0 = Do not compute radiation pressure
perturbation
1 = Compute radiation pressure perturbation
15-l6 Print opti n - sum the desired options:
1 = Print t, r, r
2 = Print t, a, e, i, 0, m, U
4 = Print t, 0, X , h E
8 = Print t, p, p, A, h
17 0 = No binary tape output
1 = Binary tape output
18 0 = Do not compute prediction reliability
1 = Compute prediction reliability (must
have weighted 6 ot 7 element DC including
the drag term)
19-22 Blank = Station Pass Prediction Parameter
Card 2 provides sensor input
XXXXX = S-file tape provides sensor input
23-32 Number of passes
33-^2 Delta t (min.)* either side of closest
approach
SPWDC
4 May 1964 ^-80 M-U-123/OOO/OO
Deck Column Position Card Type Number Punch
^3-52 Delta t (min.), output per delta t (must have
weighted 6 or 7 element DC including the
drag term)
53-62 Minimum height (deg.)
79 8 • Parameter card number
80 P • Card type
13 Station Pass Prediction Parameter Card 2 (Prediction-by-station
option only)
1-4 Station number
5-14 0N (station latitude)
15-24 \w (station longitude west)
25-34 H (meters) (station height)
79 9 - Parameter card number
80 P = Card type
14 Program Execution Parameter Card
1 0, Blank = No differential correction
1 = Run differential correction
2 0, Blank = No prediction
1 = Compute time prediction
2 = Compute station prediction
3 0 = Print t, U, ß for 1st pass
1 = Print t, U, 0, Ae, Ac* cos 6, Ae,
Ac* cos h (km.), A6 (km.) for 1st pass
2 = Print At, U, ß, Ae, Ac* cos 6, Ae, Ac* cos h
(deg.), A6 (deg.) for all passes A A A
3 = Print At, U, ß, Ae*U, Ae.V, Ae.W, Ae, Ay cos 6
Ae, Aor cos h (deg.), A6 (deg.) and means
for all above values for 1st pass only
78-79 10 = Parameter card number
80 P = Card type
4 May 1964 4-8i
SPWDC
IM-LX-I23/OOO/OO
Deck Column Position Card type Number Punch
15 Observation Cards (optional)
16 Sensor Cards (optional)
17 Satellite Number Cards (optional)
18 Element Set Cards (optional)
19 End of Case Card
20 End of Job Card
21 End of Schedule Tape Card
22 Blank Card
4.3.IO.3 OBSWGT Weighting Tape Format
Deck Position
NOTE:
Column Card Type Number Punch
Program ID Card
1-8 70WEIGHT
9 11, 8, 2 punch = Card type
Observation/Sensor Weighting Card (in lieu of Function Weighting cards)
1-3 Sensor number
4 0 - Sigma data is for all observations from
the specified sensor
2 = Sigma data is for the next observation
only
a1 - p (km.) 9-l6
17-24
25-32
33-40
41
<?2 = p (km./sec.)
c = A or a
a, = h or 6
11, 8, 2 punch = Card type
If a sigma value is not input, leave the field blank.
Function weighting card 1 (im lieu of Observation/Sensor Weighting card)
1-3 Sensor number
4 1 = Parameter data is for a function
5 0, Blank = Last parameter is contained on
this card
1 = Next card is also a parameter card
4 May 1964 4-82 TM-LX-123/OOO/OO
Deck Column Position Card Type Number Punch
9-l6 Function 3D (left adjusted)
17-80 Parameter (follow the last parameter by
an 11, 8, 2 punch)
4 Function Weighting Cards 2-10 (in lieu of Observation/Sensor
Weighting card)
1-3 Sensor number
4 1 = Parameter data is for a function
9-l6 Function ID
17-24 9th parameter (if appropriate)
25-32 10th parameter, followed by an 11, 8, 2 punch
4.3-10.4 Output
The maximum program printout consists of differential correction output, •
prediction output, prediction reliability output, and error comments.
4.3.10.4.1 Differential Correction Output
The differential correction output may appear in several different forms
depending on the input option selection. Basically, two formats are avail- 1
able and the other options add or subtract information from them.
4.3.10.4.1.1 Type 1
The first type of printout consists of the residuals for all of the observations,
followed by the RMS and corrections to the elements, and the corrected elements.
The format of the output is like that of SGPDC (see section 4.3.8.3)
4.3.10.4.1.2 Type 2
The second type of differential correction output contains the following
information:
1. Station number
2. Time of observation
3. Residuals for U, V and W in kilometers where U is the unit vector along
radius vector, V is the transverse unit vector, and W is the unit
vector perpendicular to the orbit plane.
4. Range, range rate, and angular residual means and standard deviations.
5. U, V and W residual means and standard deviations.
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h May 1964 4-86 TM-LX-123/OOO/OO
4.3.10.4.2 Prediction Output
For prediction by time there are three output options which may be requested
separately or in combination- These contain in addition to time:
1. First option
a. Position (X RADII, Y RADII, Z RADII)
!>. Velocity (XDOT RAD/KEMIN, YDOT RAD/KHUN, ZDOT RAD/KMEN)
2. Second option
a. Osculating orbital elements
a (ARADIl)
e (E)
i (I DEG)
Q (NODE DEG)
m (OMEGA DEG)
U (U DEG)
3. Third option
a. Subsatellite track
0 (PHI DEG)
\„ (LAMBDA DEG)
h (H KM)
For prediction by station pass there is an additional option to output:
1. Time
2. Acquisition coordinates - p, p, A, h
4.3.10.4.3 Prediction Reliability Output (not currently used)
The optronal prediction reliability output will print at each prediction
point:
1. Standard deviation in predicted position.
2. Standard deviation in predicted velocity components.
Wiese values will be given referred to the cross-track, in-track, and out-
of-plane coordinates and also referred to the inertial x, y, z coordinate
system.
4.3.10.*+.4 Error Comments
All error printouts by the program are self-explanatory and need not be listed
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4 May 1964 4-89 TM-LX-123/000/00
4.3.II ORBITAL INTERSECTION - XROADS
4.3.11.1 Purpose
The XROADS program computes the point of closest proximity between tvo orbits,
and operates in one of four modes:
a. "Primary" Mode - the program establishes a position and time of
intersection or closest approach of two orbits.
b. "Test Case" Mode - the program computes the elements of a second
orbit, given an initial orbit and the intersection parameters.
c. "Direct Entrance to Function Minimization" Mode - when the time
of intersection is known quite accurately, the program goes
directly to the final stages of proximity computation.
d. "Ephemeris Computation Only" Mode - the program computes
ephemerides in position and velocity for given element sets.
4.3.11.2 Input - Schedule Tape Mode only (Toggle 24 On)
Deck Column Position Card Type Number Punch
1 Schedule Tape Card
2 Job Card
3 Remarks Card
4 Program ID Card
1-6 SPSJ0B
9-14 XRCiADS
IT 0 = Parameter cards and Element Set cards
input
1 = Parameter cards, Satellite Number cards
and E-file tape inputs.
18 0 = Hardcopy output
80 J = Card type
5 Parameter Card Number 1
7 1 = Parameter card number
4 May 1964 4-90 TM-LX-123/OOO/OO
Deck Column Position Card type Number Punch
5 (Continued) 8 0 = Primary mode case
1 = Test mode case
2 = Direct mode case
3 = Ephemeris mode case
9-12 Year of estimated intersection (if zero,
program computes value)
13-19 DDD.DDD ••= Days since beginning of year of
estimated intersection.
20-27 +.xxx+xx (hadians) = Convergence criterion 1
(typically = + .100-04)
28-35 +.XXX+XX (Dimensionless) = Convergence
criterion 2 (typically = + .200-01)
36-43 +.XXX+XX (Radians) = Convergence criterion 3
(typically = + .100-04)
44-51 +.xxx+xx (Days) = Convergence criterion 4
(typically = +.100-07)
52-59 +.XXX+XX (Dimensionless) = Convergence
criterion 5 (typically = +.200+02)
60-67 +.XXX+XX = Weighting factor (typically =
+.100+-1)
68-69 Maximum number of iterations in Loop 1 -
e.g., 10
70-71 Maximum number of iterations in Loop 2 -
e.g., 10
72-73 Maximum number of iterations in Loop 3 ~
e.g., 10
74-75 Maximum number of iterations in Loop 4 -
e.g., 20
80 P = Card type
•
«*e?«s=a
XHQADS
%
4 May 1964
Deck Position Card Type
4-91 TM-LX-123/OOO/OO
Column Number Punch
6 Parameter Card Number 2
7
8-15
16-23
24-31
32-39
40-47
48-49
80
2 = Parameter card number
+.xxx+xx (km) = Variance in x 0
+.XXX+XX (km) = Variance in y 2
+.XXX+XX (km) = Variance in z 2
+.xxx+xx (sec) = Variance in t
+ .XXX+XX (days) = Interval for emphemeris
output
Half the number of time points for ephemeris
output
P = Card type
Parameter Card Number 3 (Required only for Test Case Mode - Case l)
7 8 = Card number
8-14 DDD.DDD (Days since beginning of year) = Epoch
for which the second element set is to be
generated by the test case generator (case l)
15-21 DDD.DDD (Days since beginning of year) •
Time at which input perturbations are
applied by the test case generator
22-29 i'Xxx+xx (m/sec) = Tangential component
of velocity impulse
3O-37 +.XXX+XX (m/sec) = Normal component of
velocity impulse
38-45 +.xxx+xx (m/sec) = Transverse component
of velocity impulse
46-53 +.xxx+xx (ra) = x component of position error
54-6l +.xxxj;xx (m) = y component of position error
62-69 ^.xxx+xx (m) = 2 component of position error
70-77 +.XXX+XX (Sec) = Time error
80 P - Card type
XROADS
k May 196h 4-92 TM-LX-123/OOO/OO
Deck Column Position Card Type Number Punch
8 Data Cards
a. Case 0, Case 2 and Case 3*
(1) Input Option 0:
(a) Parameter card 1
(b) Parameter card 2
(c) Element set 1
(d) Element set 2
(2) Input Option 1:
(a) Parameter card 1
(b) Parameter cr.rd 2
b. Case 1
(1) Input Option 0:
(a) Parameter card 1
(b) Parameter card 2
(c) Parameter card 3
(d) Element set 1
9 End of Cas s Card
10 End of Job Card
11 End of Schedule Tape Card
12 Blank Card
3.H.3 Output
4.3.11.3-1 Normal Output
The primary output of the program consists of the position and time in each
of the orbits at the intersection as veil as the differential quantities vhich
describe the characteristics of the intersection. The specific values are:
1. Times in days (Tl, T2)
2. Position coordinates in kilometers (XI, Yl, Zl, X2, Y2, Z2)
3. Velocity components in km/sec (X1D, YID, Z1D, X2D, Y2D, Z2D)
k. Velocity magnitudes (SID, C2D)
• •15'WWr*x$MtiPi$
XRQADS
h May 19& 4-93 TM-LX-123/OOO/OO
5. Geodetic latitude at the intersection point with geodetic radius (GEOD
LAT)
6. Longitude (LONG)
7. Slant height (HEIGHT)
8. Time difference in seconds (DT)
9. Position coordinate differences in meters (DX, DY, DZ)
10. Velocity component differences in meters per second (EKD, DYD, DZD)
11. Velocity magnitude difference in meters per second (DSD)
12. Component of velocity along radius vector in meter's/sec (DRD)
13. Component of velocity impulse tangent to vehicle path in meters/sec
(TANGENTIAL COMP. OF DELTA RDOT)
Ik. Component of velocity impulse which is normal to vehicle path but in
the orbital plane in meters/sec (NOEMAL COMPONENT OF DELTA RDOT)
15. Component of velocity impulse which is normal to the orbital plane in
meters/sec (TRANSVERSE CCMP. OF DELTA RDOT)
16. F, E? - DG, A, D + G, B where
F = (*g - xxf + (y2 - yx)2 + (z2 - Z;L)
2 + (t2 - tx)2
o 2 02 02 a? y z t
D =
c)t2
3^2
-^ a tx2t2
0-^ at22
4.3.II.3.2 Ephemerides
The optional ephemerides output consists of the position and velocity in each
of the orbits for a number of times equally spaced about the mean time of the
•
XROADS
h May 1964 h-9k TM-LX-123/OOO/00 i
intersection. The quantities are:
1. Position coordinates in kilometers x'Xi, Yl, 21, X2, Y2, 72)
2. Times in days (Tl, T2)
3. Velocity componenets in km/sec (X1D, Y1D, Z1D, X2D, Y2D, Z2D)
4. True arguments of latitude in degrees (Ul, U2)
5. Separation in kilometers (SEPARATION
4.3.11.3»3 Error Comments
Six significant error printouts may also appear from the program:
1. Nl MAX EXHAUSTED - failure to converge on t (times at which u's
are equal).
2. N2 MAX EXHAUSTED - function F is greater than allowed value (see
input parameters) at converged value of t .
3. N3 MAX EXHAUSTED - failure to converge on the times corresponding to
the geometrically determined values of u.
k. NU MAX EXHAUSTED - failure to converge in the function minimization
loop.
5. SADDLE POINT - function minimization process yields times at a saddle
point.
6. REIATIVE MAXIMUM - function minimization process yields times at a
relative maximum.
In all six cases, the program continues processing, in the first four cases
using the latest values of t.
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4 May 1964 4-97 TM-LX-123/OOO/OO
4.3.12 OTHER
de following programs in the Element Determination area are seldom used
by the analyst. A brief description of each program is given.
4.3.12.1 CCOE
The CCOE program calculates, from an input element set, the cartesian coordinates
(x, y, 2) and the components of velocity, (x, y, z) of a satellite for a
specified length of time at given intervals. The output can be expressed
in either kilometers or earth radii.
4.3.12.2 HANSEL
The HANSEL program produces a teletype tape for transmission to SCAF (Space
Track Center Alternate Facility). The tape contains the SPADATS object
numbers and element set numbers of all satellites whose elements were updated
during a specified time period (normally 24 hours.)
4.3.12.3 MSGV
The MSGV program produces, for transmission to specified field sites, a set
of teletype tapes containing newly updated element sets. The type of element
sets (seven or four cards) can be specified as an input option. The program
is normally run once a day.
4.3.12.4 SEAI
The SEAI program generates a new SEAIC tape from standard SPADATS data cards.
The program will build a new tape or update an existing tape by replacing,
adding or deleting records.
The files contained on the SEAIC tape are as follows:
1. Sensor file
2. Element file
3. Acquisition file
4. Information file
5. Communication file
k May 196k i^-98 TM-LX-123/000/00
k.3.12.5 SUM
The SUM program summarizes the contents of the SEAIC tape. All files or only
selected files (toggle option) can be specified for output in hard copy
format.
-MbMaULKWV.MuKlritVnilMSE- »»MHHWi—WffWlimMllimiUIIIWiaWBgffgW
U May 1964 4-99 TM-LX-123/OOO/OO (Page 4-100 Blank)
k. 4 OBSERVATION ACCRJISITI ON AREA
The Observation Acquisition area includes the programs that generate
acquisition coordinates (GLASGP, LAP, ENSCHED, OBSERV, XYZLA, ORPS and
POSE), the position and status programs (PSR, PREPINT, and GRNTRK) and the
bulletin programs (BLTNSGP and SYSBULL).
0
BNSCHED
4 May 1964 4-101 TM-LX-123/OOO/OO
4.4.1 BAKER-NUNN SCHEDULE - BNSCHED
4.4.1.1 Purpose
The BNSCHED program computes sets of predicted acquisition coordinates for
a group of satellites and specified Baker-Nunn sensors.
4.4.1.2 Input - Schedule Tape Mode Only (Toggle 24 On)
Column Deck Position Card Type Number Punch
1 Schedule Tepe Card
2 Job Card
3 Remarks Card
4 Program ID Card
1-6
9-15
IT
18
SPSJ0B
BNSCHED
0 = Parameter card, Sensor Number card,
S-file, E-file (all element sets)
and I-file tape inputs
1 =* Parameter card, Sensor Nvmber card,
Element Set cards, S-file and I-file
tape inputs
2 = Parameter card, Sensor Number card,
Satellite Number card, S-file, E-file and
I-file tape inputs
3 = Parameter card, Sensor Number card,
Sensor card, E-file (all element sets)
and I-file tape inputs
4 = Parameter card, Sensor Number card,
Sensor card, Element Set cards and I-file
tape inputs
5 = Parameter card, Sensor Number card,
Satellite Number card, Sensor card,
E-file and I-file tape inputs
0 = Hardcopy and TTY output
1 = Hardcopy output
BNSCHED
h May 1964 4-102 IM-LX-123/000/00 i
Deck Position Card Type
5 Base Time Card (optional)
Column Number Punch
NOTE:
7
NOTE:
8
1 Base Year (last digit)
2-10 Base Day
25-28 Base message number
79 J = Card type
80 P = Card type
The Base Time card is optional. If not used, the information is
taken from the last case executed.
Parameter Card
2-10 Beginning time (days since Base Day)
11-19 Ending time (days since Base Day)
20-21 Total number of sensors on the Sensor
Number card(s)
Minimum start track angle (deg.)
Minimum elevation angle (deg.)
P = Card type
29-33
3^-38
80
Sensor Number Card
1-3
k
Sensor number
1 - Secret
2 = Secret/NoForn
3 • Confidential
h = Confidential/NoForn
5 *= Unclassified
6 * Unclassified/EFTO
5 Y - Emergency
0 = Operations - Immediate
P = Priority
R = Routine
Cols. 1-5 may be repeated, once for each sensor, up thru col. 75»
80 P = Card type
Satellite Number Card
1-8 Satellite number (rt.-adj.)
I ^W^wjTO^-TM«^-^-»^*«*?« .
4 May 1964 4-103
BNSCHED
aM-IX-323/OOO/OO
Deck Position Card Type
Column Number Punch
9 Data Cards:
(1) Element Set cards (optional)
(2) Sensor cards (optional)
10 End of Case Card
11 End of Job Card
12 End of Schedule Tape Card
13 Blank Card
4.4.1.3 Output
Program printout consists of the following information:
Addressing information
Message identifier
Station number
Date — day, month, year
Acquisition data containing:
a. object number
b. time of start track — hours, minutes, seconds
c. star chart map number and indicator
d. azimuth in tenths of degrees
e- altitude in tenths of degrees
f. initial track angle in degrees
g. angular velocity in seconds per second
h. final track angle in degrees
i. right ascension in hours and minutes
j. sign of declination and declination in degrees
k. position angle in degrees
1. check word
m. time of start of next predictions
BNSCHED
4 May 1964 4-104 TM-LX-12 3/000/00
.
SAMPLE PRINTOUT, BNSCHED
VD DXA325DHB744 00 ENTA.FB JHNISL DE SPA TRK 4lH 20/1732Z ANR 0 2OI732Z ZEX m SCAF LG HANSCOM FLD MASS TO JHNISL/DET 4 2SURVILISQ JOHNSTON ISLAND IFO ENT AFB/lST AERO ENT AFB COLO BT UNCLASS/E F T 0 / 1AER0 OOPS 66617 40423 0732 CAMERA PREDICTIONS K)R STATION AT SAND ISLAND(B/N)
66617 40423 00162 00732 53450 34711 00162 00734 19340 34541 00162 00735 46030 34131 00162 00737 12150 33381 00162 00738 38260 32311 00162 00740 05350 31l6l 00162 00741 31350 30241 00162 00742 58400 29681 00162 00744 24380 29411
03380 00303 38007 02870 01304 37018 02440 02805 73035 02110 04907 28058 01960 07808 22088 02010 10807 79118 00260 13506 37142 02640 15^04 89160 03090 16803 76172
043Ö1 10344 04491 02349 04580 10353 04040 24357 05090 43001 05050 62006 04140 80023 20270 83144 19000 73171
28180 79599 51951 88582 28098; 74184 87255 66293 00523
NEXT PREDICTIONS START AT DAY 115.499-
EXPLANATIONS:
Line 1; 666fc.ll 14042 3l
Message ID •Station •Date
not used —ob j. number
not used time of start track —— Star map number Star map indicator Azimuth Not used Altitude
Line 2: fOCp^ JCE732 534301 E4
-Not used
TM EIS Pqfo 3öor>jl Epqil lich44] EST8Ö Initial trk. angl
Angular velocity- ;J
Final trk. angle — Right ascension-
Sign of declination- Declinati on——
Pass angle— check word
•
•
BLTNSGP
4 May 1964 4-105 lM-LX-123/OOO/OO
k.k.2 BULLETIN WITH SIMPLIFIED GENERAL PERTURBATIONS - BLTNSGP
4.4.2.1 Purpose
The BLTNSGP program computes an ephemeris (set of predictions) of future
satellite positions based on the orbital elements describing the motion of
the satellite. The program integrates the orbit using the SGP technique.
4.4.2.2 Input
4.4.2.2.1 Automatic Mode - in an OCS sequence
a. The satellite number from the SATTB tape.
b. The corresponding element set from the E-file tape, including
the number of the initial revolution of Part II.
c. OCS Toggle number On = Desired OCS sequrv:e.
d. Toggle 44 On = Non-addressed bulletin on tape 5 for printing/punching.
4.4.2.2.2 Schedule Tape Mode - (Toggle 24 On)
Deck Column Position Card Type Number Punch
1 Schedule Tape
2 Job
3 Remard (optional)
4 Program ID
1-6 SPSJ0B
9-15 BLTNSGP
IT 0 = Satellite numbers card, E-file and
I-file tape inputs
1 = Parameter card and element set cards
inputs
l8 0 = Hardcopy and TTY outputs
1 = Hardcopy output comments (alpha
number)
19-72 Comments (alphanumeric)
BLTNSGP
4 May 1964 4-106 TM-LX-223/OOO/OO
Deck Coluirn Position Card Type Number Punch
5 Satellite Numbers Card (optional)
6 Parameter Card (optional)
1 N = Non-addressed bulletin
- = Pre-addressed bulletin from I-file
2-24 Satellite Number
7 0 = TTY input
1 = No TTY input
8-9 Last two digits of year satellite
was launched
10-11 01 = er "X
01 = & IGY World Wide Code
03 = v j o4 = 6 y
12 Component (No. assoc. pcs.)
13-27 Radio frequencies, 5 digits each, in
lOOths of a megacycle
34-40 Initial revolution
41-47 Final revolution
48 0 = No grid
1 = Standard grid
2 = Special grid
49-55 Grid revolution
60-61 Grid increment (no decimal pt.)
62-65 Grid latitude
66-67 Bulletin year
68-70 Bulletin number
80 P = parameter card
Data Cards:
a. Input option 0: None
b. Input option 1:
(l) 7-card Element Set Cards
•
•
BLTNSGP
4 May 1964 4-109 TM-LX-12 3/000/00
PART III. REDUCTION TO OTHER LATITUDES AND HEIGHTS FOR REV LAT MINUTES LONG HEIGHT
N PLUS CORR KILQM LAT MINUTES LONG HEIGHT»
S PLUS CORR KILOM*
SN 00 SN 10 SN 20
.00 2.97 £25.
.00 359.24
1117.8V 1096.7V
NS 00
358.39 1079.ov NS 10 NS 20
?3-20 193.39 192.66 191.85 190.82 ifo-3? 187.18
1222.8V* 1246.1V* 1268.3V* 1288.7V* 1306.3V*
SN 30 SN 40
8^2 11.85
17.90
357.32 344,82
IO65.2V 1055.4V 105^ To4<
NS 30 NS 40
62.53 65.69
^09 SN 50 SN 60
353.54 349.60
^9.6V 104'7.8V
NSr50 N&60 72.15 183.34
1320.2V* 1329.6V*
SN 70 SN 80
21.02 24.79 26.36 27.93
341.25 309-.12
lW.h 7V 1056.9V
NS 70 NS 80
75.52 79.57
175.17 143.76
I333.5V* 1329.7V*
N PT NS 80
277.25 245.03
IÖ6.L.3V 1066.4V
S PT SN 80
8I.26 82.94
112.30 79.77
37.80 33.82 31^3
1325.5V* 1319.6V*
NS 70 NS 60
31.71 34.88
212.23 203.76 199.76"
108i,7V 1097.2 1114.6 "
SN 70 SN 60
"56T9T ?o-3i
1299.6V* 1277-4V*
NS 50 NS 40 NS 30 NS 20 NS 10 NS 00
37.95 40.99. 44^3 47.07
197.50 1133.7 196.02 194.96
K SN 50 SN 40
1154.4 1176 M
93.51 96.6
SN 30 SN 20
1252.2 * 1225.0 *
99.7 102.80
50.13 13^20
194.12 193-39
1199.4V 1222.8V
SN 10 SN 00
105.82 IOS.94
30.05 28.99 28.14
1196.9 * 1169.IV* 1142.6v*
27.37 1117.4V*
4.4.2.3.4 Part IV - The description of SATOR (modified Orbital Elements for
Prediction Purposes) is as follows*
Code word: SATOR
Symbolic form:
SAT0R aabbc
iiiii jkkkl
00000 PPPPP
RAFRE sssss
deeff ggggZ hhhhX N0WES
ARPER 11111 mnnnX PERI0D
ECCEN. qqqqq PERRA rrrrrr
(sssss repeated RATASC ttttt
as necessary)
Kev:
aa = Last two digits of year satellite launched
bb = Greek letter designation, 01 - Alpha, 02 - Beta., etc.
c = Component
d = Reference time (time of perigee passage closest to epoch):
last digit of numerical notation for month; i.e,, 1 = January
or November, 2 = February or December, 3 = March, etc.
BLTNSGP
h May 1964 4-110 TM-DC-12 3/000/00
ee = Reference time: date
ff = Reference time: hour
gggg - Reference time: minutes and hundredths of minutes
Z = Universal time, Greenwich Mean Time
hhhh = Inclination in degrees and hundredths of degrees.
If the orbit inclination is negative (satellite
launched vestward) group is preceded by NEGAT.
X = Always an X
PART IV 64o4"A 20718
5658Z 08315 01882 RADEG
SATOR 27906
20311 ARPER
8l48X 2186X
NOWES PERIOD 46036 394
RAFRE 00000 36.70
ECCEK 00000
PERRA 03279
•
GLASGP
4 May 1964 4-111 TM-LX-12 3/OOO/00
4.4.3 GENERAL LOOK ANGLES USING SIMPLIFIED GENERAL PERTURBATIONS - GLASGP
4.4.3.1 Purpose
'Rie GLASGP program computes sets of predicted acquisition coordinates for
a group of satellites and their associated sensors, using the anomalistic
data in an element set. The program integrates an orbit using the SGP tech-
nique.
4.4.3.2 Input
4.4.3.2.1 Automatic Mode - in an OCS sequence
a. The satellite numbers from the SATTB tape.
b. The corresponding element sets from the E-file tape.
c. The sensors associated with each satellite from the A-file tape.
d. The acquisition coordinates for each sensor from the A-file tape.
e. The Look Angle message parameters from the A-file tape.
f. OCS number Toggle On = Desired OCS sequence.
g. Toggle 44 On = addresses from I-file, not C-file
4.4.3.2.2 Schedule Tape Mode (Toggle 24 On)
Deck Column Position Card type Number Punch
1 Schedule Tape Card
2 Job Card
3 Remarks Card
4 Program ID Card
1-6 SPSJ0B
9-14 GLASGP
17 0 = Satellite number card, S-file, E-file and
A-file tape inputs
1 = Sensor, Element Set and Acquisition cards
18 2 = Hardcopy and TTY outputs
3 = Hardcopy output
80 J = Card type
GLASGP
4 May 1964 4-112 lM-LX-123/OOO/OO
Deck Column Position Card Type Number Punch
5 Data Cards:
a. Input Option 0:
(l) Satellite Number card (max. = 4 per case)
b. Input Option 1:
(1) Sensor cards (max. = 31 Per case)
(2) Element Set cards
(3) Acquisition cards (max. = 31 per case)
NOTE: Initial and final revolution are specified only if N and N^ +15
on the 7th Element card are not acceptable to the analyst.
6 End of Case Card
7 End of Job Card
8 End of Schedule Tape Card
9 Blank Card
4.4.3.3 Output
The program printout is essentially a Look Angle message containing the
following information:
1. Addressing information
2. Satellite name and number
3. Element set number
4. Initial and final revolution of computation
5. Sets of acquisition coordinates containing:
a. Time
b. Angular quantities and/or
c. Ränge and/or
d. Range rate and if desired
e. Elevation angle of the sun and satellite illumination.
k May 19& *-113 (Pag« k-llk Blank)
GUSGP
BI-ÜC-123/OOO/OO
SAMPLE PRINTOUT. GLASGP
00 SPATR* OE RUWQALD 2611 ]7/l«2nZ INK 0 1719202 ZEX PH 1AÜ0SPCTLSC EN1 AFB COLO TO SPATRK/lAENCSfCTLSO ENT APB COLO AfORNC •T UNCLAS SPACETFACK CENTER 44 3317 903 CNT AFB COLORACC «6P 62B-UPSI 1 SAT, N* COMPUTATIONS STARTED AT REVOLUTION NO« 269ft
903 ELEN 17 VISUAL PASSES
PAQE i
REV ZEBRA im ettv AZIH RANOi RATE R,At DEC SUNS ILLUN1 NO. OAT MR *|ft9 AKO. ANO, KH, KM/REC DEG, DES ELE ¥ NATION
3317 44 1 6.4C 3916 170.9 2961 «i;i Al,126 •11,327 «7 »9 35,4 3317 44 1 7.4C 4413 162,0 2933 •.4 A7.071 «9,466 «7 .7 33,6 3317 44 1 6.4C 4611 151,6 2932 .3 73,043 .358 -7 .9 31,6 3317 44 1 9.4C so:* 139.1» 2975 1*0 79.001 5,939 .6 •1 30,1 3329 49 1 -67,4c 4019
4612 208.4 2967 «•2,2 44,130 •6,330 «19 •3 39,7
3325 49 1 46.4C 204.0 2871 •i;§ 49.623 «,594 «19 •5 33,9 3329 49 1 6«.4C 5919 197.7 2798 •.8 •15.631 9,396 «19 •7 32,2 3329 49 1 50.4C #214
A813 188,3 277? •.0 A2.139 11.307 «19 ,8 30,9
3329 49 1 U#«C 173.8 2791 • 6 A8.7U 17.013 «16 i0 28,8 3329 49 1 5«.*>C 7S19 1*2.4 2853 1,3 75.466 22.25U «16 i2 27,2 3329 49 1 53.4C 7214 127.4 2955 1.9 62.374 28,690 «16 |4 25,7 3333 46 2 32.4C «616 23V.2 2959 •.5 «1,060 20.914 -23 >• 29,1 3333 46 2 23,4C 46^6 240.0 2944 • 0 97,266 24.046 «24 >1 27,9 3333 46 2 24,4c 7612 241.7 2966 .7 A3,950 31,223 -24 i3 26,6 3348 46 0 41.4C 3919 184.1 2907 «2.2 46,178 •15,762 •! »9 43,6 3346 48 0 42,4C 4114 176.7 2797 •Ü4 94.442 •9,644 «2 il 41,8 3346 46 0 43.4C 4619 18/,* 2737 •.5 *Q,949 »3,647 «2 »3 39,9 3346 48 0 44,4C 51|4 155,4 2726 .2 «7.526 2.990 «2 i9 36,9 3346 «6 0 45,4t 54[2 141,8 2769 1.0 74,146 6,473 «2 i7 36,2 3348 46 0 46.4C 9911 127.6 2856 1.9 P0,732 13,663 .2 »9 34,9 3346 48 0 47,4C Mi4 114.4 2964 2.4 67,206 16,623 »3 »1 39,7
COHPUT ATIONS STCFPCD AT REVOLUTION NO t 3399 NEXT REVCLLTXCh STlRTS AT DAY 49,046 JAT , NO 503 ELEM 17
>»>>»NKNN
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-•
GRNTRK
k May 1964 -115 lM-lJC-123/ooo/oo
h.k.h GROUND TRACK - GRNTRK
4.4.4,1 Purpose
The GRNTRK program computes a sübsatellite track of a satellite betveen two
specific revolutions at a given tiiae increment«.
k.k*k.2 Input - Schedule Tape Mode Only (Toggle 24 On)
Deck Column Position Card Type Number .Punch
1 Schedule Tape Card
2 Job Card
3 Remarks Card
4 Program ID Card
1-6 SPSJ0
9-14 GRNTR
IT 0 =- P
6
18
so Parameter Card
1-3
20-24
26-30
32-34
37-46
49-58
80
Data Cards:
a Input Option 1
(l) Element Set Cards
0 a Parameter card; E-file inputs
1 = Parameter card and Element Set cards
1nputs
0 = Hardcopy output
1 - Hardcopy and TTY output
J -- Card type
Satellite number
Initial revolution (without Start Time)
Final revolution (without End Time)
Delta time interval (min )
Start time, Y'YMMBDHHMM (without Initial Rev.)
End time, YYMMDDHHMM. (without Final rev.) D = Card type
GRNTRK
4 May 196*4 4-116 TM-LX-123/OOC/OO
Deck Column Position Card Type Number Punch
T End of Case Card
8 End of Job Card
9 End of Schedule Tape Card
10 Blank Card
4.4.4.3 Output
The output of the program is a printed ephemeris. The length is governed
by the starting and final revolutions or starting and ending times on the
input parameter card. The time interval between printed points is also
variable and determined by the parameter card. Quantities printed are:
1. Epoch time
2. Time (year, month, day, hour, minutes)
3. Latitude in degrees
4. East longitude in degrees
5. Altitude in kilometers
6. Revolution number
;RYTPJC
k May 1 >61* U117 lag© Ull6 Blank)
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LAP
h May 1964 4-119 TM-LX-123/OOO/OO
4.4.5 LOOK-ANGLE PROGRAM - LAP
4.4.5.1 Purpose
The LAP program computes a set of predicted acquisition coordinates for a
given satellite and each specified sensor, using the nodal data in an ele-
ment set. There are three sub-programs:
a. the General Look Angle Program - GIAP
b. the Baker-Nunn Look Angle Program - BLAP
c. the Special Look Angle Program - SLAP
4.4.5.2 Input - Schedule Tape Mode (Toggle 24 On)
Deck Column Position Card type Number Punch
1 Schedule Tape Card
2 Job Card
3 Remfrks Card
4 Program ID Card
17-19 RUN
25-27 LAP
28-32 ,DATA
5 Element Set Cards
6 Alert Deck Request Card (optional)
1-3 Satellite number (right adjusted)
5-7 Element Set number (right adjusted)
20-24 Initial revolution for computation
26-30 Final revolution for computation
55 5 = Card type
7 LAr Request Card
1-3 Satellite number (not required if card is
for Alert deck)
5-7 Element number (must be -10 if card is for
Alert decx)
20-24 Initial revolution; or initial day number for
SLAP (not required if card is for Alert deck)
LAP
U May 1964 4-120 «IM-IX-12 3/000/00
Deck Position Card Type
optional for GLAP
and SLAP, not re-
quired for BLAP
Column Number
26-30
32-34
36
3T
38-42
43-45
46-48
49-51
52-54
55
56
56
Punch
Final revolution; or final day number for SLAP
(not required if card is for Alert deck)
Time separation between points (optional for
GLAP, SLAP; not required for BLAP)
blank - 2 minutes
0 or blank = All passes
1 = Visual passes
0 = Short output format
1 = Long output format
Maximum range, km (NM if GLAP and Col. 56 = l)
blank =1x10 km or N.M.
Minimum elevation
blank = 0°
Maximum elevation
blank = 90°
Minimum azimuth
blank = 0°
Maximum azimuth
blank = 360°
0 = All-point GLAP
1 = One-point GLAP
3 = Three-point GLAP
4 = BLAP
8 = P.LAP
GLAP range units for output (optional)
0 = Kilometers
1 - Nautical miles
BLAP Importance (optional
3, 2 or 1, where 3 is most important
LAP
k May 1961+ fc-121 TM-LX-123/OOO/OO
Deck Column Position Card Type Number Punch
57 BLAP Reply (Optional)
3, 2 or 1, vhere 3 is most urgent
58 BLAP Element Indicator (optional)
0 = New elements
1 = Old elements
66-72 Perigee distance (optional for BLAP, not
required for GLAP, SLAP);
q-term if q / a (i-e);
blank = q from element card
8 Sensor Card
NOTE: Pairs of one Request card and one Sensor card are required for each
sensor for which look angles are to be computed. These pairs con-
stitute the Alert Deck if card 6 is used.
9 End of Data Card
10 End of Job Card
11 End of Schedule Tape Card
12 Blank Card
k.k.5.3 Output
The exact output obtained from the program depends upon the combination of
options selected in the request card. The general output obtained depends
on which of the three major subprograms (GLAP, SLAP, BLAP) is chosen in
the LAP type option.
k.k.5.3.1 GLAP Output.
The printout for this portion of the program contains:
1. Station and satellite numbers of the prediction
2. Station and satellite names
3. Element number
k. Acquisition data ordered by revolution and time within revolution:
LAP
k May 1964 4-122 TM-LX-123/OOO/OO
a. Revolution number
b. Time of predicted poin: (GMT)
c. Elevation and azimuth in degrees
d. Range in kilometers
e. Optional elevation and illumination angles of the sun.
5- Day of next revolution, satellite number, and element number.
6. If computations were inconsistent, the residuals of time (min.),
right ascension of ascending node (deg.), and height (km.) are printed.
The number of data lines per revolution number is determined by the type
of GIAP requested.
1. One data line is put out for the point of closest approach in one-
point GLAP.
2. Three data lines are produced in three-point GLAP. The first and third
lines are for the points immediately above the minimum elevation angle
of the station. The middle line is for the point of closest approach.
3. A variable number of data lines is produced by all-point GLAP, starting
with the first po^t above the station horizon and proceeding by in-
crements of delta Lime to the last point above the other horizon.
• . • • - i
LAP
• 4 May 1964 4-123 TM-IX-12 3/000/00
SAMPLE PRINTOUT, GLAP
BBBBBBBBBBBBBBBBBB 300 444
•
TRINIDAD 300 62B-KAPPA COMPUTATIONS STARTED AT REVOLUTION NO.
REV ZEBRA TIME ELEV AZIM RANGE* NO. DAY HR MIN ANG. ANG. KM *
SAT. NO. 444 ELEM. 32 ALL PASSES*
2*
32 32 32 32 32
33 33 33 33 33 31 33 33 33 33 37 -2L
303 00 12.09 1.1 100.7 303 00 15.40 6.4 187.9 303 00 18.78 11.9 187.2 303 00 22o21 17.7 186.9 303 00 25.67 23.8 185.9 303 00 29.15 10-3 185.2 3Ö3 00 32.63 37.1 18^.3
32 303 00 36.07 44.5 183.3 32 303 00 39A7 52.4 181.8 32 303 00 42.81 60.9 179.3 33 303 00 46.07 70.0 174.3 ^ ^OT 00 49.24 79.4 159.1
"953^ 9139* 8723* 8290* 7844* 7389*
303 00 52.30 84.2 303 00 55-24 75.8 303 00 58.07 64.8 303 01 0,78 53.7 303 01 3.36 42.9 303 01 5.83 32.9 onrj m A T7 00 A
6482* 6048* 5643* 5280* 4974*
83.0 33.4 23.4 19.6 17-9 16.
30? 01 8.17 23.8 16. 303 01 10.39 15.5 16..2 303 01 12.51 8.1 16.2 303 01 14.51 1.4 16.3 303 11 34.54 1.5 57-4 303 11 35-60 2.5 79.4
4740* 4591* 4;35* 4572* 4695* 4893*
37 303 11 36.66 1.8 99.4 37 303 11 37.74 0,1 114.4
COMPUTATIONS STOPPED AT REV.-NO. NEXT REVOLUTION STARTS AT DAY 303 * MACHINE COMPUTATIONS CONSISTENT
5151* 5454* 5788* 6144*
1459* 2422* 1613* 1931*
40* 853 SAT 444 ELEM 2*$
300 300 300 300 300 300
300 300 300 300 300 300 300 300 300 300 300 300 300 300 300 300 300 300
300 300
LAP
4 May 1964 4-124 TM-LX-123/OOO/oo
4.4.5.3.2 SLAP Output
The Special Look Angle output is identical to GIAP output. Prediction points
are separated by the delta time of the request card. Minimum elevation is not
tested; instead, the iteration is continuous throughout the requested time
interval.
4.4.5.3.3 BLAP Output
Baker-Nunn Look Angle output contains the following information:
1. Satellite name and number
2. Station name and number
3. Eight words of packed coded data plus a code number, station number
code, and object number on the first line only. The eight words
contain:
a. year, month, day of culmination
b. reply code
c. azimuth angle in degrees and tenths of degrees
d. altitude setting in degrees and tenths of degrees
e. operational priority
f. angular velocity in seconds of arc per second
g. track angle of shadow entry or exit (hour of culmination,
angle in degrees)
h. time of culmination in minutes and seconds
i. height in statute miles
j. check sum word
4. Uncoded look angle data
a. time of prediction point (GMT)
b. elevation and azimuth in degrees
Co angular velocity in seconds of arc per second
d. slant range in miles
e. height in miles
5. Day of next revolution, satellite number, and element number.
6. If computations were inconsistent, the residuals of time, right
ascension, and height, are printed.
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OO/OOO/SST-XI-WI. (nwra: 9^-1 •••<*)
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OBSERV
k May 19& U-127 TM-LX-123/OOO/OO
k.k.6 OBSERVING SCHEDULE - OBSERV
k.k.6.1 Purpose
The OBSERV program computes sets of predicted acquisition coordinates for fan
and tracker type sensors. It is usually used for all satellites in the system
over a specified sensor.
^.4.6.2 Input - Schedule Tape Mode Only (Toggle 2k On)
Beck Position Card type
Column Number Punch
1 Schedule Tape Card
2 Job Card
3 Remarks Card
k Program ID Card
1-6
9-lU
IT
18
SPSJ0B
0BSERV
0 = Parameter card, S-file and E-file tape
inputs
1 = Parameter card, Element Set cards and
S-fiie tape inputs
2 = Parameter card, Element Number cards
and S-file and E-file tape inputs
3 * Parameter card, Element Set cards and
Sensor cards inputs
k - Parameter card, Sensor cards, Element
Number cards and E-file tape inputs
0 « Hardcopy and TTY output
1 = Hardcopy output
OBSEKV
h May 19Ö+ I1-I28 TM-LX-02 3/000/00
Deck Position Card Type
5 Parameter Card
Column Number
1-k
6-12
13-19
20-25
26-29
30-33
3h
35
37
38-39
53-56
79
80
Fan Card (optional)
1-6
7-12
13-18
19-2h
25-30
Punch
Sensor Number (rt. adj.)
xxx.xxx (days) = Beginning time (days since
beginning of year)
xxx.xxx (days) = End time (days since beginning
of year)
xxxxxx = Maximum observable range
xx.x = Beam width
Year
0 = Fan number output (fans only)
1 = Elevation angle output
0 = Nautical units for range and range rate
1 = COS units for range and range rate
0 = Unclassified
1 = Confidential
2 = Secret
3 = Secret/NoForn
Priority (printed on output message)
Message number of first message to be
generated
R = Card type
P = Card type
xxxx.x = 1st fan elevation angle ^or azimuth,
if col. 77 is V-punched)
xxx.xx = 1st fan minimum azimuth (or elevation,
if col 77 is V-punched)
xxx.xx - 1st fan maximum azimuth (or elevation,
if col. 77 is V-punched)
Fan number (rt. adj.)
2nd fan (see cols. 1-6)
OESERV
4 May 1964 4-129 TM-IX-123/OOO/OO
Deck Column Position Card type Number Punch
31-36 2nd fan (see cols. 1-12)
37-42 2nd fan (see cols. I3-18)
43-48 Fan number (rt. adj.)
49-54 3rd fan (see cols. 1-6)
55-60 3rd fan (see cols. 7-12)
61-66 3rd fan (see cols. 13-18)
67-72 Fan number (rt. adj.)
73-75 Sensor number
77 V = Vertical fan indicator
79 F = Card type
80 P = Card type
NOTE: A maximum of seven fan cards may be input per sensor.
8
Tracker Card (optional)
2-6 -99*0 = tracker request
19-24 xxx.xx = Minimum elevation
25 3=3 points/pass
5=5 points/pass
7=7 points/pass
Sensor number
F = Card type
P = Card type
73-75
79
80
Address Card
1-32
67-72
79
80
Data Cards
a. Input Option 0:
b. Input Option 1:
(l) Element Set cards
Sensor address (32 BCD characters)
Sensor number
A = Card type
P = Card type
None
OBSERV
i 4 May 196k 4-130 IM-TJC-12 3/000/00
Card Column Position Card Type Number Punch
c. Input Option 2:
(l) Element Number cards
d. Input Option 3:
(1) Sensor cards
(2) Element Set cards
e. Input Option 4:
(1) Sensor cards
(2) Element Number cards
10 End of Case Card
11 End of Job Card
12 End of Schedule Tape Card
13 Blank Card
4.4.6.3 Output
Program printout consists of 4 parts.
4.4.6.3.2 Part 2
Part 2 contains a Satellite Summary for the receiving station and consists of
the following information:
1. Satellite numbers.
2. Satellite number of any which are decaying.
3- Satellite numbers of any 100 days past epoch.
4. Element numbers
I
I
OBSERV
h May 196U U-131 TM- IX-12 3/OOO/OO
SAMPLE PRINTOUT, OBSERV
PART 2, SATELLITE SUMMARY
SAT. SUMMARY FOR STA-850
059,369,503
DECAYING
OOO
100 DAYS PAST EPOCH
000
SAT.NO./SET NO.
059/120 369/018 503/016
k.k.6.3.3 Part 3
Part 3 contains the teletype heading with priority, station name, message
number classification, and current time.
k.k.6.3-h Part h
Part h contains the look angle schedule, sets of acquisition coordinates with
the following information:
1. Satellite number
2. Element number
3. Time in hours, minutes, and hundredths of minutes
h. Elevation in degrees
5. Azimuth in degrees
6. Range and range rate in nautical or CGS units
OBSERV
4 May 1964 4-132 TM-LX-123/000/00
SAMPLE PRINTOUT, OBSERV
PART 4, LOOK MGLE SCHEDULE
UNCLAS SPACETRACK 308 03l4.80 LOOK ANGLE SCHEDULE FOR POINT MUGU(FPS-l)
SAT ELB4 TIME ELEV AZMTH RANGE R-RAT] DAY 305 OI/II/63 (m)
369 18 1034.27 .9 58.1 1746 -I.5 369 18 1037.87 4.5 87.I 1569 -.0 369 18 1209.70 1.1 l6.1 1711 -3.5 369 18 1216.96 64.2 100.2 494 -.0 369 18 I349.OI 1.0 348.3 1713 -2.8 369 18 1354.70 14.8 296.3 1132 -.0 059 120 I.405.47 1.0 187.I 1966 -1.9 059 120 1411.18 7-2 147-3 1599 -.0
DAY 306 02/11/63 369 18 0102.21 10.8 266.5 1053 .0 503 16 0107.34 1.0 302.5 5962 -1.6 503 16 0147.65 67.6 130.2 1522 .0 503 16 0441.65 1.0 300.6 4265 -2.2 503 16 0501.24 10.4 230.0 2279 .0
PSR
4 May 1964 4-133 TM-LX-123/OOO/OO
4.4.7 POSITION SITUATION REPORT - PSR
4.4.7-1 Purpose
The PSR program computes satellite position information at a given time for
the Position Situation Report, and computes satellite status information at
a given time for the Satellite Situation Report.
4.4.7.2 Input - Schedule Tape Mode only (Toggle 24 On)
Deck Column Position Card Type Number Punch
1 Schedule Tape Card
2 Job Card
3 Remarks Card
4 Program ID Card
1-6 SPSJ0B
9-11 PSR
17 0 = Parameter card, I-file and E-file tape
inputs
18 0 = Hardcopy and TTY output
1 = Hardcopy output
80 J = Card type
5 Parameter Card (max. = 11 cards for Satellite Situation Report)
1 0 = Position Situation Report output
1 = Satellite Situation Report output
2 = Both reports output
2-3 Hour of report
4-5 Minutes of report
6 Z = Zulu time (CMT)
9-10 Day of month of report
12-14 Month of report
l6-19 Year of report
23 0 (or blank) = Suppress debris output in
Satellite Situation Report
1 = Output all satellite data in Satellite
Situation Report
-
PSR
k May 196k I+-I3I+ TM-IX-123/OOO/OO
Deck Column Position Card Type Number Punch
2k 0 (or blank) = Perigee and apogee in statute
miles in Position Situation Report
1 = Perigee and apogee in kilometers in
Position Situation Report
80 P = 1
6 End of Case • Card
7 End of Job Card
8 End of Schedule Tape Card
9 Blank ( :ard
.7. •3 Output
k.h.7.3.1 Position Situation Report
The printout of the Position Situation Report gives the following quantities:
1. Object name
2. Satellite number
3. Latitude in degrees
h. West longitude in degrees
5. Inclination in degrees
6. Period in minutes
7« Apogee and perigee in kilometers or statute miles (as specified on the
input parameter card)
8. Revolution number
9. T„, L^, Right Ascension^ for this revolution
10. Classification (blank if unclassified)
k.k.7.3.2 Satellite Situation Report
The printout of the Satellite Situation Report consists of the following
information:
Part 1 - Objects in orbit inclusive or exclusive of debris (option or
input parameter card)
PSR
h May 1961+ 4-135 IM-LX-123/OOO/OO
1. Time of report
2. Satellite name and code name
3 - Source
h. Launch date
5. Anomalistic period in minutes
6. Inclination in degrees
7. Apogee and perigee in statute miles
8. Transmitting frequency, if any
9. Comments from parameter cards
Part 2 - Objects removed from orbit
1. Satellite name and code name
2. Source
3. Launch date
k. Decay date
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SYSBULL
4 May 1964 4-137 TM-LX-123/OOO/OO
4.4.8 NOnAL SYSTEM BULLETIN - SYSBULL
4.4.8.1 Purpose
The SYSBULL program corrects the orbital parameters affecting the time equa-
tion which describes the motion of a given satellite, and computes an ephem-
eris of future satellite positions with respect to the equator and other
latitudes.
4.4.8.2 Input - Schedule Tape Mode (Toggle 24 On)
Deck Column Position Card IVpe Number Punch
1 Schedule Tape Card
2 Job Card
3 Remarks Card
4 Program ID Card
17-19 RUN
25-31 SYS3ULL
32-36 ,DATA
5 Parameter Card
2 0 = Har<
1 = Hardcopy and TTY output
11 0 = Use nodal period in element set
1 = Compute nodal period
6 Element Lead Card
8 7 = Card, type
7 Element Set Cards
NOTE: From 1 to 25 element sets are allowed; there must be one for each
Bulletin Request Card.
8 Bulletin Request Lead Card
8 8 = Card type
9 Bulletin Request Card (all numbers right justified)
1-3 Satellite number
4-6 Element Set Lumber (only if elements are non-
current)
SYSBULL
4 May 1964 I+-I38 TM-LX-123/OOO/OO
Deck Column Position Card Type Number Punch
NOTE: Cols. 7-10 are used only if the elements are to be corrected.
7 Order of the least-squares equation
8-9 Number of least-square points
10 0 = Time equation correction
1 = Right ascension equation correction
11-13 Number of corrected element set
14-18 Epoch revolution number of corrected element
set
NOTE: If cols. 11-18 are blank, no element set will be punched.
19-25 Perigee distance (earth radii), only if
q ± a(l-e)
26-30 Initial revolution number for test bulletin
31-35 Final revolution number for test bulletin
NOTE: If cols. 26-35 are blank, no test bulletin will be output.
36 0 = Previous bulletin reference message fr~
Part I output
1 = List elements for Part I output
37-39 Bulletin number for output
40-1+4 Initial revolution for Part II output
4^-49 Final revolution for Part II output
NOTE: If cols. 36-49 are blank, Bulletin Parts I and II will not be
output.
50 0 = No grid (part III) output
1 = Standard grid output
2 = Special grid output
51-55 Grid revolution number
56-57 Minimum special grid latitude
58-59 Maximum special grid latitude
60-6l Special grid latitude increments
62-65 Any special latitude (optional)
NOTE: Cols. 56-65 are blank unless a special grid is requested.
SYSBULL
4 May 1964 4-139 TM-IX-123/OOO/OO
Deck Column Position Card Type Number Punch
66-67 Last two digits of the year for which
computations are to be made
68 0 = Hardcopy output
1 = Hardcopy and TTY output
69 0 = Unclassified output
1 = Classified output
70-72 Analyst number (optional)
76-78 Day number (optional)
NOTE: The Element Lead, Element Set, Bulletin Request and Bulletin
Request Card sets may be repeated as often as desired.
10 Least Squares Point Card
0 1-10 Delta t (days) or delta right ascension
(degrees)
11-20 Number of revolutions from epoch
NOTE: There is one least squares point on each Least Squares Point card,
and the number of cards (points) appears in cols. 8-9 on the pre-
ceding Bulletin Request card.
11 Trailer Card (follows the last of the input sets)
8 9 = Card type
12 End of Date Card
13 End of Job Card
14 End of Schedule Tape Card
15 Blank Card
4.4.8.3 Output
The contents of output are determined by the bulletin request card and the
option card. Maximum printed output consists of least squares correction,
a test bulletin, the three parts of the edited bulletin, and an unedited
f ) bulletin.
SYSBULL
4 May 1964 4-140 TM-LX-123/OOO/OO
4.4.8.3-1 Least Squares Option
A. Time equation correction
1. T. time at the node in days
2» P j nodal period in days/rev
3. C, rate of change of period in days/rev
4. d, rate of change of c in days/rev
5. least squares points from input (^t , AN)
6. N by (N+l) matrix representing the normal equations of least
square fit where N is the order of the curve
7« Computed increments for AT,AP,AC, Ad
8. incremented elements
B. Right ascension correction
1. P n
2. c
3. ft, right ascension of ascending node in degrees
4. ft, first derivative of ft
5. ft/2, half of second derivative of ft
6. least square points ( A ft , A N )
7- N by (N+l) matrix
8. Computed increments for Aft, Afl, Aft/2
9. incremented elements
If a nodal u term was input, an anomalistic equation correction is output with
the following quantities:
1. four points of (T. _, A N) where T is time of perigee in days
2. a 4 x 5 normal matrix
3. computed anomalistic equation with T , P (anomalistic period), TT a
C (anomalistic c- term), d (anomalistic d-term) a 'a
k May 196k *-l*l
SYSBÜLL
TH-ÜC-123/OOO/OO
SAMPLE PRHTPOUT. SYSBULL
LEAST SjjMAhfcs SBUTiCii
SATELLITE 764 LEAST SQUARES. O.75O72O6O+O02 0.6121941*0-001 -0.10992000-005 0.00000000+000
-O.OOOO7OOOO 0.^ 0.007640000 *• ) 0.008200000 10. ( 0.010370000 14. > input points (&t , tfl) O.OIO690OOO 15. 0.011280000 16. < O.OI2I3OOOO i8.y
H x fo.70000000+001 0.82000000+002 0.11820000+004 0.17776000+005 0.60240000-001
(H+l) < Matrix
0.82000000+002 0.11820000+001* O.I7776OOO+OO5 0.27611400+006 0.85511000+000 0.11820000+004 0.17776000+003 O.276II40O+OO6 0.43943920+007 O.I269441O+OO2 0.17776000+005 0.276111*00+006 O.4394392O+OO7 0.71241042+008 O.19524863+OO3
-< D.6986U588-004 O.II549697-OO2 -0.40158214-004 O.7588068O-OO6 0.75071990+002 0.62371*1*10-001 -0.4l2574l4-004 O.7588068O-OO6— —corrected
SATELLITE 764 LEAST SQUARES FOR ANOMALISTIC EQUATION elements
76.0821*55730 -2. 76.3287883350 2. T n 76.759835050 9. T ' 77.375571930 19.
/ ro. 40000000+001 O.280OOOOO+OO2 O.45OOOOOO+OO3 O.7588OOOO+OO4 O.30654665+OO3 4 x 5 I 0.28000000+002 0.1*5000000+003 O.7588OOOO+OO4 O.1369140O+OO6 0.2l6l4670+004 Matrix 4 0.1* 5000000+003 O.7588OOOO+OOI* 0.13691400+006 0.25351^80+007 0.3VT59773+005
0.75880000+001* O.I36914OO+OO6 0.25351^80+007 O.4757745O+OO8 O.58667894+OO6
< ). 76205621+002 0.61581912-003 -O.2726485O-OO6 -O.96OI7II2-OO9
BXPLAHA'. PIONS:
T.inp ?;
N
1 ± Ö.75072060+002 I I0.61219440-OO1I [-0.10992000-005
±- 0.00000000+000
Line 14: AT, AP,
1! 3— I-0.69864588-004] 10.11549697-002 *t "±
-Q.40158gl4-Q04l I O.7588068O-OO6 1
Line 25:
1 O.76205621+OQ2 ] lo.6l58l912-003l I-0.27264850-0061 |-0.96017112-009)
SYSBULL
4 May 1964 h-lh2 IM-IX-12 3/000/00
4.1i.8.3,2 Test Bulletin Option
revolution number (REV)
time at node computed from updated elements in days (TN NEW)
time at node from original elements in days (TN OLD)
difference between new and old times (DELTA T)
right ascension of ascending node from updated elements in degrees (RAN NEW)
right ascension of ascending node from old elements in degrees (RAN OLD)
difference in right ascensions (DEL RA)
SAMPLE PRINTOUT, SYSBULL
TEST BULLETIN SAT NO. 764 ELEM 4.
tfEV TN NEW TN OLD DELTA T' RAN NEW RAN OLD DEL RA 53- 75*07199013 75.07206000 -0.00007 172.786 172.771 0.015 54. 75-134324o4 75.13327834 0.00105 172.841 172.826 0.015 55- 75.19657999 75.19449448 0.00209 172.896 172.881 0.015 56. 75-25876253 75.25570842 0.00305 172.951 172.936 0.015 57* 75-32087621 75.31692017 0.00396 173-006 172.991 0.015 58. 75.38292559 75.37812971 0.00480 173.06l 173.046 0.015 59* 75,44491522 75.43933707 0.00553 173-115 173.100 0.01s 60. 75.50684965 75.50054222 0,00631 173.170 173.155 0.015 61. 7-5.5687331+4 75.56174517 O.OO699 173.225 173-210 0.015 62. 75.63057114 75*62294592 O.OO763 173280 173.265 0.015 63. 75*69236729 75.68414448 0.00822 173-334 173.320 0.014 64. 75.75412646 75.74534083 0.00879 173.389 173.375 0.014 65. 75.81585320 75-80653499 0,00932 173.443 173.430 O.OI3 66. 75-87755205 75-86772695 O.OO983 173.498 173.485 0.013 67» 75.93922758 75.92891671 O.OIO3I 173.552 173-540 0.013 68. 760 OOO88I+33 75.99010438 0.01078 173607 173.594 0.012 69. 76.06252686 75-05128964 0.01124 173.661 173.649 0.012 70. 76.12415972 76.. J1247281 O.OII69 173-716 173-704 0.011 71» 76a8578746 76.:7365378 0 01213 173.770 173.759 0.011
SYSBULL
4 May 1964 4-143 TM-LX-12 3/000/00
4.4.8.3.3 Edited Bulletin Option
4.4.8.3.3.1 Part I
1. Bulletin number
2. Satellite name
3- Epoch revolution
4. Epoch time in days
5. Anomalistic period in days/rev, (Pa)
6. First and second derivatives of the period (c, d)
7. Semi-major axis in earth radii, (a)
8. Eccentricity, (e)
9. Right ascension of the ascending node in degrees (ft)
10. First derivative and one half of the second derivative of the
right ascension of the ascending node, (Cl, Ö/2)
11. Argument of perigee in degrees (<a)
12. First derivative and one half of the second derivative of argument of
perigee ((i>, UJ/2)
13. Mean longitude in degrees, (L)
14. Inclination in degrees, (i)
SAMPLE PRINTOUT, SYSBULL
EDITED BULLETIN, PART 1
Bulletin Epoch
J| SL Sat. Name
time
00i 00 \ BBBBBBBBBBBBBBB 764 BLTN 04 1964'-I2A// IN/3 PARTS./PART I.*
,071 76.I8579 O.O615819 -O.273-OO6 -O.96O-OO9 1.03227 O.OÖ541* /173-770 0.884 0.002 116.498 -4..229 -0.0007 186.87 95-70*
0 Q
Epoch Rev ff/2 ® © S/Z (L) ©
SYSBULL
( 4 May 1964 4-144 TM-LX-123/000/00
4.4.8.3*3-2 Part II = For each crossing of ascending node
1. Date
2. Revolution number (REV)
3. Time in hours, minutes, hundredths of minutes (TIME Z)
4. Longitude west in degrees
SAMPLE PRINTOUT, SYSBULL
EDITED BULLETIN, PART 2
PART II. S-N EQUATOR CROSSINGS.* REV TIME Z LONG W REV TIME Z LONG W REV TIME Z LONG W*
16 MAR 64* 071 0427-63 66.91 072 0556.27 89.10 073 0725.02 III.30* 074 0853.T8 133.49 075 1022.56 155.69 076 1151.37 177.90* 077 1320.21 200.12 078 1449.08 222>34 079 I618.OO 244.58* 080 1746.97 266.83 081 1916.01 289.09 082 2045.10 311-37* 083 2214.27 333-67 084 2343.51 355.99*
17 MAR 64* 085 0112.84 18.33 030 0242.26 40.69 087 0411.78 63.07* 088 0541.40 85.49 089 0711.13 107.93 090 0840.98 130.39*
4.4.8.3«3-3 Part III - For a grid revolution
Direction of crossing
Latitude in degrees
Time in minutes \ since crossing
West longitude in degrees / ascending node
Height above earth in kilometers
Visibility indicator
Argument of perigee
Latitude at perigee
Direction at perigee
SYSBULL
4 May 1964 4-145 TM-LX-123/OOO/OO
SAMPLE PRINTOUT, SYSBULL
EDITED BULLETIN, PART 3
PART III. REDUCTION TO OTHER LATITUDES AND HEIGHTS FOR REV 83. LAT MINUTES LONG HEIGHT LAT MINUTES LONG HEIGHT •
N PLUS OORR KILOM S PLUS CORR KILOM* SN 00 0,00 0.00 254.8 NS 00 44.16 191.04 210.4 SN 10 2.49 1.62 245.8 NS 10 46.62 192.66 220.8 SN 20 4.97 3.31 237.6 NS 20 49.09 19^-35 232.8 SN 30 IM 5.14 230.4 NS 30 51.58 196.18 245-9 SN 40 9<93 7.26 233.9 NS 40 54.08 198.30 259.6 SN 50 12.42 9.89 218.2 NS 50 56.60 200.94 273.1 SN 60 14.92 13.62 213.1 NS 60 59.15 204.68 285.6 SN 70 17 .*5 20.17 208.4 NS 70 61.75 211.25 296.5 SN 80 20.15 39<25 203.6V NS 80 64.52 230.35 305.3V
N PT 22.17 95.55 2OO.3V S PT 66.62 286.66 309.8V NS 80 2k, 20 151.84 197.2V SN 80 68.71 3^2.97 312.3V NS 70 26.88 170.92 193-7 SN 70 71.50 2.08 312.4 • NS 60 29.40 177*47 191.1 SN 60 74.11 8.65 309.4 NS 50 31.88 181.19 189.8 SN 50 76.68 12.39 303.9 NS 40 3^ 35 183.82 189.9 SN 40 79.23 15.04 296.4 NS 30 36.80 185.92 191.8 SN 30 81.76 17.16 287.5 NS 20 39.25 187-75 195.8 SN 20 84.28 19.01 277.9 NS 10 41.70 189.43 202.0 SN 10 86.79 20.70 268.0 NS 00 44.16 191.04 210.4 SN 00 89.24 22.32 258.4
GRID SATELLITE 764 ELEMENTS 4. REVOLUTION NO. 8 3. DAY NO, 76.93
ARG OF PERIGEE = 166.49824 + (-4.22911 ) X ( 76.92658 - 76.18579 ) = 113-36535 = 66.N GOING N-S.
SYSBULL
k May 1964 u-ike 1M-LX-12 3/000/00
4.4.8.3.4 Unedited Bulletin (not optional)
1. Revolution (REV)
2. Time at node in days (T SUB N)
3. Time at node in hours, minutes., hundredths of minutes (TIME Z)
4» Right ascension of ascending node in degrees (RA SUB N)
5. Longitude west in degrees (LONG)
SAMPLE PRINTOUT, SYSBULL
UNEDITED BULLETIN
UNEDITED BULLETIN NO, 04 SAT NO. 7 64 ELIM 4.
REV T SUB N TIME Z RA SUB N LONG 071 76ol&479 0427-53 173-77019 66.91 072 76.24741 0556.27 173-82524 89.10 073 76.30905 0725-02 173-88019 III.3O 074 76.37069 0853-78 173-93503 133-49 075 76.43234 1022.56 173.98978 155.69 076 76.49401 1151-37 17]+. 04444 177.90 077 76,55570 1320 21 176009900 200.12 078 76c61742 1449*08 174.15348 222.34 079 76 67917 1618.OO 174=20789 244.58 080 76.74096 1746.97 174.26221 266.83 081 76.80279 1916.01 174.31646 289.09 082 76.86466 2045.10 174.37064 311-37 083 76.92658 22 ,1427 174.42476 333.67 084 76.98855 2343-51 174 J\ 7882 355-99 085 77^05059 0112.84 174o5328l 18.33 086 77-11269 0242.26 174.58676 40.69 087 77-17485 0411-78 174.64065 63.08 088 77.23709 0541.40 17]i,69449 85.49 089 77 299J«o 0711.13 174.74829 IO7.93 090 77 36180 0840,98 174.80205 130.1*0
4.4.8.3.5 Punched Card Out pat Options
Punched card output consists of.
1. Seven and four-card element sets when an element update is made
2. Look angle request card when an edited bulletin is requested
(see section 4,4*5.1> card number 7«)
3« Edited bulletin when requested
XYZLA
h May 1964 k-lkl TM- DC-12 3/000/00
k.k.9 X, Y, Z, COORDINATES LOOK ANGLE REPORT - XYZLA
4.4.9-1 Pur pose
The XYZLA program computes sets of predicted acquisition coordinates for a
given satellite and specified sensors, using ephemeris data from the MUNENDC
or Interplanetary programs.
4.4.9.2 Input - Schedule Tape Mode (Toggle 24 On)
Deck Position Card Type
1 Schedule Tape Card
Job- Card
Remarks Card
Column Number Punch
Program ID Card
17-19
25-29
30-3^
Parameter Card
1-4
5-7
8-9
10-11
12-13
14-17
25-3*4
44
RUN
XYZLA
,DATA
Year of predictions
Day of the year
Hour of the day
Minutes of the hour
Seconds
Starting time of predictions (thousandths of a
second , col. 14 contains decimal point).
Maximum time increment or range for predictions,
in minutes from the starting time (Cols. lU-17).
If blank, computations will cover all input
ephemeris data.
0 - Ephemeris data input by cards
1 = Ephemeris data input by tape
XYZLA
4 May 1964 4-148 m- LX-12 3/000/00
Deck Position Card Type
Column Number Punch
45 0 = Compute all passes
1 = Compute only visible passes
46 0 = Positive elevations only acceptable
1 = Positive and negative elevations acceptable
47 1 = Output punched ephemeris cards
48 0 - Topocentric output
1 = Geocentric output (incl. day, time, right
ascension, declination and range)
49 0 ä Topocentric output plus right ascension
1 = Topocentric output plus hour angle
6 Sensor Card
7 Satellite ID Card (required only when using ephemeris cards input)
l-l6 Satellite name (alphanumeric)
8 Ephemeris Card (optional)
1-12 x geocentric coordinate (in earth radii)
13-24 y geocentric coordinate (in earth radii)
25-36 2 geocentric coordinate (in earth radii)
37-48 x geocentric coordinate
I49-6O y geocentric coordinate
61-72 z geocentric coordinate
73-^0 Time increment (min.. ), from the starting time
of predictions (parameter card, Cols. 1.4-17)
NOTE: Ephemeris cards are ordered hy increasing time increment.
9 Blank Card (required for each tape or card input set)
10 Blank Card (required only i'or each card input set)
11 >1nd of Data Card
12 End of Job Card
13 End of Schedule Tape Card
14 Blank Card
XYZLA
4 May 1964 4-149 (Page 4-150 Blank)
TM-LX-123/OOO/OO
4.4.9.3 Output
The basic printout of this program is a schedule of predicted look angles for
a particular station at specific times. The quantities printed are:
1. Satellite name
2. Station name
3. Data
a. Day of year, hour, minute, and fraction of minute of the search
point.
b. Predicted right ascension, declination, azimuth, and elevation
in degrees.
c. Predicted slant range in kilometers.
d. Elevation and illumination angles of the sun.
SAMPLE PRINTOUT, XYZLA.
640402 VENUS *
LOOK ANGLES FOR BMEWS 3 FYLNGDALE*
DAY TIME Z
93 1124.73 93 1204.73 93 1244.7^ 93 1324.73 93 140*4.73
93 1444.73 93 1524.73 93 1604.73 93 1644.73 93 1724.73 93 1804.73 93 1844.73 93 1924.73 93 2004.73 93 2044.73 93 2124.73 93 2204.73
R.A. DEG 87.IH 87.19^ 87.225 87.215 87.175 87.113 87.037 86.954 86.870 86,791 86.721 86.664 86.623 86.600 86.596 86.612 86.647
DEC DEG. -1.045 -1.408
-I.725 -2.OO6 -2,254 -2.^76 -2.674 -2.853 -'.013 -3.158 -3.289 -3.408 -3.516 -3.615 -3.705 -3.788 -3.865
AZIM ANG. 94.060
102.422 111.020 120.007 129.520 139-665 150.478 I6I.896 173.731 I85.688 197.441 208.711 219.330 229.253 238.530 247.273 255.626
ELEV ANG. 1.620 7.053
12.362 17.397 21.995 25.978 29.160 31.366 32.450 32.335 31.024 28.605 25.221 21.043 16.244 10.984 5.406
RANGE KM. I28967 I38587 148121 157603 I67063 176524 186010 195536 205116 214758 224467 234243 244081 253977 263918 273892 283884
SUNS ELEV 39-9 40.7 40.1 38.2 35-2 31.2 26.6 21.4
15.9 10.2 4.4
-1.3 -6.9
-12.3 -17.2 -21.6 -25.2
ILLUMI NATION 103.5* 103.4*
103.3* 103.3* 103.3* 103.2* 103.2* 103.2* 103.2* 103.1* 103.1* 103.1* 103.1* 103.1* 103.1* 103.1* 103.1*
t
r
«:
4 May 1964 4-151 - TM-UC-123/OOO/OO (Page 4-152 Blank)
4.4.10 OTHER
The following programs in the Observation Acquisition area are seldom used by
the analyst. A brief description of each program is given.
4.4.10.1 ORPS
The ORPS program is used for predicting search times for observing satellites
at a given sensor. The program first computes the X,Y,Z search point coordinates
of a satellite, then computes the right ascension,, declination, azimuth, eleva-
tion, and slant range from these points in the same manner as the XYZIA program.
4.4.10.2 POSE
The POSE program computes a search ephemeris for a given station and a given
point in space. The program is used when a sensor detects an unknown object.
The assumption is made that if the object is a satellite it will come close to
the same point in inertial space on the next revolution. Therefore, the look
angles are calculated for the time, which is equal to the observation time
plus the smallest orbital period expected. If the point is visible at the
station, the quantities are written on the output tape,
The orbital time is then updated by a specified time increment and compared to
the largest orbital period expected. If this period is within limits, the
search ephemeris is computed for this new time.
4.4.10.3 PREPRINT
'The purpose of PREPRINT is to supply the subsatellite point and related data
of all satellites at a specified time.. The west longitude and time of the
last ascending node are also computed for each satellite. The following
information is contained in the output,
a. Satellite name; number and element set number
b. Latitude and west longitude at report time
c. Inclination a»~d period
d. Apogee and perigee
e. Eccentricity and height
f. Revolution number and time of ascending node, right ascension and
longitude of the node,
h May 1964 4-153 ^ üM-LX-123/OOO/OO (Page \-Y)k Blank)
4.5 INTERPLANETARY AREA
This section includes the interplanetary programs (HELIO, MUNENDC and NEAR)
HEL.K
4 May 1964 4-155 TM-LX-12 3/000/00
4.5.I HELIOCENTRIC - HELIO
4.5-1-1 Purpose
The HELIO program computes the heliocentric trajectory of a satellite given
the launch and target points, the launch date and the flight time.
4.5.1.2 Input - Schedule Tape Mode (Toggle 24 On)
Deck Position Card tyPe
Column Number Punch
1 Schedule Tape Card
2 Job Sard
3 Remarks Card
4 Prog ram ID Card
3-7-19
25-29
30-34
RUN
HELIO
,DATA
5
5-6
10-11
13-14
16-17
01 - Card number
Year of launch
Month of launch
Day of launch
6
5-6
10-17
02 = Card number
Name of launch planet
7
5-6
10-17
03 = Card number
Name of target planet
8
5-6
10-13
use COMET)
04 = Card number
xx.x (Days) = Time of launch increment
•
HELIO
k May 1964 4-156 IM-LX-123/OOO/OO
Deck Column Position Card Type Number Punch
9
10
11
12
13
Ik
15
16
5-6 05 = Card number
10-13 Number of time-of-launch increments
5-6 u6 = Card number
10-14 xxx.x (Days) = Initial time of flight
5-6 07 = Card number
10-13 xxx.x (Days) = Time of flight increment
5-6 08 = Card number
10-13 Number of transit time increments
5-6 09 = Card number
10 0 = Initial value of sigma only
1 = Long coast time only
2 = Short coast time only
3 = Short and long coast times
5-6 10 = Card number
10-l6 xxx.xxx = Initial sigma value
5-6 11 = Card number
10-15 xx.xxx = Sigma increment
5-6 12 = Card number
10-11 Number of sigma increments
KELIO
c h May 1964 4-157 QM-LX-123/OOO/OO
Deck Column Position Card type Number Punch
17
5-6 13 = Card number
10-18 xxxxx.xxx (km.) = The perifocal distance of
the escape hyperbola taken
equal co the earth-centered
radius of the parking orbit.
18
19
5-6 lk = Card number
10-16 9.0E+37 (km.) = Crossover factor in millions
5-6 15 = Card number
;.0 0, Blank = Standard output
1 = Special output - ephemeris tape (Logical 7),
hard copy of X Y and Z geocentric coordinates
of the probe (earth radii) and X, Y, and Z
heliocentric equatorial coordinates (A.U.)
2 = Same as Option 1 except: heliocentric
coordinates are ecliptic, not equatorial
9 = Same as Option 1 plus: separation distance
between target and present position on the
transfer ellipse, and additional values
describing the transfer ellipse and escape
hyperbola
12-l4 xxx - Start time (days past injection)
l6-17 xx = Start time (hrs. past injection)
19-20 xx = Start time (min. past injection)
22-24 xxx = Stop time (days past injection)
26-27 xx = Stop time (hrs. past injection)
29-3° xx = Stop time (min. past injection)
32-35 xxxx = Time interval (min.) between position
computations
HELIO
4 May 1964 4-158 TM-IX-123/OOO/OO
Deck Position Card Type
20
Column Numbe- Punch
37-38 xx B Launch date year (of selected transfer
conic)
40-4l xx = Launch date month (of selected transfer
conic)
43-44 xx = Launch date day (of selected transfer
conic)
46-50 xxx.x = Time of flight (days) of selected
transfer conic
52 1 = Long coast time
2 = Short coast time
54-57 xxxx = Maximum number of iterations (OOOO-
9999) which the program will go through
in calculating the eccentric anomaly
for the present position on the hyper-
bola; if blank, the program assumes 200
5-6 15 = Card number
10-16 XXX. XXX ">
18-24 XXX.XXX
26-32 XXX.XXX
34-4o xxx*xxx C
42-48 XXX.XXX >
50-56 XXX-XXX p
58-64 XXX.XXX
66-72 XXX.XXX
Selected azimuths to be
processed up to a max. = 8
HLLIO
4 May 1964 4-159 TM-LX-123/OOO/OO
Deck Column Position Card Type Number Punch
17 X
25 X
33 X
4l X
^9 X
57 X
65 X
73 X
21
5-6 17 = 10-18 zxxx.
22
23
24
One of these columns must contain
an "E" to indicate the last
azimuth on the card
True anomaly in the
hyperbolic orbit at
injection
5-6 l8 = Card numbc••-
10-l8 xxxxx.xxx (sec.) = Time from launch to
parking-orbit injection
5-6 19 = Card number
10-18 xxxxx.xxx (sec.) = Time of final burn
5-6 20 = Card number
10-18 xxxx.xxxx = The arc subtended at earth's
center during ascent from launch
to parking orbit
—<"-**«*«**• -rm
HELIO
4 May 1964 4-160 IM-LX-I23/OOO/OO
Deck Column Position Card Type Number Punch
25
26
27
28
5-6 21 = Card number
10-18 xxxx.xxxx - The arc subtended at earth's
center during final burn out of
the parking orbit to injection
5-6 22 = Card number
10-18 xxxxx.xxx (sec./deg.) = The inverse parking
orbital rate
5-6 23 = Card number 0
10-l8 xxxx.xxxx = Longitude of launch site
5-6 24 = Card number
10-18 xxxx.xxxx0 m Latitude of launch site
23-24 03 = This is last card in deck
Blank = This is not last card in deck
NOTE: Cards numbered 25-36 will only be used when Card 3 has been designated
as a COMET in cols. 10-18. Otherwise, Card number 24 is the last
card in the deck.
29
5-6 25 = Card number
10-24 .xxxxxxxxxxxxxx (km. /sec. ) = Mean gravitation
of the target body
I k May 1964 k-l6l
HELIO
IM-LX-I23/OOO/OO
•
Deck Position Card Type
30
31
32
33
3^
3r;
Column Number Punch
5-6 26 = Card number
10-l8 xx.xxxxxx (A.U.) = Semi major axis of
target body
5-6 27 - ?ard number
10-l6 .xxxx^.x - Eccentricity of target body
5-6 28 = Card number
10-17 x.xxxxxx (yr.) = Time change from 1950.0 to
present date, for eccentricity
(may be zero)
5-6 29 = Card number
10-l8 xx.xxxxxx = Inclination to the ecliptic of
the orbit of the target body
c-6 J'
10-17
5-6
10-19
30 = Card number
x.xxxxxx (yr.) = Time change from 1950.0 to
present date, for inclination
(may be zero)
31 = Card number Q
xxx.xxxxxx = Longitude of ascending node of
the target body
HELIO
h May 196-' 4-162 m-ix-12 3/000/00
Deck Position Card Type
36
37
38
39
ko
Column Number Punch
41
42
43
5-6
10-17
32 = Card number
xx.xxxxx (yr.) = Time change, from 1950.0 to
present date, for node
(may be zero)
5-6 33 - Card number Q
10-19 xxx.xxxxxx = Argument of perihelion for the
target body
5-6 34 ~ Card number
10-17 xx.xxxxx (yr.) = Time change, from 1950.0 to
present date, of perihelion
5-6 35 = Card number
10-l8 xxxxxxx.x (Julian) - Date of perihelion passage
of target body minus 2430000
5-6 36 = Card number
10-14 COMET
23-24 03 s This is last ':ard in de
End of Data Card
End of Job Card
End of Schedule Tape Card
Blank Card
HEUO
4 May 1964 4-163 m-LX-123/OOO/OO
4.5.I.3 Output
The normal program printout contains four parts. A special output option
also may be included.
4.5.I.3.I Part .1 - Input Conditions
This section contains the following quantities:
1. Greenwich hour angle in degrees (GHA)
2. Perifocal distance of the escape hyperbola in km. (PER)
3. True anomaly in the hyperbolic orbit at injection (TA)
4. Launch site latitude in degrees (LAA)
5. Launch site longitude in degrees (LOL)
6. Time from launch to parking orbit injection in seconds (T02)
7. Final stage burning time in seconds (T23)
8. Angle subtended at earth's center between launch and parking orbit
injection in degrees (P02)
9. Angle subtended at earth's center during final stsge burning (P23)
10. Inverse orbital rate during parking orbit coasting in seconds per
degree (ORB)
11. Crossover distance in millions of km. (RS)
12. A.U. to million km. conversion factor (A.U.)
13. Gravitation constant for launch planet, km /sec. (GML)
1<+. Gravitation constant for target planet, km /sec. (GMT)
4. -, 1.3' 2 Part 2 - tfel ioct ntr ic Con ic Group
The second part of the printout contains the following quantities:
1. Flight time in days (TF)
2. Pun-to~launch-pl*inet distance at launch time in A.U. (RL)
3. Sun-to-arr:val-planet distance at arrival time in A.U. (RP)
4. Heliocentric central angle in degrees (HGA)
5. Semi-major axis of transfer ellipse in A.U. (SMA)
6. Eccentricity of transfer ellipse (ECC)
7« Communication distance at arrival in millions of km. (RC)
HELIO
k May 1964 k-1.6k TM-LX-123/OOC/OO
8. True anomaly in transfer ellipse at launch time in degrees (TAL)
9- True anomaly in transfer ellipse at arrival time in degrees (TAP)
10. Inclination angle of transfer ellipse to ecliptic plane in degrees (INC)
11. Celestial latitude at launch time in degrees (LAL)
12. Celestial latitude at arrival time in degrees (LAP)
13» Celestial longitude at launch time in degrees (LOL)
lh. Celestial longitude at arrival time in degrees (LOP)
15 Speed at launch time in km-/sec. (VL)
16. Path angle at arrival time in degrees (GAL)
17 Speed at arrival time in km./sec. (VP)
18. Path angle at arrival time in degrees (GAP)
19. Launch-placet speed at launch time in km./sec (Vl)
20. Arrival-planet speed at arrival time in km./sec - (V2)
21. Departure angle at launch time in degrees (DA) 9
22. Arrival angle at arrival time in degrees (AA)
23. Angle between launch hyperbolic excess velocity vector and launch
planets orbital plane in degrees (GL)
2h. Angle between launch hyperbolic excess velocity vector and arrival
planets orbital plane in decrees (GP)
25. Sun-target planet-probe angle (Zeta P) in degrees (ZAP)
2.6* Sun-launch planet-probe angle (Zeta L) in degrees (ZAL)
27 Sun-launch planet-target planet angle (Eta) in degrees (ETA)
28. Distance of periapsis in km (RCA)
29- Distance of apoapsis in km. (APO)
30* Period in days for the transfer ellipse (PRD)
31. Time of last theoretical perihelion passage (TAU)
32. Longitude of ascending n_>de of transfer ellipse in degrees (LAN)
33. Argument of perihelion of transfer ellipse in degrees (AOP)
HELIO
k May 1964 h-165 m- ix-12 3/000/00
k.5-1.3-3 Part 3 - Planetocentric Conic Group
lie third part of the printout contains the following quantities:
Hyperbolic excess speed at launch in km./sec- (VHL)
Declination of launch asymptote in degrees (DLA)
Right ascension of launch asymptote in degrees (RAL)
Hyperbolic excess speed at arrival in degrees (VPL)
Declination and right ascension of arrival asymptote in degrees (DPA,RAP)
1
2
3
k
5
6
7
8
9
10
11
12
2 2 Twice the total energy or vis viva in km. /sec. (C3)
Eccentricity (ECC)
Distance from launch planets center at injection in km. (RAD)
Injection speed in km./sec. (VEL)
Injection path angle in degrees (PTH)
Component of unit impact parameter in (T Bar) and (R Bar) directions (BT,BR)
Component in T and R directions of impact parameter in km. (B.T, B.R.)
k.^.l.^.k Part k - Launch to Injection Conditions Group
The fourth part of tM printout is composed of the following quantities:
1. Launch azimuth in degrees (LAZ)
2„ Launch time in seconds past midnight of launch day (TL)
3. Injection time in seconds past midnight of launch day (Tl)
k* Injection declination, right ascension, and launch azimuth in degrees
(DEC, RA, AZ)
5. Parking orbit coast time in seconds (CST)
6. Time fvom launch to injection in seconds (TLI)
7. Angle between injection and the outgoing launch asymptote in degrees (CA)
8. Injection longitude in degrees (LON)
9. Latitude and longitude at start of final burning in degrees (LA2, L02)
10. Launch, and injection times in hours, minutes and seconds (TL, Tl)
HELIO
h May 19& h-l66 TM-LX-123/OOO/üO
4.5«1•3•5 Part 5 - Geocentric and Heliocentric Position and Time
The part of the program printout is optional (see input parameters) and
contains the following data:
1. Start time - year, day of year, month, day, seconds, and hundredths of
seconds
2. For each position:
a. Time in day of year, hours, minutes, seconds (TTME)
b. Time in minutes relative to start time (DELTAT)
c. x,y,z geocentric position of probe in earth radii (GEO)
d. x,y,z heliocentric position in A.Ü. (HELIO)
3. Position and velocity components of injection point vector
(X, Y, Z, XDOT, YDOT, ZDOT)
•-
n
SAM
PLE
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19
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1858.5
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L
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96
2
INPU
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DIT
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S G
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290.3
98
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101.6
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9.5
99
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PER
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GM
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65
64
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13
3
98
60
3.1
99
TA
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G
MT
3.7
00
8.2
40
3
24
12
3.6
68
LA
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OR
B 28.3
17
1
4.6
89
0
LO
L
RS
279.4
57
0
. T
02
49
8.8
78
HE
LIO
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NT
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CO
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T
F
149.0
0
RC
52
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3
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289.9
65
V
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964
Z
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50
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PRD
2
92.8
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RL
T
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L
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ZA
L
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1
59
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1
91.9
23
35.2
066
52.9
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7
1.1
78
RP
T
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V
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DA
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TA
LA
N
EA
RT
H
0.7
19
51
3
21
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7
26
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45
134.7
88
33.6
65
289.9
70
TO
HC
A
INC
G
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A
A
RC
A
AO
P
VEN
US
16
1.9
36
2
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4.7
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67.4
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1
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20
0.0
94
SMA
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204
22.1
85
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54
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1
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LA
P G
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GP
0.1
95369
0.9
23
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4
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5
PLA
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B
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37
1.2
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RA
L
RA
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243.0
65
6
57
1.6
6
-I6772.I
VP
L
VE
L
B.S
6.0
07
3
II.6
36
3
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DPA
PT
H
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2
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2
RA
P 218.9
85
LAUN
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INJE
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CO
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LAZ
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0.0
00
T
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C
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41
28
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T
LI
4
72
8.9
9
TL
2
020
10
TI
CA
T
I
77939.5
140.5
55
2138
59
DE
C
LON
16.3
55
2
02
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8
RA
L
A2
98.7
33
12.9
42
A
Z
L02
66.5
58
195.3
69
r 8
8
9
SAM
PLE
PR
INT
OU
T,
HE
LIO
O
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(IN E
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1H
RA
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AR
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PER
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X
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45
Y
0.
5503
97
Z
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897
XDOT
-
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3499
45
1962
1942
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9.45
3
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84
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29
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6319
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0091
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6355
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0.3
6041
732
TIM
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ELTA
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194
21
38
59
0.
195
3
38
59
36O
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195
9
28
59
720.0
195
15
38
59
10
80
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195
23
38
59
14
40
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195
5
38
59
1800.0
• 8 Y
GEO
Z
GE
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XH
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Y
HE
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ZH
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0.9
74395
0.2
94229
5
4.0
59
90
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6.5
46
80
80
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5
4.5
84
58
91
30
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f IS 8
MUNENDC
4 May 1964 4-169 •M-LX-^/OOO/OC
4. 5.2 UNIFIED ENCKE WITH DIFFERENTIAL CORRECTION - MUNENDC
U.5.2.1 Purpose
The MUNENDC program computes a satellite's predicted position and velocity
with respect to the Earth, Moon and Sun for specified time intervals given
the satellite's position and velocity at a starting time.
4.5.2.2 Input - Schedule Tape Mode (Toggle 24 On)
Deck Column Position Card Type Number Punch
1
2
3
4
Schedule Tape Card
Job Card
Remarks Card
Program ID Card
17-19
25-31
32-36
Parameter Card 1
1-4
5-6
7-8
9-10
11-12
13-18
25-40
Parameter Card 2
1-12
13-24
25-36
RUN
MUNENLC
,DATA
Year of epoch
Month of epoch
Day of epoch
Hour of epoch
Minutes of epoch
xx.xxx = Seconds of epoch
Satellite name
x geocentric coordinate of initial position
(in ea: t) radii)
y geocentric coordinate of initial position
(in earth radii)
z geocentric coordinate of initial position
(in earth radii)
MUNENDC
4 May 1964 4-170 TM-LX-I23/OOO/OO
Deck Position Card Type
Column Number Punch
37-^8 x geocentric coordinate of initial velocity
(in earth radii/k min.) \ / e /
49-60 y geocentric coordinate of initial velocity
(in earth radii/k min.)
6l-72 z geocentric coordinate of initial velocity
(in earth radii/k 1 min.)
NOTE: All quantities on this card are given in floating point format =
+XXXXXXXX+XX. The decimal point is assumed at the right of the
mantissa.
7 Parameter Card 3
1-10
11-20
21-24
25-26
27-28
29-30
31-32
33-38
39-^2
43-44
45-46
i*7-48
49-50
51-^6
57-67
68
69
70
Runge-Kutta error criterion for position
Runge-Kutta error criterion for velocity
Year of initial time of ephemeris
Month of initial time of ephemeris
Day of initial time of ephemeris
Hours of initial time of ephemeris
Minutes of initial time of ephemeris
xx.xxx = Seconds of initial time of ephemeris
Year of final time of ephemeris
Month of final time of ephemeris
Day of final time of ephemeris
Hours of final time of ephemeris
Minutes of final time of ephemeris
xx.xxx - Seconds of final time of ephemeris
Initial integration step size, At (min.),
(decimal anywhere in field)
0 - variable At
1 = fixed At
0 e Do not print moon satellite number
1 = Print moon satellite number
0 = Print every 42 lines
-
MUNENDC
h May 1964 4-171 TM-LX-123/OOO/OO
Deck Column Position Card Type Number Punch
8 Parameter Card 4 _ ***
1 0 = Do not correct Encke element M o
1 = Correct Encke element M o
2 0 = Do not correct Encke element l/a
1 = Correct Encke element l/a
3 0 = Do not correct Encke element c*
1 = Correct Encke element c*
4 0 = Do not correct Encke element s*
1 = Correct Encke element s*
5 0 = Do not correct Encke element a*
1 = Correct Encke element a*
6 0 = Do not correct Encke element 6*
1 = Correct Encke element 6*
20 Correction iteration (any number from 1 to 9)
25-30 Absolute maximum of observation residuals in kms.
31-36 Absolute maximum of range rate residuals in km/sec
37-40 Rejection parameter.
9 Observation Cards
10 End Card
11 Sensor Cards
12 End Card
13 2nd of Data Card
14 End of Job Card
15 End of Schedule Tape C;.rd
16 Blank Card
4.5.2.3 Output
The printed output for MUNENDC contains two parts.
4.S.2.3.1 Part 1, Ephemeris Output
4.5.2.3.I.I Page 1
The quantities printed on Page 1 are:
.'. t (TIME SUB 0)
c'. displacement error (DISPLACE ERROR)
MUNENDC
4 May 1964 4-172 TM-LX-123/OOO/OO
3. displacement rate error (DIS.RATE ERROR)
4. A t (DELTA TIME)
5. semi-latus rectum (PARAMETER)
6. e (ECCENTRICITY)
7. q., perifocal distance (Q)
8. K (M-O-TILDE)
9. l/a (ONE OVER A)
10- P components (PX; FY,, PZ)
11. ^components (QX-TILDE,QY-TILDE,QZ-TILDE)
12. Time (TIME)
13» x>y> an^ z components of position displacement from the
reference orbit (XSI, ETA, ZETA)
14. x,y, and z components of velocity displacement from the
reference velocity (LAMDA, OMEGA, PSI)
15. first 12 points from lunar and solar ephemerides tapes.
I+.5.2.3.I.2 Page 2
The quantities on this page are a printout of the elements identical to Page
1. Since the first page appears only after initialization, this page is
necessary to show the elements after rectification.
4.5.2.3.1.3 Pages 3 and 4
These pages describe the first two time points of the ephemeris. The
items printed are:
1. geocentric position, velocity, and distance for the reference orbit
2. same for the vehicle in its actual trajectory
3« geocentric position vectors of the moon and the sun
4. position vectors and dista'.jes of the moon and the sur. iron; the vehicle
5- position and velocity deviations from the reference orbit
6. magnitude, radial, and tangential components of the velocity vector;
1,fcie time interval
7- perturbative accelerations; distance of the vehicle above earth's
equator; other intermediate quantities
. •
MUNHIDC
4 May 1964 4-173 TM-LX-123/OOO/OO
8. position and velocity of the actual vehicle from the earth in
laboratory units.
At the point of closest approach to the moon the full page output will again
be printed for that point. The comment "THIS PAGE CONTAINS A POINT OF
CLOSEST APPROACH TO THE MOON" is printed at the bottom of the page.
At the point at which rectification occurs the full page output appears
twice. The first page will have the points before rectification. The
comment "THIS IS THE POINT AT WHICH RECTIFICATION OCCURS" will appear at
the bottom of the page. The second full page printout will be the first
point of the new reference orbit.
This type of output will also be given after 42 or 10 integration steps
(input option).
1+.5.2.3.1.4 Page 5 and 6
For the remainder of the ephemeris computation, only one line per time
point is given containing:
1. time (TIME)
2. geocentric coordinates of position (X,Y,Z EARTH-ROCK, G-RADIl)
3. coordinates of velocity (X,Y,Z DOT ER)
4. geocentric distance (R EARTH-ROCK, G-RADIl)
If the option to print moon-satellite coordinates is used, the next page will
be one line per point consisting of:
1. time (TIME)
2. coordinates of moon-satellite position (X,Y,Z MOON-ROCKET, G-RADIl)
3- coordinates of sun-satellite position (X,Y,Z SUN-ROCKET, G-TADIl)
4. distance of object from moon (R MOON-ROCKET, G-RADIl)
MUHENEC
h May 19Ö* k-nk 34-UC-123/000/00
1
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-175
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IM-LX-123, 000, 00
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k May 196U U1T6 TM-rjc-12 3/000/00
a 4. a
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MUNENDC
k May 196k 4-177 TM-lÄ-323/OOO/OO (Page U-I78 Blank)
4.5.2,3.2 Fart 2, Differential Correction Output (not currently used)
1*.5.2.3.2.1 Section 1
This section contains the residuals printed in tabular form. The quantities
are:
1. sensor (STAT)
2. time (TIME)
3- range residual (RHO RES1D)
h> range rate residual (RODOT RESID)
5- right ascension residual (R.A. RESID)
6. declination residual (DECL RESID)
1, azimuth residual (AZIM RESID)
8. elevation residual (ELEV RESID)
An asterisk appears next to residuals which are rejected.
k.5«2.3.2.2 Section 2
This section contains corrections made to auxiliary quantities which are
translated by +he program to element corrections;
1. RMS value of residuals in position (SUM)
2. AM (DEL M-O-TIL)
3o A (l/a) (DELTA I/A)
h, Ac* (DELTA C*)
5. Ls* (DELTA 3")
6. Aa* (DELTA ALP'IA*)
7. A6* (DELT DELTA*)
1+.5.2.3.2.3 Secti_cn_^
This section contains the corrected elements and the position and velocity
coordinates (at t ) listed as fellows:
1. M (M-0-TLLDE)
2. l/a (ONE OVEP A)
3. P components (?X,PY,PZ)
h. Q components (QX-TILDE. QJC-TILDE, QZ-TILDE)
NEAR
4 May 1964 4-179 W4-LX-123/000/00
4.5.3 NEAR-EARTH CONIC - NEAR
4.5* 3*1 Purpose
The NEAR program computes possible trajectories for lunar flights and other
missions in which the probe remains within the Earth's sphere of influence-.
The powered flight phases are based on a configuration involving an initial
burn time, a circular intermediate parking orbit coasting phase and a final
burn time terminating in injection into the transfer conic. The transfer
conic solutions include escape trajectories of both elliptical and hyper-
bolic form depending upon the magnitude of the energy expended during the
final burning stage.
Given launch point, launch azimuth and arrival date, the program computes
launch time, injection point into the transfer conic, time of flight,
coast time and other trajectory properties.
4.5.3.2 Input - Schedule Tape Mode (Toggle 24 On)
Deck Column Posit ion Card Type
Schedule Tape
Number
Card
Punch
1
2 Job Card
3 Remarks Card
4 Program ID Card
17-19 RUN
25-31 NEARBBA
32-36 ,DATA
Deck Scaling Column Posit ion Factor Number Punch
5 F2.0 5-6 01 = Ca
F2.0 10-11 Last 2 digits of year of launch (optional)
F2.0 13-14 Month of launch (optional)
F2.0 16-17 Day of launch (optional)
NEAR
4 May 1964 4-180 TM-LX-123/OOO/OO
Deck Scaling Column Position Factor Number Punch
F2.0 5-6 02 = Card number
F2.0 10-11 Last 2 digits of year of arrival
F2.0 13-14 Month of arrival (optional)
F2.0 16-17 Day of arrival (optional)
F2.0 5-6 03 = Card number
F2.0 10-11 Time of flight (optional)
12 13-14 Number of arrival dates (optional)
F3-0 l6-l8 Minimum allowable coast time (optional)
F2.0 5-6 04 = Card number
F6.2 10-15 Initial launch azimuth
F5-1 17-21 Perigee distance (km.) (optional) (if given,
the program will compute eccentricity)
05 = Card number
Azimuth increment
Azimuth used to compute the energy term
(optional) (if 7777-, program assumes = 102 )
10
F2.0 5-6
F3.1 10-12
F5.1 14-18
F2.0 5-6
12 10-11
11 13
06 = Card number
NUsibcr of azimuth increments
1 = Use short coast time
2 = Use long coast time
3 = Use both coast times
F8.2 15-22 Distance from earth's center to injection into
transfer conic (meters) (optional) <
h May 196U 4-181
NEAR
TM-LX-12 3/000/00
Deck Scaling Position Factor
11
12
13
Ik
15
16
IT
F2.0
FT- k
F2.0
F8.3
F2.0
F8.3
F2.0
T8.h
F2.0
F8.1+
F2.0
F9.6
F2.0
FU.O
F2.0
F^.2
Column Number Punch
5-6 OT = Card number
10-l6 Angle between perigee and injection
5-6 08 = Card number
10-lT Time from launch to injection
5-6 09 = Card number
10-lT Time during final burn
5-6 10 = Card number
10-lT Angle from launch to injection into parking
orbit
5-6 11 = Card number
10-lT Angle made during final burn
5-6 12 = Card number
10-18 Inverse parking orbital rate (sec./deg.)
5-6 13 = Card number
10-13 Longitude of launch point (deg.)
15-l6 Longitude of launch point (min.)
18-21 Longitude of launch point (sec.)
NEAR
4 May 1964 4-l82 IM-LX-123/OOO/OO
Deck Scaling Column Position Factor Number Punch
16
19
20
21
F2.0
F4.0
F2.0
F4.2
F2.0
F3.0
F2.0
F4.2
F2.0
F3-0
5-6 14 = Card number
10-13 Latitude of launch point (deg.)
15-l6 Latitude of launch point (min.)
18-21 Latitude of launch point (sec.)
5-6 15 = Card number
10-12 Lunar longitude (deg.) (optional)
14-15 Lunar longitude (min.) (optional)
17-20 Lunar longitude (sec.) (optional)
5-6 l6 = Card number
10-12 Declination of outgoing asymptote (deg.)
(optional)
F2.0 14-15 Declination of outgoing asymptote (min.)
(optional)
F4.2 17-20 Declination of outgoing asymptote (sec.)
(optional)
F2.0 5-6 17 = Card number
F3.0 10-12 Greenwich hour angle at launch (deg.)
(optional)
F2.0 14-15 Greenwich hour angle at launch (min.)
(optional)
F4.2 17-20 Greenwich hour angle at launch (sec.)
(optional)
I k May 196k ^-183 TM-LX-123/OOO/OO
Deck Scaling Column Position Factor Number Punch
22
23
2k
F2.0 5-6 l8 = Card number
F2.0 10-11 Right ascension of outgoing asymptote
(hrs.) (optional)
F2.0 13-lU Right ascension of outgoing asymptote
(min.) (optional)
FU.2 16-19 Right ascension of outgoing asymptote
(sec.) (optional)
F2.0 5-6 19 = Card number
FT.6 10-l6 X-component of outgoing asymptote (optional)
F2.0 5-6 20 = Card number
FT-6 10-l6 Y-component of outgoing asymptote (optional)
25
F2.0 5-6 21 *s Curd number
FT.6 10-l6 Z-component of outgoing asymptote (optional)
NOTE: If the declination and righc ascension of the outgoing asymptote
are given, the X-, Y- and Z-components will be computed.
26
2T
F2.0 5-6 22 = Card number
F9-T 10-18 Energy term (km. /sec. ) (optional) (if TTTTT.,
the program will compute this value)
F2.0 5-6 23 = Card number
F6.6 10-15 Eccentricity (optional) (program computes
this if perigee distance is given)
NEAR
KEAR
k May 196h 4-184 TM-LX-123/000/00
Deck Scaling Column Position Factor Number Punch
28
F2.0 5-6 2k = Card number
F7.2 10-16 Semi-latus rectum (meters) (optional)
(unnecessary if eccentricity>1.0, energy
term> 0 or is to be calculated)
12 18-19 03 = Last input record indicator
29 End of Data Card
30 End of Job Card
31 End of Schedule Tape Card
32 Blank Card
4.5.3.3 Output
The program output printout shows the input items for a case followed by the
outputs. The input section contains 24 lines, one line corresponding to
each of the 24 input cards. The output section contains the following
quantities:
1. Components of S, the outgoing asymptote (SX, SY, SZ)
2. Declination and right ascension of the outgoing asymptote (DAO, RAO)
3. Earth moon distance at encounter (Rl)
4. Launcher latitude and longitude (LAT, LON) 2 2
5. Twice the total energy per unit mass, km. /sec. (C3)
6. Eccentricity and semi-latus rectum of the conic (ECC, PAR)
7» True anomaly at injection (TA)
8. Distance to perigee (RCA)
9. Inverse parking orbit rate (KPD)
10. Time of first and final burn (TLP,TFB)
11. First and final burn arcs (PLP, PFB)
12. Greenwich hour angle at encounter (GHA)
13' Lunar phase angle (LPH)
NEAR
k May 19ÖI 1+-185 TM-LX-12 3/000/00
14,
16,
11.
18,
19.
With
Longitude of the moon at encounter (LOM)
Distance to injection (RAD)
Injection velocity (km./sec.) and injection path angle (VEL, PTH)
Launch date - month, day, year (LAUNCH EATE)
Time of flight in hours (TF)
Arrival date - month, day, year, hours, minutes, seconds (ARRIVAL DATE)
each launch azimuth the following quantities are printed:
Launch azimuth (LNCfi AZMTH)
Launch time - hours, minutes, seconds GMT (LNCH TIME)
Time from launch %o injection in seconds (L-I TIME)
Injection latitude and longitude (INJ LAT, INJ LON)
Range along the earth's surface (RANGE)
Inject-or. right ascension and azimuth (INJ RT ASC, INJ AZMTH)
Injection time - hours, minutes, seconds, GMT (INJ TIME)
Parking orbit coast time (PO CST TIME)
Latitude and longitude of second stage ignition (ING 2 LAT, ING 2 LONG)
NEAR
1* May 19Ö» U-lS* TM-UC-12 3/000/00
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k May 1964 4-187 QM-LX-123/OOO/OO (Page 4-188 Blank)
4.6 SPECIAL PURPOSE AREA
This section includes special purpose programs (DUPE, MAKETAPE. TELTYP,
WRTSENT, RESPLT, DUMP, RPTGEN, ICONDIS, TAPEOP, KISPRO, MESNO and TAPEGEN).
RESPLT
4 May 1964 4-189 TM-IX-123/OOO/OO
4.6.1 RESIDUAL PLOT - RESPLT
4.6.1.1 Purpose
The RESPLT program reduces observations against specified element sets and
outputs the residuals on punched cards which can be used in the EAI Data
Plotter.
4.6.1.2 Input - Schedule Tape Mode only (Toggle 24 On)
Deck Position Card Type
Column Number Punch
1 Schedule Tape Card
2 Job Card
3 Remarks Card
4 Program ID Card
1-6
9-14
IT
18
SPSJ0B
RESPLT
0 = Observation cards, S-file and E-file tape
inputs
1 = Observation cards, Element Set cards and
S-file tape inputs
2 = Observation cards, Element Number cards
and S-file and E-file tape inputs
3 = Observation cards, Sensor cards and
E-file tape inputs
4 = Observation cards, Element Set cards and
Sensor cards inputs
5 = Observation cards, Element Number cards,
Sensor cards, and E-file tape inputs
0 = Hardcopy and punched cards output
RBSPX/3
h May 1964 4-190 TM-LX-12 3/000/00
Deck Position Card Type
Column Number Punch
5 Data Cards:
a. Input Option 0:
(l) Observation cards
b. Input Option 1:
(1) Observation cards
(2) Element Set cards
c. Input Option 2:
(1) Observation cards
(2) Element Number cards
d. Input Option 3=
(1) Observation cards
(2) Sensor cards
e. Input Option h:
(1) Observation cards
(2) Element Set cards
(3) Sensor cards
f. Input Option 5*
(1) Observation cards
(2) Element Number cards
(3) Sensor cards
6 End of Case Card
7 End of Job Card
8 End of Schedule Tape Card
9 Blank Card
RESPLT
h May 1964 4-191 TM-LX-123/OOO/OO
4.6.1-3 Output
4.6.1.3.1 Printout
The printed output of RESPLT consists of reduced observations sorted by
revolution number. Quantities are:
1. Satellite number
2. Observation number
3. Revolution number
4. Time (min./lOO) since epoch
p. Vector magnitude (km.)
6. Revolution number (N/lOOO) since epoch
7. Element number
8. Association status
9. Sensor number
SATNO OBSNO 034 034 034 034 034 034 034 034 034 034 034 034 034
43334 43335 43336 43337 43338 43339 43340 433^1 43343 43344 433^ 43346 1*3347
REV
10731 10731 10731 10731 10731 10731 10731 10731 10731 10731 10731 10731 10731
DT(MIN) -.0012 -.0010 -.0010 -.0011 -.0010 -.0009 -.0009 -.0012 -.0010 -.0012 -.0011 -.0013 -.0012
VMAGN
48 48 52 48 41 43 5* 49 54
51 62 53
NREV .007 .007 .007 .007 .007 .007 .007 .007 .007 .007 .007 .007 .007
ELNO ASTAT 119 119 119 119 119 119 119 119 119 119 119 119 119
STA
039 039 039 039 039 039 039 039 039 039 039 039 039
SAMPLE PRINTOUT, RESPLT
RESPLT
h May 1964 4-192 TM-LX-123/OOO/OO
h.6.1.3.2 Punched Card;
The punched card output of the reduction is used as input to the data
plotter. The output consists of:
1. Stop card (to allow operator action)
2. Axes cards
3. Graph labeling cards (characters S, E, R, T)
h, Deta (satellite number, element number, epoch revolution number,
epoch time in days)
I
I 4 May 1964 4-193 TM-LX-12 3/OOO/CO
I
4.6.2 OTHER
The following programs in the Miscellaneous area are seldom used by the
analyst. A brief description of each program is given.
4.6.2.1 DUMP
The purpose of the DUMP program is to dump the contents of core memory, in
mnemonic and octal format, onto the system output tape. The DUMP program
can be initiated by a console interrupt or by manually executing a jump at
the computer console. In either case, the program is read in and operated
by EXECM0D1.
4.6.2.2 DUPE
The DUPE program provides the means for duplicating tapes in the B-2 System.
The program will duplicate a specified number of the blocks or until a
sentinel block on tape is reached. The program automatically rewinds both
tapes and checks the identification blocks before duplicating.
4.6.2.3 HISPRO
The purpose of the HISPRO program is to reduce the EMEWS historical data on
the system output tape to a readable formet.
The program will process the following types of EMEWS input messages and
indicate either test or real mode:
a. Individual impacts
b. Equipment status at sites 1, 2, and 3
c. Radar status at sites 1, 2, and 3
d. Threat summary
e. Manpan Threat summary
I
4 May 1964 4-194 TM-LX-123/000/00
4.6.2.4 ICONDIS
The purpose of the ICONDIS program is to produce a teletype tape of sub-
satellite tracks for input to the ICONORAMA display equipment in the NORAD
COC. The maximum number of satellites which can be displayed simultaneously
is twelve if the updating time interval is two or four minutes^ or eight if
the updating time interval is one minute.
The geographical background for the display is a Mercator projection with the
following limits:
78 north latitude, 69 south latitude with the east-west break of 60
east longitude. There is no overlap in longitude.
4.6.2.5 MAKETAFE
The MAKETAFE program produces, from cards, an input tape in a format acceptable
to the TELTYP program. The program has an option to break up the message into
90-line segments.
4.6.2.6 MESNO
The MESNO program types on the console typewriter the current message number
of the SEAIC tape and provides the operator with the option to change this
number via the typewriter.
4.6.2.7 RPTGEN
The RPTGEN program produces a hard copy report in a specified format from
input cards.
4.6.2.8 TAPEGEN
TAPEGEN is a utility program run under SYS (Philco 2000 operating system)
control to generate binary master tapes for the B-2 System. The program has
the following seven modes of operation:
a. Mode i - generates a new binary master from an RPL (Running Program
Language) tape..
% 4 May 1964 4-195 lM-LX-223/OOO/OO (Page 4-196 Blank)
b. Mode 2 - same as Mode 1 with the added feature of allowing octal
corrections to be inserted in the specified programs.
c. Mode 3 - updates the old binary master with new RFL programs.
d. Mode 4 - same as Mode 3 with the added feature of adding octal
corrections.
e. Mode 5 - updates the binary master with octals only.
f. Mode 6 - updates the old binary master by deleting all
program, specified by the operator on the console flexowriter.
g. Mode 7 - converts a Philco 2000-211 binary master to a 212 binary
master.
4.6.2-9 TAPEOP
The TAPEOP program provides the B-2 System with the following tape maintenance
capabilities.
a. Write a sentinel block
b. Rewind any system tape
c. Skip a specified number of blocks or to a sentinel block
d. Copy a specified number of blocks or to a sentinel block
e. Compare two tapes for a specified number of blocks or to a sentinel block
4.6.2.10 TELTYP
The TELTYP program is used to convert an output tape, written by other
programs such as MAKETAPE, to teletype format (Baudot code). The program
searches for a particular start sentinel and then converts all of the message
until an end sentinel is located. It then writes all of the converted data
back onto the system output tape for off-line processing.
4.6.2.11 WRTSENT
I The WRTSENT program provides the means for writing sentinel blocks on tapes
or rewinding tapes in the B-2 System.
* 4 May 1964 4-197 TM-UC-123/OOO/OO (Page 4-198 Blank)
4.7 1620 COMPUTER PROGRAMS
This section includes the 1620 programs used by the analyst (Jacchia,
King-Hele/Findley and Launch).
r
i
JACCHIA
k May 1964 4-199 TM-LX-I23/OOO/OO
4.7.1 JACCHIA II SATELLITE DECAY PREDICTION - JACCHIA
4.7.1.1 Purpose
The Jacchia program computes a predicted satellite decay revolution up to
100 revolutions after the input revolution. The computation may be
performed by either or both of two methods:
4.7.1.1.1 Method A uses an equation whose solution approaches zero as the
stepped revolution number in the equation approaches the decay revolution
of the satellite.
4.7-1.1.2 Method B is essentially a plotting method.
4.7.1.2 Input
4.7.1.2.1 Input Mode A (legal only using Method A)
Deck Column Position Card Type Number Punch
1 Satellite Number Card
1-10 Satellite number (right adjust)
2 Data Card
1-10 x.xxxxxxxx (days) = Period
11-20 xxxxxxxx.x = Revolution number
3 Data Card 2: same as Data Card 1
4. Data Card 3: same as Data Card 2
NOTE: Data cards must be in ascending order by revolution number.
4.7.1.2.2 Input Mode B
Mode B uses one Satellite Number card (see Mode A format) and from 6 to 100
Data Cards (see Mode A format). Data Cards must be in ascending order by
revolution number.
JACCHIA
h May 1964 4-200 TM-U-123/OOO/OO
if. 7.1.2. 3 Input Mode C
Mode C requires from 6 to 100 seven-card element sets. 'The element sets
must be in ascending order by element set number.
4.7.1.3 Toggle Switch Settings
Switch Position Input Method
1 On A only A only
1 Off. Program tests switch 2
2 On B B
2 Off C B
3 On see SW 2 A in addition to B
3 Off: No effect
k On: Input, data not printed on typewriter
4 Off: Input data printed on typewriter
4.8.1.U Output
The printed output consists of the following information:
1. Satellite number
2. Number of input points (Method B)
3- Period in days and revolution number (input data)
4. Decay revolution
I
I
JACCHIA
k May 1964 4-201 (Page 4-202 Blank)
TM-LX-123/OOO/OO
SAMPLE PRINTOUT, JACCHIA II
„Satellite number
number of points
Rev J. — 713
.06293789
.. 06290442
.O6280657
,06264376
.06257386
-O624C596
- 06240441
.06220669
,06202944
.061T7842
.O6I643O3
7-0
28.c
85.0
191.0
235.0
300.0
31^.0
393-0
455.0
512.0
535*0
DECAY ON THIS REV -
.06293789 7.0
.O6257386 2 35-C
.06164303 535.0
DECAY ON THIS REV -
> Method B
591.0
Method A, points selected by the program
601.0
r k May 196k 4-203 (Page 4-204 Blank)
KING-HELE
TM-LX-12 3/000/00
r
4.7.2 KING-HELE/FINDLEY DECAY PREDICTION
4.7.2.1 Purpose
The King-Hele and Findley programs both compute a predicted satellite decay
day using the same input but different formulas. The two programs are run
together.
4.7.2.2 Input
One seven-card element set is the only input required.
4.7.2.3 Output
The printout consists of the following quantities:
1. Satellite number
2. Element set number
3. Predicted day of decay from January 1, and day and year if before 3
years. The output contains both King-Hele and Findley methods.
SAMPLE PRINTOUT, KING/HELE FINDLEY
DECAY PREDICTIONS
DAYS FROM JAN 1 DAY AND YEAR,-IF BEFORE 3 YEARS
SAT EL KING HELE FINDLEY KING HELE FINDLEY
713 11 29 25 29 1964 25 1964
i
1620 LAUNCH
k May 1961* 4-205 TM-LX-123/OOO/OO
4.7-3 1620 LAUNCH
4.7.3•1 Purpose
The 1620 Lauren program computes a set of nominal elements given nominal
input data.
4.7.3.2 Input
Deck Column Position Card Type Number Punch
1 Parameter Card 1
1-3 Satellite number
4-6 Element. Set number
9-20 Satellite name
40-50 Eccentricity
51-64 Inclination
2 Parameter Card 2
1-9 Day of launch
10 0 = Launch direction south
1 - Launch direction north
11-24 Anomalistic period
25-36 Time (sec.) from lift-off to injection
37-50 Latitude of injection (4 is north and - is
south)
51-64 Longitude of injection (+ is west and - is
east)
65-78 Perigee (ir earth radii)
1620 LAUNCH
h May 196i; 4-206 Tft-LX-123/000/00
4.7-3-3 Output
The printout of the program is the same as the punched card output, that
is, a standard T-card element set. L , C , and C are omitted. Specifically
the quantities printed are:
1. Satellite number.
2. Element set number.
3« Satellite name.
k. Epoch revolution (o).
5- Eccentricity, e.
6. Inclination, i.
7. Epoch year (always current year).
8. Epoch time. T . o 9. Anomalistic period, P (days/rev). a
10. Right ascension of node, Q (deg.). ^
11. Argument of perigee cu (deg.).
12. Perigee distance (earth radii).
13- Change in right ascension, Cl (deg./day).
Ik. Change in argument of perigee, w (deg./day).
15. Semi-major axis, a (earth radii).
16. Nodal period, P (days/rev).
IT« Bulletin expiration time, always current year, first month,
first day.
l8. Ele me nt card numb e r s.
k May 1964 4-207 (Page 4-208 Blank)
1620 LAUNCH
TM-LX-12 3/OOO/OO
SAMPLE PRINTOUT 1620 LAUNCH
I
Satellite no.
—"Element set no.
•Card No.
1—Satellite name
I—Epoch Year
SOI 0 1 SAMPLE 1
SOI 0 2 1964 (Pa)
soi 0 3
S01 0 4
SOI 0 5
soi 0 6
SOI 0 7
.06265722
(a) 1.044662
(Epoch rev) (e)
0.0155 x (t0)
41.97791 (O)
214.67115
(ft) , -2.92204
M 155.14981
W , -1.77324
(Pn) .O6266655
(BLTN Date) 2040101
(i) 70.0
(q) 1.02847401
E
E
E
E
E
E
E
#
r
*
k May 1964 4-209 TM-LX-123/OOO/OO (Page 4-210 Blank)
4.8 STANDARD SYSTEM INFORMATION
This section includes the following standard items of system information:
a. OCS Sequences
b. Schedule Tape Operation - card and tape requirements
c. Observation Card
d. Satellite Number Card
e. Sensor File Card
f. Element Set File Cards
g. Acquisition File Card
h. Information File Cards
i. Communication File Cards
j. SEAI File Deletion Card
4 May 1964 4-211 (Page 4-2:2 Blank)
OCS SEQ
TM-LX- 22 3/000/00
OCS Number:
Toggle Control
Programs:
0CS4 0CS5 (Zics6
4-Up 5-Up 6-Up
ORCON ORCON ORCON
RASSN RASSN
SGPDC
4.8.1 OCS Sequence
4.8.1.1 Group 1: Must also have accompanying indication as to source of
observation input,
jfcsi** 0CS2 0CS3
2-Up 3-Up
ORCON ORCON
RASSN RASSN
SGPDC SGPDC
BLTNSGP ELTNSGP
GLASGP
4.8.1.2 Group 2: R Tape must be mounted prior to initiation of sequence.
OCS Number: 0CST 0CS8 0CS9 0CS1O 0CS11**
Toggle Control: T-Up 8-Up 9-Up 10-Up
Programs: RASSN RASSN RASSN RASSN
SGPDC SGPDC SGPDC
BLTNSGP BLTNSGP
GLASGP
4.8.1.3 Group 3: After initiation, Executive program will request a table
of satellite numbers (SATTB) to be entered.
0CS12 0CS13 0CS14 0CS15** 0CS16 0CS1T
12-Up 13-Up 14-Up
SGPDC SGPDC SGPDC
BLTNSGP BLTNSGP
GLASGP
OCS Number:
Toggle Control:
Programs:
l6-Up 17-Up
BLTNSGP BLTNSGP
GLASGP
** OCS Number: 0CS18
Toggle Control:
Pi ograms: GLASGP
JÖCS19
18-Up
0CS2O** 0CS21**
**currently not used.
SCHED TAPE
4 May 1964 4-213 TM-IX-12 3/000/00
4.8.2 Schedule Tape Operation
4.8.2.1 Standard Card Formats
Card Type
Schedule Tape Card
Job Card
Column Number
1-8
9
8o
17-19
25
Punch
TO SCHTP
11, 8 and 2 = * = end of block
J = card type
J0B
1 = first schedule tape program run
2 = second schedul tape program run
etc.
Remarks Card (optional)
17-19 REM
Program I.D. Card (see program)
Parameter Card (see program)
Data Cards (see program)
End of Case Card (optional)
1-8
9
8o
End of Data Card (optional)
17-23
End of Job
1-8 END0FJ0B
END CASE
11, 8 and 2 = * = end of block
J = card type
ENDDATA
SCHED TAPE
4 May 1964 4-214 TM-IÄ-12 3/000/00
Column Card Type Number Punch
9 11, 8 and 2 = * = end of block
80 J = card type
End of Schedule Tape
1-8 ENDSCHEB
9 11, 8 ana 2 = * = end of block
80 J = card type
Blank card
4.8.2.2 Deck Format
10
9 / L ank flnrri
7
8 iBnfl nf SebfiflJto
fend nf Job h |End of Case/Data
i £
6
2 .' Remarks
Program ID
x JS. Schedule Tape
3
4.8.2.3 Input Tape Requirements
See Figure 4-1
Program
Logical Tape Unit ID
ID
0 1
2 3
k 5
6 T
8 9
! 10
U
12
BLTNSGP
X X
X X
BNSCHED
X X
X
X EsPÖD
6LA&5P
X X
X X
GRNTRK
Input
X X
HELI
Ö In
put
X X
EPHH
4ERI
Ö (XYZLA)
EPHQ4ERIS
10ANULE
^U B
UKA
A
X X
T
IOHG
X X
X X
I ORF
X X
X X
LAP
Blank
X X
X LOCVEC
Input
X X
X X
MUNENDC Input
X EPHEMERlS
SCRAM
SCRATCH
SCRATCH
X NEARBBA Input
3PHB
4ERI
S X
OBSERVE FANCARDS X
X X
TO SCRA
TO SCRA
JO SRADUN
X OBSSEP
X fOR TAPE
TO SCRA
(Hi-pri)
TO SCRA
(Lo-pri)
PSR
X X
X TO SCRA
X RASÖ
M X
TO SEAI1
(SRCHEK)
X fOR
TAPE 70 ÖR
ADU
(SRTMRG)
TO SCRA 70 SR
ADU*
X
REDUCT
Input
X X
X STELTAPE
SCRATCH
*
RESPLT
X X
X X
ROC
Input
X X
X TO SCRA
X SEAI
Input
X SCRATCH/
old
70 SEAI1
X
lev
X
SGPDC
X
i TO SEAI1
(backup^
X TO SRADU
TO SCRA
X
SPIRDECI
spvm
c X
X X
TO SRADU
TO WEIGH1
X r
SYSB
ULL
input
X
X X
70 S
CRA
X
XRQADS
X X
X X
XYZLA
Input
X X
Blank/
EPHEMERIE
Blank
X
NO
TE:
T
ape
#1 -
TOB
INM
ST,
Tap
e #2
=
TO
SCH
TP,
T
ape
jfb
= TO
SE
AI1
, T
ape
#1
1
= T0
OU
TPU
T
Fig
ure
4-1
In
itia
l T
ape
Set
up
3
'<
»-0
03 C\v
n
03
as
i O
o
o
o~
o
CO
w
k.8.3 Observation Card Format
Column Card Type Number Punch
OBS CARD
4 May 1964 4-217 TM-LX-123/000/00
Observation Card
1-3 Satellite number. Column 1 contains a
minus sign if this is a classified ob-
servation; + or - are not allowed o o
4-5 Equipment Type
6-9 Sensor Number
10 Accuracy or Signal Strength
11-15 Date
16-24 Time (Z)
25-30 Elevation/declination. Column 2; can
be overpunched + or -.
31-37 Azimuth/right ascension. Column 31 can
be overpunched + or -.*
3S-UU Slant range (km.)
4.5-53 Range rate (kin./sec. ) with implied
decimal point between columns 46 and 47;
or f'iaximum frequency shift (cycles/sec. )
with implied decimal point between
columns 52 and 53«
* A minus overpunch in col. 31 indicates cols- 25-30 and 31-37 are declination
and right ascension respectively.
OBS CARD
May 196k 4-218 fnri TM-UC-323/000/00
Card Type Col'.jmn Nunber
5^
Punch
0, Blank = Range rate in cols. ^5-53
1 = Maximum frequency shift in cols.
1*5-53.
Brightness at observation time (see
paragraph k.8.3*2)
Max irr. \n brightness
Minimum brightness
Time interval of brightness
Date or line number
Message number
Equinox (see paragraph h.8.3«3)
Observation number (assigned by 0RC0N)
Switch indicator used by manual system
Card type (code type = Any numeric be-
tween 0-9) identifies an Observation
Card. 0 = Unknown, 1-9 coded accord-
ing to the Association Status as deter-
mined in RASSN.
I.8.3.I Column 10: Accuracy
Either accuracy or signal strength may be indicated in column 10.
If entry in columns k and 5 is 31 ör greater, column 10 contains signal
strength. If entry is 30 or less, column 10 contains accuracy.
33-57
58-59
60-61
62-63
6^-65
66-69
TO
73-78
79
80
OBS CARD
May 1964 -219 TM-LX-123/000/00
Code Figure
0
Accurac" Q-i <T ignal Strength
k
Signal weak, results
poor.
Signal questionable.
Normal observations made under fair Signal strength good,
conditions. reliable measurement.
Observations slightly under par due Signal fair.
to outside interference (e.g. some
clouds, reduced visibility).
Observations only poor due to out-
side interference.
Only estimates possible (malfunction
of instrument. Too short time of
object seeing).
Doubtful observations, unable to
verify either object or instrument
behaviorc Observations should be
considered only as tentative«
Ue8o,2 Columns 55-63 Cross Section, Frequency - for manual runs only
The block containing columns 55 through 63 is a dual purpose block where
cross section and frequency, or magnitude and time interval are indicated.
In order to specify cross section ana frequency, a minus is used in column 5$.
No sign is used in column 58 when this block contains magnitude and time
interval
Cross section, given in square meters, is listed in columns 55 through 57«
To indicate less than one square meter cross section, use appropriate numbers
and a minus in column. 55» thus in effect, putting, a decimal point before
column 55- For larger values where three digits would not be sufficient,
use a plus in column 55 to represent ten times the indicated value (adding
a zero to the value listed).
OBS CARD
h May 19#+ 4-220 OW-LX-123/OOO/OO
Frequency in megacycles, is listed in columns 58 through 63 with the decimal
point understood to be located between columns 60 and 6l. In rare cases it
might be desirable to increase the range of frequency given either side of
the decimal point. To do this, use a minus in column 63 to move the point
one place to the left, or a plus in column 63 to move the point one place to
the right.
4.8.3.3 Column 70. Equinox
Column 70 contains year of Equinox as specified by the following:
0 = year of date
1 = 1900
2 = 1925
3 = 1950
k = 1975
5 = 2000
6 = 1850
7 = 1855
8 = 1875
9 = to list actual year, if not provided above, list last two digits
of year in columns 71 and '[2 and use a minus in column 70 for 18
and a plus in column 70 for 19- Example: Equinox of I961 would
contain "+6i" in columns 70, 71, and 72.
SAT NO CAFD
h May 1964 4-221 IM-LX-12 3/000/00
(Page 4-222 Blank)
4.8.4 Satellite Number Card Format
Column Card Type Number Punch
Satellite Number Card
1-8 Satellite Number (rt. adj.)
NOTE: Cols. 1-8 may be repeated, once for each satellite, up through
col. 72.
80 R = Card type
V
SENSOR CARD
( k May 1964 4- 223
(Page 4-224 Blank)
TM-LX-123/OOO/OO
4.8.5 Sensor File Card Format
Column Card Type Number Punch
Sensor File Card
1-4 Sensor Number
5-11 0° (+N) = lat
between sols. 7-8)
12-19 X (+W) = longitude (decimal assumed
between cols, 1.5-16)
20-25 H (meters) = altitude (decimal assumed
after col. 25)
33 Classification (U, C, S)
37-5^- Location (descriptive)
60-76 Remarks
79 # = this sensor is in S-file
80 S = Card type
ELEMENT 7 CARD
k May 19& 4-225 TM-LX-12 3/000/00
h.8.6 Element Set File Card Formats
4.8.6.1 Seven-Card Element Set
Card Type
Element Card 1
Element Card 2
Column Number
1-3
k-6
8
9-18
23-36
37-50
51-614
80
1-3
k-6
8
9-12
23-36
80
Punch
Satellite number (rt. adj.)
Element set number (rt. adj.)
1 = Card number
Satellite name for Element File Update
N = Epoch revolution
e = Eccentricity
i - Inclination (degrees)
Card type (Code type = E, F, G, or H):
E = Nodal Elements
F = Nodal Elements from Lockheed
G = Nodal Elements from NASA
H = Nodal Elements from N M
Satellite Number (rt. adj.)
Element set number
2 = Card number
Year of T o T = Time of Epoch (day and fraction
of days in year)
Card Type (Code type = E, F, G, or H):
E = Nodal Elements
F = Nodal Elements from Lockheed
G = Nodal Elements from NASA
H = Nodal Elements from N M
ELEMENT 7 CARD
h May 196h 4-226 TM- IX-123/000/00
Card Type
Element Card 3
Element Card k
Column Number Punch
1-3 Satellite number (rt. adj.)
k-G Element set number (rt. adj.)
8 3 = Card number
9 -22 P. = Anomalistic Period at Epoch (days/
rev.)
23-36 f* - Right Ascension of ascending node
(deg.)
37-50 jo - Argument of Perigee (deg.)
5.I-6U Q - Perigee (earth radii)
80 Card type (Code type = E, F, G, or H):
E = Nodal Elements
F = Nodal Elements from Lockheed
G = Nodal Elements from NASA
H = Nodal Elements from N M
1-3 Satellite number (rt. adj.)
h-6 Element set number (rt. adj.)
8 k = Card number
9-22 C = Rate of change of period in days/
(rev.)
23-36 '< = Time derivative of Right Ascen-
sion of ascending node (deg./day)
37-50 i = Time derivative of Argument of
Perigee (deg./day)
80 Card type (Code type = E, F, G, or H):
E = Nodal Elements
F - Nodal Elements from Lockheed
G - Nodal Elements from NASA
H = Nodal Elements from N M
k May 1964 4-227
EiaffiHT 7 CARD
TM-DC-12 3/000/00
Card Type
Element Card 5
Element Card 6
Element Card 7
Column Number
1-3
4-6
3
80
1-3
4-6
8
9-2*
23-36
37-50
51-64
80
1-3
4-6
8
23-29
Punch
Satellite number (rt. adj.)
Element set number (rt. adj.)
5 = Card number
Card type (Code type = E, F, G, or H):
E = Nodal Elements
F = Nodal Elements from Lockheed
G = Nodal Elements from NASA.
H = Nodal Elements from N M
Satellite number (rt. adj.)
Element set number (rt. adj.)
6 = Card number
a = Semi-major axis (earth radii)
P = Nodal period (days/rev.) rt
C = Rate of change of nodal period 2
in days/(rev.)
C = Phase angle coefficient (optional)
Card type (Code type = E, F, G, or H):
E = Nodal Elements
F = Nodal Elements from Lockheed
G = Nodal Elements from NASA
H = Nodal Elements from N M
Satellite number (rt. adj.)
Element set number (rt. adj.)
7 = Card number
Initial Revolution, decimal may be
punched in column 29
ELEMENT 7 CARD
k May 1964 4-228 TM-LX-123/000/00
Card Type
7 (Cont'd)
Column Number
30-36
37-50
51-58
59-66
67
Punch
Final Revolution, decimal may be
punched in column 36
YMMDDHHMMSS.SS = Expiration date of
Bulletin
XXXXX.XX = RMS
Number of observations used in obtain-
ing RMS
Blank or 0 = Correct all elements
1 = Do not correct the inclincation
2 = Do not correct the drag term
3 = Do not correct inclination or
drag term
h - Correct time equation only
8 = Do not rerun if drag term becomes
positive
9 = Do not correct the inclination or
rerun if drag term becomes
positive
+ = New epoch is time of last accept-
able residual. Initial revolution
of the new bulletin is the revolu-
tion which the satellite is on at
the time of program run. New
bulletin time = operational time
of old bulletin, which stops at
time of program run.
- = New epoch is time of last accept-
able residual. Initial revolution
of new bulletin is the final rev.
ELEMENT 7 CARD
k May 1964 4-229 TM-LX-123/OOO/OO
Column Card Type Number Punch
minus 1 of old bulletin. New bulle-
tin time = 4/3 old bulletin.
E = Used only when elements are good but
bulletin is expiring or epoch is
greater than 100 days.
NOTE: +, -, or E used only for OCS runs.
ELEMENT 4 CARD
4 May 1964 4-230 m-LX-12 3/000/00
.86.2 Four-C'-rd Element Set
Card Type
Element Card 0
Column Number
4-6
8
9-11
13-14
16-24
26-28
30-31
32
Punch
0 = Card number
Blank = SPADATS number
4-9 = SPASUR number used prior to
SPADATS number
Satellite number
Blank = SPADATS elements
9 = SPASUR elements
Element Set number
Last two digits of year
Greek letter designator
Piece number
US = United States"
SR = Russia
FR = France
UK = England
CA = Canada
JA = Japan
0 = Unknown
1 = Scientific
2 = Weather
3 = Navigation
4 = Communications
5 = Manned
Country of Origin
Functional Type
ELEMENT h CARD
h May 196k 4-231 IM-lÄ-123/OOO/OO
Column Card Type Number Punch
33 0 = Silent
1 = Transmitting
2 = Rocket body silent
3 = Rocket body transmitting
h = Metal or other fragment
9 = Unclassified elements of all foreign
launched vehicles
35-36 Last two digits of epoch year
38-39 Month of epoch
1+1-^2 Day of epoch
kk-k6 Bulletin number
48-^9 Month of bulletin issue
51-52 Bay of bulletin issue
5I4-56 Number A revolutions covered by
bulletin
Element Card 1
1 1 = Card number
2-12 Sam- as cols» 2-12, Card number 0
13-26 xxxxx.xxxxxxxx = Modified Julian Day of
epoch
28-38 xx.xxxxxxxx (e.r.) = a, semi-major axis
iiO-50 +.XXXXXX+XX (e.r./clay) = da/dt, the first
time derivative
of a
ELEMENT k CARD
h May I96U •'1-232 m-Lx-12 3/000/00
Card Type
Element Card 2
Element Card 3
Column Number
52-62
6k-66
l
2-12
13-20
22-29
31-38
ko-kj
1+9-55
57-62
6k-66
1
2-12
13-20
22-29
Punch
2 2 +.xxxxxx+xx (e.r./day/day) = d a/dt ,
the second
time deri-
vative of a
Check Sum - the arLthmetic sum of digits
in each line, plus one for
each minus sign
2 = Card number
Same as cols. 2-12, Card number 0
xxx.xxxx = Inclination
xxx.xxxx = Argument of Perigee
xxx.xxxx = Right Ascension of the
ascending node
.xxxxxxx. = Eccentricity
xxxx.xx (min.) = Anomalistic Period
xxxxxx (km.) = Height of Perigee above
Earth's Equatorial Radius
Check Sum
3 = Card number
Same as cols. 2-12, Card number 0
xxx.xxxx = Mean longitude
+XX0XXXX (deg„/day) =du>/dt, first
time derivative
of the Argument
of Perigee
4 May 1964 ^-233
ELEMENT 4 CARD
TM-LX-^ 3/000/00
Card Type
3 (Cont'd)
Column Number
31-38
40-47
49-55
57-62
64-66
Punch
+XX.XXXX (deg./day) = dp/dt, first
time derivative
of the Right
Ascension of the
ascending i ode
+.XXX+XX (per day) = de/dt, first time
derivative of eccen-
tricity
+.XXXXX (min./day) = dP /dt, first time
derivative of the
Anomalistic Period
Revolutions from launch
Check sum
ELEMENT HM CARD
4 May 1964 4-231* TM-LX-123/000/00
4.8.6.3 N M Element Set
Card Type
Element Card 1
Column K*. Ji>er
1-12
13-21+
25-36
37-^8
Punch
t = Initial time point of integration
(min.), (floatingpoint)
A t = Integration time step interval
(min.), (floatingpoint)
tf = Final time point to "be integrated
(min.), (floating point)
d = The caliber or reference diameter
of the vehicle (meters), (floating
point)
49-60 m = The weight of the vehicle (kilo-
grams), (floating point)
79 1 = Card number (not used in manual
programs)
80 Card type (not used in manual prograns)
NOTE: Floating point numbers are given in the format: _+.xxxxxxx+xx
Element Card 2
1-12
13-24
25-36
37-^8
49-60
L - mean longitude at initial time o
(radians), (floating point)
axN, (floating point)
a N, (floating point)
h = x-component of angular momentum,
(floating point)
y-component of a:
(floating point)
h = y-component of angular momentum, 1/
ELEMENT m CARD
k May 196k (Page ^-236 Blank)
m- Lx-12 3/000/00
Card Type
2 (Cont'd)
Column Number
61-72
79
80
Punch.
hr = z-component of angular momentum,
(floating point)
2 = Card number (not used in manual
programs)
Card type (not used in manual programs)
MOTE: Floating point numbers are given in the format: +.xxxxxxx+xx
ACQ CARD
4 May 1964 4-237 TM-LX-I23/OOO/0O
4.6.7 Acquisition File Card Format
Card Type
Acquisition File Card
Column Number
1-3
15-18
20-24
26-1 ju
32-34
36
37
38-42
43-45
46-48
Punch
Satellite number (rt. adj.)
Element set number (rt. adj.)
Sensor number (rt. adj.)
Initial revolution = first revolution
for which Look
Angles are com-
puted
Final revolution = last revolution for
which Look Angles are
computed
Grid size = interval between successive
Look Angles (min.)
1 a Look Angles are desired for visual
passes
0 = Look Angles are desired for all
passes, whether visual or not
0 = Short output format
1 = Long output format (includes sun's
elevation and illumination)
Maximum range that the sensor can read
(km.)
Minimum elevation that the sensor can
read (deg.)
Maximum elevation that the sensor can
read (deg.)
ACQ CARD
k May 1964 4-238 TM-LX-12 3/OOO/OO
Column Card Type Number Punch
U9-51 Minimum azimuth that the sensor can
read (deg.)
52-5U Maximum azimuth that the sensor can
read (deg.)
55 0 = Generate all-points look angles
(rise to set)
3 = Generate CPA (i.e., generate first,
last, and point of closest approach'
look angles
k = Generate BAKER-NUNN look angles
6 = Generate all points-scheduling
(i.e., write Look Angles on Schedule
Type)
9 = Generate CPA-scheduling
56 1 --- Hardcopy and TTY output
0 = TTY outputs
57 C-type Output Coordinates (see Figure k<
80 A » Card type
INFO CARD
h May Y)6h ^-239 TM-LX-123/OOö/GO
U.8.8 Information File Card Format
Card Type
Information Card 1
*)
le
t-3)
Information Card 2
Column Number
5 6-8
9-10
11-12
11+
17-21+
25-U0
hi-kz
^5 J+T-U8
»»•9-72
75-77
78-79 80
1-8
9-16
17-3-
Punch
0 = Geocentric elements in cols. 51-55
1 = Cols. 51-55 blank
2 = Heliocentric elements in cols. 51-55
3 = Barycentric elements in cols. 51-55
Classification (U, C, S)
Satellite Number (rt. ad,).)
Last two digits of year of launch
Greek .letter-number designator: 01 = a ,
etc.
Component no. A-Z
Satellite name - alphanumeric
Common name
Launch day
Launch month
Launch yea: (last 2 digits)
Launch site
SPADATS number
01 = Card number
I = Card type
Booster country
Payload country
Mission or Description
Weight (kg.)
#
INFO CARD
k May 1964 4-240 TM-LX-12 3/000/00
Card Type
Information Card 3
Information Card 4
Column Number Punch
4l-48 Shape
49-56 Length (meters)
57-64 Height (meters)
6S-72 Width (meters)
75-77 Satellite number (rt. adj.)
78-79 02 = Carl number
80 I = Card type
1-3 Diameter (meters)
25-32 M = Radar Cross Section
4l~56 Type Transmission
57-bl Tumbling date
62-64 Tumbling rate (rev/min)
75-77 Satellite number (rt. adj.)
78-79 03 = Card number
8ö I - Card type
l-l6 Stabilization
17-24 Maneuver characteristics
25~32 xxxxxxx = Transmitting frequency
NOTE: Cols. 25-32 may be repeated, once for each frequency, up through
col. 64.
75-77 Satellite number (rt. adj.)
78-79 04 = Card number
80 I = Card type
INFO CARD
h May 1961+ 4-241 •-LX-12 3/000/00
Column Card Type Number Punch
Information Card 5
1-8 Anomalistic Period (days)
9-16 Inclination
17-24 Apogee
25-32 Perigee
33-^0 Eccentricity
75-77 Satellite number (rt. adj.)
78-79 05 = Card number
80 I = Card type
Information Card 6
21 Classification
25-26 Country code (US, SR, JA, UK, CA)
31-32 Box score code
U. S. EARTH PAYLOAD 00
U. S. EARTH DEBRIS 01
U. S. SPACE PAYLOAD 02
U. S. SPACE DEBRIS 03
USSR EARTH PAYLOAD 04
USSR EARTH DEBRIS 05
USSR SPACE PAYLOAD 06
USSR SPACE DEBRIS 07
U. K. EARTH PAYLOAD 08
U. K. EARTH DEBRIS 09
U. K. SPACE PAYLOAD 10
U. K. SPACE DEBRIS 11
OTHER EARTH PAYLOAD 12
OTHER EARTH DEBRIS 13
OTHER SPACE PAYLOAD 14
OTHER SPACE DEBRIS 15
INFO CARD
h May 1964 1+-242 TM-LX-12 3/000/00
Card Type
Information Card 7
Column Number
75-77
78-79
30
25-72
75-77
78-79
80
Punch
Satellite number (rt. adj.)
06 = Card number
I = Card type
Address codes (zero prior to 3 letter/
number codes) e.g. OSCA, 0659
Satellite number (rt. adj.)
07 - Card number
I = Card type
COMM CARD
k May 1964 4-243 TM-LX-12 3/000/00
4.8.9 Communication File Card Format
Card Type
Communication Card 1
Column Number
1-4
5
6
7
8
9-15
16
17-64
73-79
80
Punch
Sensor number (rt. adj.)
1 - Second card follows
0, Blank = No second card
0 - Unclassified
1 - Unclassified/EFTO
2 - Confidential
3 - Confidential/Noforn
4 - Secret
5 - Secret/Noforn
R - Routine
P - Priority
0 - Immediate
Z - Flash
A - Aircomnet
R - 1 Aero
S - SSO
Unclassified routing indicator (ift. adj.)
"From" line indicator:
0 = NORAD SPADATS
1=1 Aero
5 = SSO CONAD
"To" line
Classified routing indicator (ift. adj.)
C = Card type
COMM CARD
4 May 1964 4-244 TM-LX-123/OOO/OO
Column Card Type Number Punch
Communication Card 3 (for information and pass lines only)
1-40 Information line, including routing
indicator (lft. adj.)
41-72 Pass line
80 C = Card type
•
SEAI DELETE CARD
4 May 1964 4-245 (Page 4-246 Blank)
TM-LX-123/000/00
4.8.10 SEAI File Deletion Card Format
Card Type Column Number
SEAI File Deletion Card
1
2-5
6-8
80
Punch
D = Card type
Satellite Number (rt. adj.)
Sensor Number
Card type (S, E, A, or I)
1 July 1964 5-1 lM-LX-123/OOO/OQA
(Page 5-2 Blank)
Section 5
APPENDICES
The following information is included in the Appendices section:
a. Forms
b. Miscellaneous - constants, conversion factors, charts, etc.
I c. Observation formats.
I d. Glossary
1 July 1964 5-3 1M-LX-123/000/00A (Page 5-4 Blank)
5.1 POFMS
The following 1st Aerospace Squadron forms are used by the analyst:
a. Analyst Launch Checklist (Page 5-5)
b. Bulletin Input Data (Page 5-6)
c. Data Request and Routing Sheet (Page 5-7)
d. Least Squares Points (Page 5-8)
e. Look Angle Request (Page 5-9)
f. Satellite Observation Conversion Sheet (Page 5-10)
h May l°6i* 5-5 TM-LX-123/OOO/OO
ANALYST LAUNCH CHECKLIST
PRE-LAUNCH: I nrnoTflm/FTV- Nominal No: PMR Not
1 'aunch Site: No. Pieces Expected:
Transmitting Frequencies:
Size and Weight:
NOMINAL DATA. Injection: Latitude: _ Longitude: rime(L/0+Sec)
ELEMENTS
O To ^n(days)
i p n(min) h)
c R*A A
RA U q e
POST LAUNCH
Launch Time: Obj No: Int'l Desig:
SENSOR LOOK ANGLE SCHEDULE
\ ..EV 315 316 328 329 330 036 337 339 340 34C NAV Other r i
Remark •:
lACi > Forn x 31, ! -lar 6 4
h May 10 61* 5-6 ÜM-IX-123/OOO/OO
BULLETIN INPUT DATA (Right Adjust All Fields)
ORIGINATOR DATE
FIELD DESCRIPTION COLUMN
1 SATELLITE NUMBER 1-3
? ELEMENTS NUMBER (give only if non-current) 4-6
_1 , 1
3 LEAST SQUARES ORDER OF EQUATION 7
4 LEAST SQUARES. NUMBER OF POINTS (see following sheet) 8-9
5 LEAST SQUARES: IN, PUNCH "0" RAH, PUNCH "1" 10
— ; 7
UPDATED ELEMENTS NUMBER 11-13
UPDATE TO REVOLUTION NUMBER 14-18
8
9
PERIGEE IN EARTH RADII (give only if q F a. (1-e.) 19-25
TEST BULLETIN STARTING AT REVOLUTION NUMBER 26-30
10 TEST BULLETIN ENDING AT REVOLUTION NUMBER 31-35
11 IF DESIRE BULLETIN, PART 1 LIST ELEMENTS, PUNCH "1". IF DESIRE REFER TO PREVIOUS BULLETIN, PUNCH "0".
36
12 BULLETIN NUMBER 37-39
13 BULLETIN FROM REVOLUTION NUMBER 40-44
14 BULLETIN TO REVOLUTION NUMBER. NO: PUNCH "O" 45-49
15 rpn STANDARD: PUNCH "1" bKiU- SPECIAL: PUNCH "2" {see Items 17-20 below)
50
16 GRID AT REVOLUTION NUMBER 51-55
17 SPECIAL GRID: LOWEP LATITUDE (generally 0) (only if "2" punch for item 15)
56-57
18 SPECIAL GRID: UPPER LATITUDE 58-59
19 SPECIAL GRID: INCREMENT 60-61
20 SPECIAL GRID: SINGLE LATITUDE 62-65
21 YEAR (last 2 digits) 66-67
22 PRINT ONLY. PUNCH "0" PUNCH (for transmission). PUNCH "1".
68
23
24
CLASSIFIED, PUNCH "i" UNCLASSIFIED PUNCH "0"
69
ORIGINATOR'S NUMBER 70-75
25 DAY OF YEAR 7fi-80
1st AEROSPACE SQ »O C FORM
k May 19& 5-7 TM-D:-123/OOO/OO
DATA REQUEST AND ROUTING SHEET
srcu«;TV CLASSIFICATION INPUT
Q J UNCL ASS [ ] SECRET
OUTPUT j
• UNCLASS [_} SECRET |
PATF JOB NUMBER PRIORITY
1 DELIVER INPUT TO ORIG
i
ELEMENTS
1 OBSERVATIONS
SATELLITE AND ELEMENT NUMBER ROU
ROUTING INSTRUCTIONS
TING TIME OUTPUT COPIES DELIVER TO OTHER
DISPATCHER PRINTOUT ORIG
DATA CONVERSION
CARDS
PAPER T AND PRI
ORIG
COMPUTER APE *TOUT
ORIG
DD 1
ORIGINA ....
PROGRAM*
TOR
ANALYST DSSO
• -
«ER j DISPATCHER
\ i ! DATA 1
OTHER AGENCIES TELEPHONE NUMBER SIGNATURE
JOB TYPES REMARKS
\ ocs
RFO
NUMBER
JCTIONS
DC
SEAI
SUM
6UL
GLA
FAN
— "
C UPDATE
wETINS
o
T PUNCH
NGS
=MLE
RUN
PRE
PRIN
LIST
COM
TEST
< • >
USE CODI
ACS A '. ' v 'OHM 11
FtBf?
k May 19öfc 5-8 TM-LX-I23/OOO/
COLS
LEAST SQUARES POINTS
1 2 3 4 5 6 7 8 9 10 Ü 11 12 13 14 15 16 17 18 19 20
•
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1 July 196U TM-LX-123/000'y
• !.<*•* 1 1 1 1 I I ' 1 1 ! : 1 ! T 1U3HIH i 1 j 1
1 I 0t>3IM3 1 ' 1 1 '
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l 1 i $ 1 1 ) s 1 I ! 1
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a x ft ! 1 i ft 1 1 ; 1 i
• x • " . «!x »- P « X
£ ! | • 1
* 1 ! | 1 1 i $ | j j 1
* 4 S O s S
0 s - X K
K
P » €
ss» si
5 * X
X
« 0 u
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5 u 0
s ° fc Ü
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£ 1 : ! 1 ! 1 fi 1
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9 1 5 1 t» • i 1 | 1 » •e 1 I 1 1
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M a» *
o- - •
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1 »- _ Si
>»> 1 - — w
- 1 1
I
1 July 1964 5-11 TM-UC-023/OOO/OOA (Page 5-12 Blank)
5.2 MISCELLANEOUS
The following information is used by the analyst:
a. Conversion Factors
b. Modified Julian Days
c. Oblate Spheroidal Earth Model Distance
d. Right Ascension of Greenwich
e. Satellite Elevation and Slant Range
f. Semi-major Axis vs. Period
g. Mathematical constants
h. Formulas
i. Minutes and seconds to degrees
4 May 196k 5-13 TM-LX-I23/OOO/OO
5.2.1 Conversion Factors
TO CONVERT INTO MULTIPLY BY
D
days minutes 1,440.0
days seconds 86,440.0
degrees (angle) minutes 60.0
degrees (angle) quadrants 0.01111
degrees (angle) radians 0,01745
E
earth radii kilometers 6378.165
earth radii miles (naut.) 3443.93^
earth radii miles (stat.) 3963.2O8
F
feet centimeters 30.48
feet kilometers 3.048 x 10"
feet meters 0.3048 1
feet miles (naut.) 1.645 x 10"
feet miles (stat.) 1.894 x 10"'
feet/min cms/sec O.5080
feet/min feet/aco 0.01667
feet/min kms/hr 0.01829
feet/min meters/min 0.3048
feet/min miles/hr 0.01136
feet/sec cms/sec 30.48
feet/sec kms/hr 1.097
feet/sec knots 0.5921
feet/sec meters/min 18.29
feet/sec miles/hr O.6818
feet/sec miles/min O.OII36
4 May 1964 ,-l4 TM-LX-123/000/00
TO CONVERT INTO MULTIPLY BY
feet/sec/sec cms/sec/sec 30.48
feet/sec/sec kms/hr/sec 1.097
feet/sec/sec meters/sec/sec 0.3048
feet/sec/sec miles/hr/sec 0.6818
H
hours days 4.167 x 10"2
hours seconds 3,600.0
K
kilograms pounds 2.205
kilometers earth radii I.56785 x 10"
kilometers feet 3,28l.
kilometers miles (naut,) 0.5299569
kilometers miles (stat-) 0.6214
kilometers yards 1,094.
knots feet/hr 6,080.
knots kilometers/hr I.8532
knots nautical miles/hr 1.0
knots statute miles/hr 1.151
knots yards/hr 2,027.
knots feet/sec 1.689
M
mean solar day sidereal day 1.00273791
mean solar day sidereal time 24h03m56s.555
meters feet 3-281
meters kilometers 0.001
meters miles (naut.) 5.396 x 10"1*
meters miles (stat.) 6-23.4 x 10" *
h May 1964 5-15 TM- IX-12 3/000/00
TO CONVERT INTO MULTIPLY BY
meter s yards 1.094
meters/min feet/min 3.281
meters/min feet/sec O.C5468
meters/min kms/hr 0.06
meters/min knots O.O3238
meters/min miles/br 0.03T28
meters/sec feet/min 196,8
meter s/sec feet/sec 3.281
meters/sec kilometers/hr 3.6
meters/sec kilometers/min O.06
meters/sec miles/hr 2.237
meters/sec miles/min 0.03728
meter: s/sec/f sec ft/sec/sec 3.281
meter; s/sec/j sec kms/hr/sec 3.6
meters/sec/t sec miles/hr/sec 2.237
miles (naut. •) earth radii 2.9036 x 10"
miles (naut, •) feet 6,080.27
miles (naut, .) kilometers 1.853
miles (naut. -) meters 1,853.
miles (naut, .) miles (statute) 1.1516
miles (naut. .) yards 2,027-
miles (stflt. .) e.urth radii 2.52321 x 10
miles (stat •) feet 5,280.
miles (stat. ) kilometers 1.609344
miles (stat. ) meters 1,609.
miles (stat. .) miles (naut.) 0,8684
miles (stat. ) yards 1,760.
milesy /hr feet/min 88. miles/hr feet/sec 1.467
miles, 'hr kms/hr 1.609
miles. 'hr kms/min 0.02682
-4
4 May 1964 5-16 TM-LX-123/OOO/OO
TO CONVERT
miles/hr
miles/hr
miles/hr
miles/hr/sec
miles/hr/sec
miles/hr/sec
miles/min
miles/min
miles/min
miles/min
rounds
R
radians
radians
radians
radians/sec
radians/sec
radians/see
revolutions
revolutions
sidereal day
sidereal day
Y
yards
yards
yards
yards
INTO MULTIPLY BY
Knots 0.8684
meters/min 26.82
miles/min 0.01667
feet/sec/sec 1.467
kms/hr/sec I.609
meters/sec/sec 0.1+470
feet/sec 88.
kms/min I.609
mile s (naut.)/mi n 0.8684
miles/hr 60.O
kilograms O.4536
degrees 57.30
minutes 3,438.
seconds 2.063 x 105
degrees/sec 57.30
revoluti ons/min 9.549
revolutions/sec 0,1592
degrees 360,0
radians 6.283
mean solar dayj 0.99726957
mean solar time 23h56V.091
kilometers 9-144 x 10"'
meters
miles (naut.)
miles (stat.)
0.9144 -4
4.934 x 10
5-682 X 10" '
4 May V)6k TM-LX-12 3/OOO/OO
5.2.2 Modified Julio; Days - 196*1
DOM JAN FEB 1 MAR APR M AY JUN ! DOY MJD DOY MJD DOY MJD DOY MJD DOY MJD IDÖY MJD
1 : 1 38395 32 38426 61 38455 92 | 38486 122 38516 153 385W 2 p 96 33 27 62 56 93 j 87 123 17 154 48
3 3 9T 3^ 28 63 57 94 88 124 18 155 49 4 1* 98 35 29 64 58 95 89 125 19 156 550
5 5 99 36 430 65 59 96 490 126 520 157 51 6 6 400 37 31 66 ^60 97 91 127 21 158 52 7 7 01 38 32 6T ' 61 98 92 128 22 159 53 3 8 02 39 33 68 62 99 I 93 129 23 160 54 9 9 03 40 34 69 63 100 94 130 24 161 55
10 10 04 4l 35 TO 64 101 95 131 25 162 56 11 11 05 42 36 71 65 102 96 132 26 163 57 12 12 06 43 3T T2 66 103 97 133 27 164 58 13 13 0T 44 38 T3 67 104 98 134 28 165 59 14 14 08 45 39 T4 68 105 99 135 29 166 560
15 15 09 46 440 75 69 106 500 136 530 167 61 16 16 410 4T 41 76 470 107 01 137 31 168 62 IT IT 11 48 42 77 1 71 108 02 138 32 169 63 18 18 12 49 43 78 72 109 03 139 33 170 64
19 19 13 50 44 79 73 110 04 l4o 34 171 & 20 20 14 51 45 80 74 111 05 141 35 172 66 21 21 15 52 46 81 75 112 06 142 36 173 61 22 22 16 53 4T 32 76 113 07 143 37 174 68
23 23 IT 54 48 83 77 114 08 144 38 175 69 24 24 18 55 49 84 73 115 09 145 39 176 570 25 25 19 56 450 85 79 116 510 146 540 177 71 26 26 420 57 51 86 480 117 11 147 41 178 72 27 27 21 58 52 87 81 118 12 148 42 179 73 28 28 22 59 53 88 82 119 13 149 43 18C 74 29 29 23 60 5^4 89 83 120 14 150 44 181 75 30 30 24 90 84 121 15 151 45 182 76 3J (31 25 1 91 85 152 46
.„_..
k May 1964 5-18 TM-LX-I23/OOO/OO
5.2.2 Modified Julian Days - 1964- (Continued)
DOM JUL AUG s EF 0 CT IVOV DEC DOY MJD DOY MJD DOY
245~J MJD DOY MJD DOY MJD DOY MJD
1 id 3 38577 214 386O8 38639 275 38669 306 387OO 336 3ÖT30 2 184 78 215 09 246 640 276 67O 30T 01 337 31
i 3 185 79 2l6 610 24T 41 277 71 308 02 338 32 k 186 580 2 IT 11 248 42 278 72 309 03 339 33 5 18T 81 218 12 249 43 279 73 310 04 340 34
| 6 188 82 219 13 2 50 44 28O 74 311 05 5*1 35 7 189 3< 220 14 251 45 281 75 312 06 342 36
1 8 190 84 221 15 252 46 282 76 313 OT 343 37 9 191 85 222 l6 253 47 283 if
1 ( 314 08 344 38 10 192 86 223 IT 254 48 284 78 315 09 3^5 39 11 193 8T 224 18 255 49 285 79 316 710 346 740 12 19^ Qd 225 19 256 650 286 680 31T 11 347 41 13 195 89 22b 620 QC7 51 287 81 318 12 348 42 14 196 590 22T 21 256 52 288 82 319 13 349 43 15 197 91 228 22 259 53 289 83 320 14 350 44 16 198 92 229 23 260 54 290 84 321 15 351 45 IT 199 93 2 30 24 26I s^ * 29i ^ 322 16 352 46 18 200 94 2 31 2p 262 50 J92 66 323 17 353 47 19 201 95 232 26 263 57 293 8T 324 18 354 48 20 202 96 2 33 2T 264 58 294 88 325 19 355 49 21 203 97 234 28 265 59 295 89 326 T20 356 750 22 204 98 25^ 29 266 660 296 690 32T 35T 51 23 205 99 236 63O 26? 61 297 91 328 2? 3JÖ 52 24 206 600 237 31 268 62 298 92 #9 23 3>9 53 25 20T 01 1 y~ 269 I 6 *! 299 93 330 24 360 54 26 208 02 239 270 t'i 300 94 331 25 361 55 27 209 03 240 3^ 271 ! J? 301 95 332 26 3'-'2 56 28 210 04 241 35 272 66 302 96 333 27 57
29 '11 05 242 36 2T3 f-p
303 97 334 28 364 58 212 06 24 3 37 274 68 304 98 '>i'.j 29 365 59
31 213 07 244 305 99 _
366 760
k May 19& 5-19 (Page 5-20 Blank)
5.2.3 OBLATE SPHEROIDAL EARTH MODEL
( * I /^GEOCENTRIC 6379
6378
6377
6376
6375
6374
6373
6372
6371
6370
6369
6368
6367
6366
6365
6364
6363
6362
6361 —
6360
6359
6358
6357
6336
•m-uc-123/ooo/oo
£— | EQ UATO 1 "I 1 *
1
|
CU •= 6378. 165 KM
/ ä 1/498.3 #p= 6356.783 KM
p = ded/tf SIN2 ^ +
A» cos2 /)*
GE
TJ-
.OCEN
F 5UI
TRIC DISTANCE TO
»FACE OF AN OBLATE -
— —
SPHEROIDAL EARTH MOD EL
N. OF s. wu L
0 + 5 10 15 20 25 30 35 40 45 50 55 60 65 70 75 80 85 90 OB
/(GEOCENTRIC
i 4 May 1964 5-21
(Page 5-22 Blank) TM-LX-12 3/000/00
5 2 .4 Right Ascension of Greenwich, 0 Jan, 0000Z
1957 99-3902 1958 99.1514 1959 98,9127 i960 98,6740 1961 994209 1962 99-1822 1963 98 9^35 1964 93 7048 1965 99-4517 1966 99.2130 1967 98 9743 1968 98 7356 1969 99.4825 1970 99-2438
OEG.
k Mty 19& 5-23 (Rige 5-2U Blank)
TM-IÄ-123/OOO/OO
5*2.5 SATELLITE ELEVATION AND SLANT RANGE
CHART FOR DETERMINING ELEVATION a SLANT RANGE OF SATELLITE
AO. »STANCES ARC IN STATUTE MILES- 3 STATUTE MILES EOUAL APPROXIMATELY • KILOMETERS
SO» ALTin
f* *****
TO CENTER OF EARTM
TO CENTER
h May 1 )6U 5-25 TM-LX-123/000/00
5.2.6 L'EMI-MA.'. :< AXI. 7i . li-ia«
K)
y Of
to 3
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$ B5J3 o
CM 3 3 3
fM CM CM —
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po po I !
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vi P pi O pN O p> C"fc
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ljuly 1964 5-28 TM-LX-123/OOO/OOA
5*2.7 Mathematical Constants
5.2.7.1 Earth Constants
The gravitational potential of the earth for general perturbations calculations
is defined by:
U = 1 - Zl J ( Jf ] P (sin 0) n=2 n r J n r'
(1) , where
GML, the geocentric gravitational constant, (2)
= 3.986032xl020 cm3/sec2. (3)
a , the mean equatorial earth radius,
= 6378.165 km
r = the radial distance from the dynamical center is a units
0 = the geocentric latitude
and P (sin 0) is the Legendre polynomial.
The zonal harmonic coefficients are •
J2 = 1082.30x10" '6 (3/2 J2 = J)
J = -2.3x10 (5/2 J3 = H)
J, = -1.8x10 (-35/8 Jh = D)
and(-15A Jk = K)
J . are not considered.
f, the flattening of the earth (implicit in all calculations for U values,
and used in all geometrical calculations),
= 1/298.30 = O.OO33523.
lJuly 1964 5-29 TM-LX-123/OOG/0OA
5-2.7-2 Sidereal Constants.
u), the earth sidereal rotational rate,
= 1.002T3T9093 mean sidereal rotations/mean solar day
Qn, the mean right ascension of the Greenwich meridian at VJ
0 U.T. on 0 January,
= 98.70478 degrees (1964)
= 99.45171 degrees (1965)
= 99.21298 degrees (1966)
(1) The special perturbations programs used for precision satellite position
determination apply geopotential functions which are both longitude and
latitude dependent. The Kozai zonal coefficients (SAO Special Report
No. 101, 31 July 1962) are generally used.
(2) The values of GM^, a , f, J , J~, and Ji are those recommended by
Kaula (NASA TND-1848, May 1963).
(3) In SPACETRACK computations, k is used, where _i
kg = (GMj2 = O.O7436662 earth-radii/minute.
(The value 0.07436574 was used prior to March 1964.)
In general perturbations programs k Ai and k are assumed to be equal.
ljuly 1964 5-3O TM-IOC-12 3/OOO/OQA
5.2.8 Formulas
5.2.8.1 Definition of Symbols
a semi-major axis (units of earth radii unless otherwise specified)
b semi-minor axis
ß difference between orbital plane as defined by elements and orbital plane defined by ovservation
C. anomalistic drag term (days/rev )
CN nodal drag term (days/rev )
D. anomalistic drag acceleration term (days/rev )
D nodal drag acceleration term (days/rev )
e eccentricity
h apogee height
i inclination
k geocentric gravitational constant (k = 84.48932 or 205.82)
L mean longitude at epoch o
Xy injection longitude (west) i
\y longitude of the theoretical ascending node on revolution zero o
M mean anomaly
Q right. ascension at any time t v
Q right ascension at ascending node G
Uj argument or perigee
(jü, argument r? perigee at time T * At.
ID nou.ii.ai argument of perigee c
uo time derivative of u>
1 July 1961+ 5-31 TM-LX-123/OOO/OOA
p semi-latus rectum
P. anomalistic period
PN nodal period
0. injection latitude
q perigee height
r distance from center of earth to satellite
r observation position vector of satellite
R revolutions
AR revolution from T to T o
T time at &R revolutions since T
m -L .
1
C a
time of injection (days)
T epoch time
G_ rieht ascension of Greenwich at T TV o 0
v angle between perigee point and some specified point in the orbit
V velocity at apogee a
(V ) circular velocity of a satellite at a height equal to apogee height
(V ) circular velocity of a satellite at a height equal to perigee height C P
V velocity *t perigee
w unit vector normal to orbital plane
1 July I9ö4 5-32 TM-LX-123/OOO/OOA
5.2.8.2 Miscellaneous Formulas
a = - h * 9
ß = sin - (r.w)
e = a
q (v )- (vay 1 h - q . p'
e = x - a = TTh = WT2 - *> or 1 ' WT2
L = M + m + Q ; + Q , if 1 * 90
Q+ = Q + h (At) + i 5 (At)""; 0° £ Q < 360(
o O O
o = - 9-96 a ''cos i
(1 - e2)2
,2 0) = <j) + d) (At) + i ul (A4
"-)"; where 0 £ u) < 36O GO O
u>, = u) + d) A
. = 4.98 a'T//2(5 cos2 i-1)
(1-e2)2
ra ^ 3/2
P =(-p—); PA is in minutes; if a is in ER, let k = 84.48932
if a is in Stat. miles, let k = 205-82
or PA - .05867294? (a)3'2 (P is in days, a in ER)
r 360 N PN l 36O + X pi PA
q = a (l - e)
r == 1 + e cos v
T»To+ PN (AH) + CN (AR)" + 0N (AR)
PM; (2rr= 6.2831853)
V h - V q G p
July 1964 S-33 (Page 5-34 Blank)
TM-LX-123/oOO/OOA
5-2.9 Minutes and Seconds to Degrees
Minutes to Mins Seconds to Minutes to Mins Seconds to Decimal of or Decimal of Decimal of or Decimal of Degree Sec.
00
Degree
.00000
Degree
.50000
Sec.
30
Degree
.00000 .00833
.01667 01 .00028 .51667 31 .00861
.03333 02 .00056 •53333 32 .00889
.03000 03 .00083 •55000 33 .00917
.06667 04 .00111 .56667 34 .00944
-08333 05 .00139 .58333 35 .00972 .10000 06 .OOI67 .60000 36 .01000 .11667 07 .00194 .61667 37 .01028
.13333 08 .00222 I .63333 38 .01056
.15000 09 .00250 .65000 39 .01083
.16667 10 .00278 .66661 40 .01111 j
.18333 11 .00306 .68333 41 .01139
.20000 12 •00333 •70000 42 .OII67
.21667 13 .00361 .71667 43 .01194 |
.23333 14 .OO389 •73333 44 .01222 j
.23000 15 .00417 .75000 45 .01250 i .26667 16 .00444 .76667 46 .01278 |
.2833: 17 .00472 .78333 47 .01306
.30000 18 .00500 | .80000 48 •01333
.31667 19 .00528 .81667 49 .01361
.33333 20 .00556 .83333 50 .01389
.35000 21 .OO583 .85000 51 .01417
.36667 22 .006ll .86667 52 .01444
.38333 23 .00639 .88333 53 .01472
.40000 24 .OO667 .90000 54 .01500 1
.41667 25 .00694 .91667 55 .01528
.43333 26 .00722 •93333 56 .01556
.45000 27 .00750 .95000 57 .01583 ,46667 28 .00778 .96667 58 .0l6ll .48333 29 .OO806 .98333 59 .01639
2i-
%
i July 196U 5-35 TM-LX-123/oOO/OQA
5.3 OBSERVATION REPORT FORMATS
Observations are received in the following formats:
a. Standard A
b. Station 315 old format
c. Holloman
d. Moonwatch
e. SAO Baker-Nunn
f. SATEV (Muedon)
g- SATOF
h. SATUG
i. Trinidad
0- Synccm
k. 681/682
1. Millstone
Each format is given, and the procedures for handlogging the information onto
standard Observation cards are described. (See section 5-1 for appropriate
form).
5.3-1 Standard A Format
The following stations use the Standard A Format:
a. Shemya 3U5
b. Shemya 316
c. Turkey 337
d. Turkey (new) 315
e. Laredo
f. Moorestown
g. SPASUR
h. Minitrack
i. Prince Albert
j. BMEWS
k Trinidad
1 July 196k 5-36 TM-LX-123/OOO/OQA
5.3.LI Example
tSTAa OBJEC YMoDa HHMMSSsss DDdddd DDDdddd NNNNNnn NNnnnnS HHccc
)))))
Line Code Meaning
Connecting call code
Observation type (see figure 5«l)
SPADATS sensor number
Observation accuracy/signal strength
SPADATS object number
Date of observation
Time of observation
Elevation
Declination (O = north, 1 = south for last digit)
Azimuth
Right Ascension
Slant range (nautical miles)
Range rate (nautical miles/second), sign (S): 0 = +,
1 = -, 2 = unassigned
Hit count (HH) and check sum (ccc)
Disconnect call code
5.3.I.2 Handlogging Procedures
1. First line is the connecting call code and is not used in manual
processing.
2. Second line:
a. First digit of the word is the code for the observation type.
See figure jj.l for the associated two-digit code to be logged
in cc U-5. The next three digits are the SPADATS sensor number;
log zero in cc 6 and the number in cc 7-9« The last digit, accuracy,
is logged in cc 10.
b. Second word is the SPADATS object number; log the last three digits
in cc 1-3-
c. Date of observation is the third word and is logged in cc 11-15.
1 •bi)i>J)i)
2 t
STA
a
OBJEC
YMoDa
3 HHMMSSsss
DDdddd/
(DDdddS)
DDDdddd/
(HHMMSSs)
NNNMnn
NNnnrmS
HHccc
k )))))
1 July 1964 5-37 TM-LX-123/00O/OQA
3. Third line (first data line):
a. Log the first word, time of observation, in cc 16-24.
b. The second and third words represent elevation and azimuth unless
the observation type is zero or two (ist digit second line). In
that case, they represent declination and right ascension.
(1) Log elevation, second word, in cc 25-30. Log azimuth, third
word, in cc 31-37.
(2) Log the first five digits of declination in cc 25-29 and add
a zero in cc 30. If the last digit of this second word is a
one, an eleven punch is needed in cc 25« Log right ascension,
third word, in cc 31-37« An eleven overpunch is always
necessary in cc 31 when the report is in declination and right
ascension.
c. Slant range, the fourth word, is reported in nautical miles which
must be converted to kilometers. Multiply the digits by I.852.
The decimal point falls between the fifth and sixth digit of the
message. Range rate, fifth word, is reported in nautical miles
per second. The first six digits are multiplied by I.852, the
decimal point falls between the second and third digit of the message.
The seventh digit is a sign -- if it is a one, an eleven overpunch
is needed in cc 45; if it is a zero, plus is understood and no
overpunch is needed.
4. The classification (U or C) as indicated in the message text must be
logged in cc 71«
Figurc 5•1
Observation Type Code for Standard A Reporting Format
INSTRUMENTATION/FIELDS REPORTED
Optical-right ascension/declination Optical-elevation/azimuth Baker-Nunn-right ascension/dec. Radar-el/az/slant range/range rate Radar-el/az/slant range Rad iometric-el/az BMEWS-Site 1, Site 2 SPASUR FPS-17-el/az/slant rante/range rate Doppler-range rate
INPUT OUTPUT (1st digit, line two) (cc 4-5)
0 01 1 01 r, C 16 3 25 4 22 5 51 6 25 7 51 8 21 9 41
1 July 1964 5-38 TM-Lx-123/ooo/octA
5.3.2 Station 315 Old Format
5.3.2.1 Example
SYrMo MessgNr XXX OBJ XXX bt
Line Code
1 S
YrMo
MessgNr
2 XXX
OBJ
XXX
DaHHMMSSs
mm X
XX
3 bt
DaHHMMSSs NNTOC XX
Meaning
Station indicator
Year and month of observations
Message number
Line number of observation
SPADATS object number
Elevation and azimuth
Day and time of observation
Slant range (nautical miles)
End of line (for handlogging purposes)
Doppler channel
End of message
5.3'2.2 Handlogging Procedures
1. First digit of first line is station indicator, and in this case vould
be logged as station 0315 in cc 6-9- The second two digits are the
year of observation, and the last digit is logged in col 11. The last
two digits of the first word is the month, and is logged in cc 12-13.
a. The second word of the first line is unused for logging purposes.
2. Second line (first data line).
a. First word is unused for manual processing.
b. Second word is the SPADATS Object number and is logged in cc 1-9«
c. Third word is elevation and azimuth, and is logged in cc 25-30,
3I-37. (See 315 Handbook).
d. Fourth word is day and time of observation. Log the first two
digits in cc 1^-15• Log the time of the observation (next seven
digits) in cc 16-22, adding zeros in cc 23-2^.
f lJuly 1964 5-39 TM-LX-123/OOO/OQA
e. Slant range, the fifth word, is reported in nautical miles which
must be converted to kilometers. Multiply the digits by .'..852,
and log in cc 38-44. The last character of the fifth word is not
logged.
f. Sixth word (two digits) is not used at SPADATS.
3. The type is 21, and is logged in cc 4-5, if slant range is omitted,
log type 01 in cc 4-5«
I
1 July 196U 5-1*0 TM-LX-I23/OOO/OOA
5.3-3 Holloman AFB Format
5.3.3.I Example
DAY OBJECT HH MM SS.s DDD.dd DD.dd
Line Code Meaning
1 DAY Zebra Day of Observation
OBJECT SPADATS Object Number
HH MM SS.s Time of Observation
DDD.dd Azimuth (degrees)
DD.dd Elevation (degrees)
5.3«3*2 Handlogging Procedures
1. SPADATS sensor number is reported in the message text. Sensor number
is 050. Log in cc 7-9« preceded by a 0 in cc 6.
2. Log type 01 in cc h-5, and 0 for accuracy in cc 10.
3. Zebra day is reported. Convert to current date using calendar, and
log in cc 11-15«
h. The remaining fields are described in the message. Log in appropriate
columns.
5. Classification (U or C) as indicated on the message is logged in cc 71«
lJuly 1964 5-4l IM-LX-123/OOO/OOA
5.3.J+ Moonwatch Format
5.3.4.1 Example
SENSORNAME RSTAT OBJEC
Line Code Meaning
YMoDa EHHMM SSsss DDDmm UDDmm CCCCC
SENSOR NAME
R
STAT
OBJEC
YMoDa
E
HHMM
SSsss
DDDmm
U
DDmm
CCCCC
Reporting Method
SAO Sensor Number
SAO Satellite # International Designation, Yr. of
Launch, launch number, and piece #
Date of Observation
Epoch of Star charts
Time of Observation (hours and minutes)
Time of Observation (seconds)
Azimuth or Right Ascension (if R.A. HHMMm)
Unused digit if elevation
Elevation or Declination (if Dec. SDDmm, 0 = north,
1 = south in first digit)
Check Group. Sum of all digits in corresponding column.
Units digit only, tens digit not carried forward.
5.3.4.2 Handlogging Procedures
1. The first word is the alphabetic sensor name. It is not logged.
2. The first digit of the second word is the reporting method. If the
digit is zero, the observation is in elevation and azimuth. If the
digit is one, the observation is reported in right ascension and
declination. The next four digits is the SAO sensor number, this
must be converted to SPADATS station number. Log in cc 6-9«
3. The third word is the object's international designation. Convert
to SPADAT object number, and log in cc 1-3•
h. The fourth word is the date of observation and is logged in cc 11-15.
1 July 1961+ 5-1+2 lM-LX-123/OOO/OOA
5. The first digit of the fifth word is Epoch of 3tar Charts.
0 - Present
1 - 1855
2 - I875
3 - 1900-1920
4 - 1950
Epoch of Star Charts is logged in cc "JO. The remaining four digits and
all the digits of word six is time of observation, log in cc l6-2h.
6. The seventh word is azimuth or right ascension. If right ascension,
log the first four digits in cc 31-34> multiply the last digit by 60
and log the result in cc 35"37* (Right ascension is always indicated
by an eleven punch in cc 3-0« If the first digit of the second word is
0, the observation will be in azimuth, log the first three digits in
cc 31-33» Convert the next two digits to decimal of degree by using
the table in section 5»2.9> and log in cc 3^-37«
7. The eight word is elevation or declination. If elevation is indicated
by reporting method, the first digit is unused. Log the n xt two digits
in cc 25-26. Convert the last two digits to decimal Ox' cu.0ree by using
table five, and log in cc 27-30. If declination is indicated, first
digit is sign (l indicates an eleven punch in cc 25, 0 is plus and is
understood). Log next tvo digits in cc 25-26, and convert the last
two digits to decimal of degree by using the table in section 5«2.9>
and log in cc 27-30.
8. The ninth word is the check sum and is not used in handlogging.
9. The type is 01, and is logged in cc k-5.
10. The accuracy is zero, and is logged in cc 10.
11. The classification (U or C) as indicated in the message must be logged
in cc 71.
July 1964 5-43 TK-LX-123/OOO/OCA
S.3.5 SAO Baker-Nunn Format
Baker-Nunn Sensors are as follows:
B-N Sensor Number Name
01 Organ Pass 02 01ifants Fontain
03 Woomera 04 San Fernando
05 Tokyo 06 Nainital
07 Arequipa 08 Shiraz
09 Curacao 10 Jupiter 11 Villa Dolores 12 Maui
13 *Edwards Ik *Cold Lake
15 *Harestua 16 Santiago
17 *Sand Island
* Non-SAO station
5-3-5-1 Example
•ptbtbipu) YrMoDaXXXX 222St YMoDa OBJEC PIECE WHHMM SSsss HHMMm SDDMM CCCCC
WHHMM SSsss HHMMm SDDMM CCCCC YMoDa OBJEC PIECE WHHMM SSsss HHMMm SDDMM CCCCC
)))))
Line Code Meaning
1 $$$$$ Connecting Call Code
YrMoDaXXXX Message Date/Control Number-
2 222 Format Cod d Indicator
St B-N Sensor #
YMoDa Date of Ob servation
SPADATS Sensor Number
0033 003^ 0035 0036
0037 004l 0038 0042 00^5 0044 0046 0047 0030 0032 0029 inactive
0031
OBJEC PIECE Satellite # International Designation (Year of Launch,
Launch § or Greek letter, and piece in group)
W Value of culmination time difference
HHMMSSsss Time of Observation
1 July 196^+ ykk IW-LX-I23/OOO/0OA
Line Code Meaning*
HIIMMm Right Ascension
S Sign (0 = +, 1 = minus)
DDMM Declination
CCCCC Check group. Sum of all digixs in corresponding column.
Units digit only, tens digit not carried forward.
h Additional observation.
5 YMoDa Designates change in date.
6 Observation (see line 3)
7 ))))) Disconnect Call Code.
5.3-5*2 Handlogging Procedures
1. The first line of five dollar signs and the message date/control number
is not used in manual processing.
2. Second line:
a. First word is the format code indicator, followed by the Baker-Nunn
sensor number. Convert the two digit sensor number to the SPADATS
sensor number shown on the preceding page and log in cc 6-9«
b. The second word, date of observation, is logged in cc 11-15.
3. Third line:
a. The first two words are the object's international designation;
convert to SPADATS object number, using Satellite table, and log
in cc 1-3.
b. The first digit of word three is not used. Log the remainder of
the word, and word four, time in cc l6-2h.
c. Right ascension is the fourth word. Log the first four digits in
cc 31-3^« Multiply the fifth digit by 60 and log the result in
35-37• An eleven overpunch must be logged in cc 31«
d. The first digit of word six, declination, is the sign; n" it is a
one, an eleven overpunch is needed in cc 25, but if it is a zero
no overpunch is needed. Log the next two digits in cc 2^-26.
Convert the next two digits to decimal of degree (section 5»2«9) and
log in cc 27-30.
e. The last word is unused In handlogging.
x. Baker-Nunn is type l6, and is logged in cc h-cj. Log (U or C) as
classification in message indicates in cc 71.
1 July I96U i-*5 TM-LX-123/000/00A
5.3.6 SATEV Format
The following is a list of COSPAR Station numbers with the corresponding
SPADATS Station numbers.
COSPAR SPADAT
3101 0075
3102 0076
3103 0079
3,10k 0080
3129 008l
3130 0082
3131 OO83
5.3.6. 1 Exampl e
SATEV STATt 03JEC rMoDa HHMMS SssDD DMM// DDMM/ bt
Line Code Meaning
3
SATEV Format Code Indicator
STAT COSPAR Sensor #
t Observation type (See figure 5-2)*
OBJEC International Designation (sat. #) Yr of launch, launch
number, piece in group,
r Data Type Code (see figure 5-2)**
MoDa Date of Observation
HHMMSSss Time of Observation
DDDMM// Azimuth
DDMM,/ Elevation
bt end observation
5o3.6.2 Handlogging Procedures
1. First word of line is format indicator and is not used in handlogging.
a. The first four digits of second word is COSPAR sensor number.
Convert to SPADATS sensor number using COSPAR sensor listing, above,
and log in cc 6-9. The last digit is observation type code,
(figure 5-2). Log 01, type, in cc I4--5.
i July 19bh 5-k6 m-LX-123/OOO/OQA
b. Convert the third word, satellite number, to SPADATS object
number using satellite table.
c. The first digit of word four is data type. (Figure 5.2) The
last four digits are month and day of observations. Log in cc 12-15.
The year is understood to be the current year, and is logged in cc 11
2. Second line:
a. Log the first five digits of word one and the next three digits of
word two, time of observation, in cc 16-23 adding 0 in cc 2k.
b. Azimuth is the last two digits of word two and the first digit of
word three, log in cc 31-33- If the data type is 2 the next two
digits should be converted to decimal of degrees using the table
in section 5*2«9> and logged in cc 3^-37«
c. Elevation is word three, log the first two digits in cc 25-26.
If 2 is the data type, convert the last two digits to decimal of
degree using the table in section 5*2.9, and 1°6 *n ^7-30. ^ I
is the data type, log the digits in cc 27-28 adding 0 in cc 29-30.
3. If reporting type is 1, SATEV may omit the last digit of azimuth and
elevation, in which case the minutes are in decimal of degree. Slashes
are between and at the end of observation parameters.
h. Log 0 in cc 10 for observation accuracy, and the classification (U or C)
as indicated on the message in cc 71«
1 o'niy 1964 5-Vf TM-LX-123/OOO/0OA
Figure 5.2
observation Type Coded As:
1 - photographic; cinetheodolite
2 - photographic; fixed camera or small telescope
3 - photographic; tracking camera or telescope
k - photographic; telescope
5 - Visual; naked eye or binoculars
6 - Visual; telescope (low power)
7 - Visual; telescope
8 - Visual; theodolite
9 - Visual; telescope
C - other instrument or unknown
**Data Type Coded As:
1 - Azimuth/Elevation (degrees and thousandths of degree)
2 - Azimuth/Elevation (degrees, minutes, tenths of minutes)
3 - Equatorial (right ascension/declination) Epoch 1950-
k - Equatorial (right ascension/declination) Epoch of date.
5 - Equatorial (right ascension/declination; Epoch of BD chart 185
6 - Equatorial (right ascention/declination) Epoch of CD chart 1575
1 July 1964 5-48 TM-LX-123/OOO/OOA
5.3.7 SATOF Format
5.3-7.1 Example
STATION DaHHx MMSSs HHMMm SDDMM IBbCC
Line Code Meaning
1 STATION Station Name
Da Day of Observation
HH Hour of Observation
x Unused Digit
MMSSs Minutes and Seconds of Observation
HHMMm Right Ascension
S Sign
DDMM Declination
I Accuracy of observation
B Stellar Magnitude
b Tenths of Magnitude
CC Check Sum (Sum of all digits in observation)
5.3'7'^ Handlogging Procedures
1. The first word is station name. Convert to SPADATS sensor number,
and log in cc 6-9«
2. Day of observation, first two digits of word two, is logged in cc 14-?5
Hour of observation is the third and fourth digit, log in cc l6-l7.
Current year and month are logged in 11-13» The last digit of word two
is unused.
3. Log the third word, minutes/and seconds of observation, in cc 18-22
adding 0 in cc 23-24.
4. Log the first four digits of word four, right ascension in cc 3I-34-,
multiply the last digit by 60 and log the result in cc 35-3^, adding
0 in cc 37' Right ascension is always indicated by an eleven punch in
cc 31.
lJuly 1961+ 5-^9 TM-LX-123/ooo/öOA
5. First digit of word five is sign. 0 signifies plus and is not logged.
1 indicates minus and an eleven punch is logged in cc 25. Log the
next two digits in cc 25-26. Convert the last two digits (section 5*2.9)
and log in cc 27-30. If the units digit of the minute field is an x, the
tenths position is tenths of degree. Log digit in cc 27.
6. First digit of last word is observation accuracy. Log in cc 10.
7- Type is 01, and is logged in cc U-5.
8. Object number will be in the message text. Log in cc 1-3»
9- Classification (U or C) as indicated on message is logged in cc 71«
1 July 1964 5-50 TM-LX-123/OOO/OOA
5-3.8 SATUG Format
5.3.8.1 Example
STATION DaHHx MMSSs DDDdx DDdxx IBbCC
Line Code Meaning
1 STATION Station Name
Da Day of Observation
HH Hour of Observation
X Unused Digit
MMSSs Minutes & Seconds of Observation
DDDd Azimuth
X Unused Digit
DDd Elevation
XX Unused Digits
I Accuracy of Observation
B Stellar Magnitude
b Tenths of Magnitude
CC Check Sum (Sum of all digits in observation)
5.3.8.2 Handlogging Procedures
1. Station name, first word, is converted to SPADATS sensor number
and logged in cc 6-9«
2. The first two digits of word two is day of observation. Log in cc 14-15
Current month and year is logged in cc 11-13« Hours of observation is
the third and fourth digit, and is logged in cc 16-17. Last digit of
group is unused.
3. Minutes and seconds, word three, is logged in cc 18-22 adding 0 in
cc 23-24.
h. Log the first four digits of word four, azimuth, in cc 31"3** adding
0 in cc 35-37« Last digit of group is unused.
5. Elevation, word five, is logged in cc 25-27 adding 0 in cc 28-30.
The last two digits of group are not used.
1 July 196h 5-51 TM-IX-123/OOO/OQA
6. Accuracy of observation, first digit of last word is logged in
cc 10. Remaining digits are unused.
7- Type is 01. Log in cc U-5«
8. Satellite number will be in message text. Log in cc 1-3-
9. Classification (U or C) as indicated on message is logged in cc 71
i
1 July 196U 5-52 IM-LX-I23/OOO/OOA
5.3-9 Trinidad Format
5.3.9.1 Example
SS511 OBJty STATa YMoDa HHMMSS.ss DD.d DDD.dd NNNN )))))
Line Code Meaning
1 $$$$$ Connecting Call Code
2 SS511 Format Code Indicator
OBJ SPADATS Obj #
ty Observation type
STAT SPADATS Sensor #
a Observation Accuracy
YMoDa Date of Observation
3 HHMMSS.ss Time of Observation
DD.d Elevation (degrees)
DDD.dd Azimuth (degrees)
NNM Slant Range (Nautical Miles)
C End of Line Indicator
h ))))) Disconnect Call Code
5.3«9.2 Handlogging Procedures
1. First line ($$$$$) is not used in handlogging.
2. Second line:
a. The first word of line two is the format indicator and is unused.
b. The first three digit& of word two is SPADATS object number, log
in cc 1-3. The last two digits of word two is observation type
and is legged in cc U-5.
c. SPADATS Sensor number, the first four digits of word three, is logged
in cc 6-9«
d. The last word of line two is date of observation, and is logged in
cc H-15.
1 July 1964 5-53 IW-LX-123/OOO/OOA
3. Third line:
a. The first word is the time of observation and is logged in cc 16-23
e4j4MM „ r\ -;»-, „„ o)' OVXVX^IIK <-* v -til *-v~ t_~t •
"b. The second word of line three is elevation and is logged in cc 25-27
adding 0 in cc 28-30.
c. Azimuth, the third word, is logged in cc 31"3^> adding 0 in cc 35-37
d. The fourth word is slant range reported in nautical miles. Convert
the four digits to kilometers by multiplying by 1.852, and log the
result in cc 38-blt.
e. The last word, one digit, is unused in manual processing.
h. Trinidad may submit observations without slant range, in which case
type 01 is logged in cc 4-5»
5. The classification (U or C) is logged in cc 71« Classification is
indicated on the message.
1 July 19& 5-5U TM-UC-123/OOO/OQA (
5.3.10 SYNCOM II Format
The following is a list of Syncom Station names with the corresponding SPADATS
Station numbers:
SYNCOM STATION MAKE SPADATS STATION NUMBER
SYNT1H 0909
SYNCS2 09C1
SYNCS3 0902
SYNCS4 0903
SYNCS5 0904
5.3.10.1 Example
))))) OBJBC STATNA Y^MDD HHMM SSsss T DDd STATNA YUMDD HHMM SSsss T KKKKKKkkk STATRA YYMHDD HHMM SSsss T Kkkkkk STATNA YYJMDD HH*W SSsss T DDDd •ww Line Code Meaning
1 ))))) Precedes Object #
OBJEC International Designation Satellite #
2-5 STATNA Station Name
YYMMDD Dtue of Observation
HHMMSSsss Time of Observation
T Type Code (See Figure 5.3)
XXXXXXXXX Data (3-9 characters: see Figure 5.3)
6 $$$$1 End of Observation
5.3.10.2 Handlogging Procedures
1. The first word of line one is unused in handlogging. The second word
is the SAO satellite number, convert to SPADATS number by using Satellite
table. Syncom II 633H is object number 634, and is logged in cc 1-3*
2. Each observation consists of k lines. The station name is the first
word of each line. Convert to SPADATS sensor number, and log in cc 6-9.
The second word of each line is date of observation, and is logged in i
Mi
1 July X9Sk 5-55 OM-LX-123/OOO/OCA
cc 11-1 j. Time is word three and four of each line. Use only line one,
the average observation time, and log in cc l6-2k. The fifth word is the
observation type code (l digit). See figure 5.3»
a. 'jtype code 5 indicates elevation in degrees and tenths of degree
(3 digits). Log in cc 25-27 adding 0 in cc 28-30.
b. Type code 1 indicates slant range in meters (9 digits). The
decimal point falls after 6th digit. Insure decimal point is in
the correct place on log sheet. Log in cc 38-^» The last digit
is rounded off.
c. Type code 9 indicates range rate, and is logged in cc ^5-51 adding
0 in 52-53» Minus sign as indicated on message is logged in cc 1*5«
If no minus sign is indicated, plus is understood and a 0 is logged
in cc k$. The decimal point falls after the first digit.
d. Type code k indicates azimuth in degrees and tenth of degree, and is
logged in cc 31-31* adding 0 in cc 35-37.
Ttype 25 is logged in cc k-5, accuracy of observation is 0 and is logged
in cc 10.
Classification (U or C) as indicated by message is logged in cc 71*
Figure 5*3
Observation type Codes As:
1 - Range in meters (9 digits).
k - Azimuth in degrees and tenths of degree {k digits).
5 - Elevation in degrees and tenths of degree (3 digits).
9 - Range Rate in meters per/second.
Given to nearest .01 meters per/second (sign and 6 digits)
'•••**•-•-•i*»mm*W ;..„,.„„•- .-..„«M«^^- ^aWB^^^^^.^^j^^gy^^^ *Mmm&m
1 July 196^ 5-56 m-UC-123/OOO/OQA
5.3.H C&L/682 Format
5.3.II.I Example
tSTAa HHMMSS
))))) Line
OBJBC XMoDa Q DDDdd DDdd XXXXXXXX
Code Meaning
1 ***** Connlncting Call Code
2 t Observation type
STA SPADATS Sensor #
a Observation accuracy
OBJBC SPADATS Object #
YMoDa Date of Observation
3 HHMMSIJ Time of Observation
Q Data Quality
DDDdd Azimuth
DDdd Elevation
XXXXXXXX Frequency
k ))))) Disconnect Call Code
5.3.H.2 Handlogging Procedures
1. First word of line one is connecting call code and is unused in hand-
logging.
2. Second line:
a. Type, first digit, of line two is observation type. 681/682 is
type 32, and is logged in cc 4-5. The next three digits are SPADATS
sensor number. Log in cc 7-9 with a 0 in cc 6. Last digit of word
one is accuracy of observation, and is logged in cc 10.
b. Second word is SPADATS object number. Log last three digits in
cc 1-3.
c. Third word, date of observation, is logged in cc 11-15.
1 July 196h 5-57 TM-UC-123/OOO/OQA
3. Third line:
a. Time of observation, first word, is logged in cc 16-21 adding 0
in cc 22-24.
b. Data Quality, second vord, 7 - Best, k - Good, 0 - Poor, is for
analyst use only.
c. Azimuth, the third vord, is in degrees and hundreth of degrees.
Log in cc 31-36 adding 0 in 37-38.
d. Elevation, the fourth vord, is in degrees and hundredth of degrees.
Log in cc 25-28 adding 0 in cc 29-30-
e. Last vord is not used in handlogging.
h. If no header card is on the message, log information for cc 1-15 from
text of message. Station 1 is 68l and Station 2 is 682. If text of
message is omitted, message DE line will be FTMEAD. The DSSO will
advise you on necessary information for Object number, Station number,
and date.
5- The classification as indicated on message is logged in cc 71*
1 July 19& 5-59 TM-IX-123/OOO/oaA
e. Slant range is in kilometers and is logged in 39-te preceded by a
0 in cc 38. Decimal point is understood at the end of the field.
Add 0 in cc k3-kk.
f. Log digits for range rate in cc V6-50, adding 0 in cc 51-53« log 0
in cc 45. If a minus sign precedes the field, an eleven overpunch
is needed in cc U5.
g. Classification (U or C) as indicated on messages Is logged in cc 71«
1 July 1964 5-59 TM-UC-123/OOO/OQA
e. Slant range is in kilometers and is logged in 39*42 preceded by a
0 in cc 38. Decimal point is understood at the end of the field.
Add 0 in cc 43-44.
f. Log digits for range rate in cc 46-50, adding 0 in cc 51-53« I«Qg 0
in cc 45. If a minus sign precedes the field, an eleven overpunch
is needed in cc 45«
g. Classification (U or c) as indicated on messages is logged in cc 71-
1 July 1964 5-60 lM-IiX-123/ooo/oaA f
5.3.I3 Code Tables
5.3«13*1 Observation Accuracy Code*
VISUAL OBSERVATIONS: Equipment Code 01 through 20
Normal Observation made under fail conditions
Observation slightly under par due to outside interference (e.g., soaie clouds, reduced visibility)
Observation poor due to outside interference.
Only estimate possible (Malfunction of equipment, too short time of object seeing).
Doubtful observation, unable to verify either object of instru- ment behavior. Observation should be considered only as tentative.
CODED ELECTRONICS OBSERVATIONS: Equipment Code 21 through 53
0 Signal strength good, reliable measurements.
1 Signal strength fail.
Signal weak, results poor,
Signal questionable.
Column 10 of Satellite Observation Conversion Sheet
1 July 196^ 5-61 •Dt-LX-123/OOO/OCA
5.3.13.2 Instrument Code
01 Visual observation without instruments. Estimates of h, z, or or* 6 only. 02 Visual observation with binoculars or small telescopes. Estimate only. 03 Optical observation with wide circles (Accuracy not better than * l/2 Degree). Ok Same as 03, accuracy + l/2 to l/lO Degree. 05 Same as 03, accuracy better than + l/2 Degree & Time better than l/5 Second. 06 Same as 03, accuracy better than 1 Minute of Arc, and Time to l/lOO Second. 07 Special code for observations with instruments specifically designed for tracking. 11 Photographic observations with very short-ratio and eiiall frame (e.g., 35 *•*
Lecia etc.); positions obtained by simple linear interpolation in starfleld. 12 Same as 11, but carefully analyzed (measured/positions). 13 Photographic observations with larger telescope and/or larger place (e.g.,
Astrograph, Schmidt telescope, ROTI, etc.). Ik Same as 13, but carefully measured and reduced. 15 Photographic observations with special tracking camera (ballistic camera,
photheod) carefully analyzed or QUICK LOOK DATA for codes 11 or 13* 16 Photographic observations with BAKER-NUNN Cameras, direct data readout no
special reduction (preliminary data). 17 Same as l6, final analysis with all corrections made. 21 Radar observations with fixed beam antenna. 22 Radar observation with moving beam, no self-tracking feature. Data readout
from position of dials. 23 Radar observation with moving beam antenna "TH tracking capability. Data
readout by dials. 2k Same as 22, data readout automatic. 25 Same as 23, data readout automatic. 31 Passive tracking data from telemetry systems \e.g., TIM-18). Disk with
diameter of less than 20 feet. Angular data accuracy not better than 1 degree. 32 Same as 31, disk diameter between 20 and 59 feet. 33 Same as 31, disk diameter over 60 feet. 3k Same as 31. 35 Same as 32 with angular accuracy better than + 1 Degree. 36 Same as 33 + l/lO Degree. 37 Same as 31. 38 Same as 32 but angular data accuracy better than • l/lO Degree. 39 Same as 33- kl Doppler observations (passive track). Signal strength accuracy see section 5«3»13-1 k2 Direction finding system. Signal strength accuracy U3 Interferometer system. Signal strength accuracy 51 Fence observation (Minitrack). 52 Fence observation (Microloc). 53 Fence observation (Doploc).
1 July 1964 5-62 OM-LX-123/OOO/OQA I
5»3*13» 3 Time Accuracy Code
0 = At the full second (next 2 digits must be zeros).
1 «s At the l/lO second (last digit must be zero).
2 = At the 1/100 second (last digit).
5 « At the ten second digit (accuracy + 5 second: second digit can be 0 to 9)
9 * At the minute (any seconds will be considered estimates only).
5.3«13.4 Time Zone Code
0 = ZULU (Z)
k m Eastern Daylight (EDT)
5 = Eastern Standard (EST) Central Daylight (COT)
6 * Central Staudard (CST) Mountain Daylight (MDT)
7 • Mountain Standard (MST) Pacific Daylight <H)T)
8 = Pacific Standard (PST)
a
• 1 July 196^ 5-63 IM-LX-123/OOO/0OA
5.4 GLOSSARY OF ABBREVIATIONS
COSPAR
CPA
DC
DIA
DIP
DMNI
DMNO
DOM
DOY
EFTO
ER
IGY
MJD
N-M Element Set
OCS
Q-Points
RA
RMS
- Committee on Space Research, an international space agency
established by the International Council of Scientific Unions.
- Closest Point of Approach.
- Differential Correction.
- Defense Intelligence Agency.
- Display Information Processor. The computer used to generate
the BMEWS displays in the NORAD COC.
- Device for multiplexing non-synchronous inputs.
- Device for multiplexing non-synchronous outputs.
- Day of month.
- Day of year.
- Encrypted for transmission only.
- Earth radii, as a unit of distance. Also earth's rotation.
- International Geophysical Year.
- Modified Julian Day.
- An element set based on vectors. N is a geocentric unit
vector directed toward the ascending node. M is a vector
directed toward and in the same plane as the orbit path
and normal to N.
- Orbit Computation Sequences.
- The effective fix on an object which results from scan-to-scan
comparative analysis in a fan from either detection radar or
tracking radar at the SKEWS sites.
- Right ascension.
- Root mean square.
j__*H^j^~c^£|jgygg|
••-:-• -•-. ^sgrnsBF.ys«! • «tii^-sgi»«
1 July 196^ 5-64 TM-LX-123/OOO/OCA il
SAO
SATBV
SATOF
SATOR
SATTB
SATUG
SEAIC
SRADU
STC
SSO
SYNCOM
Punning Program Language.
Smithsonian Astrophysical Observatory.
A code that defines the particular format in which observations
from COSPAR stations are received.
A code that defines the particular format in which observations
from COSPAR stations are received.
Satellite orbits.
Satellite table, containing satellite numbers automatically
selected by the RASSN Program for further processing.
A code that defines the particular format in which observations
from COSPAR stations are received.
Sensor, Element, Acquisition, Information and Communications
files.
A B-2 tape file containing Sorted Reports, Associated,
Doubtfully Associated, Unassociated.
Sunnyvale Test Center, Sunnyvale, California.
Special Security Officer, Air Force Security Service Network.
Defines code format in which observations are received from
this satellite source.
- The Philco Utility Program System.
' "«'SWfr mVJ•
14 August 1964 (Last Page) TK-LX-123/OOO/OB
DISTRIBUTION LIST
ADC (60 copies)
Electronic Systems Division U96L System Program Office L. G. Hanscom Field Bedford, Massachusetts
Lt. R. A Jedlicka (ESSXE-2) W. C. Morton, III (ESSX) R. E. O'Neil (ESSXE-2) 36 copies Colonel T. 0. Wear (ESFX) Captain E. T. Winston (ESSXE-l)
SDC
A. Drutz (Washington) M. H. Goer R. C. Long (CS) - 10.copies J. F. Matousek (CS) R. L. McMurtrie - l6 copies J. B. Munson (SM) J. M. Plante R. A. Richmond - 2$ copies