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REFERENCE TRAJECTORY PROFILE

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~:~. NATIONAL AERONAUTICS AND SPACE ADMINISTRATIO~ . :588~ .'................... MSC INTERNAL NOTE NO. 68-FM-269

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N74-71962

Unclas1673400/99

MANNED SPACECRAFT CENTERHOUSTON,TEXAS

Lunar Mission Analysis Branch

and

Orbital Mission Analysis Branch

MiSSiON PLANNiNG AND ANALYSIS DIVISION

(NA;JA-TM-X-69977) APOLLO MISSION Fw~~CE~~AFT~liEFEhENCE TRAJ~CTOBY. VOLUME 1:~~~E~~NCt ~nAJECIOdY PEOFILE (LAUNCHED 14AJGD~~ 196~) (NASA) 103 p

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MSC INTERNAL NOTE NO. 68-FM-269

PROJ ECT APOLLO

APOLLO MISSION F SPACECRAFT REFERENCE TRAJECTORYVOLUME I - REFERENCE TRAJECTORY PROFILE


By Lunar Mission Analysis Branch andOrbital Mission Analysis Branch

October 28, 1968

MISSION PLANNING AND ANALYSIS DIVISION

NATIONAL AERONAUTICS AND SPACE ADMINISTRATION

MANNED SPACECRAFT CENTER

HOUSTON, TEXAS

Approved: jJL~d ';C. A.e.;r~~~L. Berry, Chief 7Lunar Mission Analysis Branch

Approved:~~ et: J!~'''~I---__fa~Lineberry, Chief .-1Orbital Mission Analysis Branch

/1 /7 /J 11, I

CONTENTS

Section Page

l.0

2.0

SUMMARY., ••

INTRODucrrON

": I .

1

2

3.0 DATA USED 'IN 'THE GENERATION"OF 'ri'liE FMISSIONREFERENCE TRAJECTORY • • • • .' • • • • • • • •

4.0 REFERENCE MISSION PROFILE DESCRIPTION'

4.1 LM-active RendezvouS Phase. •4.2 CSM-act1ve 'Rendezvous Phase".4.3 Transearth Phase••• ••••

5.0 REFERENCE TRAJECTORY EVALUATION • •

REFERENCES • • • • .' • • • • : • • •.• ' •

iii

2

368

8

94

Table

I

II

TABLES

., .SEQUENCE OF MANEUVERS FOR 1M-ACTIVE RENDEZVOUS

P1i.A.SE . • . . • • • . • • • • • ,_ .• • • • • •

SEQUENCE OF MANEUVERS FOR CSM-ACTIVE RENDEZVOUSPIiASE . . . . . . . . . . . • • . . . . . . .

Page

9

10

III MISSION RADAR TlMELINE.

(a) Docki~g to TEl initiation(b) Transearth phase . •

IV MISSION SHADOW TlMELINE.

(a) Docking to TEl initiation(b) Transearth phase . . . • . .

iv

1111

1313

Figure

1

2

3

4

5

6

7

8

9

10

11

12

13

14

FIGURES

Relative motion (curvilinear, CSM-centered) forLM-active phase of Mission F .. •.....

Time history ofLM-to-CSM elevation angle for1M-active phase of Mission F . . '.. . ..

Time history of CSM-to-1M elevation angle. forLM-activephase of Mission F . • .....

Time history of CSM-LM-sun angle for LM-activephase of Mission F . . .

Time history of vehicle-to-vehicle range for1M-active phase of Mission F . .

Time history of vehicle-to-vehicle range rate forLM-active phase of Mission F

Time history of CSM lead angle for LM-activephase of Mission F . . . . .

Relative motion (curvilinear, 1M-centered) forCSM-active phase of Mission F . . . . .

Time history of LM-to-CSM elevation angle forCSM-active phase of Mission F . .. ...

Time history of CSM-to-LM elevation angle forCSM-active phase of Mission F . . • . .

Time history of LM~CSM-sun angle for CSM-activephase of Mission F . .

Time history of vehicle-to-vehicle range forCSM-active phase of Mission F

Time history of vehicle-to-vehicle range ratefor CSM-active phase of Mission F

Time history of LM lead angle for CSM-activephase of Mis sian F .. . . ...

v

Page

14

15

16

17

18

19

20

21

22

23

24

25

26

27

Figure

15

Page

Time histories of trajectory parameters for thetransearth injection phase.

(a) Inertial velocity versus time from TElinitiation. . . .. ..... 28

(b) Selenographic altitude versus time fromTEl initiation . . . . . . . . . . . 29

(c) Selenographic flight-path angle versus timefrom TEl initiation . . . . . . . . . . . 30

(d) Vehicle pitch angle (local horizontal coordinatesystem) versus time from TEl initiation 31

(e) Vehicle yaw angle (local horizontal coordinatesystem) versus time from TEl initiation 32

(f) SPS propellant used versus time from TElinitiation . . . . . . . . . . . . . . 33

16 Trajectory parameters as a function of launch azimuthfor lift-off on July 15, 1969.

(a) TEl tN • . . . . . . . · · . 34(b) TEl plane change . . . · . · 35(c) SPS propellant used for TEl 36(d) Inclination of powered return 37(e) Transearth flight time · . · . 38

17 Trajectory parameters as a function of launchazimuth for lift-off on July 16, 1969.

(a) TEl t:.V . . . . . . . . . . .(b) TEl plane change . .. ..(c) SPS propellant used for TEl(d) Inclination of powered return(e) Transearth flight time ....

18 Trajectory parameters as a function of launchazimuth for lift-off on July 18, 1969.

(a) TEl t:.V . . • .. .....(b) TEl plane change . . . . . .(c) SPS propellant used for TEl(d) Inclination of powered return(e) Transearth flight time ....

vi

3940414243

4445464748

Figure

19 Trajectory parameters as a function pf launchazimuth for lift-off on July 22, 1,969.

Page

20 Trajectory parameters as a function of launchazimuth for lift-off on August 14, 1969.

(a)(b)(c)(d)(e)

(a)(b)(c)(d)(e)

TEl /:;V . . . . . . • . . . .TEl plane change . . . . . .SPS propellant used for TElInclination of powered return . . • .Transearth flight time . .'. .'. .

TEl ~V • • It It It • • It It • • It

TEl plane charige . . . • . . .SPS propellant used for TElInclination of powered ~eturn

Transearth flight time . • • . • .

. . .

4950515253

5455565758


(a) TEl /:;V . . . . . . . . · · · 59(b) TEl plane change . . . · · · . . 60(c) SPS propellant used for TEl . . 61(d) Inclination of powered return 62(e) Transearth flight time · · . · , 63


(a) TEl /:;V • • • • • • • • • • • •(b) TEl plane change . . . . . . . •(c) SPS propellant used for TEl(d) Inclination of powered returp(e) Transearth flight time ....


6465666768

TEl plane change . . . . . .SPS propellant used for TElInclination of powered returnTransearth flight time . . . .

r _ ,\CJ./

(b)(c)(d)(e)

TEl Anu v • 6970717273

vii

Figure Page

24 Trajectory parameters as a function of launchazimuth for lift-off on September 13, 1969.

(a) TEl 6.V .(b) TEl plane change . . .. .(c) SPS propellant used for TEl(d) Inclination of powered return(e) Transearth flight time ..•..


(a) TEl 6.V. . .(b) TEl plane change . . . . . .(c) SPS propellant used for TEl(d) Inclination of powered return(e) Transearth flight time .


(a) TEl 6.V . . . . . . .. ..(b) TEl plane change. . ...(c) SPS propellant used for TEl(d) Inclination of powered return(e) Transearth flight time ...


(a) TEl 6.V. .(b) TEl plane change .(c) SPS propellant used for TEl(d) Inclination of powered return(e) Transearth flight time ....

viii

7475767778

7980818283

8485868788

8990919293

c'

APOLLO MISSION F SPACECRAFT REFER'ENCE TRAJECTORY

VOLUME I - REFERENCE TRAJECTORY PROFILE


By Lunar Missiop Analysis Branch andOrbital Mission Analysis Branch

1.0 SUMMARY

This volume, Volume I, in, combination with Volumes I and II of theMission G reference trajectory and Volume II of the Mission F referencetrajectory, is a detailed reference mission profile for one typicallunar orbit mission launched on August 14, 1969. The launch azimuth is720 and translunar injection occurs over the Atlantic Ocean during thesecond revolution of the earth parking orbit.

The mission phases from launch through descent orbit insertion inlunar orbit are essentially the same as those in the Mission G referencetrajectory and, therefore, are not described in this document. Theprimary emphasis of this document is on the lunar orbit operations whichinclude a LM-active rendezvous and a CSM-active rendezvous, since theseare the phases which differ most significantly from Mission G. Thelunar orbit operations are related to the same lunar site, II-P-2, asthe Mission Greference trajectory (Volumes I and II).

Since there is no lunar orbit plane-change maneuver by the CSMwhile separated from the 1M, as there is for Mission G, the transearthinjection and transearth coast phases differ slightly from Mission G.For this reason data are, shown for these phases for the August 14, 1969,72° launch azimuth mission, and for the other launch days and launchazimuths being considered for the third quarter of 1969.

This reference trajectory satisfies all of the mission-relatedtest objectives for MissIon F.

2

2.0 INTRODUCTION

This volume presents the Mission F profile for the first launchopportunity, 72° launch azimuth, first injection opportunity onAugust 14, 1969, and transearth phase scan data for the other launchopportunities being considered for the third quarter of 1969.

I

Since Mission F differs from Mission G only in the lunar orbitoperations and transearth injection, the tables and figures of thisvolume present data only for these mission phases. A complete traj ectory listing is presented in Volume II on the Apollo Mission Freference trajectory (ref. 1).

The ground rules and guidelines used in the design of the referencetrajectory are defined in reference 2. The spacecraft weight configuration and vehicle performance data are the same as used in the G missionreference trajectory (refs. 3 and 4) with the exception that, for theLM maneuvers, the LM ascent propellant tanks are half loaded.

3.0 DATA USED IN THE GENERATION OF THEF MISSION REFERENCE TRAJECTORY

The primary input used in the computation of the Mission F referencetrajectories can be obtained from the following sources:

Input

Mission objectives ..Mission constraints and ground rules.Nominal LPO timeline ..ReS and consumables budget.Vehicle characteristics:

CSM weights . . . . . . .CSM performance properties.LM weights. . . . . . . . . .LM performance properties .

Ground support facility positionsand capabilities .•....

Lunar landing site positions.Standards and constants . . .

Reference no.

5b, 7

89

10111012

13, 1415, 16

17

•

3

4.0 REFERENCE MISSION PROFI1E DESCRIPTION

This section provides a brief summary of each phase of the referencemission from 1M-active rendezvous through transearth coast. The othermission phases are identical to those found in the Mission G referencetrajectory (refs. 3 and 4) .

4.1 LM-active Rendezvous

Since several significant changes have been made to this phase sincethis volume was generated, the data in this document should be consideredas only roughly representative of the most recent profile. 8ee reference18 for a description of these recent changes.

Figures 1 through 7 present a description of the (manned) 1M-activephase of Mission F. In brief, the phase occurs in lunar orbit andconsists of a nominal Hohmann descent sequence and a nominal in-orbitascent-tc;,-rendezvous sequence, the two secluences separated by a phasi~g

period. '

.One of the primary objectives of Mission F is to demonstrate all

phases of Mission G except those directly. involving the ":J}.j powereddescent and powered ascent. Relative to the 1M-active phase, thisobjective is accomplished by incorporating between the Hohmann descentand the in-orbit ascent approximately one revolution,'during which therequired adjustment in CSM lead angle is made. This phase angle adjustment is at least approximately 22.5°, since the CSM trails the 1M at theend of Hohmann descent by approximately 7° and must lead the 1M atnominal 1M insertion by approximately 15.5°.

As in Mission G, the LM-active phase begins with the C8M/1M dockedconfiguration in a 60-n. mi. circular lunar orbit. The 1M activities(including 1M/CSM separation) prior to the Hohmann descent are performedas in Mission G. The descent orbit insertion (DOl) is performed by adescent propulsion system (DPS) burn (71.6 fps, horizontal, retrograde)1950 prior "to the landing site so that the resulting pericynthion(50 OOO-ft altitude) occurs 15° prior to the landing site, the positionat which the powered descent is initiated in Mission n. For Mission F,however, a second 1M maneuver is performed approximately 7.2 minutes(23.5°) past pericynthion, or approximately 2.5 minutes (8.5°) past thelanding site. This second LM maneuver is a DP8 burn of 172.4 fps(horizontal, posigrade) designed to establish at the resulting 1M perieynthion a C8M lead angle equivalent to that which occurs at nominalpowered ascent cutoff in Mission G. This second maneuver is referred to

4

in this document as phasing. Since phasing is performed approximately23.5° past the original pericynthion, the resulting pericynthion occursabout 16° past the original pericynthion (or approximately 1° past thelanding site). The apocynthion altitude of the phasing orbit is195.2 n. mi., which affords the required CSM catch-up time betweenphasing and the resulting pericynthion. The CSM lead angle is approximately _9° at phasing and 15.5° at the resulting pericynthion. Theresulting pericynthion altitude is approximately 60 000 ft, which is

the nominal altitude at powered ascent cutoff for Mission G. Just priorto this resulting pericynthion, the 1M descent stage is jettisoned. Thenat pericynthion an ascent propulsion system (APS) maneuver of 207.6 fps(horizontal, retrograde) is performed to establish the equivalent of thestandard 1M insertion orbit (30- by 9.9-n. mi.) of Mission G. Thismaneuver is referred to as insertion. At completion of insertion, theconditions are equivalent to those at powered ascent cutoff forMission G, except that the LM ascent stage is considerably heavier sinceonly a relatively small amount of APS propellant has been utilized.

Following insertion, the nominal LM in-orbit ascent profile(essentially the same as presented for Mission G) is followed. Table Ipresents information for each of the maneuvers during the LM-activephase.

In table I, the ~t's in column 2 are the elapsed times between theimpulsive times of the burns. An ullage 01' approximately 2 fps fromthe pressurized RCS is required for each of the listed LM maneuvers(column 3) which utilizes a propulsion system other than the pressurizedRCS. (The pressurized RCS utilizes propellant from the pressurized RCStanks.) The notat ion "DPS (FT)" indicates that the DPS goes to full thrustafter 26 seconds at 10 percent thrust. The notation "RCS (intc.)" indicates RCS thrusting utilizing APS propellant through the interconnect.The 6V (column 4) for TPF is the theoretical value for the impulsive velocity match, and the other values (burn duration and 6t's) relative to theterminal phase finalization are based on a theoretical impulsive TPF.The burn durations in column 5 for the DPS and APS burns are the burndurations for the main propulsion system; i.e., the RCS ullage times arenot included. However, for the RCS (intc.) burns the ullage times areincluded in the listed burn durations. The burn durations are based ona LM loading at earth launch equivalent to that for Mission G (totalLM = 33 053 lb, 1M ascent stage = 10 729 Ib). The burn attitude(column 6) is measured counterclockwise from the local horizontal in thedirection of motion to the direction of the impulsive 6V vector. Wherethe RCS is not the main propulsion system, the indicated RCS thrusterusage (column 7) refers to ullage.

Additional profile information is presented in the figures. Itis noted that the segments of the curves from insertion to TPF areessentially the same (except for time reference) as the insertion-to-TPFcurves in reference 3.

•

5

Figure 1 is a relative motion profile (curvilinear, CSM-centered)from DOl to TPF. The darkness periods (for CSM) and 10-minute timeticks relative to DOl are indicated.

Figures 2 through 7 present time histories of various relativeparameters time-referenced from DOl. In each of the figures, themaneuvers and darkness periods are indicated.

Figures 2 and 3 are time histories of the LM-to-CSM elevation angleand the CSM-to-1M elevation angle, respectively. Figure 4 provides thesame information for the CSM-LM-sun angle. Elevation angle is definedas the angle (measured counterclockwise) from a vehicle's local horizontal in the direction of motion to its line of sight to the applicableobject (the other vehicle or the sun).

Time histories of vehicle-to-vehicle range, range rate, and centralphase angle (CSM lead angle) are shown in figures 5., 6, and 7, respectively. From figure 5. it can be seen that throughout the total profilethe range (between the CSM and LM) does not exceed the rendezvous radarlimit of 400 n. mi.

A 10° sun elevation angle at the time of the first (separated-1M)pass over the landing site was assumed for the mission profile. Thissun elevation is the mid-point value of the current limits on sun elevation at landing for Mission G (3° to 17°). Although a 10° sun elevation at landing was also assumed for the Mission G profile, TPI isperformed 5. minutes prior to darkness for Mission F so that the ~t frominsertion to TPI is 12 minutes longer than the corresponding ~t forMission G.

All of the LM maneuvers prior to the rendezvous terminal phase arenominally horizontal burns. In addition to the economical factor(which applies for all the horizontal maneuvers), the horizontal thrustingis incorporated for phasing, insertion, and CSI due to safe-pericynthionconsiderations.

A major consideration in designing the ~t from DOl to phasing wasto incorporate a value which would result in approximately a 60 OOO-ftpericynthion altitude for insertion. For example, if phasing were tooccur approximately 3 minutes later than the time specified, theresultir~ pcricynthion altitude would be approximately 2 n. mi. abovethe desired value. In addition to yielding the 60 OOO-ft pericynthionaltitude, the incorporated DOI-to-phasing ~t affords a free-flight lookat the landing site area prior to phasing.

6

4.2 CSM-active Rendezvous Phase ~

There have been several significant profile changes for the CSM-activerendezvous phase since the data for this volume were generated. For themost recent profile see reference 19.

The presented rendezvous profile is essentially applicable for anysimulated landing site or for any translunar time, or both. Since theground elapsed time (g.e.t.) for initiation of the profile would varyfor the different landing sites or different translunar times, or both,the profile's maneuvers are referenced to ground elapsed time only fora specific trajectory. The phasing maneuver (the initial separationmaneuver following the undocking) occurs about 13 hours after dockingat completion of the 1M-active rendezvous. The time references shownfor each maneuver in table II are the ilt from the phasing maneuver andthe ilt from the previous maneuver.

Prior to the CSM-active rendezvous the docked configuration(CSM/LM ascent stage) is in the nominal 60-n. mi. circular orbit. Theprofile begins after the crew has set the LM in the selected attitudemode, unmanned the 1M, and undocked. The selected attitude mode hasnot yet been determined.

The NCC/NSR sequence was selected instead of the CSI/CDR sequencefor two related reasons. The phasing and coelliptic maneuvers necessarilyhave to be ground-computed for either sequence since there is no onboard(CMC) solution capability; however, the NCC/NSR sequence requires onlytwo maneuvers (NCC and NSR) prior to terminal phase, whereas theCSI/CDR sequence would require three maneuvers prior to terminal phase,since CSI could not be used as the separation maneuver.

The phasing maneuver (NCC) is targeted to establish 90 minutes lateran offset [ h = 10 n. mi. (CSM above) and il8 (LM central leadangle = -2.89°] at which the coelliptic maneuver (NSR) is to occur. Thephasing maneuver is a near-radial-down SPS burn of 71.2 fps and 4.0-secondsburn duration. As a result of the total selection of parameters,this maneuver occurs about 54° east of the landing site. The perigeealtitude of the orbit between the phasing and coelliptic maneuvers is42 n. mi. The profile's maximum relative range of about 67 n. mi. alsooccurs during this phase. The coelliptic maneuver is an SPS burn of36.1 fps and 2.0-seconds burn duration; the LlV-vector is about 15°below the positive horizontal; and the maneuver occurs about 27° east ofthe landing site. The ilt between the coelliptic maneuver and TPI isapproximately 38 minutes. TPI is a near-line-of-sight-thrusting SM Resburn of 15.6 fps and 43.4-seconds burn duration. The TPI elevationangle utilized is 206.6° (or _26.6°). TPI occurs approximately at themid-point of darkness about 2° east of the landing site. A 130°terminal phasing is incorporated, and the CSM approaches from above.The theoretical values for TPF are 23.7 fps and 66.9-seconds burnduration.

7

The extent of the final braking depends on the real-time situation(that is, 8M RCS and 1M electrical power margins). Should the CSMclose to station-keeping conditions, the station keeping would probablybe terminated by a small separation maneuver to avoid recontact problems prior to TEl.

The total ~t between the phasing maneuver and the end of braking isslightly more than 3 hours. The RCS propellant usage is approximately thatwhich would be required in any actual rescue situation. The SPS propellant usage is slightly less than that reqUired for the normal four-impulserescue sequence, but is substantially less than that required iffive-impulse and six-impulse rescue sequences were used.

Table II is a sequence of maneuvers for the CSM-active rendezvousphase and includes various pertinent data associated with each maneuver.The ~t's in the second and third columns are from maneuver initiationto maneuver initiation. The ReS thruster usage refers to ullage whenthe SPS is the main propulsion system. The SPS burn durations do notinclude ullage. The burn attitude is the direction of thrust at burninitiation; it is measured (starting upward) from the direction-of-motionlocal horizontal to the direction of thrust. All values relative toTPF are based on a theoretical (impulsive) TPF.

Presented in figure 8 is the relative motion profile (curvilinear,1M-centered). The darkness periods (for the 1M) and 10-minute time ticks(relative to the phasing maneuver) are indicated.

Figures 9 through 14 present time histories of various relativeparameters, time referenced from the phasing maneuver (NCC). For eachof the figures, the occurrence of the maneuvers and the designateddarkness periods are shown.

Figures 9 and 10 are time histories of 1M-to-CSM and CSM-to-1Melevation angles, and figure 11 is a time history of the 1M-CSM-sunangle. CSM-to-1M visibility problems exist if the vehicles are in daylight and the CSM-to-1M elevation angle is within approximately 15° ofthe CSM-to-sun elevation angle. Visibility problems also exist when theCSM-to-1M elevation angle is between approximately 200° and 340°(i.e., a lunar surface background exists) and the lunar surface is litby the sun, or, in some cases, by earth-reflected light. The 1M .tracking light is visible to the CSM if the LM +Z-~xis points withinapproximately 35° of the LM-to-CSM elevation angle.

Elevation angle is defined as the angle (measured counterclockwise)from a vehicle's local horizontal in the direction of motion to its lineof sight to the applicable object (the other vehicle or the sun).

8

Time histories of vehicle-to-vehicle range, range rate, and centralphase angle (LM lead angle) are shown in figures 12, 13, and 14, respectively.

4.3 Transearth Phase

Since there is no CSM lunar orbit plane change in Mission F asthere is in Mission G, the transearth injection and coast phase isslightly different than in the Mission G reference trajectory.

Tables III and IV show the radar and shadow timelines from CSM-1Mfinal docking following the CSM-active rendezvous through transearthcoast.

Figure 15 shows the time history of significant parameters duringthe transearth injection maneuver for the August 14, 1969, 72° launchazimuth, first opportunity mission. These data were generated with aprecision integrated powered-flight simulation.

Figures 16 through 27 show scans of selected TEl and transearthcoast trajectory parameters for the other launch opportunities beingconsidered for the third quarter of 1969. These data were generatedusing patch-conic computer programs. The 1969 launch dates included inthe scans were July 15,16,18, 22; August 14,15,17, 21; and September 13,14, 16, 19. These dates are identical to the Mission G launch dates considered and result from targeting the F mission to the same lunar sitesas the G mission.

5.0 REFERENCE TRAJECTORY EVALUATION

All of the comments in the reference trajectory evaluation sectionof the Mission G reference trajectory, Volume I (ref. 3) apply alsoto the Mission F reference trajectory. It should be pointed out againthat this reference trajectory does not reflect the recent changes tothe 1M-active and CSM-active rendezvous phases as documented inreferences 18 and 19. Therefore, the profiles described should be considered as only roughly representative of the most recent missionplanning.

~

TABLE I. - SEQUENCE OF MANEUVERS FOR 1M-ACTIVE RENDEZVOUS PHASE

fit fromResultant

previous Main tN,Burn Burn RCS LM orbit,

Maneuver propulsion duration, attitude, thruster h /h ,maneuver, system

fps sec deg usage a pmin n. mi.

-

DOl DPS(FT) 71.6 30.2 180.0 +X, 2-jet 60.0/8.2

Phasing 64.5 DPS(FT) 172.4 15.5 0.0 +X, 2-jet 195.2/9.9

Insertion 124.7 APS 207.6 15.0 180.0 +X, 2-jet 31.9/9.9

CSI 30.0 RCS( intc. ) 28.8 18.0 0.0 +X, 4-jet 45.7/17.0

CDH 42.5 RCS( intc.) 38.9 24.2 0.0 +X, 4-jet 45.7/45.0.-

TPI 43.5 RCS (irttc . ) 25.8 32.0 37.3 +X, 4-jet 61.2/44.4

TPF. 46.2 RCS 29.8 36.9 297.3 -Z, 2-jet 60.0/60.0

8 The 1M descent stage is jettisoned just prior to insertion.

'0

TABLE 11.- SEQUENCE OF MANEUVERS FOR CSM-ACT1VE RENDEZVOUS PHASE

lit-from ResultantII~ from previous Main RCS IIV, Burn Burn CSM orbit,

Maneuver phasing (NCC), propulsion thruster duration, attitude, h /h (conic) ,min maneuver, system usage fps sec deg a p

min . an. m~.

Phasing (NCC) SPS 71.2 4.0 277.1 68.6/42.0

Coelliptic (NSR) 90.0 90.0 SPS 36.1 2.0 344.86 68.5/68.3

TP1 130.0 40.0 RCS +x, 4-jet 15.6 43.4 190.06 67.9/57..5

TPF 172.4 42.4 RCS -x, 4-jet 23.5 66.4 117.4 60.2/59.7

aAltitude measured with respect to the landing site radius.

•

I-'o

TABLE 111.- MISSION RADAR TIMELINE

Acquisition TerminationStation g.e.t., Azimuth, Elevation, Range, g.e.t., AZimuth, Elevation, Range,

hr:min:sec deg deg n. mi. hr:min:sec deg deg n. mi.

(a) Docking to TEl initiation

Merritt Island 121:08:09 -114.06 8.02 205 040.28 121:46:28 -109.72 .56 206 736.42Grand Bahama 121:08:09 -112.59 6.82 205 111.99 121: 42 :31 -109.02 -.00 206 574.93Carnarvon 121:08:09 107.13 .74 205 482.36 121:46:09 103.83 8.64 206 243.60Guam 121:08:09 112.85 18.57 204 428.23 121:46:03 116.73 26.38 205 227.23Hawaii 121:08:09 166.01 49.98 202 899.22 121:46:14 179.58 50.78 204 107.20Guaymas 121:08:09 -134.01 30.57 203 775.35 121:46:25 -127.22 24.33 205 353.22Corpus 121:08 :09 -123.86 21.51 204 261.35 121:46:26 -118.49 14.51 205 907.29Canberra 121:08:09 86.75 32.32 203 692.64 121:46:12 81.26 39.74 204 571.34Goldstone 121:08 :09 -142.43 28.55 203 878.92 121:46:22 -134.63 23.46 205 396.44Guam 122:32:45 122.98 36. )~7 204 661.88 123:44:19 137.50 48.87 203 986.78Carnarvon 122:32:51 99.34 19.13 205 572.46 123:44:19 93.68 34.55 204 624.06Canberra 122:32:54 72.07 49.13 204 106.64 123:44:29 53.58 61.86 203 561.10Hawaii 122:32:57 -162.71 49.22 204 095.07 123:44:35 -142 .22 41.37 204 312.80Goldstone 122:33:05 -125.39 16.10 205 726.50 123:44:42 -114.66 3.83 206 351.68Guaymas 122:33:06 -1l9.42 25.62 205 754.32 123:44:45 -1l0.83 2.83 206 475.11Corpus 122:33:06 -112.09 5.09 206 374.68 122:58:24 -109.34 -.00 205 477.20Guam 124:30:57 152.57 55.61 203 684.49 125:42:42 -177.54 58.81 203 452.80Carnarvon 124:30:57 88.84 45.29 204 077.06 125:42 :40 80.57 60.89 203 392.49Canberra 124:31:09 31.04 68.40 203 322.48 125:42:50 -16.69 70.78 203 160.80Hawaii 124:31:14 -131. 43 33.87 204 581.16 125:42:55 -120.55 20.80 205 167.72

(b) Transearth Phas~[TEl initiation - 125:58:01.6 g.e.t.; TEl cutoff - 126:00:16.6 g.e.t.]

Carnarvon 126:16:31 72.69 68.60 203 898.59 134:06:18 -108.33 -.00 197 841.29Guam 126:16:32 -161.85 57.41 204 195.70 131:13:42 -107.73 -.00 201 260.37Canb~rra 126:16 :40 -38.27 67.32 203 925.59 132:02:44 -110.32 -.00 200 305.28Hawaii 126:16 :41 -115.92 13.78 206 256.40 127:19:50 -108.88 -.00 205 985.26Ascension 130:04:59 107.01 .00 202 648.55 142:16 :58 -107.21 .00 187 469.51Madrid 130:35:51 113.47 .00 202 033.77 140:23:37 -113.73 -.00 189 954.41Grand Canary 130:57:40 109.85 .00 201 573.19 141:34:05 -110.06 -.00 188 414.89Antigua Isle 133:)16:14 108.14 .00 198 218.56 144:55:16 -108.44 .00 183 856.72Bermuda 134:21:33 110.93 .00 197 527.05 144:42:35 -111.30 .00 184 148.39Grand Bahama 135:05:60 109.65 .00 196 621.34 145:46:35 -110.01 -.01 182 645.39Merritt IslaLd 135:18:40 110.05 .00 196 350.88 145:52:59 -110.41 -.00 182 493.74Corpus 136:24:35 109.87 .00 195 024.33 147:02:00 -110.28 -.00 180 849.77Guaymas 137:18:56 109.99 .00 193 862.39 147:54:59 -110.40 -.00 179 577.32Goldstone 137:57:24 111.94 .00 192 973.84 148:06:07 -112.33 -.01 179295.79Hawaii 140:26:02 108.98 -.00 189 903.65 151:20:45 -109.45 -.00 174 419.02

aEntry tnterface is at 206h40m28.8s g.e. t.

f-'f-'

TABLE 111.- MISSION RADAR TIMELINE - Concluded

Station Acquisition Termination

g.e.t., AZimuth, Elevation, Range, g.e.t., Azimuth, Elevation, Range,hr:min:sec deg deg n. mi. hr:min:sec deg deg n. mi.

(b) Transearth Phase" _ Continued[TEl initiation - 125:58:01.6 g.e.t.; TEl cutoff - 126:00:16.6 g.e.tJ

Canberra 142:32:44 llO.51 .00 187 ll3.07 156:09:18 -1ll.10 -.00 166 715.09Guam 143:57:06 108.00 -.00 185 192.64 155:16:52 -108.49 -.00 168 155.62Carnarvon 145:11:48 108.60 -.00 183 467.60 158:13:13 -109.15 .00 163 213.45Ascension 154:09:49 107.65 .01 169 976.96 166:25:48 -108.28 .00 148 033.58Madrid 154:44:24 114.60 -.00 169 037.50 164:26:35 -115.42 -.00 151 899.06Grand Canary 155:04:45 110.73 -.00 168 485.16 165:39:14 -1ll.46 .00 149 557.68Antigua Isle 157:54:11 109.06 -.00 163 754.33 169:02:37 -109.79 -.00 142 726.96Bermuda 158:31:25 112.10 -.00 162 682.90 168:47:53 -112.93 -.01 143.23Grand Bahama 159:15:34 110.75 -.01 161 401.39 169:52:57 -1ll.57 -.00 140 969.64Merritt Island 159:28:33 1ll.20 -.00 161 049.11 169:59:09 -112.01 -.00 140 751.52Corpus 160:35:04 1ll.06 -.01 159 051.33 171:08:36 -1ll.91 .00 138 279.39GuaytnBs 161:29:37 1ll.20 -.00 157 408.22 172:01:48 -112.07 -.00 136 349.36Goldstone 162:08:52 113.29 .00 156 209.54 172:11:40 -114.24 -.00 135 987.33Hawaii 164:37:52 110.25 -.01 151 541.08 175:29:33 -1ll.17 -.00 128 494.08Canberra 166:40:06 1ll.70 .00 147 563.25 180:28:09 -112.76 .00 116 214.87Guam 168:09:40 109.27 -.01 144 546.49 179:28:38 -110.25 -.00 118 760.62Carnarvon 169:21:20 109.77 .00 142 082.27 182:31:57 -110.80 .00 110 724.48Ascension 178:25:52 109.14 .00 121 396.86 190:50:22 -110.54 .00 85 610.92Madrid 179:09:04 117.24 -.00 119 584.25 188:36:51 -119.21 -.00 92 881.80Grand Canary 179:26:40 112.84 -.00 118 842.05 189:55:01 -114.61 -.00 88. 679.94Antigua Isle 182:16:49 1ll.06 -.00 III 404.03 193:25:35 -113.01 -.00 76 503.69Bermuda 182:57:58 114.67 -.00 109 530.78 193:05:20 -116.97 -.01 77 734.07Grand Bahama 183:41:40 113.16 -.00 107 511.92 194:14:08 -115.47 -.01 73 488.57'·!erritt Island 183:55:12 113.68 -.00 106 879.16 194:19:45 -116.07 -.00 73 134.54Corpus 185:03:05 113.63 -.00 103 655.54 195:32:53 -116.39 -.00 68 879.61GuaytnBS 185:59:00 113.88 -.00 100 931.68 196:26:09 -116.69 -.00 64 818.42Goldstone 186:41:28 116.44 -.00 98 819.20 196:32:28 -119.62 -.00 64 382.57Hawaii 189:11:05 113.07 -.00 91 061.45 200:07:11 -116.85 -.00 48 256.54Canberra 191:05:28 113.95 .01 84 761.33 206:34:06 -19.85 -.00 2 158.48Guam 192:48:43 112.27 -.00 78 736.59 205:11:24 -120.00 .00 16 837.45Carnarvon 193:55:02 112.22 .00 74 692.08 206:34:15 54.47 .00 2 125.29Carnarvonb 202:33:33 -91.69 71.11 31 999.99 206:34:15 54.49 .00 2 125.30Guam 206:01:22 -123.68 .00 8 933.14 206:39:02 115.79 .00 9 948.88

a 06h IlL sEntry interface is at 2 40 c8.8 g.e.t.

bC-band station; acquisition on range

I-'f\)

13

TABLE IV.- MISSION SHADOW TlMELINE

Lighting".

g.e.t. of entrance,hr:min:sec

(a) Docking to TEl initiation

Stm1ight 121:08:01Ltmar penumbra 121:10:47Ltmar umbra 121:10:11

. Ltmar penumbra 121:56:18Stm1ight 121:56:27Lunar penumbra 123:08:29Ltmar umbra 123:08:44Slllllight 123:54:57Lllllar penumbra 125:07:06Lllllar umbra 125:07:09Lllllar penumbra 125:53:27Slllllight 125:53:29

(b) Transearth phasea

[TEl initiation - 125h58mOl.6s g.e.t.,

TEl cutoff - 126hoOm16.6s g.e.t.]

Earth penumbra 206:16:54Earth umbra 206:17:07

aEntry interface occurs at 206h40~8.8s g.e .t.

-- - - y--- ,_

I ,~~ '-----r-----.-- ,~ Darkness (CSMI

~ 1----- I A 10 minute time ticks

7 ~I",- relative to 001 --

, -"V

...-~

V "'"V ""'~!7 '\jf 1\

I '\

{\.\\

TPF-.. ...-001

I •~ ~-----f: DH

\i I ~~ ~ /~ T~I- '"'\ i ~ Vi ~ ~

" l/ •, CSI ~I ' ~~, v-"Phasing" -- ~~..... V1 '- 1------- l---- I I

---------- ----- ------ 1r~ 1-"1 nsertion"

i i 'Of

140

120

100

80

Ec

C 60'"E'"u'"~'5 40<;;

:e'">'-

'" 20'"~ '"~ .8~ '"u :2

-' 0;:0~&>

:520

40

60240 200 160 120 80 40LM ahead 0LM behincfl 80 120 160

Curvilinear horizontal displacement. n. mi.

200 240 280 320 360 400

f-J~

Figure L- Relative motion (curvilinear, CSM-centeredl for LM-active phase of Mission F.

~

\-'\Jl

v I I I1/ I DarkneSj (1M

I

I LM-CSM elevation angle

1/r--

CSM

I LMLr--

r--

/I

Direction of motion in -local horizontal plane

.;jII'

/r-- Phasing.......V· II

1,1 Third braking maneuve~",

Second braki n9 maneuver

/ I II I ,First braking maneuver~

/ 111/

I J/ I/

TPI-bI"?I"",,VOPI II nsertlion~

CDH"" ~~

40

80

120

360

280

320

240

enQ>"C

200Q>

e;,c:'"c:0

~ 160>i!:!I.LJ

o 40 80 120 160 200 240 280 320 360 400 440 480

Elapsed time from 001, min

Figu re 2. - Time history of LM-to-CSM elevation angle for 1M-active phase of Mission F.

/~ I I I II I I

1/ ",---- PhasIng Third braking maneuve~ ~ Darkness (CSMISecond braking maneuver""

/ .I I. I I ~lFirst braking maneuver """

/ II1/ f

I I7 L7I TPI-VInsertion-~ ~CSI

1/ V ." f-- l.----"~l,-DH

'--DOl 1//I

IICSM- LM elevation angle

f--

Direction of motion in f--

local horizontal plane

CSM~

I----

f--

j

If-f--

LM

j I I I I 1 I I

360

320

280

240

=Q)"0

~200

=c:ttl

c:0....ttl 160>~I.LI

120

80

40

o 40 80 120 160 200 240 280 320 360 400 440 480

J--I0\

Elapsed time from DOl, min

Figure 3. - Time history of CSM-to-LM elevation angle for LM-active phase of Mission F.

/ /) ~~I~~~~I DarkteSS /CSM)

/ I CSM-LM-sun angle

I If---

CSM

I T

,.£,""-

CSI~

!-

-

1/~

-4

1 Third braking maneuver-'\.I I 1 I

Insertion y firstbraking mane~r~.~ -

TPI .<X' ~ -Second braki ng maneuvery f---

/ // /

.;.~ / II \// /

:2-

/j CDH-....

Phasing~ /- ID~h,Y 7

360

320

280

240

l6'"0

~ 200c:n:l

C:::::lVl

:§ 160~V'lU

120

80

40

o 40 80 120 160 200 240 280 320 360 400 440 480

f--'---J

Elapsed time from DOl, min

Figure 4. - Time history of CSM-LM-sun angle for lM-active phase of Mission F.

200

240

~ Darkness (CSMl

-. -- -t--~

I \ ---

I \--- ~-- --~-_.- -- -- of--

I1\!

~,~ - ----- ----~r--- ----

II '?t-I nsertion

\--

~-.. --r---~j------

t\ I! /

----- -~ -- --- ._-

1\ --- ---- -

I !\I

I--- ------ -_.-r---- - ---r---

Phasing~ \1', -"SI

\ I ~~

'\ [\----- -

/,

\---,

f-- --

"".r ~.

1/ 1\ -' First braking maneuver

.' ~~,,~s~condl braki1ngmaneuver -

rD?1 i- ~~r-- third I __

TP\J ~~,aking,/ l m~neuver

520

480

440

400

360

320E

coJC'>

~ 280

'"u:c~o...ClJ

~.cClJ>

160

120

80

40

o 40 80 120 160

18

200 240 280 320 360 400

Elaosed time from 001, min

Figure 5. - Time history of vehicle-to-vehicle range for LM-active phase of Mission F.

19

\ CSI~ /

~ Darkness (CSM

'-I-I nsertion

\ rM'

\ I/~

\ V TPI)'*'"

r--T-+----i---ti>-+---+--+----i+--+-+---+,.-----jThird braki ng maneuver=-.:-t--+_+---+Second braki ng maneu'ver""", ,""

1r-+-+-----i-+i\-+--i'-+----i+--+-+--+--,.!",TFirsl braki ng maneuver""I'...~'t+---t _ _j

\ l DH::p.,. /~

1400

1200

1000

800

( 1\

600 \1\ \

/' ~Phasing

\V> 400

\.ea:;~ /<1>en ZOOc

1/E<1>U

/:c<1>;- 0fl 1'-001~u:c

<1>> -200

-400

~

I¥

-600

-800

-1000 f--t--t--+-+--+--+---t--t---t---f--lr--t--t--+-+--+--+---t---f--l

-1200 040 80 120 160 200 240 280 320 360 400

Elapsed Ii me from DOl, mi n

Figure 6.- Time hislory of vehicle-Io-vehicle range rale for LM-aclive phase of Mission F.

I\)o

5204804404003603202802402001601208040

I ~IDarl ness CSMV--\,

i I \, , CSM lead angleI I

I I ! / , :\ I .f--

I ! '\1M1-1 nsertlOn

7 \f--

i

, , I-----

I

I 1\ II-----

I ! Center of moon

i I I \~CSII-----

I I

! I ! I I i ~I I i 1"'- ,---1tDH

"~TPL

, 001 '"I-- First braking maneuver

~ ./ Third braking maneuver

~ ~Second braking maneuver

I 1\ I J! I

I i

\ I! i, !

I

i ~I i

!r-Phasing

\, J.

"\III I

20

24

-16o

16

12

8CO'

'"-0

'"enc 4'"-0

'".!!!::;:VlU

0

-4

-8

-12

Elapsed time from 001, min

Figure 7. - TIme history of CSM lead angle for LM-active phase of Mission F.

-~Ir-NSR

i_ ..V T 1-./ -----N.~

1 ~ •i \

11 \l

V First braking-IThird braking maneuv~r", ~ Iman~uver r

NCC../' '-Second brakingmaneuver r----

\~\ /\ L1\ 1/

/

~ V

"'"[7

i'o.

"~ V~~ Darkness (LMI ~i--- =:: ..• 10 minute time ticks

relative to NCC

Curvilinear horizontal displacement. n. mi.

12

8

0.>4.>

.- 0E.c

'"c::::i!:,Vl

"E U o0.> ;:E 00.> a;u .c

-[~II> Vl'0 U 4raut:~

~ 8c:.:;;:....::J

U

12

16

2090 80 70 60 50 40 30 20 10 0 .10

CSM aheacfCSM behind20

[\)

\-'

Figure 8. - Relative motion (curvilinear, LM-centeredl for CSM-active phase of Mission F.

v V--I I~

/'V Da,kneSj UMI

/LM-CSM elevation angle

,CSM >--

V

'ML/ >--

1/I---

'-NCC Direction of motion inlocal horizontal plane

i

! /Third braking maneuver_ V

~ /Second braking maneuver

IYI I I IFirst braking maneuver ')

!

! 1//

t /I

I TP~VNSR ~

.....~

0'>Q)"0

Q)

e;,c::'"c::o-~~....

360

320

280

240

200

160

120

80

40

o 20 40 60 80 100 120 140 160 180 200 220 240

f\)f\)

Elapsed time from NCC, min

Figure 9. - TIme history of LM-to-CSM elevation angle for CSM-active phase of Mission F.

360

320

280

240

=Q)"C

..!!:!200

=c:roC0

~ 160Q)

i:i

120

80

40

/

Second braki ng maneuver-

1/ ~~ Dark,ness lCSMI

)Af-Third braking ~aneu~erI I I· IFirst braking maneuver)

//

/IF I~V

NSR~'\Oo.

~

V -----/

.-/

/CSM-LM elevation angle f---

/

/ Direction of motion in I------

V local horizontal plane

CSM I---'----NCC

f---

I---

LM

f\)w

o 20 40 60 80 100 120 140 160 180 200 220 240


Figure 10. - TIme history of CSM-to-LM elevation angle for CSM-active phase of Mission F.

~

\ ~~ Darknesf (LMI/

I I \ LM-CSM-sun angle

II \T

I---

i /NSR

L f------

I 1\ I---

I \ CSM Sun

I \~

I \1 \

'I \

I \fE \/

~/1\~Nee\ V TPI\

~

\ First braking maneuver~,. h -Second braking maneuver

~

I "' - Thi~d bralking ~aneJverI I I I

180

160

140

120

0'>C1>"C

~ 1000'>C

'"c::lVII

:E 80VIU

I

:s60

40

20

o 20 40 60 80 100 120 140 160 180 200 220 240

[\J

+""

Elapsed time from NeC, min

Figure 11. - Time history of LM-CSM-sun angle for eSM-active phase of Mission F.

v-~/

~///,Darkness (LM)/ .'" '/

~.

/ \. -NSR

7 .~(/

"

/ r\./

.,~,.

/

/ 1\/ TPI/ \\

\/

/ 1\v '\

J Second braking maneuver I\..~il"TUVHTrst brtng rneuvr .........

llNfC

70

60

50

.E.c...,

40CftCIII....!:!.~~

">I 30il"u:i:

">20

10

o 20 40 60 80 100 120 140 160 180 200

f\)

'0


Figure 12. - Time history of vehlcle-to-vehicle range for CSM-actlve phase of Mission F.

26

20018016014012010080604020

0\

I ~~ Darkness ILMI1\

1/ \~- -~---

/ \~_ .. - r---

I \I

'-'- -.-- r----

,/1\

/ \lJ \1"''-/ ce \

\

--r--,\

__"0[----~

\ .---

~\.- .--- Third braking maneuverI I I I {J

t-- Second braking maneuver+--

\--- [-----

I I I I ~1-_ irst braking maneuver-,- -~- ----- 1--- t----

l-- .-r - --.

\

1--- --- /I~ I- t -- 1 --- --

.._-- 1---- e---- --- --

.- -- ----~ --- [---. _~I~ /~/ 1/

. _- ~.

V~

\----- ----

- ..

'\TN R

--.l~_ - - --~

o

20

160

-60

-120o

-20

-100

-40

60

-80

80

100

120

140

C1> 40E

C1>0>c:l.!C1>u:c~

~C1>

u:c

C1>>

Elapsed time from NCe. min

Figure 13. - Time history of vehicle-to-vehicle range rate for eSM-actlve phase of Misssion F.

27

I I J_~-

!I I Darkness (LM)

~~-

Third braking maneuve~~

I~NCCI

Se~ond ?raking ma~euver "

~I First braking maneuve~,

'\-- ~-

/ --

\ I /\ /

--

\/

1\ , I /\ I

T 1"".'1

\ 1 /I

\ I I 1/I

I j1\ 1

\ I I l!! I

\ I j----.l, I I ! I\ i ---l---

,I

\j I if 1

1-~\ i I / I

! \ ! I NS,R---...I I I, < 1! --+-I \-t--I

I I-,--u-~I I

! II I il CSM lead angleI it I II

LM CSM -

V1\ il-

I II

I r \~l,f If---

'---

1 I I ICenter at moon

II I

I I ! I I I II4 4~__L..L_LLLL[_.L--.l....--'----.l.I-----1_l-1----.L.---..l..-I------'------11. 0 20 40 60 80 100 120 140 160 180 200

-4.0

-3.6

-3.2

-2.8

-2.4

.8

-1.2

-.8

-.4

o

.4

C">Q>

"0 -1.6~C">C

'""0'"~ -2.0

:s

Elapsed time from NCe, min

Figure 14. - Time history of LM lead angle for CSM-active phase of Mission F.

8800

8400

3000

7600

Ul

.Eo.. 72001:-00QJ>03

~ 6800QJ

-=

6400

6000

5600

28

,

1//

//V

V/

V/

VV

1//

V/

V/

V/

V/

V/

V

/

5200o 20 40 60 80 100 120 140

Time from TEl initiation, sec

Cal Inertial velocity versus time from TEl initiation.

Figure 15.- Time histories of trajectory parameters for the transearth Injection phase.

I

I-

//

//

7/

7Ii

/v

/

//

~V

I--

I ,~-

61.6

61.2

60.8

60.4

.'E.c..

60.0C1l"0:l.....:;:;rtl

.!2.<::Cortl 59.6~

Ol0CC1l

C1lU'l

59.2

58.8

58.4

58.0o 20 40

29

60 80 100 120 140


(b) Selenographic altitude versus time from TEl initiation.

Figure 15.- Continued.

30

3.2

2.8

2.4

2.0'"OJ

-c,

OJ

'"C~

..s::: 1.6....~C.I....

..s:::

'"l4:

.~1.2..s:::

c.~...'"0cOJ

OJVl

.8

.4

o

//

1/J

/7

/1/

/v

/

V/

/[7

/,/

/~ - ------

-.4o 20 40 60 80 100 120 140


(cl Selenographic flight-path angle versus time from TEl initiation.


-- -- - - -----

V/

//

V/

VV

/

/V

/

//

/V

/V

/V

/

//

V

6

5

4

3

Cl'CIJ

-0,

2J!!Cl'c::~

..c::Co).."0.

J!! 1Co)

:r:~

0

-1

-2

-3o 20 40

31

60 80 100 120 140


(d) Vehicle pitch angle (local horizontal coordinate system) versus time from TEl Initiation.

Figure 15. - Continued.

v V"

/

/'V

./V

VV

/'V

V/

VV

/

.

-.6

-.7

-.8

-.9

01(l)

"0..-1.0(l)

0>s:::lI:l

~

~

~-1.1u

:c(l)

>

-1.2

-1.3

-1.4

-1.5o 20 40

32

60 80 100 120 140


(e) Vehicle yaw angle (local horizontal coordinate system) versus time from TEl initiation.


33

14012010080604020

3x 10

/

V/

VV

Vv

/v

/

VV

/v

/V

/

VV

/v

/V

/

Vo

2

1

7

9

8

6

.D.."'C

5Q)Vl~.....l::

.,!;!Q)0-0

'""0- 4V'JCl.V'J

3


(f) SPS propellant used versus time from TEl initiation.

Figure 15.- Concluded.

102989490868278

,/

First opportunity /f-----

____ Second opportunity /

I /V

/V

/

V,V

/'/

",V/

/ ./

V/

V,/

/V

./

V /v

//

//

/ /)/

/./

/V

-~ --- -

//

- ~~- -

./-

2760

2740

2756

2744

2764

2768

2736

273274

..><]

WI- 2748

~ 2752.....

Launch azimuth, 'VL' deg

(a) TEl l:::.V.

Figure 16.- Trajectory parameters as a function of launch azimuth forlift-off on July 15, 1969.

Fi rst opport unity____ Second opportunity

f---

./

".,/

-'./

",/

-'

"",/

;'./

'" /,/

""./ V./" .//./ V

~ /'

" /,/

~/

,/ V/

V./

,,/

"/

I I I I I I I I I I I I I ,

.56

.55

.54

.5301Q)

"'0..W~ .52"3-

<l..Q)01c::~

...t: .51c.>Q)c::~

c..UjI- .50

.49

.48

.4774 78 82

35

86 90 94 98 102

Launch azimuth, 1\1 L' deg

(b) TEl plane change.


8810

8800

8790

..0 8780..

lJJl-I-0

8770......""C

Q)VI::s....c:coQ) 8760e.0l-e.

tilc..til 8750

8740

8730

/

First opportunity /

- ____Second opportunity 1/- . -- ...

//

I

/

~/

//

/ V/

/ V// V;

,

/;;'

~ /V;'~.. V

".~ /.;~

V/

v

-- L t-- --f--

-'V

,./._-

:/V /

872074 78 82 86 90 94 98 102

Launch azimuth, IjI L' deg

(c) SPS propellant used for TEl.


IFirst opportunity

- ___ Second opportunityI----

,.'"/

'".J''''

1,./

/'"..

I,.

~ ...../

,.' V~/ /"

~ ..../

V/

~//

V./

./ V/"

/"V

~V

,.,

I I I I I I I I I

38.36

38.32

38.28

01 38.24(I)-0..C>-:=;......(I)>-

38.20-0(I)>-(I)

~0D..

.......0 38.16c0

......l'I:lC

Uc

38.12

38.08

38.04

38.0074 78 82

37

86 90 94 98 102


Cd) Inclination of powered return.


38

1029894

. - _._-!I I,,

I--

_FiU. opportunity_':'e: Jild opportunity r----I

iI

j -

~!

-II I

tI-II

l-I

!"~, I

I ---l..............

t'-...... .....

I ~r- __._I ...... ,

,- --'"-!'1' ....

! 1'- ...-~ . .- -

..- f--

-_.-.--

9086

t-i

I ..·-t--

Ii······ t I

(.. 1--- i

LZlIlllCh ilzill1lllh, l\J L' deq

Firfllre 16.- Conrlllded.

39

'1"1,",.LVO104100928884

2772 r---r-------r-- .. I. i I. I I j 'rl-J---I~: H i-t ! ---.--First opportunity

2768 f---+_.- j -HI'_-+1=1-L ~.:=.-=..:-s' cond opportunityi I I' I

i ' I I ! Iii2764 I----+--i+-,-_I -~Ii-l1--~L!I---+--+-v--?--+-v-/-+----l

2760 1-----+---+

1

- -t --I. LJ---l.l:'--+/-/--+---+--+------<r---+----+-- _l_J j I ~ , !

<Jl 2756 I----_+_- Ll I , v / i ~,-+----+---+------I-----4

~ f, -US,. J=-J- i, /

i L.'r I I I i//I-Il.l . 275 2 f----+--+--~'_iL__i----- _--L_ ---'---I-----'.~=----+-_+_--+-____l

I /" I 'i,.·~'·

I-----+---+--r-t-v---l_-+----.__+_L l,,/ _L·._-+---+-_~-1

2748 f-T-/.-+-v_/_+-_"-t--__ /~ /V j._-+---+--+---l

1--1'--+-----1~_1 VI i __+-i!--+_-I-I_~-+--+-~2744 ±fl' I : I '._- -- :--t--l~ -t-,I'--+_~II---+------1-----1~

I t'I '

2740 f---+--¥-'- --'----+-----t--- __.L__ + -+-I---+--+----+-~V ! It iii t 1

i ~-H.---~_.-+_. ~-I----I----+---,,-,.., L ,-V_L---,--_L-L_l __ 1__L_J_J__--L.1_..L..---L._l....--_LIJU

80

(a) TEl .W.

Figure 17.- Trajectory :-lr:'nlctfT Y I ,unctiJIl d laullch azimuth for

lift-off 011 July 16, lS'69.

40

108

... _---

104

-+---+--- -

-L ----t-----

.J__L-__

10096

/

92

_J

/

8 ()L)

I

I I

-- -t - ~- - 1

I I

I •

---- --- t, I

----

--1- T I

2.2

0 1---+----+-:--~-Il~rl -I J-' <'+_/-+----+---+---------J

2.18 t--+-- il- '/f! ·1

1

t~/ /2.14

2.12

2.0ei -

III

I... f·-

±l2.06 80 ; ~-

..Q)

01CC'I:l~

U

Q)CC'I:l

c..

WI-~ 2 . 16 I---+---

WI-

Launch azimuth, lJi L , net)

(Ii) TEl pl.lllc C11.1 11 II' •

Figure 17.- ContiJ1lleci.

41

108.10410096928884

First opportunity- - - - Second opportunity

;~"

~'..

"~"

//,

,/,/

/' /'~ /

,/ // /

V" /"~ V"",,/ V

-"~ /

.. ,

./

V/

/ "

/..

.//',

8730

871080

8790

8800

8780

- -8720

.0-- 8770..

I.UI-...0

8760......~,lIl~....c:lU

<1l -8750.g-...0..

(/)

a..(/)

8740

Launch azimuth, \jIL' deg

Cd SPS propellant used for TEl.


90

80

70

g' 60"0..C...:::3....QJ... . 50

"0QJ...QJ3:0c.......

400c0

:.::;«lC-(.)c 30

20

10

First opportunity____ Second opportunity

---- -_._- . -- -

o80 84 88 92 96 100 104 108




92.8

92.4

92.0

91.6

91.2

..90.8-'=

~

<l)

E....-'=.!? 90.4;:;::-'=....

n:s<l)VIcn:s 90.0..I-

89.6

89.2

88.8

88.4

First opportunity\. ____Second opportunity -'\

'\

'"""'\I\.'\

"- \.

" "\~

\.

'"\

"\.

'"\.

1\

I"""\ I""\.

""""\. "'-1\"\. ,

\.

" \.

\.

'"'\..

'" "\.

I'

"

88 •0 1...1_...L---lI_---...l...._J.I_-L_-'------'-_-'-_.L.---L_-'-_---'-----J_--'-_--'-----''------'-----'

76 80 84 88 92 96 100 104 108 112


(e) Transearth fl ight ti me.


44

11010610298949086

I

1/

I~

First opportunity /I- - - - Second opportunity V

/V

~

1/"~

~

/~~ -- ~

I V1-- /

V/ /

/ V_L_V V

/ /V V

;' v/-~-~- f----v/ /

/ /-'

VV

V_.~- -f- -_ ..~~-

~_/

V/ 1--- -f-._-~ -

/V

.- -~-

2758

2762

2752

2764

2760

2748

2750

274682

<Il 2756a........,

><:]

1.L.l2754I-

Launch azimuth, IjIL' deg

Ca) TEl ~V.

Figure 18.- Trajectory parameters as a function of launch azimuth for

lift-off on July 18, 1969.

11210810410096928884

IFirst opportunity

- - - _Second opportunityI---

I/

/,/

/

I,

~

""' V~

"- ,/ /

"' II' VV

~ ,/

'" V' 1,./V~ 1--/ ---1-- --

I3.057

80

3.058

3.060

3.059

3.065

3.066

3.067

3.064

C1<1l

-0.. 3.063-UJI-~

<I..<1l 3.062C1s:::lI:l

..s:::u<1ls:::lI:la. 3.061

UJI-

Launch azimuth, li'L' deg



//

First opportunity /

- ____ Second opportunity //

/

/1

//

I

/ //

JI /

J

I' /I,I /

I //1/ //

1/ // /

1/ //

" /,,/

V/

V/

/V

.//

--_1..........- --~~ - ---

8718

8714

8710

8706

8702

..0

~

jjj 8698I-...0.....-cQ)III

8694~....c:

..!!!Qjc.~

8690c.V'la..V'l

8686

8682

8678

8674

867076 80 84 88

46

92 96 100 104 108 112Launch azimuth, IjIL' deg

Cc) SPS propellant used for TEl.

Figure 18.- Continued,

-- --,----,..-I I

IFirst opportunity

- ___ Second opportunityr----

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

90

80

70

Ul 60Q)

""0..C...::l.....Q)... 50

""0Q)...Q)

~0a......

400

c0:;:;n:lC

(.)

30c

20

10

o80 84 88 92 96 100 104 108

Launch azimuth, IJiL

, deg

Cd) Incl i nati on of powered return.


48

- --f-----\--- ~ I--~--t____t--_j

--1-----1---- - ----+--+-----1

+---f---+----

93.6 f-------t-----t---t--

"",9 5. 2 1------1-~-t__---~t__ - - ~-+_"<'\--+--t-- - ---I---t__~ ~~ ~-~ --

1'\ -+-----1--+-- --

94.8 l---+""-,-+--+-------1--+--~"'----f_-

" , ~ ~ ~-f-- --

94.

4

~~f---+- ~_~ - ,_ _, __. _ ""~ ------+-----+---t--t--+----

94. a f-----+--+--+--- --t~--:,-t-,,--t----+ -+-------t---- ~

\ -----1----- ---- C----~I""'"~~--+--+---+----+---+---j

---- -~---

'1\

96

.4

.------r--..-----r------r----r-~r-----r----.--~~~_~-r_-r Ll-_--~I---:---'cI~r'\. First opportunity

I '" - - - _Second opportunity96. a I-----f------'lt-~--t----+--~ ~- -~~+---+~--- --- -~- - - I-- I I f-----

~- - -~ - f-----j--t-----t--+--t-

95.6 f-----+---+ --+!\.-\<-+---+--t__-+---- --~-I--- --- +----f------+-_t_--+---t---t--~1'\

Q)

E

..ct:reQ)l/lC

~t-

'..c

92.4 1----+---+------ f--- f--- --+--+----+---1----1----

~-f- ----r--~-

\.-- -- -- --~-

\.t- ----I-----t- ~--

\.

92.8 I----+--+--t--- t__- -- ---------I--~-----~~,

,--'\.

[,

93.2 f----+-+--

--+---t--t____t-_t_- --f-~-___+----f___--I-----~-- ~

116112__'---_ ~ ~ __ L_ _ ~_~ --'-_...L-._-'---------'

92 96 100 104 1088884


(e) Transearth fligllt lil-Ie.

Figure 1S. - COllel uded.

2890

2880

2870

2860

~ 2850......><I1L.JI- 2840

2830

2820

2810


-

~"

,",.,"...............

v ......~~

1/~v ........ /'~

....... V......./-' "

~"I" V

-" /'

V V

....VV

V I-"'"

28000

/,\

uv01100;

on00 96


Ca) TEl bV.

100 104 108

Figure 19. - Trajectory parameters as a function of launch azimuth forlift-off on July 22,1969.


,/

/

/

/

"/

V/

1//

--- -- / c---

//

.","~~- ~--10-'- V-

1/" // 1/

,/

~/

./,,/

V V.-- --

.084

.082

.080

01 .078Q)

""C..ll.JI-~ .076<I..Q)

01=ro.!::(,)

.074Q)

=roc..

UJI-

.072

.070

.068

.06680 84 88

50

92 96 100 104 108

Launch azimuth, '" L' deg




I---

,..,1 ..

""/' 'I...~

/ "I "/ \.I

~

/ V ~ \I ./ r--... "II / "- \/ " \

V '\ \J r\.

V \ \\

1\ \I\..

" \1\ \

\ \,,~

\\

I I I I I ,

8820

8800

8780

..0 8760..

UJJ-"-0 8740---0Q)Vl::s....l:n:l

8720Q)c.0"-c.

V'la.V'l 8700

8680

8660

864080 84 88

51

92 96 100 104 108




28.20

28.18

28.16

,.,. 28.14..l::

...~,.,.::3....Q),.,.

28.12-0Q),.,.Q)

:=0a.

......0 28.10~

0~ra~

u~ 28.08

28.06

28.04

52

I'-...............

'"First opportunity

____ Second opportunityI---

..........~._~---- --- ----

'" '" "'-~r-- ....

~, ......

~" "' "",I' '",

r"...., ........

"~ ,""~

...1',

t' ,I' ,

""- ......I' ,

28.0280 84 88 92 96 100 104 108




53

78.0

78.8

81.2

I

'"irst opportunity

- _ Second opportunity

"-'\

'"~"\

'"I\.

" '\'-

"- "," "I" ,

'~,",

r\.

'\. "\t\.

",I\..

'" '.:-.

\-..-,.

. '"~,

"-

""~",

78.4

79.2

82.4

82.0

81.6

80.8

..r::1::ra<IIVlCrat= 79.6

....r:: 80,4

;:: 80.0

84 88 92 96 100 104 108 112 116Launch azimuth, \jIL' deg

(el Transearth fl ight time.


2910

2900

2890

2880

VI 28700---..><I

~ 2860

2850

2840

2830

First opportunity____Second opportunity

r-

r

/

"/

~"

/",

/

",V//

"" V./

"" /- --

V,V",

" .. .~

V". 100-/

VV

VV

1,../V.

V",

282072 76 80 84 88 92 96 100


(a) TEl /).V.

Figure 20. - Trajectory parameters as a function of launch azimuth forlift-off on August 14,1969.

o

-.02

-.04

-.06g'

"'0..-UJI-

-.08~

<I..QJ

8'"'.r:u -.10QJc

..!l!0..

UJI- -.12

-.14

-.16

55

\;'/

First opportunity~'

I---____Second opportunity

.J'

V/

V,/

.J'

,/V /

V·/

V

'"" VI;

~

~ V"' ..... ./.-

.... ", """ VV'

/V

./V

V V~

-. i872 76 80 84 88 92 96 100

Launch azimuth, IjJ L' deg



I"First opportunity V

- ____ Second opportunity ./V

./~

.//

.//

./V

./ J/.// V/ /

/./

/-7

Vl//

V/,

~V/",

///

7/

//

V/

/7

v

8980

8960

8940

..c 8920..

UJI-,.,.0 8900.....

"'0Q)VI::::I....t:lIS

Q) 88800-0,.,.0-

(f)

a..(f) 8860

8840

8820

76 80

56

84 88 92 96 100




57

100969288848076

First opportunity /'"f--

____Second opportunity

",;'

~

v'~

V/

'"/V V/

~

.", Vl,;'~.", V./

V Vl.,.- .... ~

~" V-,.. /

/V

1/v

~/

./V

./V

I I I I I I I I , ,26.0

72

26.2

26.4

27.4

27.6

27.8

~ 27.2-0..C..:::s....q.1.. 27.0~..IU~

8.'+-.

26.80c0

ic~ 26.6


(d) Inclination of powered return.


80.8

80.4

80.0

79.6

79.2

...s:: 78.8,OJE:;:;.....s::.~ 78.4.s::~I1lOJIIIt:I1l 78.0..I-

77.6

77.2

76.8

76.4

58

First opportunity

"____Second opportunity

'"--

'"~~~

'""..... '\....

" I\.... \"

~, \... I~,

" I'.," '\

1', i\.\ \I,

'\

,, ,,1'\.,

.....,,

..

76 80 84 88 92 96 100 104 108

Launch azimuth, "'L' deg

(e) Transearth fl ight time.


2890

2880

2870

2860

VI 28500........><J-lLJ

2840....

2830

.2820

2810

59

I IFirst opportunity

__ - _Second opportunity

~-:~,.

/

/V

",'

;I'

,. /"

i-' ./I-"

V ""-~/"" V

~~ .... ./

.."..~

/'"" ./

V~

./

~V

V V

?ROO- _. ·7276 80 nil

0'1 88 92 96 100


(a) TEIl:i.V.


.18

.16

.14

.12~

"'C..-L.LJl- .10.;.

<]..cvCl=lU-= .08(.)

cv=lUCo

L.LJ .06l-

.04

.02

60

First opportunity- - - _Second opportunity

f----

~

/'

///'

/

'"/,/

~

~

"./',/

V/'

VJ,/

~,/ V" ./

"." /,/'

~

..... :/~".

./'

/V"

"./".....-

V/

~

~

o72 76 80 84 88 92 96 100




8920

8900

8880

..0 8860..

wI-...0 8840.....

"'0Q)U)

:::3....t:l'll

Q) 8820a.0...a.

V)

0-V) 8800

8780

8760

61

First opportunity V'- - __ Second opportunity /'

~

/'V

/'.. V

/'/

V/ ~

V V/ V

v V//'~

/ /V

~

/ 1// V..

/ ~V..,V

/

V/

V/

V/

V

874072 76 80 84 88 92 96 100




62

100

ill

84


29.8

ITI-r--',--il-r- I JlFLQPLJilY ·I-~i..30.0_~ I' - __ Socond OPP"I"n1IYh,1±-,--, -!~ ;-'-+1ll

_--4--t~ 1-_ 1

.j -i. -I LL_I'-- '-,-·1- I I ---+ '_, ) :

I . i-~ J_-t-- t-~- '-~L_!-t , , I I _Li-- I I I

1 i -l--L , - r I -i---L-i----'i-_LL+-,-!-- "-x-! I J,--J---t-++- I_~I --.-<t'-~ I -t-!, .J' -, I , .... ,. I -'-- I I

--1- 1! ... I I, _1.- !' - , . "1",{ i'

-- J I A:.----11-

11'..- , IU

--t-b~1 --t--+-- _: _1_~tiL-1 --- _ I I

I ill :

i I l-l-c-i--'--''-- --', i I I ,

'I L_1,. ---,---'t-- 1;-----1i----t-_ L__, I I!I I -- t __ I. -j--- i!L---l- '- I "

~'+-+-1L~I I.J.. ,,_-'

u(1)...(1)

~o0..

......oc=ZII:!s::

Us::

..s::...::;..(1)...

- ". ered retu'n.,- "1",·, DOWtdi Inc: ll'd' ." •.

2 1 - Continued.Figure •

:~l.4~. I I I

r- ~1 -- --+----+ --+---<1'""-'--+--+---+--+-,__.1-_-_-_....J_L_-=F:-:-jr.Ls""'t-0p-lp-o-:"rt-unLit'-y-+,--I

o r=;---i~~--+-I_-1-_+ 1----+,-+-__t--t-- - - - _Second Oi:i,ortunity~

" ~ J___ "" L

"b O. 2 f--+---+--~-+---+------.:l-t-~---t--!--_+---+--+_-+---+-+-__t--+--+----i

7'} ,8 1---"'-rl--+--+----+.--+--+--+r\-~'\.-!---+___+--+-+__l-_+_-+_-I__+__1I\.

" '\7\' .4 1-,-_I_---if--...~-,,----+--+--+-__t---+--+I\.~\.---i-_+-_I_-t___+-_+_-+___+-....,

...

79. 0 f--+--+--+--+-"-'~-+-____+---+-+-__t-"\~-+----if---+--_I_-!---+--l~

78 _6 1---+---+--~-+--+--+-~--+--+---1'--+---+-~f--+---+--t---+--l

78 . 2 1---+--1--~____+--+---

/741--+----f--+--+-+-+--+-+-+---+--t-----'\--t-----"1---t---t--t---t--1

-,....., ( ...../ i ~ l)

72 76

2870

2860

2850

2840

~ 2830--..><J

~ 2820

2810

2800

2790

64

First opportunity___ Second opportunity

f---

",,'"

",

"'"",

1/'"./",

",'"./

/'""

1/'"~~

"~",

V /""."

V/

~V

~

"./

278072 76 80 84 88 92 96 100

Launch azimuth, IjJ L' deg

(a) TEl !::..V.


65

I

First opportunity,

____Second opportunity II--- ,

I

I,

,I

I

)',/'

,/I

I /I' [7

I /,VII'

,VI

I // /

1/ 1// /

V //

/V

V1/

/

o

.008

.004

-.028

-.004

-. 040 .....---'-1_~_172 76 80 84 88 92 96 100 104 108


-.032

-.036

-.008

C'lC1l

-c-.012':-

wf-~

<3~

C1l -.016C'ls:::l'Cl~

<.)

C1ls:::~ -.0200-

wf-

-.024




~

,. ...~

,..';t"

,..'"

//,

/ V/ J,,.....~

~

//

V/

/ V/

//

V,I

//

/,/ /

/ //

V

/vV

/V

8900

8880

8860

..0 8840..

jjjI-...0 8820.....

"'0Q)C/l~....t::lIS

Q) 8800Q.0...Q.

(/')

a.(/') 8780

8760

8740

872072 76 80

66

84 88 92 96 100

Launch azimuth, 'ilL' deg



61

100969288848076

",i'

~

First opportunity ~____Second opportunity ",

t----

"i.'",

/

/~

/ VV./.-

VF

/V·

~

l/ II'"

/ /V //

v1/"~ . "

/ VV

VV

V/

~/V

I I I I I I I I I I I

28.58

28.44

28.46

28.4272

28.56

28.60

~ 28.54-0..I:...:3....Q)

28.52...-0Q)...Q)

~

&...... 28.500I:0

:;:ilI:lI:-g 28.48


Cd) Inclination of powered return •


68

108104100969288848076

First opportunity____Second opportunity----'" '"'"""'\

'\.'\

I' '\,"

I'",,

""-,", '\

\.." '\,

"\

'""

'",I" ,

," ,

" , ." ,

" \..

",

79.8

79.072

79.4

80.2

80.6

82.6

83.0

83.4

83.8

82.2

....s::, 81.8

Q)

E...........s::.~

-= 81.4.s::~tlIQ)IIIc:~

81.0I-

Launchazimuth,ljIL' deg

(el Transearth flight time.


2840

2836

2832

2828

2824

~ 2820.....-><]

~ 2816

2812

2808

2804

~

Fi rst opportunity ",

- ____ Second opportunity ~/

//

./

//

/I

/

/1 ..,~ V

/ // //

/ V/

/ // /,

/ /,/ /io'

//

V/

,/

/

280072 76 80 84 88 92 96 100

Launch azimuth, 'lJL' deg

(a) TEl AV.


70

W1-

-. 76 ~~~-r----T----1--r-rIIl_J

____ t- irst opportunity i j_. 77 I---+--+--+---+--+--+---I--=--r:-:-:- ::-._.:-~econd opportunity '- _

r----+---+---+----t--------t-----+----+- - .1----- -1--r I '

-.78 i_

''-~ ,!--11~~- 79 ~ _",,~,~ -+~ =ti~J_,,~ij

~ -.80 ',,~ h--'--J L-I.~ -.81 I---+-+--'-I~,-----~-~,.,~_,_il~ "... I ""

',I ~~-.82 I---+---+----+--+-------~--r-------"~-._--, I ~_

~I-t--'~>·+-Ti

'. 83 ~--+--+----+--+--t----t-+---t-~-:-~:f-'~-..,...:--·---J---- i =1i' '- i '

" '-. 84 t----+--t--+---+--t--+---II---+--~--+--+----+-~--

~-+---+---II---+---+---II- -+--+--/-------f_-+---+--t

1009688 92848076

-.85 L.-~_....L.-__I-~_....L.-----l -'--_.I- L --'-_-'--_'-------J__--"

72


(h) TFI plane change.


I I j I !,I i

I I"

First opportunity !\-+

. _ .- __ Second opportunit~i,\

\II 'I. ,

. I\ I..

1\ \I

I

\,

I\

i\ \I

I

\,

I

- \ I I,I\ \ I

\, I /\ /

\ !' I /,/..

\,

"......../ I;'

\ /\ /

\ /~

\ //

I~-' ./V

I I I I I I ,

8680

8670

8660

:!! 8650..

L.LJto-

a 8640....."I;

I8630•k

'"Q.V) 8620

8610

859072 76 80

71

84 88 92 96 100




72

100969288848076

First opportunity ,,'____Second opportunity ",;- ,-- ,-----'-' ----

'"/",/

/,/

,/

/ V./

/ /V

,V

/ /I

/V

/I /

/ /I

/V,,

'/I/

~/ V/

//

//

/

/V

39.04

39.18

39.16

39.20

39.02

39.0072

39.14

0'1OJ

-c..l: 39.12...:3....OJ...

13...OJ:= 39.100a.

......0l:0:;:;

39.08"'l:-(,)l:

39.06


(d) Inclination of powered return •


73

'\ First opportunity___ Second opportunity

1\\

1\\

\1\

\,

\"'\ 1\

'\ \

" I\.

\ \I' \.\

~ f\."

~\ '~

\ ~,

,'\

I'

"'\

""" ........

" "- ~

84.072 76 80 84 88 92 96 100 104 108


85.2

84.4

84.8

87.2

87.6

88.0

88.4

88.8

...86.8..s:::..

Q)

E:;:;......s:::Cl

86.4;:;::..s:::.......ra0)<Il=ra 86.0.......

85.6



2890

2880

2870

2860

~ 2850......

-><]

WI- 2840

2830

2820

2810


I---- --

",,/

/

~

1,..-/

~

",./

1,.-""

/_/

~/./

V/

",."/~

"... V1,;".."",.""

/V

./V~

V V

280072 76 80 84 88 92 96 100


Ca) TEl /).V•

Figure 24. - Trajectory parameters as a function of launch azimuth forIift-off on September 13,1969.

75

//

First opportunity /

I'--'-____ Second opportunity /.

/1/

//

j

/

/,/

~

/ /",,1 /

/'V

/~ V

/ /V V

/ // V

I /II' V

~ /

V V/

/V

/. /

V/

V/

-.096

-.13272 76 80 84 88 92 96 100 104

-.128

-.100

-.124

-.092

-.104

C'lQ)

"'0 -.108...-UJI-

03-<I

...Q) -.112C'ls::~

...s::<.)

Q)s::~

-.116a.

UJI-

-.120

Launch azimuth, IIJL

, deg



II

--lI First opportunity I~_______ - .- - _Socond oPPortunill_'!

I_- 1......--+__1__ J_I---+-f. . .~--:'I #} lI ,10'" ~

;"-

..-! I".

~-

~ --1I

I ~I

! II I/---_ ... .-

j~ !

/,

VV ,

/

./V

/

II ./

/--, ~-- ,-

I/'r--./~' ---

/ 1/V :

1//

V/

/ :/

I / I !--+--I /V-i

\

l/ -W II

/V

I/

V iI- .

.IV/

I

8920

8900

8830

8860.0

.."

I-

<5 8840,-';:IQ)(/)

::l

"m 8820OJa..0....a..

(J')

c..8800<f)

8780

8760

874072 76 80

76

84 88 92 96 lGu




77

28. 28 t--t--+--~--i--+--t--t---+---+--+---I--+-~I:.-.."'+.-

~/

'-6' 28. 24 ~-+--t--+--+--+--+--+--f-----p.'"---+--+-+--+----f

~ ~/s::::; I~'+4 ~ ~

~ 28.2 0 t---t--+--+--+--t---+:r/~-~~I---+--I---+7'/'--+-~

] ,,/ ~ V"'"~ '" /'~ ~ //'0 28 .16 ~-+--+--+-7""-t--+--+--~-+--+-7"'-+---+--+--+---1

.~~ '"g r /'

.~ '"c ~'" ~g 28.12,," ....V

/V28. 08 ..--t--+--+-~~-+---f--+--..--t--+--+--f---1

/'"

28. 04 1---+~~~/_-+--+--+--+--+---+--+--+---+--+--+----1./V

28.00 I I I I I , , ,

72 76 80 84 88


92 96 100

{d) Incl ination of powered return.


18·

10810410084 88 92 96

Launch azimuth, IjJL' deg

8076

'"First opportunity

___ Second opportunity -

I\."r\.

"\\.'\

'\

"\ \"'~ ~

"' \.I' I\.

"' '\,,

",

~-

~,I'

\.,",""' ",

","',

,""" I'

"' ~

82.4

83.2

82.8

83.6

79.6

80.4

80.0

78.872

79.2

82.0

....r:: 81.6~

Ql

E:;:;.....r::.~

81.2.r::1::tUQlVIl::

~ 80.8I-

(e) Transearth flight time.

Figure 24. - Concluded.

2880

2870

2860

2850

III 2840a.........><]

~ 2830

2820

2810

2800

19


..,.~

"".... ..,.""

"",.""

,,"" '.~ ...V

"" " ,,/V

" ...." V I."""

..,."" ~,.V ~

..... ' ..........,.V

-""""/""

V

279072 .."

10nnOU

nil0"+

nn00 nL

7V,,,,,.1.VV


Ca) TEl tN..

Figure 25.- Trajectory parameters as a function of launch azimuth forlift-off on September 14,1969.

.26

.25

. 24

·23~

"'C..-IJJI-

.2203-<]..QJC'ICl1:l~

u .21QJcl1:lCo

LLJI- .20

.19

.18

80

First opportunity___Second opportunity

f--

.10-

;'~

;'

";'

/~

./~

~

V/

Vi./

/ /~

I-" /"". /";'

.I /,. "",~ /".

~ V./

/V

./",,/

V

.1772 76 80 84 88 92 96 100





~

,.,.,.,.,.

".,.,,/',

/ ~

//

/i

1;0//

V",

V/,

V/-/,

V/

" /

/ V" /

//

/,I

V/

,

8900

8880

8860

.0 8840..

LiJ~

~8820.....

"'0~III:::s

~~ 8800Q.0....c..

(/)Q.(/) 8780

8760

8740

872072 76 80

81

84 88 92 96 100




28.95

28.94

28.93

01 28.92(l)-0..s:...:::s.....(l)...

28.91-0(l)...(l)

==0a......0 28.90s:0.....~s:(,)s: 28.89

28.88

28.87

82


I----

~

~~

'"r--.............

~I'

"'" r--. i'......"-.......

" "'".....~

" ~,"r--.. ,"r--.. r--...

" ""~~ ,

",~

...

',,-"

i' ,28.86 .

72 76 80 84 88 92 96 100




First opportunity_ - _ Second opportunity -

.............~

~~

~'-......

.... ....~....... ~........

~.....................

....... -............~........

........ ...................

................

..............

..... ....

, I , ! ! .-

87

86

85

84....

...s::..Q)

E.... 83.......s::0'1

--...s::........ra 82Q)VIs::ra....I-

81

80

79

7872 76 80 84 88 92 96 100




84

90888684828078

I IFirst opportunity

____ Second opportunityt--

"..-

/'V

7V

"..-~- .j..-

",

/V

- r- ---- ---~1-

V/'v

",'"~--~-

_._._--

./--- -- --

"..'"- - _._~. ---I-- - -

./V

-- --

.,VI;'"

VV

V----•. _-_.

V--- --

./V

--

/-- --- - - - ---

-- ----- .---

2820

2824

2828

2832

2808

279676

2804

2800

~ 2816"-~

><J1.l.JI- 2812

Launch azimuth, 4' L' deg

(a) TEl b.V.

Figure 26. - Trajectory parameters as a fUllctioll of launch azimuth forlift-off 011 September 16,1969.

/ I~

/ First opportunity

"___Second opportunity

I---/

1://

:/

:/1

L.

/

:/

:/

/./

//

/./

/J

V/

/V

/1/

/

V/

/V

V/

/V

V---

.568

.564

.560

.556

.552OlQ)

"'0..ijjI- .548.;-

<3

oJOls:::rcl

.544.s::0Q)s:::rclC.

ijj.540I-

.536

.532

.528

.52476 78 80 82

85

84 86 88 92


{bl TEl plane change.

Fi9ure 26.- Continued.

8780

8770

8760

..0 8750..

lJ.J~~

08740.....

"Q)Vl::l....t:10

Q) 8730c..0~

c..Vla.Vl 8720

8710

8700

86

First opportunity~- 1-- ____Second opportunity- 1"- ....

r- ......

" '" ,,

\"

~\

- \----I"-.. \

'"r--... ~\........

\"- \

'\ ,r\.\

1\\

\'\

869076 78 80 82 84 86 88 90


(c) SPS propellant used for TEl.,


90888684828078

"-~ First opportunity

- Second opoortunitv

'"'""""~'" '"'""-

",.........

'-......

......

" ......... ,

'- ,"-

"-......

""-

"-......

I I I I I I "I I I ,25.24

76

25.28

25.52

25.32

25.60

25.56

0'>25.48<lJ

"'0..C...::s.....<lJ...

"'0 25.44<lJ...<lJ:t0a......0

25.40c0.....III.Euc

25.36


Cd) Incl ination of powered return.


88

90888684828078

First opportunity____Second opportunit~

'" "~" .......

""-~

'"r--...."-

"" """....... ,

1' ....

", ,"' .... '- ,

...........~ ,

" ,

87.0

86.2

86.6

84.2

83.8

83.476

85.8,..~..

ClJE

:;:;85.4....

~

Cl

~

~....,..~ 85.0ClJIIIC~,..I-

84.6




2890

2880

2870

2860

VI 2850Co.......><3wI- 2840

2830

2820

2810


--~-

10--'"1..00 .....

" .....~-

-~

.....~ ..... .-

~,..

,," /"~ ..... V

",..

10-- ..... ~

~,..

,,- /VV V

-"

V /

')ann,-vvv72 76 80 84 88 100


(a) TEl tN.

Figure 27.- Trajectory parameters as a function of launch azimuth forIift-off on September 19 # 1969.

90

100969288848076

I IFirst opportunitySecond opportunity

" ....J''''

~

."

.",.... 1-

,....,

,..../"

,.... /~ ./

",""" 1/V

J'

y' Vy V/

iI' 1//

:/ 1//

VV

~V

V

-1.504

-1.508

-1. 512

-1.532

-1.54072

-1.536

en -1. 516Q)

-c..-WI-~ -1.520<I..Q)ent:lU...s::u -1.524Q)t:lU0-

WI- -1.528




8720

8710

8700

8690

..c 8680..

1LJI-~

0..... 8670"0Q)til~....CIII

Q) 8660c.0~

c.(J)Q.(J)

8650

8640

8630

8620

91

First opportunity- - - - Second opportunity

I !

II

I

I

II

I

I' I\ ~,,

/, / /, ,"' ~/ /' ...

"" .... "1-0_ ",

J

\ /\ "

/

I

1'\ V

'" /~ V

'-.....t'-~V

861072 76 80 84 88 92 96 100 104




90

80

70

en 60CIJ"'C

...s:::...:::3....CIJ... 50"'CCIJ...CIJ3:00.

.....0 40s:::0:zlISs:::

(,,)

30s:::

20

10

92


to--

76 80 84 88 92 96 100




92

91

90

89

....c:..

CIJE 88::;......c:.2".......c:....16 87CIJ1II

:a..~

86

85

84

93

; , First opportunity____ Second opportunity

~

,

r'-.....'",

............ ........I

"'"r-......1' ..... ......

'"1" ... ................. ......

~....... "'-" .......

"....." ... r-.....

" j'............ r--.1' .....

....! .........I

r" ...1' ....

8372 76 80 84 88 92 96 100

Launch azimuth. III. , deg- . L



REFERENCES

1. LMAB; and OMAB: Apollo Mission F Spacecraf't Reference Trajectory.Volume II - Reference Mission Profile Trajectory Parameters(Launched August 14~ 1969). MSC IN 68-FM-197~ August 16~ 1968.

2. LMAB: Update 1 to the Lunar Orbit Mission Trajectory Ground Rules.MSC Memorandum 68-FM55-172~ May 3~ 1968.

3. LMAB: Apollo Mission G Spacecraf't Reference Trajectory.Reference Mission Profile (Launched August 14, 1969).68-FM-196, August 9, 1968.

Volume I MSC IN

4. LMAB: Apollo Mission G Spacecraf't Reference Trajectory, Volume II Reference Mission Profile Trajectory Parameters (Launched August 14,1969). MSC IN 68-FM-197, August 16, 1968.

5. NASA: Mission Requirements G-Type Mission Lunar Landing. SP08-R-008;May 23, 1968.

6. Berry, R. L.: Update 1 to the Lunar Landing Mission TrajectoryGround Rules. MSC Memorandum 68-FM55-173, May 13, 1968.

7. Joint Reference Constraints for Mission G. Flight Mechanics PanelDocument No. 68-FMP-5, July 16, 1968.

8. LMAB: Lunar Orbit Timeline to be Used in the Mission G ReferenceTrajectory. MSC Memorandum 68-FM55-117, March 25,1968.

9. Peterson, D. G.: Weight Data for Mission G. MSC Memorandum68-FM74-327, July 22, 1968.

10. CSM/LM Spacecraf't Operational Data Book, Volume III - Mass Properties.SNA-8-D-027, March 1968.

11. CSM/LM Spacecraf't Operational Data Book, Volume I - CSM Data Book.SNA-8-D-027, May 1968.

12. Univers al Mission Modular Data Book. GAEC Document LED-500-19,October 15, 1967.

13. Jiongo, E. M.: Preflight Tracking Data for the Launch Phase of. aLunar Mission. MSC IN 68-FM-38, February 14, 1968.

14. Apollo NaTigation Working Group: Apollo Missions and NavigationSystems Characteristics. ANWG TR No. AN-l.2, January 17,1967.

95

15. Frank, M. P.: Lunar Landing Sites Currently Being Used for MissionPlanning. MSC Memorandum 67-FM51-333, September 7, 1967.

16. Maynard, O. E.: Apollo Site Selection Board Meeting. MSC MemorandumPR 12/M352, January 16, 1968.

17. York, Will; and savely, Robert T.: Directory of Standard Geodeticand Geophysical Constraints for Gemini and Apollo. NASA GeneralWorking Paper No. 10, 020B, April 6, 1966.

18. OMAB: Revised LM-active Phase of Mission F. MSC Memorandum68-FM64-246, July 29, 1968.

19. OMAB: CSM-active Rendezvous of Mission F. MSC Memorandum 68-FM64-289,September 6, 1968.

~:rarj ~:~. administratio~ :588 ttt::{:f€¦ · msc internal note no. 68-fm-269 proj ect apollo...

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