iII

j,

BB-3.1.3-10-M01

(TN-AP-67-255)

PART IV

AS-204/LM-1 LAUNCHVEHICLE

OPERATIONALFLIGHT

TRAJECTORY(REVISIONI)

(PA_ ;ES (C

./")

_ _ _(RA_'A CR OR TMX_O _AD NUMBER) (CATEGORY) SPACE DIVISION CHRYSLERCORPORATION

_-3.1.3-10-MCI

(,_..4P-_7-255)

_S-2_/LM-I IAt_CH VEHICI_ OPEeATIGNAL FLIGHT TRAJECTGRT (REVISICff I)

_ULI 25, 1967

AER(_PACE PHYSICS BRANCH

CHRYSLER CflRPCRATI(R SPACE DIVISICI_

_EPARED BY T. J. k_ARTCN, A. C. G_FrER, AND B. B. BARRETT

Checked By:

R. M. Blackstock,_reflight Trajectory Unit

APPROVED:

Preflight & Raase Safety Oz.e,_

_._D:_" _ _-'_"_Taylor, Ma_gir_ Engineer

Vehicle PerfoFmaneo Group

R. H. Roee, Chief Engineer --

Aerospace Physics Branch

FOR_MCRD

This report doc_e_ts the AS-2_/I_-1 Lsunch Vehicle OperatimalFlilht TraJeetor7 (Revtsim 1). The anal_ts and docwaentation wereperformed by Aerospace Physics Branch, Chrysler Corporation Space

Division, within the scope of NAS 8-A016, Modificatio_ _FC-I, Amend-

ment _, _RR No. iO1, BB Item 3.1.3-IO-MO1, Part IV.

Ac_owledgeae_ta are lade to the personnel of Marshall Space Flight

Center, R-AERO-FM, for their assistance and cooperation.

i

TABLE OF C_T_T3

Page

_(RD .................................................................... i

TABLE _ C_ ........................................................... ii

LIST CF TABLES ..................................................... •........ iv

LIST (F ILLUSTRATIG_S ....................................................... vi

DEFIRITICRS AND SYMBOLS .................................................... wiii

SUMMARY ..................................................................... 1

l.O DrFRODUCTICR ........................................................... 2

2.0 MISSION DESCKIPTICR .................................................... 3

2.1 Mission Objectives ................................................ 3

2.2 Mission Ground Rules and Constraints .............................. 3

3.0 LAUNCH VEHICLE AND E_IRQ_q_T DESCRIPTION ............................. &

3.1 Conf:l_uration ..................................................... &

3.2 Mass Characteristics .............................................. A

3.3 Aer_c Properties ............................................ A

•A Pr@pulslo. s_t_ ................................................

_.5 _nvtreemmt Ducr_pt_ ........................................... 5

A.O GUIDANCE AND CONTROL ................................................... 6

A.1 G_ance .......................................................... 6

A.2 Coatr@l Systems ................................................... 6

5.O LAUNCH _ICLE TRAJECTCRY .............................................. 7

5.1 S-IB Stage Powered Fld4g_ Phase ................................... 7

5.2 S-IVB Stage P@wered Flight Phase ....... • ........................... 7

TABI_ _ C_f_ITS (Cont'd)

6.0

APPENDIX A.

APPENDIX B.

APP]mDXX C.

Page5.3 Orbital Flight Phase ............................................. 8

5./, Spent 8-IB Stage Tra3eetory ....................................... 8

5 5 Traeking 8umary " 8• eeee eeeeeee eeeeeeeeeeeeeeeeeee eeeeeeeeeeeeeeeeeeee

5 6 Trajectory Dispersion Sugary 8• eeoeooeoeeee eeoeooeoeeeeeoeoeeeeeooee

5.7 Xaunch Vehicle Performance Characteristics ........................ 8

_E_dP_ CE_ eoeeeoeeooeeoeeeeeeooooeeeeeeeooeeeeoooooooeeeooeeeooeeeoeeee 9

"LAUNCH VEHICLE CHARA_TICS" ............................... 78

"G_NCE PRESETTINGS" ......................................... 91

"LAUNCH VEHICLE TRAJECTORY LZSTING, ENGLIGH UNITS" .............. 98

DISTRIBUTION ................................................................. 128

2Ai

Table

1

2

3

5

6

7

8

0J

i0

ii

12

13

Appendix A:

IA

2A

3A

_A

5A

6A

7A

LIST OF TABLES

Des cription

Flight Sequence of Events .................................

Launch Vehicle Trajectory Suu_ary ..........................

S-IB Stage End Conditions of Flight .......................

S-IVB Stage End Conditions of Flight ......................

Trajectory Listing:

Trajectory Listing:

Trajectory Lis ting:

Trajectory Listing:

S-IB Stage Flight Data ...............

S-IVB Stage Flight Data ..............

Orbital Flight Data ..................

S-IB Stage Re-entry Data .............

ea__m

11

13

15

17

22

&2

_6

&7

**_,_._,,_ _,_ *_._AL_'_v o_. _oraAna_es: Launch Phase ....

Tracking and Telemetry Sta. Coordinates: Orbital Phase ....

Trajectory Dispersion Envelope at S-IB/S-IVB

Separation ................................................ 48

Trajectory Di'spersion Envelope at J-2 Engine CutoffSignal .................................................... 51

Launch Vehicle Performance Characteristics ................ 5_

"Launch Vehicle Characteristics"

Vehicle Weight Breakdown .................................. 77

S-IB Stage MAss Characteristics ........................... aN)

S-IVB Stage Mass Characteristics .......................... 81

S-IB Stage Aerodynamic Characteristics .................... 82

S-IB Stage Propulsion Characteristics ..................... 83

S-IVB Stage Propulsion C_aracteristics .................... 8_

Orbital Vent Sequence and Impulse History ................. _5

iv

Table

Appendix B:

1B

2B

3B

Appendix C:

1C

2C

3C

_C

LIST OF TABLES ( Cont' d)

Description

Pa e

"Guidance Presettings"

S-IB Stage Steering Program ................ ............... 92

S-IB Pitch Attitude Command ............................... ?S

IGM Presettings ........................................... ?A

Orbital Attitude Maneuvers ................................ 97

r'Launch Vehicle Trajectory Listings, English Units"

S-IB Stage Flight Data ....................................

S-IVB Stage Flight Data ................. .................. 104

Orbital Flight Data ....................................... lO?

S-IB Stage Re-entry Data .................................. 12A

v

LIST OF ILLUSTRATIONS

1

2

3

6

7

8

9

i0

ii

12

13

IA

15

16

17

18

19

Flight Profile:

Flight Profile:

Flight Profile:

Flight Profile:

Des crlption

Altitude vs. Flight Time " 55ee@@eee@eeeeeeoe

Altitude vs Ground Range 56• oeee eee eeeoeeee

Velocity vs. Flight Time ................ 57

Space Fixed Path Angle vs.

Flight Time ..............................................

Flight Profile: Earth Fixed Path Angle vs.

Flight Time eeeoeeeeeeeeeoeeoeoeeeee_eee eeeeee_eeeeeeeoeoo

58

59

Pitch Attitude Steering Command: S-IB StageFlight Data .............................................. 60

Vehicle Pitch Attitude Rate: S-IB Stage Flight Data ..... 61

Pitch Attitude ____ror: s-___ Stage _i_._ n._ L,_

Pitch Angle of Attack History: S-IB Stage

Flight Data .............................................. 63

Dynamic Pressure History: S-IB Stage Flight Data ........ 6_

Longitudinal Acceleration: S-IB Stage Flight Data ....... 65

Pitch Attitude Steering Command: S-IVB StageFlight Data .................................. _........... 66

Yaw Attitude Steering Command: S-IVB Stage

Flight Data .............................................. 67

Longitudinal Acceleration: S-IVB Stage Flight Data ...... 68

Vehicle Attitude Rate: S-IVB Stage Flight Data .......... 69

Attitude Error: S-IVB Stage Flight Data ................. 70

Pitch Angle of Attack: S-IVB Stage Flight Data .......... 71

Dynamic Pressure: S-IVB Stage Flight Data ............... 72

Altitude History: Orbital Flight ........................ 73

vi

LIST OF ILLUSTRATIONS (Cont' d)

2O

21

22

23

Des cription

Space Fixed Velocity History: Orbital Flight ........... 74

Pitch Attitude History: Orbital Flight ................. 75

Tracking Summary: Launch Phase ......................... 76

Tracking and Telemetry Summary: Orbital Phase .......... 77

Appendix A:

IA

2A

3A

&A

5A

"Launch Vehicle Characteristics"

Vehicle Profile ......................................... 86

H-I Engine Thrust Decay ................................. 87

J-2 Engine Thrust Buildup ............................... 88

J-2 Engine Thrust Decay ................................. 89

Mean Headwind/Tailwind Profile .......................... 90

vii

DEFINITIONSANDSYMBOLS

Aerodynamic Heating Indicator

Aerodynamic Load Indicator

Altitude

Angle of Attac_ Pitch

Axial Force

Central Range Angle

Descending Node Argument

Drag

Dynamic Pressure

Earth Fixed Position

Earth Fixed Cross Range

qvr q_lati dt vr_t

=dynamic pressure

= relative velocity

= total angle of attack

Product of dynamic pressure and angle ofattack.

Vehicle altitude above the referenced ellip-

soid measured along the geocentric positionvector.

Angle between the pitch plane relative velocity

component and the longitudinal axis of the vehicle,measured positive nose up.

Component of the resultant aerodynamic force

along the vehicle longitudinal axis (X axis

of PASCS 8a), measured positive toward thetail of the vehicle.

Angle between_instantaneous space fixed

position vector and space fixed positionvector at Guidance Reference Release

Angle measured in the equatorial plane between

the orbit plane descending node and the space

fixed meridianplane defined at Guidance Ref-ference Release.

Component of the resultant aerodynamic force

along the earth fixed velocity vector, mea-

sured positive opposite to the velocity vector.

x (Density) x (Relative Velocity) 2

Position vector components in an earth-fixed

pad-centered plumbline coordinate system.The Xe axis is coincident with the reference

ellipsoid normal, positive_pward. The Ze

axis is parallel to the earth-fixed aiming

azimuth and is positive downrange. The Ye

axis completes a right handed system. (PASCS i0)

Ye component of PASCS i0 position vector.

viii

DEFINITIONB AND SYMBOLS (toni'd)

Earth Fixed .Flight Path

Angle

Earth Fixed Velocity

Earth Fixed Velocity

Magnitude

Flight Azimuth

Geocentric Declination

Geodetic Latitude

Ground P_nge

Inclination

Longitude

Longitudinal Acceleration

Mach Number

£ngle between the earth fixed velocity vectorand the earth ftxedgeocentric position vector(PASCS Ii), measured positive downrange fromthe position vector.

Velocity vector components in PASCS IO.

_/_e 2 + _e 2 • 2+ Ze

Angle defining orientation of the space

fixed coordinate system downrange axis, Zs,at Guidance Reference Release, measured

positive east of north in plane normal to

the space fixed Xs axis at Guidance Ref-erence Release.

Angle between the geocentric radius vector

and the true equatorial plane, measured

positive north of the equator.

Angle between the reference ellipsoidnormal through the point of interest and

the true equatorial plane, measured posi-tive north of the equator.

Surface range measured from launch site to

the sub vehicle point.

Angle between the instantaneous flight plane

and the equatorial plane.

Angle between the Greenwich meridian plane

and the projection of the geocentric posi-

tion vector in the equatorial plane, measuredpositive east cf Greenwich.

That part of the total measurable acceleration

directed along the longitudinal axis of thevehicle.

_¢lativ e Velocity) - (Local Speed of Sound) "

:ix

DEFINITIONS Abq) SYMBOLS (Cont 'd)

X$

Launch Meridian

Zs

Xrn = (-_r)l (dPY)3(C_P)2Xs

X m -

X m X' r

X' Xs

Ym

" _/\,, z,Zm

Pitch Yaw Roll

X

DEFINITIONS AND SYMBOLS (Cont'd)

Mass

Non_ Force

Pitch, Yaw, Roll

Radius

Relative Velocity

Space Fixed Position

Space Fixed Cross Range

Space Fixed Flight Path Angle

Space Fixed Velocity

Space Fixed VelocityMagnitude

Time

Weight

Mass of the vehicle.t

Component of the resultant aerodynamic forcenormal to the vehicle X axis, and in the X-Zplane (PASC3 8a), measured positive towardPosition I.

Eulerian angle of vehicle attitude measured

with respect to the space fixed coordinate

system. Vehicle attitude is defined by the

ordered rotation of pitch, yaw, and roll,respectively. (See illustration)

_Xs 2 + ys2 + Zs _

Velocity relative to the atmosphere (includes

wind velocity).

Position vector components in a spaced fixed,

earth centered, plumbline coordinate system

Xs axis is parallel to the reference ellip-

soid normal which passes through the launch

site. The Zs axis is parallel to, and posi-tive in the same direction as the earth-

fixed firing azimuth. The Ys axis completes

the right handed system. This is ProjectApollo Standard Coordinate System 13. (PASCS 13. )

Ys component of PASCS 13 position vector.

Angle between the space-fixedvelocity vector

and the radius vector (PASCS 13), measured

positive downrange from radius vector.

Velocity vector components in PASCS 13.

2 ÷ 2 + 2

Instantaneous Flight time referenced to

first motion.

Weight of vehicle in pounds.

xl

S_ARY

This report documents the AS-204/LM-I Launch Vehicle Operational FlightTrajectory (Revision I). Trajectory data are tabulated for all phases of

flight for which the Saturn IB Launch Vehicle has a functional requirement.

A comprehensive summary of the launch vehicle characteristics is also

presented.

The predicted S-IB and S-IVB stage end conditions are summarized below:

Se__ration

Guidance

C_utoff Signal

Flight Time (sec) 143.523 598 •152i

Altitude (m) 63,579. 163,193.

Space Fixed Velocity (m/sec,) 2,369.58 7,821.&9

Space Fixed Path Angle (deg) 62.85A 9O. 004

Range (m) 62,766. 1,796,200.

The nominal weight in orbit capability is predicted to be 70,205 pounds.This is 3,386 pounds in excess of the nominal propellant depletion weightThe 3-sigma flight performance reserve given in Reference I, approximately

1,3OOpounds, is considered reasonable for the AS-20A/LM-I configuration.

Hence, from a performance standpoint, approximately 2,086 pounds of S-IVB

propellant is available to compensate for S-IB stage early engine shutdown

Sumsmries of the trajectory flight envelope at S-IB/S-IVB separation and

S-IVB cutoff are presented in Tables Ii and 12. These data were taken from

Reference I, with the exceptions noted, and are considered applicable to

this trajectory.

The supporting tracking and alternate mission trajectories are documented

in References 2 and 3, respectively. Summaries of the tracking coverage

are presented in Figures 22and 23.

-I-

.SECTION1

INTRODUCTION

The AS-20&/LM-I LaunchVehicle Operational Flight Trajectory (Revision I)

is presented in this document. By definition, the Launch Vehicle Opera-

tional Trajectory includes all phases of flight for which the S-IB stage

and the S-IVB/IU stage have functional requirements.

In addition, comprehensive summaries of vehicle data, sub-systems char-

acteristics, and the guidance and control modes are presented herein.

-2-

S.ECTION 2

MISSION DESCRIPTION

2.1 .MIBSI_ OBJECT_IVES: The basic purpose of the Apollo Saturn 20&/LN-I

Hissi_ is to launch and test an unmanned LM for verification of crew safety

items and to verify the launch vehicle's system performance in preparation

for subsequent operational manned space vehicle miseiorm. An S-IVB stage

propellant dump experiment is also planned after LM separation. The pri-

mary objective of the SA-20A Launch Vehicle is to insert the S-IVB/IU/Pay-

load configuration in a near earth 85/120 nautical mile elliptic orbit.

The payload consists of a Lunar Module (LM). Spacecraft LM Adapter (SIA),and a 25 ° Nose Cone. (See References h &5".)

In the event of an S-IB engine pr_ture shutdown, the desired orbit maybe attained by using the remaining seven S-IB engines, S-IVB burn, and,

if necessary, IM burn to orbit. The effects of S-IB engine prematureshutdown on mission capability are documented in Reference 3 . In the

event of S-IVB engine failure, the infllght alternate mission is LMburn to orbit.

2.2 _M!SSIC_ GROL_D PJJT_--ES_;D C_;STP_I_: The following mission criteria,vehicle constraints, and trajectory constraints have been imposed on this

traJectory:

i) Launch from AFETR Pad 37B.

2) Pad oriented launch azimuth of 90 degrees east-of-north.

3) Flight azimuth of 72 degrees east-of-north.

h) S-IB stage tilt program defined in Table IB.

5) S-IFB cutoff conditinns for 85/120 nautical mile elliptic

orbit insertion.

6) Cemanded pitch and yaw attitude rate liait of one degreeper second.

7) Average mean head/tailvind for September and October.

-3-

SECTION 3

lAUNCH VEHICLE AND ENVIRONMENT DESCRIPTION

3.1 CCNFIGURATIGM: The SA-2OA/LM-I Saturn IB Launch Vehicle consists of a

S-IB first stage, a S-IVB second stage, an instrument unit, and a payload.The payload consists of a lunar Module (LM), 25° Nose Cone, and a Spacecraft

LM Adapter (SIA). An outboard profile of the c_lete configuration is shown

in Figure IA, Appendix A.

3.2 MASS CHARACTERISTICS: The SA-20_ vehicle mass characteristics are de-

fined in Reference 6. Table IA presents a vehicle weight breakdown of the

launch vehicle . These data are consistent with Reference 6 and the tra-

Jectory presented herein. Tables 2A and 3A present a time history of the

vehicle mass and the associated center of gravity and m_nent of inertia data

for the S-IB and S-IVB stages of flight, respectively.

3.3 AERODYNAMIC PROPERTIES: Aerodynamic data for the S-IB and S-IVB stages

of powered flight were obtained from References 7-9. Flight time histories ofthe S-IB stage of flight aerodynamic data are presented in Table _A. Orbitaldrag data was extracted from Reference iO.

3 .A PROPULSION SYSTEMS : The S-IB stage is powered by eight H-I engineswhich have a nominally rated sea level thrust of 200,000 pounds each. The

predicted nominal thrust magnitude history for each H-I engine, including

thrust decay and the associated turbine engine thrust, were obtained from

Reference ii The thrust magnitude time history for each H-I engine isdelineated in Table 5A. Figure 2A depicts the thrust decay histories.

The S-IVB stage is powered by a single J-2 engine which has a rated vacuum

thrust of 200,000 pounds at a nominal mixture ratio of 5:1. However, the pro-pellant utilization system produces a Programmed Mixture Ratio (PMR) shift which

provides a high mixture ratio level and a corresponding high thrust level forapproximately 325 seconds of flight. The predicted nominal J-2 engine thrust

history from the 90% thrust level time point to the time of the guidance cut-

off signal was obtained from Reference 12 The thrust buildup and thrust decay

histories were obtained from Reference i_ Table 6A presents a sumnary of theJ-2 engine thrust history. The J-2 thrust buildup and decay histories are de-

picted in Figures 3A and &A.

Four solid propellant retro-motors (TE-M-29) mounted on the S-IB/S-IVB inter-

stage provide thrust to decelerate the S-IB stage after separation. The retro-

motors are rated at a nominal thrust level of 36,7.20 pounds each (Reference 14).

Three solid propellant ullage motors mounted on the S-IVB stage aft skirt pro-

vide a positive acceleration for the S-IVB stage to settle propellants for J-2

engine start. The ullage motors are rated at 3,_60 pounds-thrust each (Ref-erence 15).

-4-

The S-IVB Stage Auxiliary _opulsion System (APS) consists of two modules.

Each module contains three 150 pound thrust (vacuum) hypergolic rocket engines.

This system provides roll control during the J-2 burn phase and pitch, yaw androll control after J-2 cutoff.

3.5 _NVIRONM_ DESCRIPTION: The 1963 Patrick Reference Atmosphere model de-

fines the atmospheric properties incorporated in the trajectory simulation.

The earth model and potential f_nction are those of the Fischer Earth Model.

The wind profile is an average of the September and October mean headwind/

tailwind profiles defined in Reference 16. It is depicted in Figure 5A.

-5-

SECTION A

GUIDANCE AND CONTROL

The Saturn IB inertial guidance system performs navigation evaluations, issues

discrete comuands, initiates guidance and control functions, and issues steeringcc_ands to guide the launch vehicle to the prespecified targeting conditions.

These functions are accomplished by the AS-2OA/LM-I Flight Program which is

stored in the launch Vehicle Digital Computer (LVDC). Inputs to the LVDC for

navigation and steering comuand evaluations are the predetermined constants

for the different guidance modes and the inertial velocity increments sensed bythe stabilized platform accelerometers.

A.l GUIDANCE: Guidance of the AS-2OA/LM-I Launch Vehicle into orbit and

throughout the orbital phases of active attitude control is divided into three

distinct phases: (i) Pre-IGM; (2) IGM; and (3) Orbital.

The Pre-IGM phase guidance provides pitch, yaw and roll vehicle attitude com-mands as a function of the time from llftoff to the time of IGM initiation.

The S-IB stage pitch program polynomials for this mission are delineated in

Appendix B, Table IB. Also included in Table IB is a time history of the yaw

and roll attitude co, ands. A history of the pitch attitude steering command

generated by the pol_ncmials is given in Table 2B.

In the Iterative Ouidance Mode (IGM) phase, a two-stage three-dimensional formulation

Of the IGM equations and logic provides active guidance of the S-IVB stage in

pitch and yaw from the time of IGM initiation, TB3 + 17.O seconds, to J-2 cut-

off. The commanded roll attitude is zero. The IGM equations and logic pro-

grammed for the LVDC Flight Program are defined in Reference 17. The IGM pre-settings for the mission are given in Appendix B, Table 3B.

The orbital guidance mode provides pitch, yaw and roll attitude co_uands for

the planned maneuvers during the orbital phase of the mission. The specific

guidance equations are defined in Reference 17. Table AB presents a summary of

the attitude maneuvers simulated during the orbital phase. (See Reference 18. )

A.2 COntROL SYSTE_: Pitch, yaw and roll attitude control are maintained by

the four swivelable H-I engines during the S-IB stage of powered flight. The

control law, gains, and network characteristics for the S-IB stage controlsystem are defined in Reference 19.

The J-2 engine provides pitch and yaw attitude control throughout the S-IVBstage of powered flight. Roll attitude control is maintained by the Auxiliary

Frop_Ision System. The control law, gains and network characteristics of theS-IVB stage control systems are defined in Reference 19.

-6-

SECTION5

lAUNCH VEHICLE TRAJECTORY

The nc_al sequence of events for the AS-204/I_-1 Launch Vehicle OperationalFlight Trajectory (Revision !) is su_narize_ in Table i. These data are con-

sistent with Reference 20 and the Iss and propulsion data referenced herein.

Table 2 provides a s_ry of trajectory parameters at pertinent events from

llftoff to loss of attitude control. Convenient e,-maries of the end condi-

tions of flight for the S-IB and S-IVB stages of powered flight are presented

in Tables 3 and A , respectivelT. Tabulated listings of the trajectory are pre-

sented in Tables 5 - 8. Corresponding tabular listings, in English units, are

given in Appendix C. Graphical displays of the ascent trajectory profile are

sho_n in Figures 1 through 5.

The associated data tapes required for distribution by _FC, R-AERO-F, areidentified as follows :

Trajectory Listing (Printout Tape) :

CCSD/SIIdell Reel No. 5634,_FC Copy,s _elivered 7-6-67.

Data Tape (B-7 Tape):

CCSD/Slldell Reel No. 6A7_,

MSFC Copy was transmitted 7-10-67.

5.1 S-IB STAGE POWERED FI_GHT PHASE: Tabulated listings of trajectory para-

meters for this phase are presented in Table 5. The phase is initiated atOQidance Reference Release (GRR), which is assumed to be 5 seconds prior to

launch (first motion). The time of umbilical disconnect and the correspondingestabllshment of Time Base one (TBI) is assumed to be 0.2 seconds after first

metle_. The phase ends at S-IB/S-IVB p_ical separation_ which is assured to

be 1.377 seconds after Outboard Engine Cutoff signal (OECO).

A tim hlstery of the S-IB stage pitch attitude steering command is depicted in

Figure 6. Figures 7 and 8 present mumariem of the resulting vehicle pitch atti-tude rate and attitude error. A summary of the pitch plane angle of attack is

presented in Figure 9. Figure i0 presents a susmary of the dynamic pressureh_tery. The longitudinal aceeleration history is depicted in Figure ii.

In order to establish a mere realistic ncmlnal trajectory prediction, a con-

stant thrust bias equal to + O.7 per cent of the vehicle sea level longitudln_Llthrust has been included in the S-IB stage trajectory. This action is an attempt

to minimise the effects of an apparent systematic shift in the ground to flight

test performance level.

5.2 S-IVB STAGE POWERED FLIGHT PHASE: Tabulated listings of the trajectory f_

S-IB/S-IVB separation to the time of orbit insertion are presented in Table 6.

-7-

Orbit insertion is defined to be at Guidance Cutoff Signal (GCS) plus I0

seconds. GCS occurs when the space fixed velocity magnitude equals a prespeci-

fled value of 7821.A9 m/sec. This phase of the trajectory includes the ullage

rocket burns, J-2 engine thrust buildup, mainstage burn with ullage case jetti-soning and _gine Mixture Ratio (EMR) shift, J-2 thrust decay and LOX venting.

The pitch and yaw attitude angle steering commands during the S-IVB powered

flight phase are depicted in Figures 12 and 13. The acceleration history is de-

picted in Figure I_. Trajectory parameters pertinent to an analysis of the tra-Jectory from S-IB/S-IVB separation to the time of active control are depicted in

Figures 15 - 18.

5.3 ORBITAL FLIGHT PHASE: Table 7 presents tabulated listings of trajectory

parameters for the orbital flight phase of the launch Vehicle trajectory fromorbit insertion to loss of S-IVB/IU stage attitude control. Histories of al-

titude, velocity and pitch attitude for this phase are displayed in Figures 19through 21.

5.A SPENT S-IB STAGE TRAJECTORYc The re-entry trajectory for the spent S-IB

stage is smmmarized in Table 8 . This phase of the S-IB stage trajectory is

initiated at S-IB/S-IVB separation and includes the retro-rocket burns.

5.5 TRACKING SUMMARY: Radar and telemetry coverage during ascent are pro-

vided by the stations listed in Tables 9 and i0. Summaries of the tracking

and telemetry coverage for each station are presented in Figures 22 and 23.

5.6 TRAJECTORY DISPERSION SUMMARY: The predicted nominal performance character-

istics of the launch vehicle and the predicted flight environment are subject to

deviations. Therefore, to coa_lement the nominal trajectory a flight envelope isrequired. Presented in Tables ii and 12 are trajectory flight envelope summaries

at S-IB/S-IVB separation and S-IVB cutoff, respectively. These data were taken

from Reference I , with exceptions noted, and are considered applicable to this

trajectory. Based on current dispersion philosophy, two envelope components re-

quired updating. These components are the l_J and S-IB thrust misalignment devi-

ations. Updating of the l_J error effects was necessitated by a revision of 3-sigma tolerances (Reference 21). An additional S-IB thrust misalignment ms in-

corporated to determine a realistic envelope for vehicle roll attitude at S-IB/S-IVB stage separation.

5.7 IAUNCH VEHICLE PERFORMANCE CHARACTERISTICS: The predicted S-IB and S-IVBstage performance characteristics are presented in Table 13. These data are time

averages of the detailed vehicle performance data referenced herein.

-8-

SECTION6

REFERENCES

le

,

_o

_e

o

e

e

o

9.

"AS-20A Launch Vehicle Operational Flight Trajectory Dispersion

Analysis", TN-AP-66-72, 26 September 1966.

"AS-2OA/I_-I Launch Vehicle Operational Flight Trajectory (Revision I)

Tracking Analysis", BB-3.1.3-1A-MOI (TN-AP-67-260), _ August 1967.

"AS-2OA/LM-I _/V Operational Alternate Mission Trajectories",

BB-3.1.3-11-MOI (TN-AP-67-262), 31 Ju_ 1967.

"NSFC Flight Missies Directive Apollo-Saturn IB Missions (UpratedSaturn I), Appendix D", 15 April 1967.

"SA-2OA/I_-I Launch Vehicle 0peraticaal Flight TraJectory",TN'AP-67-212,28 April 1967.

"AS-20A Final Predicted Mass Characteristics, Depletion Cutoff",

R-P&VE-VAW-67-SA, 8 June 1967.

"Sat_-n _, SA-_/L_- 1 Aer_c Axial Force Characteristics",

TN-AP-67-_A, 5 May 1967.

"Sat_-n IB/LEM AS-206, Aerc_amic Static Stability Characteristics",

TB-AP-66-58, 6 October 1966.

"Aerodynamics of the Saturn IB/I_, AS-A_6 Vehicle During First Stage

Separation and Second Stage Flight ", TB-AP-66-68, 28 November 1966.

i0. "Study of Drag Coefficients for Unusual Vehicle Configurations-JanuaryProgress Report", LESC/HREC A782235, 15 February 1966; May Progress

Report I_SC/HREC A782810, 15 June 1966; June Progress Report LMSC/HREC

A 78_29, 15 July 1966.

II. S-IB Stage Prep_Isic_ Prediction: CCSD B-5 Reel No. 750_ (B6 Reel No.

12. S-IVB Stage Propulsion Prediction: CCSD B5 Reel No. 5&_3 (_FC ReelNo. _7)o

13. "Thrust Increase Envelope, Test No. 3_-036, Engine S/N J-2025; "Saturn

IB J-2 Engine Characteristics", R-P&VE-PPE-66-M-_, 11 May 1966

_e "Data for use in S-IB-O3 and Sub Vehicle Specifications and Future Sepa-

ration Studies", R-P&VE-PPE-66-M-82, 21 June 1966.

-9-

15.

_6e

17.

19.

_0.

21,

"S-IVB Ullage Rocket Typical Th_st Versus Time (Vacuum 70°F) '',

R-P&VE-PPS-65-M-65, Figure 16, 5 May 1965.

"Cape Kennedy Wind C_onent Statistics 0-60 km Altitude For 72 Degree

Flight Azimuth For Monthly and Annual Reference Periods", R-AERO-Y-90-66,

23 March 1966; "Latest Wind Estimates From 80 km to 200 km Altitude Re-

gion at Mid-Latitudes", NASA TMX-5306A, 16 June 1964.

"LVDC Equation Defining Document for the AS-206 Flight Program", MBFC No.

III-_-_23-7, IBM No. 66-207-003, 12 April 1966.

"S-IVB/CSM Orbital Attitude Timeline and Vent Schedule for the AS-206",

NAS 80M92061 (Revised by datafax to R. D. Taylor CCSD, 5 April 1967);

"Revised Venting Schedule for the AS-20A Vehicle (AS-206 Mission)",

R-P&VE-PP-67-M-23, 21 March 1967; NASA letter, Mr. Harold Ledford to

Mr. E. D. Murrah, 16 June 1967.

"Control Gains and Shaping Networks for AS-208 S-IB and S-IVB Stages". R-ASTR-F-66-237, 8 December 1966; "Control System Information for AS-20_L",

R-ASTR-NG-_O-67, 5 June 1967.

"Interface Control Document, Definition of Saturn SA-20& Flight Sequence

Program", AOM3360AC, 13 December 1965 and IRN 13, IA and 15.

"ST-12AM Platform Hardware Errors to be Used in Performing a Hardware

Error Analysis of the Saturn IB and Saturn V Launch Vehicle", R-ASTR-

NG-168-66, 12 December 1966 (C).

-IO-

TABLE 1

AS-2OA/IR-I EA_CH VE_ICLE OPERATIOWAL FLIGHT TRAJECTGRY (REVISICll I)

FLIGHT SEQUENCE OF EV_S

IICKINAL FLIGHT TIME PROGRAM

(_: m_: s_c) _ TI_ (sin)

- 0:0:05.0 - 5.00 ---

- 0:0:03.1 - 3.10 ---

0:0:00.0 0.00 ---

0:0:00.2 0.20 (0.0) 1

0:0:10.2 10.20 (10.0)1

o:o:Ao.2 Ao.20 (_,o.o)1.

0:i:1_.0 7h.O0 ---

0:i:_0.2 100.20 (300.0)1

0:2:00.2 120.20 (120.0) 1

0:2:12.5 132.50 (132.3) 1

0:2:13.2 133.20 (133.0) 1

0:2:16.0 _6.oA (o.o) 2

0:2:19.1 1.39.1k (3.1) 2

0:2:22.1 1A2..l_ (0.0) 3

o:2:_.k uJ._ ( 1.._)i'

0:2:_3.5 1&3.52 ---

(

Guidance Referemce Release (GRR).

Initiate S-IB Mainst_ge I_mttionSequence.

First Motio_.

Lift-off Si&nalj Initiate Time Base I.

Initiate Pitch and Ro].l Maneuvers.

Comtrol Gain Switch Point.

Dynamic Pressure.

Control Gain Switch Point.

Control Gain Switch Point.

Enable S-IB Propellant Level Sensors.

Tilt Arrest.

Level Sensor Activation;Initiate Time Base 2.

Inboard Engine Cut,eft (IECO).

Oatboard Engine Cutoff (OECO);Initiate Time Base 3.

Separation SilpuLl.

S-IB/S-IVB Pkvsic=l Separatim;

Control Gain Switch Point.

-ll-

TABLE 1 (Cont'd)AS-20&/LM-I LAUNCH VEHICLE OPERATIONAL FLIGHT TRAJECTORY (RE_ISIQN I)

FLIGHT SEQUenCE OF E_ENTS

NQN]]qAL FLIGHT TIME PROGRAM

o:2:._.8 z_..8_ (2.?) 3

O:2:27.2 147.19 _-

O:2:28.1 I_8.1A ---

0:2:30.8 150.8_. (8.7) 3

o:2:35 .& 155 ._ (13.3)3

0:2:39.1 159.1_ (17.O)3

O :_:45.8 285 .SA (143.7) 3

0:7:55.8 _.75.75 -----

O:9:58.2 598.15 -----

o:9:58._ 59s.35 (0.0) 4

0:i0:08.2 608.15 ----

0:i0:43.& 6&3.35 (45.0)A

O:19: 58.k 1198.35 (600.0) 4

O:53:55.0 3235.00 --

A:30:O0.O 16200.00 ----

EViCt

J-2 Engine Start Co.and.

Ullage Burn Out.

90% J-2 Thrust Level.

Camand PU Systen Activation.

Jettison Ullage Rocket Motors.

Cce_and Active Guidance Initiation.

Control Gain Switch Point.

E_R Shift Sensed by IGM.

Guidance Cutoff Signal (GCS).

Initiate Time Base 4. (Reflects an

approximate 0.2 second systems delay)

Orbital Insertion.

Nose Cone Jettison.

SIA Panel Deployment.

Separation.

Loss of S-IV_IU Attitude Control.

-12-

I I I I I I I I I I I I I I I I

A

I-I

_ I I_" ._1

-13-

TABLE 3

AS-20&/,LM-I IAUNCH VEHICLE OPERATIONAL FLIGHT TRAJECTORY (REVISION I)S-IB STAGE _ND COMDITIC_S OF FLIGHT

_light Time (t): 0ECO + 1.379 secondsRadius (R):

Altitude:

Space Fixed Velocity (V):

Space Fixed Path Angle ( @ ):

Space Fixed Flight Azimmth (AZI):

Earth Fixed Flight Azimuth (AZE):Geocentric Declination (6):

Geodetic Latitude (_ ):

Longitude ( A ) : (Pos. East )

:J.k3.5_ (sec)6_36SJ,.3. (m)

63579. (m)2369.58 (m/s)

62.85_. (deg)'75.6_A (deg)72.221 (deg)28.5_.6 (deg)28.706 (deg)

- '79.955 (deg)

_PACE FIXED POSITION AND VELOCITY CC_POM_TS

X, = 6A35696: (m)Ys = 35&77. (m_

z8 = n_z?A. (a)

is = zo_2.3A (a/s)

_8 = _.8.2s (a/s)

Zs = _.72 (m/s)p

VEHICLE ATTITUDE AND ATTITUDE RATE

Pitch Attitude Angle (_p) :

Yaw Attitude Angle (q_y):

Roll Attitude A_.e (_R):Pitch Rate _(_p )._Zaw_te (_y):

- 59.&60-0.0_

-0.00_-0.002

0.000

-O.003

(deg)

(deg!(deg;(dens)

deas _deE/s )

-14-

TABLE &

AS-2_/LM-I LAUNCH VEHICLE OPERATICRAL FLIGHT TRAJECTORY (REVISION |)S-IVB STAGE _D CCRDITI_ OF FLIGHT

Altitude:

Space Fixed Velocity (V):

Space Fixed Flight Path AnKle ( 8 ):Space Fixed Flight Aziuuth (AZI):Earth Fixed Flight Azim_h (AZE):Geocentric Declination (6):

Geodetic Latitude ($):

Lm_itude ( A ): (Poe. East)Inclination (i) :

Descending Node Ar_ent ( 8 ):

598.152 (see)65355A9. _-.)163l_• (a)

78_.A9 (_s)90.00_ (de s )85.707 (deg)85•A72 (des)31.351 (des)31.518 (deg)

-62.2A0 (dog)31.61A (deg)119 •055 (deE)

SPACE FIXED P_ITION AND VELOCITY CCMPON_rI_

Xs = 6_06692s (I=)

Is = n.2o15• (=)Zs = 2o_uo. (=)e

= -_5o•1o (m/s)

Y. = _i.o_ (m/s)

z= = 7A_ .A6 (a/s)

T_ICLE ATTITUm_ A_GLE_

Pitch Attitude Angle ( _p ) =Yaw Attitude Angle ( _y ) =Roll Attitude Angle ( _. ) =

-98.9013.3%

-O._l&

(dss)

(des)(deg)

C6CULATING CONIC PARANETER_

*Perigee Altitude = 157.38 '(kin)

*Aposee Altitude = 197.38 (kin)Eccentricity = O.OO31Semi_Jor Axis = 6555 .SA (]ca)

"Period = 88.0A

* Referenced to Equatorial Radius (6378.16 kin)

-15-

TABLE & (Cont 'd)

AS-20_/LM-I lAUNCH VEHICLE OPERATIONAL FLIGHT TRAJECTORY (REVISION I)

S-IVB STAGE END CONDITIONS OF FLIGHT

Flight Time (t): Orbit InsertionRadlus (R):Altitude:

Space Fixed Velocity (V):

Space Fixed Flight Path Angle ( 8

Space Fixed Flight Azimuth (AZI):

Earth Fixed Flight Azimuth (AZE):

Geocentric Declination ( _ ):

Geodetic Latitude ( $ ):

I_gitude (A.): (Pos. East)

Inclination (i):

Descending Node Argument ( @ ):

):

608.152 (sec)

653_557. 6")

163_8. (m)7e_.6o (m/s)89.992 (deg)

86.125 (deg)85.913 (deg)

3l._oo (des)31.567 (,leg)

•..61. _'0 (deg)31.61A (deg)

ll9.05A (deg)

SPACE FIXED POSITION AND VELOCITY CONPONENT$

Xs -_ 618173 9: "(m)_s = .1_6:L_. (,.)Zs = 2116190. (m)

Xs = -2539.69 (m/s)

Ys = A09./,9 (m/s)e

zs = 7393.86 (m/s)

VEHICLE ATTITUDE ANGLES

Pitch Attitude Angle ( ee )

Yaw Attitude Angle ( e¥ )

Roll Attitude Angle ( eR )

= -98.903= 3.38O

= -O.AIA

OSCULATING CONIC PARAMETERS

* Perigee Altitude = 157.38

* Apogee Altitude = 221.&2

Eccentricity = O.OOA9

Semi-Major Axis = 6567.57

True Anomaly = 1.60Period = 88.28

(_)(kin)

(_)(deg)(_)

* Referenced to Equatorial Radius (6378.16 kin)

(deg)(deg)

(deg)

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2t

TABLE 9

AS-2OA/IM-I LAUNCH VEHICLE OPerATIONAL FLIGHT TRAJECTORY (REVISION i)TRACKING AND T_ETRY STATION COORDINATES: LAUNCH PHASE

STATION

GEODEIIIC IATITUDE(1)

(DEGREES NORTH)

LONGITUDE(1 )

(OF R SresT2ALTITUDE ABOVE

PSOID (Mm'ma)

GLOTRAC

GLO'I_IAC i

Bassett Cove

Atlantic

Grand Turk

Bermuda

28.4-13386 -80.592263 10.95

26.61A552 -78.323580 16.15

34.881507 -76.353AO& 2.92

21.A33765 -71.145032 21.OO

32.254488 -64.838675 87.09

Telemetry

Cape Tel A 28.&63713 -80.653029 O.OO(&)_LA-CIF 28.5&2366 -80.643533 O.OO(A)

Veto Beach(2) 27.666667 -80.350000 O.OO(&)

New SmyrnaBeach(2) 29.066667 -80.916667 O.OO(A)

Powered Flight Ship 31.0OOOOO -63.000000 0.00(4)Grand Bahama 26.62851A -78.299AAA O.OO(A)

Grand Turk 21.446016 -71.IA7500 O.OO(A)

Bermuda 32.3&8102 -6A.6538OO 18.OO

C-Band Radar

MILA 28.A2A862 -80.664404 12.O2

Patrick A.F. Base 28.226553 -80.599293 15.51

Grand Bahama 26.615778 -78.3A7833 13.98

Grand Turk 21.A62890 -71.132114 28.00

Bermuda 32.3A8103 -6A.653801 24.31

Powered Flight Ship 31.0OOO00 -63.000000 0.OO(4)

ODOP

Transmitter (3) 28.444373 -80.579973 5.1&

(1.3.1.7)

Notes:I. All coordinates are referenced to Fischer Ellipsoid of 1960.

2. New Smyrna and Vero Beach receive signal strength only.3. ODOP tracks the S-IB stage during powered flight and after separation from the

S-IVB until loss of track at an elevation of zero degrees.

_. An altitude of zero meters is assumed whenever a value for the actual stationaltitude is not available.

-46-

TABLEiO

•% TAS-20&/LM-I LAL_CH __HIC_E OPERATIONAL FLIGHT TRAJECTORY (REVISION I)TRACKING AND TEI/_ETRY STATION 00ORDINATES: ORBITAL PHASE

STATION

GEODE£I C LATII_DE(1)

(DmR NORTH)LONQI mE(1) ALTITUDEABOVE(l)

Telemetry

Cape Tel & 28. &63713 - 80.653029MILA-CIF 28.5_2366 - 80.6&3533

Grand Bahama 26.62851& - 78.299&A4

Grand Turk 21.&46016 - 71.1475OO

Bermuda 32.3&8102 - 6&. 653800

Antigua 17.137333 - 61.77&955

Apollo Ship (3) 28.OOOOOO - Al. 000OOO

Canary Island 27.7&2797 - 15.598103Ascension - 7.97&314 - i&.39222.1

Tananarive -19 •018056 A7 •30_A

Ship I -27.0OOO00 96.0OOOOOCarnarvon -2A. 897356 113.716067

Hawaii 22.125267 -159.667691

Guaymas 27.958&O6 -110.720792

Corpus Christi 27.655&O0 - 97.380256

0.00 (2)0.00 (2)0.00 (2)0.00 (2)

18.00/_.20oo.oo (2)35.oo29.98

1375 .ooo.oo(2)

6&.O011/.2.00

18.0010.00

C-Band Radar

MILA 28.&2AS62 - 80.66&AOA

Grand Bahama 26.615778 - 78.3_7833Grand Turk ll.&62890 - 71.13211&

Bermuda 32.3_8103 - 6&. 653801

Antigua 17.1&&032 - 61.792859

Apollo Ship (3) 28.OOO000 - Kl. OOOOO0

Canary Island 27.7&4861 - 15 •602000Ascension - 7.95151& - l&.&12606

Pretoria -25.9&3731 + 28.358&90Tananarlve -19.018056 A7 •3OAA&A

Carnarvon -24.897&03 113.716078Woomera -30.8197 28 -136.8369 89

Hawaii 22.122092 -i 59.6653 83

Point Arguello 3&. 582903 -120.561150White Sands 32.358222 -iO6.36956&

12.O2

13.9828. O0

2_.31&9.37

0.OO

36.00152.&3

1622.&O1375 .oo

o2.00151.OO

11&0.00_6.OO

1232. O0

(2)

Notes :i. All coordinates are referenced to Fischer Ellipsoid of 1960

2. A station altitude of zero is assumed when the actual va_e is unavailable.

3. The Apollo ship will track only on the first r_volution _ately afterins ertion.

-47-

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-53- ,-I ,-I

ii 0

I,

_ABL_ 13

AS-20A/L_-I LAUNCH VEHICLE OPERATIONAL FLIGHT TRAJECTORY (REVISION I)

LA_CH VEHICLE PERFORMANCE CHARACTERISTICS

S-IB STAGE

Average Longitudinal Sea Level Thrust (ibs)

_-I Engine _rurbine

Engine #i 203877. 591. 204468.

Engine #2 202227. 655. 202882.

Engine #3 2026_. 630. 203251.

Engine #A 199535. 620. 200155.

Engine #5 202343. 590. 202933.Engine #6 205170. 647. 205817.

Engine #7 202972. 607. 203579.

_gine #8 204036. 597. 204633.

Total Average Sea Level Thrust (F): 1,627,718.

Flight Time Interval: O.O - 139.1_ seconds (IECO)

= [wt (t=o)-wt (t=139.144)-*Wa.x ] / _9.144

= 6266.82 (ib/sec) _aux: Frost ii00 ibs

Seal Purge 6 ibsIsp = F_ Fuel Additive 27 ibs

Total 1133 ibs= 259.7_ (sec)

S-IVB STAGE

High Thrust Level Flight Time Interval:

Low Thrust Level Flight Time Interval:150_S4 _ 475'.75 seconds475.75 - 598.15 seconds

AV_GE VALUES

High Thrust Low ThrustLevel Level

Vacuum Thrust (lbs)Flowrate (ib/sec)

Specific _ulse (see)

223,397- 186,979-52_._ 435.62425.3A A29.23

NOTE: The 0.7% S-IB stage bias, previously mentioned, is notincluded in these data.

-54-

Figure1

AS-20&/LM-I L_UNCH VEHICLE OP_ATIONAL FLIGHT TRAJECTORY (REVISION I)FLIGHT PROFILE: ALTITUDE VS FLIGHT TIME

200000

ALT!TUD(

8

N£

T£R$

FLIGHT T|HE_sS£C

4OO ooo

-55-

Figure 2

AS-20_/LM-I lAUNCH V_ICLE OPERATIONAL FLIGHT TRAJECTORY (REVISION I)

FLIGHT PROFILE: ALTITUDE VS GROUND RANGE

200000

100000

1000000

&ROUND RAN@E_MET[RS

ZOOOOOg

-56-

Figure 3

AS-20_/I/4-1 LAUNCH VEHICLE OP]_qTIONAL FT.TGHT TRAJECTORY (REV_ION I)FLIGHT PROFILE: VELOCrI_ VS FT.TGHT TD4E

V[LO¢!TY

4,14[T[RS/

S[COND

80oo

60O©

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_Entr_

0 ZOO 4OO Ioo

FL|GHT T| HE_sSEC

-5";'-

Figure

AS-20&/LM-I IAUNCH VEHICLE OPERATIONAL FLIGHT TRAJECTORY (REVISION I)FLIGHT PROFILE: SPACE FIXED FLIGHT PATH ANGLE VS FLIGHT TIME

F

LIGHT

PA

TH

120

IOC

8O

6©

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200 400

FLIGHT TIH[**S£C

!

-58-

Figure 5

AS-20_/LM-I L_CH VEHICLE 01_qATI_L FLIGHT TRAJECTORY (REVISION I)FLIGHT PROFILE: EARTH FIXED FLIGHT PATH ANGLE VS FLIGHT TIME

20O

[ARTH

Ir1X[D

irt.1$H

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ANGL[s

DirGItJr£

0

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FLIGHT TIH[VSSEC

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)act.

400

-59-

Figure 6

AS-2OA/I_-I IAUNCH VEHICLE OPERATIONAL FLIGHT TRAJECTORY (REVISION I)

PITCH ATTITUDE STEERING COMMAND: S-IB STAGE FLIGHT DATA

0

\\

o \-60

i \\

-8O

\

\m

o 50 ioo

FLIGHT TIME -- SEC

150

Figure 7

AS-20_/I/_-I LAUNCH VEHICLE OPERATIONAL FLIGHT TRAJECTORY (REVISION I)VEHICLE PITCH ATTITUDE RATE: S-IB STAGE FLIGHT I_TA

P!

T¢H

ATTITUD[

R

AT[4,

D

G

[

¢

g,

-£

1

50,0

FLIGHT TIH£--S£C

1DO.0 150.1

-61-

Figure 8

AS-2OA/LM-I LAUNCH VEHICLE OPERATIONAL FLIGHT TRAJECTO_ (REVISION I)PITCH ATTITUDE ERROR: S-IB STAGE FLIGHT DATA

A

T

T

I

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it

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100.0

IrL|GHT TIM(--S((:

150.0

-62-

Fi&,ure 9

AS-20_/LM-I LAUNCH VEHICLE OPERATIONAL FLIGHT TRAJECTORY (REVISION I)

PITCH ANGLE OF ATTACK HISTORY: S-IB STAGE FLIGHT DATA

5.O

ANGL£

O

ATTA

¢KS4rD[G

It

[

0o

-5.1

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!..... •

\/

100.0

FLI&HT TIH[--S[C

150,0

-63-

Figure I0

AS-20&/LM-I IAUNCH VEHICLE OPERATIONAL FLIGHT TRAJECTORY (REVISION I)

DYNAMIC PRESSURE HISTORY: S-IB STAGE FLIGHT DATA

4000

t

C

$

300¢

o

/

50.0

FLIGHT TIH£--SEC

\

lOO.O 150.0

-64-

AS-20&/LH-I IAb_CH VEHICLE OPERATIONAL FLIGHT TRAJECTORY (REVISION I)L(NG1TUDINALACCELERATION : S-IB STAGE FLIGHT DATA

6O

L0N&!

UD

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ACC£L£

ItAT10N4_

t4

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t.!!0 S0.0

FLI&HT TIH[--SEC

I00.0 150 .o

-65-

Figure 12

AS-2OA/LM-I LAUNCH VEHICLE OPERATIONAL FLIGHT TRAJECTORY (REVISION I)PITCH ATTITUDE STEERING COMMAND

S-IVB STAGE FLIGHT DATA

-_o

-6o

-8O

-i0o

inl%la_q _IGM

1

_.hi/'t _erLseO

By IGM

600

FLIGHT TIME -- SEC

-66-

Figure

AS-20&/IM-I LAUNCH VEHICLE OPERATIONAL FLIGHT TRAJECTORY (REVISION I)YAW ATTITUDE STEERING CGMMAND: S-IVB STAGE FLIGHT DATA

!

1

-5.

½

200 400 600

FLIGHT TIME -- SEC

-67-

Figure Ih

AS-20A/124-1 IAUNCH VEHICLE OPERATIONAL FLIGHT TRAJECTORY (REVISION I)

LGNGITUDINAL ACCELERATION: S-IVB FLIGHT DATA

3O

LoN

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[L[

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M/$ IC

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FLI6HT TIN[--S£C

-68-

FiEure 15

AS-20&/LM-I IAUNCH VEHICLE 0PERATIONAL FLIGHT TRAJECTORY (REVISION I)

VEHICLE ATTITUDE RATE: S-IVB STAGE FLIGHT DATA

-'I

ATTiTUDr

RA

r

D£G/

C

_ Pitch

• -- Yaw

- L

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Thrusl

IS0

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-69-

Figure 16

AS-2OA/LM-I IAUNCH VEHICLE OPERATIONAL FLIGHT TRAJECTORY (REVISION I)

ATTITUDE ERROR: S-IVB STAGE FLIGHT DATA

A

T

T

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-- Yaw

/

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140 160

FLI&HT TI HK.,sSEC

180

70-

Figure 17

AS-20&/LM-I IAUNCH VEHICLE OPERATIONAL' FLIGHT TRAJECTORY (REVISION I)*ANGLE CF ATTACK: S-IVB STAGE FLIGHT DATA

tO

ANGL[

0

aTTA

CK

D[¢;R[[

1(

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rYaw

+ = ; = : ,

P:L't,;ch

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140 160

FL|GHT T|M[**S[C

1110

-71 -

Figure 18

AS-2OA/LM-I IAUNCH VEHICLE OPERATIONAL FLIGHT TRAJECTORY (REVISION I)DYNAMIC PRESSURE: S-_VB STAGE FLIGHT DATA

300

fi

[_L........

Z

200

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140 160

FLI&HT TIM£**$£C

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-72-

AS-_&/IM-I IAUNCH VEHICLE (I_ERATIONAL _ TRAJECTORT (REVISION I)ALTITUDE HISTORY: ORI_L PLIDHT

_10000

200000

|TO000

,°.

"-?3-

F_m,-" 2O

AS-20&/LM-I LAUNCHVENICLE OPERATIONAL FLIGHT TRAJECTORY (HEVISIGN I)

SPACE FIXED VELOCITY HISTOI_: ORBITAL FLIGHT

T640

T830

7620

T810

TSO0

I_ TT90

r..)

u)

TT80

TTT

TTSO

1

t

£000

i.

i

/ q4000 6DO0 80(]0 10000 lz0n0

FLIGHT TIHE - SEC

14000

-'7'4 -

120

8O

•o_ /

2 bOO 4 ,00 61 DO

n=

n.,- 40

8_ O0 lOq O0 1£1 O0 141 O0

-00

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q

-160

FLIGHT TIME - SEC _J

Hr_

0

OoE-4u'x

_N_°

_8

OZ

0!

0

b

b,O

ii1P

,-76-

I I

<-, _i

__ •

_1<"° ° =l'< _i

--/'7-

APPENDIX A: "LAUNCH VEHICLE CHARACTERISTICS"

-78-

TABLE 1A

AS-2OA/LI-I IAUNCH VEHICLE (PIRATIGRAL FLIGHT TRAJECTORY (REVISION Z)V_tlCLE b_I_.ZT _KIX_NN

(eO_)

Spacecraft *Instr_ent Unit

S-IVB St_p DryS-I_ Resid.als

Useable Reserve Propellant (Includee FPR)

InJecti_ Weight

J-2 Thrust Deca7 Propellant and I_ VentingS-IVB Cutoff Weight

S-IVB Pr_ellant C_mmedS-IVB APS Propellant Ccr_mwdUlla_e Oases

S-DrS "90% Thrust" Weight

S-IVB GH2 Start Tank

s-D3 _A_ P_epenaatC_s_Ullap Propellant C_,_edS-IVB Det_aticm Package

S-I_ Stage Weight at Separation

S-I_ Aft Fraae Hardware

8-IB/S-I_B Interstage

S-IB Dry WeightS-IB Resld_ and ReserTes

S-ITB Freer Co_ed8-]3 Frost CQnsunods-IB Seal _ Cc,..me_S-IB Fuel Additive Cen_

S-IB Gearbex labrieant Cenamaed

Inboard Engine Thrust Deea7 Prpt Cmm_

Outboard ]b_gine That DeeaT Prpt CmsmmdTo Separation

8-IB Mainatage Prepellant Cms_ed

Vehicle Liftoff _eight

t SIA 3,95e

lariat Med_te 31,325106

Nose Cone

36,3_2_,6oo

2,k50

22&,9766

1765

31

6.,65&85,317

i0,8_3i00

I,_(X)62771A

2,1_J

70,205

'?0,/_.6

295,6&3

296,218

1,2S5,0_

--79-

Z

uJ

_fw

I

C3

U

-JUJ' I

_IJ 7 _I"I

j L'-3I_

_J _

LL _91

{-J

V_ i

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Z

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T.J

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m ¸

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I I (..9

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7L)

IX

"T_ L2

_ _1_ _

14-

!

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- 0!4"

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] _'"_ _" _ I_ _ ,_4 _ i_t _" i_-_

• • i • o • • • • • • • • e •

_MiO 12':I '_- l%1 4" U_ 0"I...4 O_ tKl_ .1" _

.......... 1...... ' .... i......f_- _" _Jo1<J _J _'_ ,._ _ _ _o 01_'_ O_ i.-_ _',U _

i

o.o. =,ooIoo_o oc olo o,o _c oc !c o:o oc c o c:

...... ._ . .,!......... f-/-.'/; ,'_;__...''I , i , i t i _ i I _ii i i i i]," i , _ , :ii

i I: i _i n i

I _o.o. qoh-oo.o, ooo!ooo _ooo-oooooo_,:=__

go t .... _ •

..... to"g:g gig g_ o o g!g glo :I_ olo _":c:, _ C, o_o _ c- o C o!o o

, L i ] ,

_ _ _'_ _ _' _, _ _ _ _' _1 _ _ _ _ _'_ __ %1_ _

t I

.... _ '1"_ N .... _

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AS-20_IA-I IA_CH VEHICLE 0PERATICRAL FLIGHT TRAJEGTORY (REVISICffI)ORBITAL _ SEQU'_CE AND _E HISTQRZ

_*T_..GHTTIH (Hr:l[i.:See)

00:09;59

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02:31:39

03:S7:o2

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01:52:28 _ O.

02:31:29 I=g]E=E 7560.*

03:1A:16 _ •O.

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Propellant D__erlment

-85-

Figure 1A

AS-2OA/LM-1 IAUNCH VEHICLE OPERATIONAL FLIGHT TRAJECTORYVEHICLE PROFILE

21 .778" SPHERICAL RADIUS

(REVISION

tNOSE CONE

STA

2170.570

TELEMETRY

SLA

8 ° 58'

RANGE

ANTENNA

HORIZON SEN'.

HELIUM

TUNNEL

ULLAGE ROCKETS

RETRO ROCKETS

COMMANDAN

STA

2034.859

HINGE COVER SPACECRAFT

STA

1781.30

ANTENNA

STA 1698.859

INSTRUMENTATION UNiTJ

TUNNEL

STA

1662.859

-- 260"

[LIARY PROPULSION

UNITS

GIMBAL

STA

1086. 157

--L STA

935. 304

TELEMETRY ANTENNA

S-IVB STAGE

ONE (I)200K THRUST

J-2 ENGINE

STA

962. 304

257" FULL SCALE

S-IB STAGE

EIGHT (8) 200K THRUST

H-I NGINES

GIMBAL

STA

100. 000

STA

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AS-20&/LM-I LAUNCH VEHICLE OPERATIONAL FLIGHT TRAJECTORY (REVISION I)H-I _INE THRUST DECAY

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-87-

Figure 3A

AS-2OA/LM-I LAUNCH VEHICLE OPERATIONAL FLIGHT TRAJECTORY (REVISION I)J-2 ENG_IE THRUST BUILDUP

THR

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--88-

Figure _A

AS-20&/IM-I IAt_CH VEHICLE OPERATIOHAL FLIGHT TRAJECTORY (REVISION I)

J-2 _IOINE THRUST DECAY

100000

II

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-89-

Figure 5A

AS-2OA/LM-I LAUNCH VEHICLE OPERATIONAL FLIGHT TRAJECTORY (REVISION I)

AVERAGE MEAN HFADWIND/TAILWIND PROFILES_ AND OCTOBER

200000

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-90-

, APPEal1 B: "t_JII_AI_E P_,ESETTINGS"

-91 -

TAELE 1_

AS-20_/IR-I _UNCH VEHICLE OPERATIONAL FLIGHT TRAJECTORY (REVISION I)

S-IB STAGE ST_RING PROGRAM

Fo£ the ti:_ segment t- T1 _<I0:

Xy = 0.

Xz = 0.

Xx = -0.3141_-9 tad. (-18. degrees)

For the time segment 10<t- T1 <-47,:

Xy = A0 + AlxT + A2xT 2 + A3x_S

A0 = -.655727 x I_-z radians

A1 = .225645 x IC-a radians/second

A2 = -.17_025 x 10-3 radians/second2

A3 = .472717 x 10 -6 radians/second 3Xx = Xz = C.

Fcr t"

×y

Xx

[me segment &7<t - T1 _96:

= B0 + £IxT + B2xT a + B3xT s

B0 .... .774282_ x 10-* radians

BI = -.945599 x 10 -3 radians/second

B2 = -.161445 x 10 -3 radians/seconds a

B3 = .858421 x 10-6 radians/secondS= Xz = C.

For the time segment 96<t - T1 $133:

Xy = C0 + CIxT + C2xT 2 + C3xT 3

CO = .489574 x 104' radians

CI = -.142762 x I0%O radians/second

C2 = .123205 x I0 -z radians/second r

C3 = -.371469 x I0 -s radians/second sXx = Xz = 0.

For the time segment t - T1 >133:

Xy = -1.037239 radians

Xx = Xz = C.

NC TE :

Xy :

T

t:

TI :

Pitch attitude ancle measured negative downrangefrom inertial v .... =al

t- TI ÷ NGZDT

time frcm GH_

time of liftoff (Time Base I), approximately 0.2seconds after -irst motion

:;GZD_: Bias to account for system delays

-92-

TABLE 213

AS_20_/LM- 1 IA(_iCH VEHICLE (PERATIabIAL FLIGHT T_aECTORY (_ISION I)

S-IB STAGE PITCH ATTITUDE C(_AND

,FLIGHT_I_ (S_)

01012

161820222&262830323_3638&OA2

_6

50525A56586O626_666870727_76?e80

PITCH ATTITUDE

,_SD, ,_ (Dm_

O.0000O.OO00

-O. 2712

-0.5231-0.8643-1.2367-1.6956

-2.2200-2.8115-3 ._65S-_.1816-_.9606-5.?985-6.69A2-?.6_9-.8.658?-9 .?225

-10.8413-12.O113-13.231_-IA._068-15.586A-16.8176-18.0611-19.31_1-20.5?4.2-21.8394.-23.1071-26.374.9-25.61_-26.9015-_.1558-29.4OO5-30.6337-31.8532-33.0558-34..2399

,FLIC,_ PITCH ATTITUDE

.COMM_ND,Xc (D_J._

82 -35.4.03384 -36.54.2086 -3? .6564.88 -38.7_259O -39.?97192 -_O.81%94. -_1.80_96 -_2.755898 --iS .7211

lO0 -4_.6279102 -_5 ._819iO_ -4.6.2958106 -47.07%108 -_7.8&193_lo -_3.59J_,112 -A9.3A68ll& -50.1096116 -50.8927118 -51.7058120 -52.5610122 -53 ._66612_ -5_._J23

126 -55 ._717

128 -56.591813o -5? .8o21132 -59.1178134. -59.A29A

IC,M InitiAtiom -59._.294.

-93-

TABI _:_ 3B

AS-20&/IM-1 _UNCHVEHICLEOP_ATI(RAL FLIGHT TRAJECTORY (REVISION I)IG_ PRESE_qING5

IV_C INITIAL

SYY. FOL VALUE UN_TS_.

Tli

T3i

73

17. sec

316.8 sec

111.7 sec

271.0 sec

Vex I 4 151.00 m/see

Vex3 4221.00 m/sec

T

XVT

YVT

ZVT

iVT

_VT

YqG_

7821.494 _/sec

6535586.

0.

0.

0.

o

782 _. 494

-9.332

Q

0.

m

m

n_/sec

m/sec

m/sec

m/see2

_ ,:.SC l]IP_ ON

TiFe frc_ ti_e _ase 3 to initiate IGM

guidance

Tine tc ge fcr first iGZ stage

Ti._;e tc gcfcr aeccnd IGZ stage

Average value of m/_1 at initiation of

second IGM stage

Average exhaust velocity (go x Isp) for

Ist IGM stage phase of flight

Average exhaust velocity (go x Is_) fcr

2nd IGM stage phase of flight

Guidance cutcff signal (GCS) criteria.

Terminal velocity for IGM equatiens

Desired terminal position vector

co_cnents in IGM coordinate syste_

Desired cutcff velccity comFonents in

IGZ coordinate system

Terminal gravitation vector components

in IGM coordinate syste_

--94-

TABLE 3B (Cont'd)

,s-_/u_-z m_CH V_UCL_ Omm*TZUaL FUGnT _ma_O_ (_mZ_ Z)IGM P_S_TTINGS

LVDC I '.'TI AL

SYMBOL VALUE UNITS

15. sec

--- 3" sec

Tr I I. 8 N/D

Tr2 O. N/D

_r3 O. N/D

--- 200. sec

T2 O. sec

A_NCM R-ASTR sec

_LD O. N/D

-.42666501 !E+O0+.49514778 E-01

+.gO30532r E+O0

-.418295.3 ,E-e2+.89838143 _E+O0

-.56717968 iE01-.90440002 IE+O0

-.27976999 IE-01-.42576733 .);:+CO

257. s- -

APt

AP3

_4

AP5

:,_6

AP7

_P8

A_9

YL,.S 2. N/D

DESCRI PTI C_,_

value of T3i to initiate IGM _V

Value of _3i to freeze IGE (6')

guidance

Mission dependent constant multiplier

for terminal range angle equation

Mission dependent constants for N3

and N4 equations

Time to initiate thrust misalignmentcorrection

Terminal steering time argument

Nominal com_utation cycle length

IGM staging flag (Eurn switch)

Transformation

coordinate system to

coordinate system

AZ = 72.

_L = 28.531856

@N = 119.0548

i = 31.6143

matrix from navigation

the (X4, Y4, Z4)

_fime from time base 3 to sample F/_

for IGM staging (Approximately 7C sec.

prior to noEinal IGM staging)

Number cf F/M decreases required for

IGM staging criteria

-95-

AS-2OA/IR-1 IAt_CHVEHICLE.OPERATIGKAL FLIGHT TRAJECTC_Y

IG_, _SETTINGS

(REVISION I)

LVDC

SY_ECL

_CC

71C

INITIAL

VALUE

0.01

UNITS

z/secZ

316.8 sec

AC 495.8 sec

A1 - 1.22 N/D

PCO 60. sec

mlC 555.888 ec

CC 35. sec

_02 1309_].96 kg

,,I 242.264 kg/sec

_3 199.427 kg/sec

DESC31PTICN

F/E c_:z_ariscn tolerance for IGM

staging

Constants for updating seccnd stage

time-tc-gc for perturbed E2R shift

Backup

Itime for IGM staging

'Constants for artificial T3 mode

time

-96-

TAN_ hB

AS-20&/LM-I LAUNCH VEHICLE OPERATICHAL FLIGHT TRAJECTORY (REVISION I)ORBITAL ATTITUDE MANEUVERS

IeI/GRT TIME

00:09:58 59e

O0:lO'_J 6A3

00:11:28 688

O0:i?:58 1198

00:50:00 3000

00:53:55 3Z35

O0: 56: 55 3415

01:31:25 5485

01:h5:55 6:355

02:20:38 8&38

02:36:38 9398

04:30:00 16200

DESCRIPTION

Maintain cutoff inertial attitude for 90

seconds after initiation of time base four

Jettison nose cap.

Initiate pitch maneuver to align S-1VB/(LM)with local horizontal and maintain [(LM) for'_rd_pobition I do_ ] with respect to local reference.

Deploy SEA panels.

Initiate maneuver to attain separation inertial

attitude. Inertial attitude specified by pitch

+_.i °, yaw -0.9 °, roll 0 ° with respect to GRRinertial reference.

Nmminal (LM) separation.

Initiate maneuver to align S-IVB with local

horizontal and maintain (SLA forward/position

I down) with respect to local reference.

Initiate inertial attitude hold using gimbalangles at specified initiate time. Maintaininertial attitude.

Initiate pitch maneuver to place S-IVB in retr_

attitude with roll axis aligned along localhori=c_tal. Maintain with respect to localreference.

initiate maneuver to pitch to 2"/0 ° and maintainwith local horizontal.

Initiate maneuver to pitch to local hori-z_tal (retro-attitude position I up) andmaintain throughout rllainder of flight.

S-IVB loss of attitude control capability.

--97-

APPENDIX C: "lAUNCH VEHICLE TRAJECTORY LISTINGS, ENGLISH UNITS"

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W. H. Mann, Jr.

L. L. McNair R-AERO-P

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(18C and I reproduciSle)

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