:, :::::::::;:;::::::::::: MSC AERONAUTICS AND SPACE ADMINISTRATION MSC INTERNAL NOTE NO. 70-FM-64. March 31, 1970

Transcription

1 \ ' ~)~{{{{~. :-: :. : : : :' : : : : : :, :::::::::;:;::::::::::: MSC f, ::m NATONAL AERONAUTCS AND SPACE ADMNSTRATON MSC NTERNAL NOTE NO. 70-FM-64 March 31, 1970 r~:~:~:~:~:rr~spacecraft OPERATONAL TRAJECTORY ::::::::::.:::::::::::: FOR APOLLO 13 (MSSON H.2) ~)~~)))) LAUNCHED APRL 11, 1970 VOLUME - TRAJECTORY PARAMETERS REVSON 1 Lunar Mission Analysis Branch, Orbital Mission Analysis Branch, and Landing Analysis Branch MSSON PLANNNG AND ANALYSS DVSON " ~. ;..... V (.. s.." ~ ~ : ( ; ~. : : -\. ~ -- ' :~; MANNED SPACECRAFT CENTER HOUSTON.TEXAS '

2 MSC MSC NTERNAL NOTE NO. 70-FM-64 PROJECT APOLLO SPACECRAFT OPERATONAL TRAJECTORY FOR APOLLO 13 (MSSON H-2) LAUNCHED APRL 11, 1970 VOLUME - TRAJECTORY PARAMETERS REVSON 1 By Lunar Mission Analysis Branch, Orbital Mission Analysis Branch, and Landing Analysis Branch March31, 1970 ) MSSON PLANNNG AND ANALYSS DVSON NATONAL AERONAUTCS AND SPACE ADMNSTRATON MANNED SPACECRAFT CENTER HOUSTON, TEXAS Approved:-::--~~~::-?:.!..::==~::=;;:= R o L. Berry, C ie Luna Mission Analysis Branch Appr ''.2~~,;L/ (... orbital Mission Analysis Branch Approve :~;:a:p~~--=-~:;=w:~ Jo Mis

3 FOREWORD This document presents Revision l to Volume of the Spacecraft Operational Trajectory for Apollo 13 (Mission H-2 ) launched April 11, Volume will not be revised. This volume presents an updated sequence of events tab.le and the detailed trajectory parameters for the first launch opportunity, first injection opportunity on April 11, The re.visipn was initiated because of the following changes. 1. The coordinates of the lunar landing.site were changed from: latitude longitude radius to n. mi. latitude longitude radius n. mi. 2. A small change in the LM weight and the descent engine performance resulted in an update to the altitude and altitude- rate history for the descent and landing phase. 3. The coordinates of the photographic site, Davy crater chain, were changed from: latitude longitude -6.o 0 to latitude l ongitude An ephemeris error appeared in the rendezvous phase for the p:r;evious Volume of the operational trajectory doc\1:ment..this error affected the inertial state vectors and the G.in. t. 's-. 5. Two earth entry guidance constants, LADPAD and LODPAD, have been changed to.30 and.18, respectively. The effect of these changes on the shape of the entry trajectory are slight. iii

4 TABLES Table SEQUENCE OF MAJOR EVENTS LAUNCH WNDOW SUMMARY Page 5 15 LUNAR LANDNG AND PHOTOGRAPHY STE POSTONS. 19 V V V V SPACECRAFT WEGHT SUMMARY ENGNE PERFORMANCE SUMMARY (a ) Service module propulsion performance (b) s 1.llllinary... Lunar module performance tabular inputs ASSUMED MSSON-NDEPENDENT EXPENDABLES MGGON RADA.T TMELNE (a) (b) ( c) ( d) ( e) (f ) MSFN station characteristics Definitions of radar table headings... CSM acquisition and termination - 0 minimum elevation CSM acquisition and t ermination - 5 minimum elevation LM acquisition and termination - 0 minimum elevation LM acquisition and termination - 5 minimum elevation J V MSSON SHADOW TMELNE X x (a ) CSM ( b ) LM SYMBOL DEFNTONS AND COORDNATE SYSTEM DESCRPTONS. EARTH PARKNG ORBT iv

5 Table Page X TRANSLUNAR COAST (a) (b) ( c) TL cutoff to hybrid transfer midcourse maneuver o Hybrid transfer midcourse maneuver. Coast from hybrid transfer midcourse maneuver to LO X LUNAR ORBT NSERTON. 283 X LUNAR ORBT COAST N 60- BY 170- NAUTCAL MLE ORBT 297 XV xv XV DO BURN LUNAR PARKNG ORBT TO UNDOCKNG CSM PARAMETERS - UNDOCKNG AND SEPARATON TO LM LANDNG ) (a ) (b) nertial selenocentric Cartesian coordinates (position and velocity).. Rotational selenographic polar coordinates (position and velocity vectors) and selenocentric osculating elements XV LM PARAMETERS - UNDOCKNG AND SEPARATON TO LM LANDNG (a) ( b) ( c) ( d) (e) (f) (g) ( h) ( i) ( j ) nertial selenocentric Cartesian coordinates (position and velocity).. nertial selenocentric ideal MU coordinate system (PGNS navigated position and velocity).... Surface range, rotational selenographic polar coordinates (position and velocity vectors), and selenocentric osculating elements Performance and weight.... Descent propellant summary... Three-body relationships - LM referenced Landing radar parameters Powered landing guidance displays Powered landing guidance coordinate system (time-to-go and position and velocity vectors) - LM.. Horizon and FDA angles v

6 Table Page XV LM/CSM PARAMETERS - UNDOCKNG AND SEPARATON TO LM LANDNG XX xx XX (a) Vehicle attitudes. (b) Relative parameters CSM LUNAR ORBT COAST TO CSM PLANE CHANGE 1 CSM LUNAR ORBT PLANE CHANGE 1 MANEUVER CSM LUNAR PARKNG ORBT COAST TO LM ASCENT '7 469 (a) (b) CSM coast to Censorinus CSM coast to LM ascent XX CSM PARAMETERS - ASCENT PHASE (a) nertial selenocentric Cartesian (position and velocity) and polar coordinates (b) Rotational selenographic polar coordinates (position and velocity vectors) 526 (c) Landing site coordinates XX LM PARAMETERS - ASCENT PHASE (a) (b) ( c) ( d) (e) (f) ( g) (h) ( i) ( j ) (k) ( 1) (m) nertial selenocentric Cartesian (position and velocity) and polar coordinates.... PGNS navigated position and velocity Rotational selenographic polar coordinates (position and velocity vectors).. Rotational selenographic parameters - radial a nd tangential velocity component and altitude above landing site. Selenocentric osculating elements. Landing site coordinates Performance and weight Ascent propellant summary. Three-body relationships - LM referenced PGNS asc ent guidance parameters - local vertical coordinate system Present position and V vector. go Horizon and FDA angles. Vehicle attitude and rates ) vi

7 TABLE Page XXV LM/CSM RELATVE PARAMETERS - ASCENT PHASE xxv LM- ACTVE RENDEZVOUS (a) Coast to rendezvous radar tracking prior to CS (b) Rendezvous radar tracking prior to CS. 587 ( c) Coast to CS 592 ( d) CS burn ( e) Coast to rendezvous radar tracking prior to TP (f) Rendezvous radar tracking prior to TP 598 ( g) Coast to TP. 610 (h) TP burn ( i) Coast to first braking gate 617 ( j ) Coast to second braking gate 625 (k) First braking maneuver (1) Coast to third braking gate 630 (m) Second braking maneuver 632 (n) Coast to fourth braking gate 635 ( 0) Third braking gate ( p) Coast to fifth braking gate 640 (q) Fourth braking maneuver ) ( r) Stationkeeping to docking 645 XXV CSM/LM COAST TO LM JETTSON 649 XXV CSM SEPARATON AFTER LM JETTSON 659 XXV LM ASCENT STAGE DEORBT (a) LM coast to deorbit 665 (b) LM deorbit burn 671 ( c) LM coast to impact XXX CSM LUNAR ORBT COAST TO CSM PLANE CHANGE xxx CSM LUNAR ORBT PLANE CHANGE 2 MANEUVER XXX LUNAR ORBT COAST (a) CSM coast to Descartes 705 (b) CSM coast to Davy Rille 714 ( c) CSM coast to TE vii

8 Table Page XXX TE BURN. XXX XXXV TRANSEARTH COAST TO ENTRY ENTRY (a) Position vector.... (b) Velocity vector.... (c) Position and velocity vector - earth - centered inertial coordinate system.. (d) MU gimbal angles (e) Aerodynamic altitudes and load factors.... (f) Direction cosines (g) Heating parameters.... (h) Aerodynamic and guidance parameters A- FREE-RETURN CRCUMLUNAR COAST (a) Translunar coast (no midcourse correction) (b) Transearth coast (no midcourse correction) A- NON-FREE- RETURN TRANSEARTH COAST TO PERGEE ) viii

9 SEQUENCE OF MAJOR EVENTS LAUNCH WNDOW SUMMARY LUNAR LANDNG AND PHOTOGRAPHY STE POST ONS SPACECRAFT WEG HT SUMMARY ENGNE PERFORMANCE SUMMARY ASS UMED M SSON-NDEPENDENT EXPENDABLES MSSON RADAR TMELNE ) M SS ON SHADOW Tl MEL NE SYMB OL DEFNTON S AND COORDNATE SYSTEM DESCRPTONS EARTH PARKNG ORBT TRANSLUNAR COAST LUNAR ORBT N SERTON LUNAR ORBT COAST N 60- BY 170- NAUTCAL MLE ORBT ( 001 BURN LUNAR PARKNG ORBT TO UNDOCKNG

10 ) SEQUENCE OF MAJOR EVENTS

11 (_ _} TABLE.- SEQUENCE OF M.AJOR EVENTS Event Time, hr:min:se c, g.e.t. Time, hr :min:sec, c. s.t. Data summary Launch 00 : 00 : 00 April 11, :13:00 Azimuth, deg Launch complex A EPO insertion 00 :11: : 24 : Geodetic latitude, deg Longitude, deg Geodetic altitude, n. mi. Velocity, fps Translunar injection Burn initiation 02 : 35: : 48: 23.5 Geodetic latitude, deg Longitude, deg Velocity, fps Apogee altitude, n. mi. Geodetic altitude, n. mi Burn termination Post- TL events 02 : 40 : :53:49.0 Geodetic latitude, deg Longitude, deg Burn duration, sec Plane change, deg Apogee altitude, n. mi. Geodetic altitude, n. mi o \Jl CSM/S- VB separation 03:05: :18:49.0 Docking 03:15: :28:49.0 CSM/LM ejection 04:00: :13:49. 0 Evasive maneuver (performed by S- VB) 04:13: : 26 : V, fps 9.4 Translunar coas t, midcourse correction maneuvers MCC- 1 a MCC- 2 (hybrid transfer) MCC- 3 MCC- 4 TL plus 9 hr 30:40: LO mi nus 22 hr LO minus 5 hr April 12, :53 : 49 19:53:49 April 13, : 39:05.3 April 14, : 39:05.3 Geodetic altitude, n. mi. Geodetic altitude, n. mi. 6V, fps Burn duration, sec SM RCS propellant used, lb Plane change, deg Geodetic altitude, n. mi. Altitude above mean lunar radius, n. mi ~iss ion rules state that if the first man euver i s less than 3 sec it will be perfor med by RCS; however, a decision has been made to perform this maneuver using SPS.

12 TABLE. - SEQUENCE OF MAJOR EVENTS - Continued Event Time, hr:min:sec, g. e.t. Time, hr:min:sec, c.s.t. Data summary Lunar orbit insertion (LO) Burn initiation 7 7: 26: :39:05.3 Mass, lb Altitude above LLS, n. mi. 69,2 Selenographic latitude, deg 2.4 Selenographic longitude, deg Perilune altitude above LLS, n. mi Selenographic inclination, deg Velocity, fps Burn termination 77:32: :45:02.4 Altitude above LLS, n. mi Selenographic latitude, deg 4.2 Selenographic longitude, deg Selenographic inclination, deg 5.4 Burn duration, sec nertial burn arc, deg 23.4 Plane change, deg.5 6V, fps SPS propellant used, lb Velocity, fps Orbital period, hr:min:sec. ' 02: 08: 41 Perilune altitude above LLS, n. mi Apolune altitude above LLS, n. mi S- VB predi cted lunar impact 77:48: :01:32.0 Selenographic latitude, deg Selenographic longitude, deg CJ'\ Descent orbit insertion (DO) 81:45 : :58:49.9 Burn initiation Mass, lb o Altitude above LLS, n. mi Selenographic latitude, deg 3.6 Selenographic longitude, deg Perilune altitude above LLS, n. mi. Apolune altitude above LLS, n. mi Velocity, fps Burn termination 81:46 : :59:12.7 Altitude above LLS, n. mi Selenographic latitude, deg 3.7 Selenographic longitude, deg Selenographic inclination, deg 5.4 Burn duration, sec 22.8 nertial burn arc, deg 1.2 Plane change, deg o.o 6V, fps Velocity, fps SPS propellant used, lb Orbital period, hr :min:sec. 01: 54:12.5 Perilune altitude above LLS, n. mi Apolune altitude above LLS, n. mi First pass over Censorinus 84: 24: 55.0 April 15, :37 : 55.0 (_ (_ "--" / _)

13 (_ J _J TABLE. - SEQUENCE OF MAJOR EVENTS - Continued Event Time, hr :min:sec, g. e. t. Time, hr :min :sec, c.s. t. Data summary Descent CSM/LM undock and SEP 99:18 : : 31 : Revolution number 12 Circularization (CSM) Burn initiation 100:37: : 50: 22.0 Mass, lb Selenographic latitude, deg Selenographic longitude, deg Selenographic inclination, deg Altitude above LLS, n. mi. Peri lune altitude above LLS, n. mi. Veloc i ty, fps Revolution number Burn termination PD (DPS ignition time) 100:37: : 33 : :50: : 46 :11.4 tiv, fps Burn duration, sec Altitude above LLS, n. mi. Perilune altitude above LLS, n. mi. Apolune altitude above LLS, n. mi". ' Velocity, fps SPS propellant consumed, lb Burn arc, deg Period, hr :min:sec Altitude above LLS, ft Velocity, fps Revolution number :58: J High gate (P63 to P64) 103 : 41: : 54:43. 4 Altitude above LLS, f t Velocity, fps Low gate (500 ft) 103: 43 : : 56:21.4 Altitude above LLS, ft Velocity, fps Vertical descent (P64 to P65) 103:44 : : 57:03. 4 Altitude above LLS, ft Velocity, fps LM landing CSM first pass over LLS 103:44: : 45: : 57: :58:13.6 tiv, fps Burn duration, min: sec DPS propellant consumed, lb Revolution number Revolut i on number :

14 TABLE. - SEQUENCE OF MAJOR EVENTS - Continued Event Time, hr :mi n:sec, g.e.t. Time, hr :min:sec, c.s.t. Data summary CSM plane change (LOPC - 1) Burn i ni ti at ion 113:46:02.7 April 16, : 59:02.7 Mass, lb Selenographic latitude, deg Selenographic longitude, deg Altitude above LLS, n. mi. Perilune altitude above LLS, n. mi. Apolune altitude above LLS, n. mi. Velocity, fps Revoluti on number Burn termination Second pass over Censorinus 113: 46 : :04 : :59 : :17 : Mass, lb 6V, fps Burn durat i on, sec Selenographic latitude, deg Selenographic longitude, deg Altitude above LLS, n. mi. Perilune altitude above LLS, n. mi. Apolune al titude above LLS, n. mi. Plane change, deg Selenographic inclination, deg Velocity, fps Revolution number Revolution number Cb CSM second pass over LLS 137:14:05. 1 April 17, : 27 : 05.1 Revolution number 31 Ascent LM lift- off 137: 15 : :28:22.5 Mass, lb Selenographic l atitude, deg Sel enographic l ongitude, deg Revolut i on number LM insertion 137 : 22 : : 35:32.4 Mass, lb 6V, fps Burn duration, sec Latitude, deg Longitude, deg Altitude above LLS, ft Perilune altitude above LLS, ft Apol une altitude above LLS, ft o (_ (_ '-----" J

15 '-.._.../,, \,,, TABLE. - SEQUENCE OF MAJOR EVENTS - Continued Event Time, hr:min:sec, g.e.t. Time, hr:min :sec, c.s.t. Data summary Rendezvous CS 138:12: :25:10.1 Revolution number Burn duration, sec 6V, fps Propellant used, lb Resultant ha/hp, n. mi /43.2 Range at cutoff, n. mi. Range rate at cutoff, fps Propulsion system LM RCS CDH 139:10: :23:28.9 Burn duration, sec 6V, fps o.o o.o TP Braking 139 : 51 : :33: :04: :.46:05.0 Burn duration, sec 6V, fps Propellant used, lb Resultant ha/hp, n. mi. Range at cutoff, n. mi. Range rate at cutoff, fps Propulsion system Revolution number Burn duration, sec 6V, fps Propellant used, lb Range at final braking, n. mi. Range rate at final braking, fps ha/hp at final braking, n. mi o 60.7/ LM RCS /58.0 \D Propulsion system Revolution number LM RCS 33 Docking LM jettison 140:50: :10: :03: :23: 59.8 Selenographic latitude, deg Selenographic longitude, deg CSM/LM separation Burn initiation Burn termination 143:15 : :16: :28: :29:04.5 Mass, lb 6V, fps Burn duration, sec Selenographic latitude, deg Selenographic longitude, deg Altitude above LLS, n. mi. Perilune altitude above LLS, n. mi. Apolune altitude above LLS, n. mi. Plane change, deg Selenographic inclination, deg Velocity, fps Revolution number o.o

16 TABLE. - SEQUENCE OF MAJOR EVENTS - Continued Event Time, hr:min :sec, g.e.t. Time, hr:min:sec, c. s.t. Data summary LM deorbit 144:39: : 52:12.6 Mass, lb t:n, fps Burn duration, sec Selenographic latitude, deg Selenographic longitude, deg LM impact 144: 55: : 08 : 31.l Mass, lb Selenographic latitude, deg Selenographic longitude, deg Velocity, fps CSM latitude, deg CSM longitude, deg CSM revolution number LOPC - 2 Burn initiation 154:21: :34 :19.6 Burn termination 154:22: :35:02.8 Mass, lb b.v, fps Burn duration, sec Selenographic latitude, deg Selenographic longitude, deg Altitude above LLS, n. mi. Perilune altitude above LLS, n. mi. Apolune altitude above LLS, n. mi. Plane change, deg Selenographic inclination, deg Velocity, fps Revolution number Pass over Descartes 158:42:43.9 April 18, 1970 Revolution number 03:55:43.9 Pass over Davy crater chain 158 : 49 :46. o o4: 02:46.o Revolution number Transearth injection Burn initiation 167:38: :51:39.1 Mass, lb Altitude above LLS, n. mi. Selenographic latitude, deg Selenographic longitude, deg Perilune altitude above LLS, n. mi. s elenographic inclination, deg Velocity, fps Revolution number f-' , _/ -

17 ...: _) TABLE. - SEQUENCE OF EVENTS - Concluded Event Time, hr:min: sec, g.e.t. Time, hr:min:sec, c.s.t. Data summary Burn termination 167:40: :53:53.8 Altitude above LLS, n. mi. Selenographic latitude, deg Selenographic longitude, deg Perilune altitude above LLS, n. mi. Selenographic inclination, deg Burn duration, sec nertial burn arc, deg Plane change, deg ~v, fps SPS propellant used, lb Velocity, fps i Transearth coast, midcour~e correction maneuvers MCC - 5 MCC - 6 MCC- 7 Entry interface TE plus 15 hr E minus 22 hr E minus 3 hr 240:49:49.6 April 19, :53:53.8 April 20, :02:49.6 April 21, :02: :02:49.6 Geodetic altitude, n. mi. Geodetic altitude, n. mi. Geodetic altitude, n. mi. Transearth coast time, hr nertial velocity, fps Geodetic altitude, n. mi. (ft) nertial f l ight- path angle, deg Geodetic latitude, deg Longitude, deg Equatorial inclination (ascending ), deg ( ) f-' f-' CM landing 241:03: :16:40.8 Geodetic latitude, deg Longitude, deg

18 LAUNCH WNDOW SUMMARY

19 15 TABLE.- LAUNCH WNDOW SUMMARY Launch date Site..... Launch azimuth, deg Launch time, hr :min, c. s.t. Free- return h, n. mi. p Hybrid transfer ~V, fps Translunar flight time, hr:min Lunar orbit inclination, deg Approach azimuth at landing, deg Sun elevation at landing, deg Goldstone landing coverage, hr :min 1 Goldstone plus Parks landing coverage, hr:min Lunar surface staytime, hr.. April 11, 1970 Fra Mauro 72 to 96 13:13 to 16 : to :45 5, ,9 to :15 10:10 Photo sites Total lunar orbit staytime Transearth flight time, hr Total mission time, hr Censorinus Davy crater chain Descartes 90 hr, 46 revs 73 to to 238

20 LUNAR LANDNG AND PHOTOGRAPHY STE POSTONS

21 19 TABLE.- LUNAR LANDNG AND PHOTOGRAPHY STE POSTONS Launch date a Eunar - site Latitude, Longitude, Altitude, name deg deg n. mi. April 11 Fra Mauro Photography sites April 11 Censorinus April 11 Descartes April 11 Davy crater chain aall altitudes shown are referenced to mean lunar radius of n. mi. )

22 ) SPACECRAFT WEGHT SUMMARY

23 23 TABLE V.- SPACECRAFT WEGHT SUMMARY ) Total CSM inert lb. CM inert, lb SM inert, lb SLA ring, lb. Total SPS propellant tanked, lb SPS deliverable, lb SPS trapped, lb Total LM at earth launch, lb. LM descent stage, lb... LM DPS tanked, lb. LM ascent stage+ RCS propellant, lb LM APS tanked, lb.. Spacecraft at earth launch (including LES ), lb... Spacecraft before T & D , ,9

24 ) ENGNE PERFORMANCE SUMMARY

25 2 7 TABLE V.- ENGNE PERFORMANCE SUMMARY (a) Service module ~propulsion performance summary Propulsion Thrust, Flow rate, sp' system lb lb/sec sec SPS RCS a ) a Two-quad.

26 28 TABLE V.- ENGNE PERFORMANCE SUMMARY - Concluded (b ) Lunar module performance tabular inputs Descent Ascent DPS RCS APS + RCS Burn Effect ive Thrust, sp' Thrust per sp' Effective time,, sec lb sec engine, lb sec thrust, lb sp sec , ) o ,

27 ) ASSUMED MSSON- NDEPENDENT EXPENDABLES

28 31 TABLE V.- ASSUMED MSSON-NDEPENDENT EXPENDABLES ) Mission-independent SPS budget Translunar MCC (120 fps ), lb Transearth MCC (Ofps ), lb SPS propellant allowances Unbalance meter, lb Mean outage, lb..... Dispersions, lb )