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Lunar-Orbit Rendezvous 1961

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Lunar-Orbit Rendezvous 1961 I -J NATIONAL AERONAUTICS AND SPACE ADMINISTRATION I LANGLEY RESEARCH CENTER ZB5·11149 I VOLUME (NASJ\-TM-7Q736) MANNED LUNAR-LANDING THROUGH USE OF LONAB-OREIT BENDEZVOUS ' VOLU�E 1 {NASA) 99 p '-----.,( =HR ,..,.-I -- Y�S"-///</9!ACCESSIONN MBER!U T U «PA.G£.8)<lf iCODEJ 'NASA CR OR TMX OR AD NUMBER) /ICC.A TitQ.ORYJ MANNED LUNAR-LA through u eNo'O'f I i LUNAR·O RENDEZVO E FOREWORD In the course of conducting research on the problem of space ren­ dezvous and on various aspects of manned space mi ssions, Langley Re search Center has evolved what is believed to be a particularly appealing scheme for performing the manned lunar landing mi ssion. The key to the mi ssion is the use of lunar rende zvous, whi ch greatly reduces the size of the booster needed at the earth . More definitely the mi ssion may be described essentially as follows: A manned exploration vehicle is considered on its way to the moon. On approach, thi s vehi cle is decelerated into a low-altitude circular orbit ab out the moon. From thi s orbit a lunar lander descends to the moon surface, leaving the return vehi cle in orbit. After exploration the lunar lander ascends for rendezvous with the return vehicle. The return vehicle is then boosted into a return trajectory to the earth, leaving the lander behind . The significant advantage brought out by thi s procedure is the marked reduction in escape wei ght required; the reduction is, of course, a direct reflection of the reduced energy requirements brought ab out by leaving a sizable mass in lunar orb it, in this case, the return capsule and return propulsion system. Thi s report has been prepared by members of the LangleyRe search Center to indicate the research that has been conducted, and what a complete manned lunar landing mission using this system would entail. For further reference, main contacts are JohnD. Bird, Arthur W. Vogeley, or John C. Houbolt. J.C.H . October 31, 1961 -= --·· i 0 U T LI N EA ND NI D E X Page FOREW O RD ••• i OU TL INE AND INDEX ii SUMMA RY AND CON CLUSION S. 1 I N T R 0 UD C TI 0N • • • • • • • 5 PAR TI PROGRAM FO R MAN NED LUNA R LA ND IN G TH ROUGH USE OF LUNA R RE NDEZV OUS 6 MISIOS N DES CR IPTI ON • • 6 Mission pr ofile and ve hicle conce pt 6 WEIGHT S BOO STER REQUIREMENT S 12 VEHICLE AND PROGRAM SCHEDUL ING • • 21 PLAN AND FlJNDIN'G • • • • • • • . 28 RELIABIITYL SAFETY AND 30 Crew sa fety • • • . • • • )0 Mission acc omplishmen t and deve lopment re liab il ity 32 PR()(;R.AM • • • • • • • • • IlEV'EI.A)� Lunar Lan de r Dev e lopment • • • . • • • Rendezv ous Op e ra tion Dev e lopmen t • • . • • Instrumen ta tion Dev e lopmen t • • • • • • • . Deve lopmen t Fac ilities forLu na r Rendezv ousMissio n •• Ana log dock ing fa cility • • • • • • • • . • • . • • • • Luna r de scen t and take -off re sea rch fa cility . • • • Luna r la nd in g re sea rch fa cility • . • . • . ••• ii Page PART II TECHNICAL ASPECTS OF THE MI S SI ON 41 GU ID ANCE INTO A LUNAR ORBIT • 41 DESCENT TO LUNARSU RFACE 51 Lunar letdown • • . 51 Lunar landing technique . 55 LUNAR LAUNCH RENDEZVOU S 59 AND General considerations 59 Launch and injection phase of rendezvous 59 Coast phase of rendezvous 60 Simulation studies 61 ABORT IN PH ASES . • 70 ALL INSTR�TION, COMMU NICATIONS, LIFESU PPORT, AND AUXIL IARY POWER . • . 73 Navigation and Guidance 73 Cormnunications 75 Life Support Sy stem • . • • . 76 Auxiliary Power . 79 THERA DIATION 92 HAZARD WEIGHTLES SN ES S 94 REF EREN CES. 95 PARI' III A P P E N D IX ADDITIO NAL FA CILITIES STUDIES - AND UNDERWAY PLANNED IN SUPPORI' OF A MANNED ( AND ) LUNAR LANDING • • . • • • • • • • • • • . • • Appears in Volume II iii l SUMMARY AND CONCLU SION S Studies made at Langley ResearchCenter of various schemes for per­ forming the manned lunar landing mission indicate that the lunar rendezvous method is the simplest, most reliable, and quickest means for accomplishing the task. This technique permits a lunar exploration to be made with a single C-3 booster. A first landing is indicated in March 1966, with a possibility of an attempt as early asNovember 1965. These dates do not require changes in previously established Apollo, C-1, and C-3 development schedules. Further, the lunar rendezvous approach contains a number of features which tend to raise the schedule confidence level; the most impor­ tant of these are: (a) TheApollo vehicle, the lander, and the rendezvous experiment can all proceed on an independent parallel basis, thus avoiding schedule con­ flicts; further, the overall development is simplified because each vehicle has only a single function to perform. (b) The lunar rendezvous approach permits complete system development to be done with C-1, which will be available and well developed, and makes the entire C-3 picture exceptionally clean and simple, thus resulting in a minimum cost program. In amplification of these general remarks, the following specific conclusions are drawn from the technical studies which are summarized in the body of this report: A. MissionApproach and Scheduling: l. The lunar rendezvous method requires only a singleC- 3 or C-4 launch vehicle. Earth orbital weights required for various system arrange­ ments are summarized in figure 1. (See also tables VI and VII later in the text.) 2. The lunar rendezvous method schedules the first landing in March 19(56. 3. The lunar rendezvous method does not require that the Apollo vehicle be compromised because of landing considerations. 4. The lunar rendezvous method allows the landing vehicle configura­ tion to be optimized for landing. 5. The lunar rendezvous method requires onlyC-1 boosters for com­ plete system development. 2 The lunar rendezvous method provides for complete lander checkout and crew6. training in the lunar landing, lunar launch, and rendezvous docking operations on the actual vehicle. B. Funding: The lunar rendezvous method results in a program cost which will be less than the cost of other methods for the following reasons: 1. Requires fewer (20 to 40 percent large boosters than other programs. ) 2. Requires no Nova vehicles. ). Requires less C-3 or C-4 vehicles than other programs. 4. Programs most flights on best-developed booster (C- 1). 5. Requires a minimum of booster ground facilities, because large boosters are avoided and because of a low launch rate. The lunar rendezvous method can be readily paralleled with some other program at least total program cost. C. Lunar Rendezvous: The lunar rendezvous under direct, visual, pilot control is a simple reliable operation which provides a level of safety and reliability higher than other methods as outlined below. D. Safety and Reliability: 1. The lander configuration is optimized. 2. The single-lander system permits safe return of the primary vehicle in event of a landing accident. ). The two-lander system provides a rescue capability. 4. Crews can be trained in lunar landing, lunar launch, and rendezvous docking operations in the actual vehicle. 5. Requires fewest number of large booster flights. Provides for most flights on best-developed booster (C-1). 6. 3 E. Abort Capability: 1. abort capability meeting the basic Mercury-Apollo requirements can be providAn ed. 2. This abort capability can be provided with no additional fuel or weight penalties. F. Lunar Lander Development: 1. Lunar lander design is optimized for landing. 2. Being essentially separate from Apollo, development can proceed with a minimum of schedule conflict. 3. Research, development, and checkout can be performed on ground facilities now under procurement and which will be available in time to meet the program schedule. G. Development Facilities: 1. The lunar rendezvous method requires no additional booster ground facilities (see item B-5). 2. The ground facilities required for rendezvous-operations develop­ ment are now being procured and will be ready. 3. The ground facilities for lander development and checkout are now being procured and will be ready. O() +=- =g()� =g()� c! �6()c4 0 c! I 200,000 H/F H/F 10 1 H/F H/0 2- H/F STOR 43 H/F SOL 9 5 H/0 H/D H/ 0 STOR 6 H/0 SOL I // // 7 10 STOR STOR 10 7 160,000- 8 8 STOR SOL. / 4 9 I SOL SOL . ' � r 9 ///// 10 9 f-- // 10 rn 8 a: 8 7 0120000 9 4 ' f- 7 ' 4 fj//: I f­ 8 a: 6 7 6 53 <( � 3 w 4 5 /(/1/ 2 .. 2 ' � I ' ;� 6 I i' / -'/ / 5 f-- 3 ! / W// / / /// 8o,ooo / / /,;:/' $ ,;. I ' f" // 2 G I f-/ //'/ [jJ //� /_,/ / ' ,.f/ ::/ ' ' '''" •/ / J ,.;;.;•/#' 3: /;:1� >/>I v //; �./j'' /:0 /' :.!''f" I / /./ /. <// //; I // / •'/ . /f'/�/ /:·/ ¢"/::;/- : //(/ /)' /;>- f'f'� ',r' v 40,000 SHOEST RING ECONOMY 2-SHOESTRING PLUSH. ------ MAN DOWN 2 MEN ON LUNAR 2 MEN DOWN 2 MEN ON LUNAR 1FO R 2-4 HRS SURFACE UP TO DAY FOR HRS SURFACE UP DAYS I TO 7 2-4 5,000 10,000 15,000 0 5,000 10,000 15,000 5,CXX) 10,000 15,000 5,000 0 WEIGHT OF RE TURN0 SPA CECRAFT 0 IO,CXXJ 15,CXXJ Figure 1. - Summary of earth orbital weights. 2E 5 I N T R 0 D U C T I 0 N For several years Langley Research Center has been actively studying various aspects of the general problem of rendezvous in space. For the past year and a half attention has been focused on using rendezvous to accomplish the manned lunar landing mission, with specific attention being given to the use of lunar rendezvous, because of its attendant benefits.
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