SATURN V FLIGHT MANUAL SA 5O7 THIS PUBLICATION REPLACES MSFC-MAN-607 DATED 16 AUGUST 1969 FOR VEHICLE SA-607; HOWEVER MEFC-MAN.607 DATED I5 AUGUST 19611 REMAINS THE BASE LINE MAN_:,_,_ FOR SA.61M ANO SA-rd)9. 15 AUGUST1969 CHAN6ED50CTOItln t969 "1 I:"_1D! ................................... ° 15 AU6UST1969 CHAHSED 50CTOItEI 1969 ___J r. _ r Reproduction for Hn-gowrmwnt uoe of t_ inl_m_ti4m of lilust_iege mmtsl_d in this publication Is not permitted without s_ifi¢ _qn_nI! of the Jsoui_ service. line in the outer margtns oY the page. TOT_J.NUMBEROF PAGESIN THIS PUBLICATION IS 246, CONSISTING OF THE FOLLOMING: lie Imue * 1]tie ........................... S OCt 1969 * A .............................. $ Oct 1969 6-2 ............................... Oripal i................. • 6-3 .............................. $ Oct 1969 64 Itum 6-10 ....................... Orqinal *',,00 ,,, O_J_d °6-11 tlml 6-12 .................... $Oct 1967 * ill. .S Oct 1969 6-13 thin 6-16 ...................... Ol_q_.l • 6-17 ............................. $ Oct 1969 I-1 thru 1-3 ........................ * i-4 ............................. $ Oct 1969 6-18 tluu 6-33 ...................... O_inal I-S 6-34 Blank ......................... "_i_inal "'''°°''''''' .......... ° ,.°..,, O_i_ • I-6 ............................. 5 Oct 1969 7-1 tent 7-21 ....................... O_l_nal • 7-22 ............................ 5 Oct 1q69 1-7 thru 1-9 ........................ Original 7-23 .............................. Orisinat * !-i0 Blank ......................... Original • 7-24 thru 7-25 .................... 5 Oct 1969 * 2-1 thru 2 20 ..................... 5 Oct 1969 • 3-1 ............................. $ Oct 1969 7-26 thru 7-30 ...................... O_inal 8-1 tima 8-20 ....................... OriginaJ 3-2 thru 3-10 ....................... Original • 8-21 tlma 8-23 .................... 5 OCt 1969 * 3-11 thru 3-22 .................... 5 Oct 1969 8-24 tluru8-26 ...................... Ori_nal * 3-23 Added ...................... 5 Oct 1969 9-i thin 9-13 ....................... Ori_nal • 3-24 Blank Added ................. 5 Oct 1969 • 9-14 _ 9-16 .................... 5 OCt 1969 4-1 thru 4-3 ........................ Oristnal 9-17 * 4-4 ............................. 5 Oct 1969 .......... Ori_nal 4-5 thru 4-23 ....................... Original • 10-1 thru 10-7 .................... 5 OCt 1969 0 4-24 Bia_l,. ......................... Original • 1041Bhmk ....................... 5 Oct 1969 5-1 thru 5-28 ....................... Original • A-! thru &-4 ...................... 5 Oct 1969 • 5-29 ............................. 5 Oct 1969 • B-i thai B-3 ..................... 5 Oct 1969 • 5-30 Blank ....................... 5 Oct 1969 • B-4 Blank ........................ •Oct 1969 * 6-1 ............................. 5 Oct 1969 • Index ! thn_ Index 7 ............... 5 Oct 1969 • Index 8 Blank .................... 5 Oct 1969 * The asterisk indicates pages changed, added, or deleted by the current change. B-I NASA Chanired 5 October 1969 tmr TABLEOFCONTENTS --cTuoH i Page General Del_flptteo ........................... I-1 SECTION II Performance ................................ 2-1 SECTION III Emergeacy Detectiqm end Precedms ................ 3-1 SECTION IV S-IC Stoge " • e • • • • • • e e e e e e e e ................. 4-1 SECTION V S-II Stage .................................. 5-1 SECTION Vl S-IVB Stage ................................. 6-1 SECTION VII Instrument Unit .............................. 7-1 SECTION VIII Ground Support Interface ......................... 8-1 SECTION IX Mission Control Monitoring ....................... 9-1 SECTION X Mission Yorioblos end Constraints ...... • ---....... .10-1 APPENDIX A Abbreviations and Acronyms °" " "°ee o'.ee..ee .eu..o A-I APPENDIX II Btbliogr_y ................................ B-I INDEX Alphobeticol .............................. Index I ( i/ii O &ATUItN V FLIOHT MAIWtAL | IIA.607 FOREWORD This manual was prepared to provide the astronaut with a sk_le mwce reference as to the characteristics and functions of the SA-$07 bunch vehicle and AS-S07 flight mission. Data on the SA-$08 and SA-509 launch vehicles and missions is included, however the 15 Aulpm 1969 manual serves as the baseline manual for these two vehicles. A change to the 15 August 1969 manual, incorporating the latest released data, w/ll be reJeued for etch vehicle, SA-$08 and SA-509, approximately 30 days prior to their respective leunch dates. The manual provides general miss/on and performance d|ita, emergency detection system information, a description of each stage and the IU, lind 8 general discussion of ground support facilities, equipment, and mimuon control. A bibliography identifies edait_,t_al references ff a !i more comprehensive study is de.red. Major hardware associated differences between the Saturn V launch vehicles SA-506 through ( SA-$09 are annotated in the manual. They are identified by reference numbers in the adjacent to the new information. These reference numbers refer to footnotes which are located at the end of each section. This manuat is for information only and is not a control document. If a conflict shoukl be discovered between the manual and a control document, the control document will rule. Recommended changes or corrections to this manual should be forwarded, in writing, to the Saturn V Systems Engineering Management Office (PM-SAT-E) MSFC, Attention: Mr. H. P. Lloyd; or the Crew Safety and Procedures Branch (CF-24), MSC. Attention: Mr. D. K. Warren. REVISION NOTE Manual MSFC-MAN-507, dated 15 August 1_69, was based on the G mimion. The information in this manual describes the vehicle configuration and mission characteristics as defined for the H-I nlission and was prepared from information available approximately thirty days prior to 5 October 1969, Each page changed to make this revision is identified by a change note at the bottom of the page. Changes of technical significance are identified on these pages by a black bar in the marBin opposite the change. Nontechnical changes such as recompt_ition of pages to accommodate new information, minor rewrite to clarify meaning and correction of typographical errors ave not identified by change bars. Changed 5 October 1969 IIIi1_ 1 i liimal ETmI I II __ TAll.| OF _ VEHICLE DESIGN GROUND RULES SATURN F SYS'I'£M DESCRIPTION .............. I-I LA vcHv mcL ossc irno ....... Nae s,4verv,,No NSTRUMelVr,,.I KI I I Safety criteria are identified by Air Force Eastern Test Range PERCEPTIBLE PRELA UNCH EVENTS ............ 1-9 (AI_:_['R) SafeW Manual 1274 and AFETR Regnlatior. 127-9. SATURN V IIYITEM DEI_RIPTION Crew safety coe._leratlom requil_d the development of an EmerlKSIcy Detection System (EDS) with equipment located The Saturn V system in its broadest scope includes throughout (he I_unch vehicle to detect emergency conceptual development, design, manufacture, conditions as they develop. If an emergency condition is transportation, assembly, test, and launch. The primary detected, this system will either initiate an automatic abort mimlon of the Saturn V launch vehicle, three-stage-to.m_pe sequeace, o5"display critical data to the flight crew for tl_ir boost hunch of an Apollo Spacecraft, establbhed the basic anab_ andreection. concept. This minion ! :eludes a suborbital start of the third stage (S-IVB) engine for final boost into earth orbit and Each powelrecl stage is defined with dual redundant range subsequent reignition to provide sufficient velocity for escape safety equipment which will effect engtne cutoff and miuiom including the lunar missions. propeSant dispersion in ,the event of a launch abort after liftoff. Engine cutoff results from closing valves and LAUNCH VEHICLE DEVELOPMENT terminating the flow of fuel and oxidizer. Propellant is disperaed by detonating linear-shaped charges, .thereby The Saturn launch vehicles are the product of a long longitudinally opening the propellant tanks. evolutionary process stemming from initial studim in 1957 of the Redstone and Jupiter missiles. Eady conceptual studies SuqwS_ration included outer proven missiles such as Thor and Titan, and conddered payloads ranging from earth orbiting satellites to The separation of the launch vehkle stages in flight required manned spacecraft such as Dynasoar, Mercury, Gemini. and desfljn studies Involving consideration of many parameters. eventually Apollo. such as time of separation, vehicle position, vehicle attitude. 'singieor dual plane separation, and the type. qnantity.and location of ordnance. The Saturn V launch vehicle evolved from the earlier Saturn vehicles as a result of the decision in 1961 to proceed with the Apollo manned hmar mission. As the Apollo mission The launch vehicle stages separate in flight by explosively definition became clear, conceptual design studies were severing a circumferential separation joint and firing made, considering such parameters as structural dynamics, retrococket motors to decelerate the spent stage. Stage stalPng dynamics, and propvlsiun dynamicL separation is initiated when stage thrust decay_ to a vah0e equal to or less than 10% of rated thrust. A short crest mode is used to allow sep_r_.._on of the spent stage, and to effect Design trade-offs were made in certain areas to optimize the ullage settling of the _cces_,e stage prior to engine ignitio|,. launch vehicle design, based on minion requirements. The beat combination of design parameters for liquid propellant A delayed dual plane separation is employed between the vehicles resulted in low accelerations and low dynamic