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Apollo 11 Mission Report November 1969

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Apollo 11 Mission Report November 1969 =-·. MSC-00171 NATIONAL AERONAUTICS AND SPACE ADMINISTRATION APOLLO 11 MISOS[ON REPORT I \ :Jj\ MANNED SPACECRAFT CENTER HOUSTON,TEXAS NOVEMBER 1969 APOLLO SPACECRAFT FLIGHT HISTORY Mission S12acecraft Description Launch date Launch site PA-l BP-6 First pad abort Nov. 7, 1963 White Sands Missile Range, N. Mex. A-001 BP-12 Transonic abort Ma;y 13, 1964 White Sands Missile Range, � N. Mex. 1- AS-101 BP-13 Nominal launch and Ma;y 28, 1964 Cape Kennedy, . - exit environment Fla. !' AS-102 BP-15 Nominal launch and Sept. 18, 1964 Cape Kennedy, exit environment Fla. A-002 BP-23 MaximUIIl dynamic Dec. 8, 1964 White Sands pressure abort Missile Range, --� \._._ -::_, N. Mex. AS-103 BP-16 Micrometeoroid Feb. 16, 1965 Cape Kennedy, experiment Fla. A-003 BP-22 Low-altitude abort Ma;y 19, 1965 White Sands (planned high- Missile Range, altitude abort) N. Mex. AS-104 BP-26 Micrometeoroid Ma;y 25 , 1965 Cape Kennedy, experiment and Fla • ..;;__ service module RCS launch environment PA-2 BP-23A Second pad abort June 29, 1965 White Sands Missile Range, N. Mex. AS-105 BP-9A Micrometeoroid July 30, 1965 Cape Kennedy, experiment and Fla. service module RCS launch environment -, A-004 SC-002 Power-on tumbling Jan. 20, 1966 White Sands boundary abort Missile Range, N. Mex. AS-201 SC-009 Supercircular Feb. 26, 1966 Cape Kennedy, entry with high Fla. heat rate AS-202 SC-Oll Supercircular Aug. 25, 1966 Cape Kennedy, \ entry with high Fla. heat load (Continued inside back cover) MSC-00171 APOLLO 11 MISSION REPORT PREPARED BY Mi ssion Evaluat ion Team / APPROVED BY George� M. LowL.c.r-- Managc�er , Ap ollo Spacecraft Program NATIONAL AERONAUTICS AND SPACE ADMINISTRAT ION MANNED SPACECRAFT CENTER HOUSTON , TEXAS November 1969 ----· - -- ·--___...- --.,__ "Houston, the Eagle has landed." iii CONTENTS Section Page 1.0 SUMMARY 1-1 2.0 INTRODUCTION 2-1 3.0 MISSION DESCRIPTION 3-1 4.0 PILOTS' REPORT 4-1 4.1 PRELAUNCH ACTIVITIES 4-1 4.2 LAUNCH 4-1 4.3 EARTH ORBIT COAST AND TRANSLUNAR INJECTION 4-1 / 4.4 TRANSPOSITION AND DOCKING 4-2 4.5 'TRANSLUNAR COAST 4-2 4.6 LUNAR ORBIT INSERTION 4-3 4.7 LUNAR MODULE CHECKOUT 4-4 4.8 DESCENT PREPARATION . 4-4 4.9 UNDOCKING AND SEPARATION 4-7 4.10 LUNAR MODULE DESCENT 4-7 4.11 COMMAND MODULE SOLO ACTIVITIES 4-9 4.12 LUNAR SURFACE OPERATIONS 4-10 4.13 LAUNCH PREPARATION 4-16 4.14 ASCENT 4-17 4.15 RENDEZVOUS 4-17 .#- 4.16 COMMAND MODULE DOCKING 4-18 4.17 TRANSEARTH INJECTION 4-19 r TRANS EARTH - 4.18 COAST 4-19 '" • 1 4.19 ENTRY . 4-20 ....... "' 4.20 RECOVERY 4-20 5.0 LUNAR DESCENT AND ASCENT 5-1 5.1 DESCENT TRAJECTORY LOGIC 5-1 5.2 PREPARATION FOR POWERED DESCEN1� 5-2 5.3 POWERED DESCENT . 5-4 iv Section Page 5.4 LANDING DYNAMICS . 5-6 5.5 POSTLANDING SPACECRAFT OPERATIONS 5-7 5.6 ASCENT 5-8 5.7 RENDEZVOUS 5-10 -� 6.0 COMMUNICATIONS 6-1 -----. 7.0 TRAJECTORY 7-1 7.1 LAUNCH PHASE 7-1 "'-- 7.2 EARTH PARKING ORBIT 7-1 - 7.3 TRANSLUNAR INJECTION 7-1 (o 7.4 MANEUVER ALYSIS . 7-2 AN 7.5 COMMAND MODULE ENTRY 7-4 7.6 SERVICE MODULE ENTRY 7-5 7.7 LUNAR ORBIT TARGETING 7-5 7.8 LUNAR ORBIT NAVIGATION . 7-6 8.0 COMMAND AND SERVICE MODULE PERFORMANCE 8-1 8.1 STRUCTURAL AND MECHANICAL SYSTEMS 8-1 8.2 ELECTRICAL POWER 8-4 8.3 CRYOGENIC STORAGE 8-5 8.4 VHF RANGING . 8-5 8.5 INSTRUMENTATION 8-5 8.6 GUIDANCE , NAVIGATION , AND CONTROL 8-6 8.7 REACTION CONTROL 8-19 8.8 SERVICE PROPULSION 8-19 8.9 ENVIRONMENTAL CONTROL SYSTEM 8-23 ·-. 8.10 CREW STATION 8-24 8.11 CONSUMABLES 8-25 9.0 LUNAR MODULE PERFORMAN CE 9-1 9.1 STRUCTURAL AND MECHANICAL SYSTEMS 9-1 9.2 THERMAL CONTROL . 9-1 9.3 ELECTRICAL POWER 9-2 v Section Page 9 .4 COMMUNICATIONS EQUIPMENT 9-2 9·5 INSTRUMENTATION 9-3 9.6 GUIDANCE AND CONTROL 9-3 9.7 REACTION CONTROL 9-19 9.8 DESCENT PROPULSION 9-22 9·9 ASCENT PROPULSION . 9-27 9 .10 ENVIRONMENTAL CONTROL SYSTEM 9-29 9 .11 RADAR . 9-29 9.12 CREW STATION 9-30 9.13 CONSUMABLES 9-30 10 .0 EXTRAVEHICULAR MOBILITY UNIT PERFORMANCE 10-1 11.0 THE LUNAR SURFACE . 11-1 11.1 LUNAR GEOLOGY EXPERIMENT 11-3 11 .2 LUNAR SURFACE MECHANICS EXPERIMENT 11-12 11 .3 EXAMINATION OF LUNAR SAMPLES 11-14 n.4 PASSIVE SEISMIC EXPERIMENT 11-17 11 .5 LASER RANGING RETRQ-REFLECTOR EXPERIMENT 11-22 11 .6 SOLAR WIND COMPOSITION EXPERIMENT 11-23 11 .7 PHOTOGRAPHY . 11-23 12.0 BIOMEDICAL EVALUATION 12-1 12 .1 BIOINSTRUMENTATION AND PHYSIOLOGICAL DATA 12-1 12 .2 MEDICAL OBSERVATIONS 12-2 12 .3 EXTRAVEHICULAR ACTIVITY 12-5 12.4 PHYSICAL �XAMINATIONS 12-5 12 .5 LUNAR CONTAMINATION AND QUARAN'nNE 12-6 -. 13.0 MISSION SUPPORT PERFORMANCE 13-1 13 .1 FLIGHT CONTROL 13-1 13 .2 NETWORK PERFORMANCE 13-2 13 .3 RECOVERY OPERATIONS 13-3 vi Section Page 14.0 ASSESSMENT OF MISSION OBJECTIVES 14-1 14.1 LOCATION OF LANDED LUNAR MODULE 14-1 14.2 LUNAR FIELD GEOLOGY 14-2 15.0 LAUNCH VEHICLE SUMMARY 15-1 16.0 ANOMALY SUMMARY . 16-1 16.1 COMMAND AND SERVICE MODULES 16-1 16.2 LUNAR MODULE 16-9 16.3 GOVERNMENT-FURNISHED EQUIPMENT 16-21 17.0 CONCLUSIONS . 17-1 APPENDIX A - VEHICLE DESCRIPTIONS A-1 A.1 COMMAND AND SERVICE MODULES A-1 A.2 LUNAR MODULE . A-1 A.3 EXTRAVEHICULAR MOBILITY UNIT A-5 A.4 EXPERIMENT EQUIPMENT A-8 A.5 LAUNCH VEHICLE A-10 A.6 MASS PROPERTIES A-10 APPENDIX B - SPACECRAFT HISTORIES B-1 APPENDIX C - POSTFLIGHT TESTING C-1 APPENDIX D - DATA AVAILABILITY D-1 APPENDIX E - GLOSSARY E-1 vii SYMBOLS AND ABBREVIATIONS A ampere ac alternating current AGS abort guidance system A-h ampere-hour ALDS Apollo launch data system arc sec arc second -� ARIA Apollo range instrumentation aircraft BDA Bermuda Btu British thermal unit CAPCOM capsule communicator CATS command and telemetry system c.d.t. central daylight time em centimeter CMC command module computer CRO Carnarvon, Australia ·csM command and service modules CYI Canary Islands D down dB decibel (also used as dBm) de direct current deg degree D/T delayed time E east e.s.t. eastern standard time FM frequency modulation - f't/sec feet per second g gravity of earth G&N guidance and navigation GDS Goldstone, California G.m.t. Greenwich mean time viii HAW Hawaii hr hour HSK Honeysuckle, Australia Hz hertz I inertia in-lb inch-pound kpps kilopulses per second kW-h kilowatt-hour lb/hr pounds per hour lb/ft2 pounds per square foot LGC lunar module guidance computer LM lunar module M mega- MAD Madrid, Spain mERU milli-earth rate unit mg milligram MILA Merritt Island Launch Area, Florida min minute millimeter msec millisecond mm MSFN Manned Space Flight Network N north NA not available pressure transducer location p ( ) PAM pulse amplitude modulation PCM pulse code modulation PM phase modulation ppm parts per million psf pounds per square foot psi pounds per square inch q dynamic pressure RED Redstone tracking ship ix REFSMMAT REFerence Stable Memb er MATrix s south S-IC, S-II , first, second , and th ird stages of Saturn V launch vehi cle S-IVB T temperature (transducer location ) TAN Tananarive us United States v volt VAN Vanguard tracking ship VHF very high frequency vox voice-operated transmitter w wes t W-h watt-hour X, Y, Z spacecraft axes degrees Centigrade de grees Fahrenheit angle of at tack micro- aj.l 1-1 1.0 SUMMARY The purpose of the Apollo 11 mission was to land men on the lunar surface and to return them safely to earth. The crew were Neil A. Arm­ strong, Commander ; Mi chael Collins , Command Module Pilot ; and Edwin E. Aldrin, Jr. , Lunar Module Pilot . The space vehicle was laun ched from Kennedy Space Center , Florida , at 8:32:00 a.m. , e.s.t. , July 16 , 1969 . The activities during earth orbit checkout , translunar injection , transposition and docking , space­ craft ejection, and translunar coast were similar to those of Apollo 10 . Only one midcourse correction , performed at ab out 27 hours elapsed time , was required during trans lunar coast. The spacecraft was inserted into lunar orbit at ab out 76 hours , and the circularization maneuver was performed two revolutions later. Initial checkout of lunar module systems was satisfactory , and after a planned rest period , the Commander and Lunar Module Pilot entered the lunar module to prepare for des cent . The two spacecraft were undocked at ab out 100 hours , followed by separation of the command an d service modules from the lunar module . Descent orbit insertion was performed at approximately 101-l/2 hours , and powered de scent to the lunar surface began ab out 1 hour later. Operation ·of the guidance and descent propulsion systems was nominal . The lunar module was maneuvered manually approximately 1100 feet downrange from the nominal landing point during the final 2-1/2 minutes of descent . The spacecraft landed in the Sea of Tranquillity at 10 2:45:40 . The landing coordinates were 0 degrees 41 minutes 15 seconds north latitude and 23 de­ grees 26 minutes east longitude referenced to lunar map ORB-II-6 (100), first edition , December 1967 .
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