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LUNAR EXPEDITION PLAN
LUNEX
MAY 1961
CLASP rFICATION CHATWC& TO
• B V . A L T ' I jpr i r Or lUy*if I V T ™
DATE f A / 7 9 - ^ f e r f g
HEADQUARTERS
SPACE SYSTEMS DIVISION
AIR FORCE SYSTEMS C O M M A N L T
DOWNGRADED AT 12 YEAR INTERVALS; NOT /.J1. L MATICALLY DECLASSIFIED. DOb D.R 5200.10
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KHl FCRCE SPACE SYSTEMS DTVISION AIR FCRCE SYSTEMS CQWAND
29 Jfey 1961
FCREtfCRD
This document provides a plan for a maimed Lunar Expedition. It was prepared to furnish more detailed Information In support of the Rational Space Program proposed by a USAF committee chaired by Major General J. B. Kolzapple. That report pointed out the dire peed for a goal for our national space program. The £unar Expedition ¥as cnosen as the goal since it not only" provides a sufficient challenge to the nation, but also provides technical fall-outs for greatly improved space capabilities-
Previous editions of this plan have provided guidance and incentive to Air Force technical groups. Consequently, their efforts have established a broad technical base within the Air Force from which rapif - ivances can be made- This capability has'been taken Into account in laying out the accelerated schedules in this plan.
CL..' r::iFICAT!ON C^AISFP To
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GENERAL LUNAR DATA Dlitont* hoiii north
mman (BIICF-) 239,000 |HloiMl»ri) 387,000
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mFJtt 2140 lutanMIH 34B0
TamptraturH um at Mnnh 101'CtD )30*C night -1S3*C
GRAPHIC INFORMATION
N a i » i Thn ftvrurt nanw Hhctid w i n odoptad frpn th* T935 Inlvmational ArinnOffkal Uniap flpmMKlBturt By"***" with minor ihnngMoy Ynkci Obwrralory in I f 5 * .
*re[*diDn An wlliuuiBRhk prajtdion porttg^i tnt n o w n o vh*r* rnHw hun p t y c r i w * troulnd by timing (ram a t Inflnlh diUm<x.
Ceniial Thi* i l a contrallad mowic. Position »a» datarniinad through H w u i a f Hlonogrophic tontml Hrobfahcd primarily hum tnn N O -y n of J. hum vid S > . SoyndMi. A coltuMrf Hiring of rhna pnitient n w pubHibid imdor th* o i m n i of the Morriotionnl Airrononiienl Union In 1»33.
MmngtapBy Th* moioic » eomprnad of photognjpln token olY*rfi«.McDonaldandMt. Wihon ObtorvoJorlai. PholDsiniphi with high carwiil-llltt hi" ongHH u r n HHrttvd ID maintain uniform portrayal of lunar crawl and prom-ianrmir and drK*ailU* marlo ragwn*.
Orrantanoli Cardrool dltncHont h a n bean Mtebl i iW In conform *rth tertogrophic tradition, not* to tea and aatt la fight, rathar than cBtronomLcai canvonlion. Th'k afnmrfltion ^HilroTa 1h* •son in Hi trvt nriaKorahip hi Hit •orlh. 1 * 0 * of th . ™ U . d»< at moan nbrnnor. i . inown.
NAMES LEGEND
Craton {dimmrlcr» m ihiloi)
100 and a m CLAVHJS SO to 100 m » U » than 50 — .
Mountain Rang*! (inngth m nilm)
400 andovct APENK1NE Kounr»i*s I H I Hon 400 »•(•£(« •!&
Mountain Poakt. Vallvyn Walk and Rilln >rrcH» Mil
OcooM, Girlfl. oayt, Sou, an: (Ivngth of motor anil in miln]
MO and«™ MARE IMBRIUM 200 to 400 MAK£ NVBIUM km man 2 0 0 SIKU1 MOXB
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CONTENTS
I .
n. in.
IV.
v.
VI.
VII.
VIII.
EC.
X.
SUMMARY
PROGRAM DESCRIPTION
MASTER SCHEDULES
DEVELOPMENT - TEST - PRODUCTION
BUDGET AMD FINANCIAL
PROGRAM MANAGEMENT
MATERIEL SUPPORT
CIVIL ENGINEERING
PERSONNEL AND TR/. "SING
INTELLIGENCE
Appendix # 1 Glossary o f Terms
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PROPOSED EIS1EM EACKfttffi PUN
K R
LUNAR EXFEDITIOH
Prepared toy Support Systeas Plans Dinaion
Approved by l l ^ i t i ^ ^ ^LxJcAjV*^^ Horaix M. Lulejian y Colonel, USAF Director, Advanced Systems Flans And Analysis
Classification c&qnsed t'i
By antfccri ty oT
Pate * j A j ^ j _
&*tM.tudr
DOWNGRADED AT 12 YEAR INTERVALS: MOT AUTOMATICALLY DECLASsiMra non niR 520010
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SECTION I
SUMMAHT
LUHAH EXPEDITIOH (U)
(LUHEX)
1 .1 TOLAE-S-458
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INDEX
TITLE PAGE 1 . 1
RECORD OF CHANGES . - , . . . , . , , 1 . 2
INDEX 1 . 3
1 . 0 SUMMARY 1-5
1 . 1 PURPOSE 1 . 5
1 . 2 BACKGROUND 1 . 5
1-3 DESCRIPTION 1 . 5
l . U MAJOR PROBLEM AREAS 1-7
1-5 MILESTONES 1 . 7
1 . 6 CAPABILITIES DEVELOPED 1 . 8
1 . 7 MAHAQEHEHT ACTIONS REQUIRED , 1 . 8
ATTACHMENTS
CHART I-A LUNAR EXPEDmON PROGRAM MILESTONE SCHEDULE
CHART I-B LUNAR EXPEDITION MANAGEMENT MILESTONES FZ6S - FY63
• • - a -
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1.0 SUMMARY
1.1 PURPOSE
The Lunar Expedition has as its objective manned exploration of the moon with the first manned landing and return in late 196?. This one achievement if accomplished "before the USSR, will serve to demonstrate conclusively that thiB nation possesses the capability to win future competition in technology. Ho space achievement short of this goal will have equal technological significance, historical Impact, or excite the entire world.
1.2 BACKGROUND
Extensive studies by Air Force-Industry teams during 1958* 1959» and i960 examined all facets of the problem and techniques of sending men to the moon and resulted in a feasible concept which is attainable at an early date and ie economical and reliable. Laboratories within the Air Force participated In this effort, thus establishing a broad technological base which can-react (illicitly to an expanded high priority program.
1-3 DESCRIPTION
The lunar mission would be initiated by the launching of the lunar payload by a large, three-stage liquid or solid propellant booster to escape velocity on a lunar intercept trajectory. The payload, consisting of a Lunar Landing Stage, Lunar Launching Stage and a manned vehicle, would use a lunar horizon scanner and a doppler altimeter for orientation prior to a soft landing using the Lunar Landing Stage. Terminal guidance using prepositioned beacons would be required for landing at a preselected site. The Lunar Launch Stage .would provide the necessary boost for the return to earth of the manned Lunex Re-entry Vehicle. Using mid-course guidance and aerodynamic braking, the vehicle would effect re-entry and a normal unppwered aircraft landing at a ZI base.
In addition to the manned vehicle a.cargo payload is Included in this plan. The cargo payload would utilize the same three-stage earth launch booster and the same lunar landing techniques. Hov-
f~&* ever it would not be returned to earth and would be used only to transport supplies and cargo to the expedition on the moon.
The primary concept recommended in this plan is the "direct shot" method since studies have indicated it could be available
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--at an earlier date and it vould be more reliable. Another, .concept. is also suggested which consists of the rendezvous and assembly of components in an earth orbit before injection into a lunar trajectory. The techniques and development required for this latter concept are documented under a separate SSP titled, S1AIHT. Therefore, no details of this concept are presented in this plan. All schedules relating the two plans have been coordinated to insure compatibility and to take advantage of mutual advances. Since neither rendezvous techniques nor large boosters have been demonstrated, both approaches must be pursued until it becomes obvious that one of than has clear advantages over the other.
The following developments are required in order to accomplish the lunar expedition:
a. A three-man Lunex Re-entry Vehicle. This vehicle must be capable of re-entry into the earth's atmosphere at velocities of 37,000 ft/sec. It must also be capable of making a conventional aircraft landing. Control and improved guidance for entering the earth's atmosphere at the proper place and angle is needed as veil as improved materials to withstand tbe high surface temperatures. Adequate life support equipment is also required. The development of this vehicle is the key to the accomplishment of the LUHEX program and is one of the pacing development items. A detailed schedule for its development is included.
b- A Lunar Landing Stage for decelerating and landing the entire payload. This stage must have the capability to decelerate 13^000 pounds from a velocity of almost 9,000 ft/sec to 20 ft/sec at touchdown. A doppler altimeter is required to provide information for ignition and control of the engine. Horizon scanners must be used to orient the payload to the local vertical.
c. A Lunar Launch Stage capable of launching the manned Lunex He-entry Vehicle from the lunar surface. Lunar ascent guidance is required to place the vehicle on the proper trajectory.
d. A three-stage earth launch booster, referenced as a Space launching system. The first stage will use either LOX/LHO with six million pounds of thrust or a solid fuel with an equivalent launch capability. The second and third stages will use LOX/LHg. The development of this space launching system is considered the
£« pacing development item for the LUHEX program. Because Of the magnitude of the booster program and the applicability of the
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booster to other programs, the plan for its development is being presented separately.
In addition to the above listed hardware developments, additional Information is required about the lunar surface such as its physical and roughness characteristics. High resolution photographs of the entire lunar surface may provide this information. Present NASA plans if expedited could provide the information for this LUMEX program. HASA's SURVEYOR (soft lunar landing) program could also incorporate radio-light beacons which vould be used later in conjunction with a terminal landing system. A core sample of lunar material is required as soon as possible so that design of lunar landing devices and lunar facilities can be accomplished.
l.h MAJOR PROBLEM AREAS
The development of techniques for re-entering the earth's atmosphere at 37,000 ft/sec is one of the major problems. Guidance equipment must be very accurate to Insure that the re-entry angle is within ± 2°. Too steep an entry angle will cause overheating and untolerable G loads, while too shallow an entry angle may permit the Lunex Be-entry Vehicle to skip out of the atmosphere into a highly eccentric earth orbit. If this happens, the vehicle tn y spend several days in the trapped radiation belts and may exceed the time limits of the ecological system.
The Lunar Landing Stage will be a difficult development because of a requirement for orientation with the local vertical when approaching the moon- It must also be guided to the selected landing site. Many tests will be required to develop the necessary equipment.
The Lunar Launching Stage will be another difficult development. The prelaunch countdown must be performed automatically and, if the launching booster is not vertical upon launch, corrections must be made in order to attain the required moon-earth trajectory.
Although the foregoing developments are difficult, no technological break-through will be required. All designs can be based on extrapolation of present technology-
# ' •
1.5 MILESTONES
Major milestones in the program are:
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a. Becovery of 'ft manned re-entry vehicle from 50,000 mllee in 1965.
b. Manned circumlunar flight in 1966.
c. Manned lunar lunging and return in 1967.
These and other significant events are shown on Chart I-A.
1.6 CAPABILITIES DEVELOPED •
The development of large boosters, rendezvous techniques and maneuverable Space vehicles, all required for the Lunar Expedition, will also provide a capability for many new and advanced space achievements. For example, the Space Launching System which will boost 13^,000 pounds to escape velocity will boost approximately 350,000 pounds into a 300 nm orbit, or will launch a manned vehicle on a pass around either Mars or Venus.
1.7 MANAGEMENT ACTIONS REQUIRED
The major Management Milestones for FX62 and FY63 are shorn on Chart I-B. Immediate attention by Management to obtain Program Approval and Funding by July 1961 is necessary if the United States is to put a "man on the moon" by August 1967.
Throughout the LUHEX program time allocated for management and Air Force technical evaluations has been kept to a minimum. This is essential to meet the schedules, and delays In providing funding as indicated, or in receiving notification of required decision, will have the direct effect of delaying the program end . objective.
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CHART I - A
LUNAR EXPEDITION PROGRAM MILESTONE SCHEDULE
CALENDAR YEARS I9( 51 1962 1963 1964 1965 1966 1967 I96S
PRELIMINARY DESIGN COMPLETE ( LUNEX PAYLOAD) "^
PROGRAM APPROVAL AND FUNDING j
ENGINEERING DESIGN AND MOCK-UP _3E ' J —
INITIATE HARDWARE PROCUREMENT 3 > RE-ENTRY VEHICLE 1 9 0 % ENS REL ) 0 LUNAR LANDING STAGE ( 9 0 % ENG REL) . j
FIRST MANNED ORBITAL FLIGHT 9 CARGO PAYLOAD ( 9 0 % ENG REL) ]} LUNAR LAUNCH STAGE t 9 0 % ENG REL) FIRST LUNAR LANDING (CARGO TEST FLIGHT) _ MANNED CIRCUMLUNAR FLIGHT 3 C A
SPACE LAUNCHING SYSTEM FLIGHT QUALIFIED : : !B£ M A L D LUNAR LANDING A»2 RETURN 3E; PtSwANENTLY MANNED LUNAR EXPEDITION q t n - _ -1 | T 1 U - " -
LUNAR EXPEDITION FUNDING REQUIREMENTS (MILLIONS) 27 112 350 710 1920 |40S 1760
WDLAR-S-458
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I B J LUNAR EXPEDITION CV 60 C*61
MANAGEMENT MILESTONES FY62 - FY63 j F n i l J D O R 1 J f M 1 1 J J A 1 1
r START PRELIMINARY DESIGN (LRV) ) * i COMPLETE PRELIMINARY DESIGN (LRV : : JIIJ * 1 PROGRAM APPROVAL AND FUNDING - — _ _ U _
1 1 ENGINEERING DESIGN COMPETITION f AND MOCK-UP "• 11 Contractor No. 1 (Lunex Payloads) If 0 Contractor No. 2 (Lunex Payloads) H I! DEVELOPMENT - PRODUCTION FUNDING II 17 DESIGN CONCEPT DECISION 11 If APPROVAL FOR HARDWARE GO-AHEAD * . , 11 CONTRACT AWARD » 23 LUNAR TRANSPORT VEHICLE PROGRAM M IS LUNAR EXPEDITION H PROGRAM V L,
n REQUIRED FUNDING (MILLIONS) » H FY-62 : : : : i " 2 E = = 31 " ~ j t - p - .
H FY-63 11 M FY-64 « « « - L _ M s* M 41 LKV - Lunex Re-entry Vehicle - Ofljj
i f M A M 1 J A 5 0 II fi J F Jl A • J J A S |
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SECTION I I
PROGRAM BESCRIFTIOH
LUHAH EXPEDITION ( u )
(LUNEX)
2.1
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MO.
: * • * . - T«* BECCRD 0 ? CHANGES
INSCRIPTION OF CHAHGE { MOE OF CEABGE
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INDEX*-
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TITLE PAGE , 2.1
RECORD OF CHANGES 2.2
INDEX 2.3
2.0 BACKGROUND •. 2-5
2.1 LUNEX PROGRAM OBJECTIVE 2.5
2.2 LUREX PROGRAM - DESCRIPTION 2-5
2.3 DESIGN PHILOSOPHY 2.7
2.k ABORT PHILOSOPHY , 2.7
2.5 EXPEDITION PLANNING .. 2.11
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2. PROGRAM DESCRIPTION
2.0 BACKGROUND
Shortly after the first Sputnik was launched in October 1957, -Headquarters, AHDC Initiated a series of studies to examine the military potential of space operations. These studies were accomplished by Industry-Air Force teams each working independently. Two of these studies which were the forerunners of this Lunex plan were "Lunar Observatory*1 and "Strategic Lunar System." The objective of the first study was to examine an economical, sound and .logical approach for establishing a manned intelligence observatory on the moon, and the second study examined the military potential of lunar operations. These studies showed that It is technically and economically feasible to build a manned lunar facility.
A third study titled, "Permanent Satellite Base and Logistic Study" is presently under way and will be completed in August 1961. This study will provide a conceptual design Of a three-man re-entry vehicle which will carry men to and from the moon. The three-man vehicle is the key item in the lunar transportation Bystem as its weight will dictate the booster sizes. For this reason it is given special attention in this plan.
2.1 LUNEX PROGRAM OBJECTIVE
The objective of the Lunar Expedition program is the manned exploration of the moon with the first manned lunar iBpfllng to occur as soon as possible. The execution of thiB plan will land three men on the moon and return them during the 3rd quarter of calendar year 1967, and will establish the Lunar Expedition . '• In 1968. Completion of this plan will require the development of equipment! materials, and techniques to transport men to and from the lunar surface and to provide a lunar facility which will allow, men to live and work in the extremely harsh lunar environment.
2.2 LUNEX PROGRAM - DESCRIPTION
The Lunar Expedi t ion Program i s p r i m a r i l y concerned wi th t h e development of t he equipment necessary t o t r a n s p o r t men and suppl ies t o t he luna r s u r f a c e .
The key development In t h i s program i s t he Lunar Transport Vehicle which i s composed of t he Space Launching System and e i t h e r the Manned Lunar Payload or the Cargo Payload. The Manned Lunar Payload c o n s i s t s of a three-man Lunex Re-Entry Vehicle, a Lunar Launch Stage , and a Lunar Landing Stage . The same Lunar Landing Stage, p lus a cargo package, composes t he Cargo Payload. The r e l a t i v e e f f o r t r e q u i r e d f o r t he development of these
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two payloads in comparison with other portions of the complete Lunar Expedition Program is shown in Figure 2-1. A breakdown of the Lunar Transport Vehicle Is shown In Figure 2-2.
The Space Launching System consists of a three-stage booster capable of placing either the (fanned Lunar Peyload or the Cargo Payload on a lunar Intercept trajectory at escape velocity. This plan does not contain development information on the Launching System since such information is contained in a separate System Package Plan being prepared concurrently. The development schedules in these plans have been coordinated to insure compatibility.
In operation, the Manned Lunar Payload, weighing 13^,000 pounds, will be boosted to escape velocity of approximately 37, OCX) ft/sec on a trajectory which intercepts the moon. Velocity will be sufficient to reach the moon in approximately 2^ days. As the Manned Lunar Pay-load approaches the moon it is oriented with the local vertical by the use of horizon scanners. The Lunar Landing Stage decelerates the Manned Lunar Payload for a soft landing at a preselected site using an altitude sensing device to determine time of ignition. Landing at the preselected site will be accomplished using terminal guidance equipment and a prepositioned beacon to effect an off-set landing.
The Lunar Launching Stage, using the Landing Stage as a base, will launch the Lunex Re-entry Vehicle on the return trajectory. In early test shots before men are included, the countdown and launch will be effected automatically by command from the earth. Small mid-course corrections may be necessary to insure re-entry into the earth's atm sphere within allowable corridor limits.
The Lunex Be-entry Vehicle will re-enter the earth's atmosphere within the allowable corridor so that It will not skip back into space again nor burn from excess heat. It will use aerodynamic braking to decelerate and will have sufficient lift capability to effect a normal uhpowered aircraft landing at a base such as Edwards Air Force Base.
Several successful unmanned, completely automatic flights of the type Just described must be completed in order to establish confidence in the system reliability before manned missions will be attempted.
Cargo will he transported to the lunar surface using the same procedures and equipment except that the Lunar Launch Stage is not needed. The Cargo Package will have a weight equal to the combined weight of the Lunex Re-entry Vehicle and the Lunar Launch Stage.
As a separate approach to the problem of placing Large payloads -on the moon, techniques of rendezvous and assembly in earth orbit .
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are being examined. Use of these techniques would require the launch, rendezvous and orbital assembly of sections, of the Manned Lunar Payload and the Cargo Payload along with tde' -required. orbital launch booster and its fuel. Ike assembled vehicle would then be boosted from orbital velocity to escape velocity and would proceed as described above. Details of the major developments required such as rendezvous, docking and orbital assembly are outlined in a System Package Plan titled, SAINT being prepared concurrently. All programming information and schedules have been coordinated with this plan to Insure compatibility and mutual support.
2.3 DESIQN PHILOSOPHY
The Lunar Expedition Plan has been oriented toward the development of a useful capability rather than the accomplishment of a difficult task on a one-time basis. The use of a large booster is favored for the direct shot approach since studies have shown this to be more reliable, safer and more economical as well as having earlier availability. However, another approach using a smaller booster in conjunction with orbital rendezvous and assembly is also considered.
The manned Lunex Re-entry Vehicle is the key Item in determining booster sizes. Its weight determined the size of the Lunar Launch Stage which in turn determined the size of the Lunar Landing Stage. The total weight of these three Items is the amount that must be boosted to earth escape velocity by the Space Launching System. In this manner the size of the Space Launching System was determined.
A 2^ day trajectory each way was selected as a conservative design objective. Longer flights would have more life support and guidance problems while shorter flights require higher boost velocity.
An abort capability will be included in the design insofar as possible. The next section describes the abort system in considerable detail.
Development and tests are scheduled on a high priority basis. Thus, the schedules shown in this plan are dictated by technological * limitations and not by funds.
The entire program as described herein is an integrated program In that later development testB build on the results of early tests. Thus, equipment and techniques are proved out early, and confidence in the reliability is obtained by the time a man is included.
2.1* ABORT PHILOSOPHY
The insertion of a man into a space system creates a safety and reliability problem appreciably greater than the problem faced toy
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any unmanned BystemT It Is veil recognized that maximum reliability Is desirable, but also known that reliabilities In excess of 6$ to 9056 are extremely difficult to achieve with systems as complex as the Lunar Transportation System- Therefore, the need for an abort system to protect the man during'the "unreliable" portions of the lunar mission is accepted.
A review of the proposed techniques and equipments to provide a "full abort" capability has shown that due to payload limitations this is not practical during the early lunar missions. Thus a reasonable element of risk will be involved. In order to decrease this element of risk and to understand where it occurs the lunar mission has been divided Into six time-periods. These time periods are as follows: '
a. Earth ascent.
b . Earth-moon t r a n s i t .
c . Lunar terminal.
d. Lunar ascent.
e. Moon-earth transit.
f. Re-entry.
The development and test philosophy for 'this program Is to launch the manned systems as early as possible in the program, but in an unmanned status. This will provide experience and allow the system to be checked out and "man-rated" before the first manned flight. It also means that the lunex Be-entry Vehicle will be used for orbital and clrcumlunar flights prior to the lunar landing and return flight. The propulsion systems used for these early flights will be used throughout the program and the experience gained from each flight will increase the probability of success in reaching the final lunar landing and return objective. Also these propulsion systems will be used concurrently In other programs and at the time of man-rating vlU possess greater launch experience than can be expected for the largest booster of the Space Launching System. This would indicate that a larger number of unmanned flights should be scheduled for the larger full boost system than for the early flights. It also points out the need for a sophisticated Earth Ascent Abort capability during the first manned lunar iimfl-twg and return flight. '
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In providing an abort philosophy for the Lunar Program it should be noted that the Lunex He-entry Vehicle, the Lunar Landing Stage -and the Lunar Launching Stage all possess Inherent abort capability if utilized properly during an emergency. With sufficient velocity the re-entry vehicle is capable of appreciable maneuvering and landing control to provide its own recovery system. The Lunar Launching and Lunar Landing Stages possess an appreciable ,£v capability that can be used to alter the payload trajectory to better accomplish recovery of the man. However, in either case the maneuvers will have to rely on computing techniques to select the best possible abort solution for any specific situation.
With this background, and with the understanding that in a future final design effort "full abort" may be required, the following abort design objectives for the Manned Lunar Payload are presented:
a. Earth Ascent Phase
(1) On Pad.
Full abort system will be provided.
(2) Lift-ofX Ho Flight Velocity for the He-entry Vehicle. .
Escape Velocity.
Full abort system will be provided.
(3) Flight Velocity for the- He-entry Vehicle to
The basic Manned Lunar Payload will provide the abort capability.
b. Earth-Moon Transit
(1) Injection
Abort capability to compensate for injection error is desired as part of the basic Manned Lunar Payload. Computing, propulsion, etc., capabilities should be designed into the basic system to provide for the selection of the optimum abort trajectory. ,
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Abort capability during Earth-Moon transit is desired for the He-Entry Vehicle by means of a direct earth return, earth orbit, or circumlunar flight and earth return. Circumlunar flight generally requires the least^v.v, but the actual selection of the optimum trajectory should be accomplished vben required by a computing capability, and executed by the Lunar Fayload.
c. Lunar Terminal
This type of abort generally results from loss of propulsion or control of the Lunar Landing Stage. Where possible the Lunar Launching Stage will be used to attain a direct or circum-lunar trajectory that terminated in an earth return. When this is not possible the Lunar Launching Stage will be used to accomplish the safest possible lunar landing. Recovery of the crew will not be provided in this system and selection of the above .alternatives will be accomplished automatically on-board. Crew recovery will be provided by another stand-by Lunar Transport Vehicle.
d. Lunar Ascent
Maximum inherent reliability by overdesign of components and systems in the Lunar Launching Stage seems to be the most logical approach for this phase due to the extreme weight penalty imposed by a separate abort system.
The early missions will be faced with the highest risk, but as a facility on the lunar surface is developed, a rescue capability and the addition of an abort capability can be developed. Ho specific abort system will be provided for this phase, but consideration should be given to tbe possibility of future lunar modifications to provide for abort.
e. ttwn-Earth Transit
This would generally be associated with a gross trajectory error, or loss of control on re-entry. The only solution is to utilize the on-board capability that remains to achieve an earth orbit. After achieving orbit an earth launched rescue mission would be initiated. This approach requires no additional abort -system to be provided for this phase.
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f. Re-entry
Exceeding re-entry corridor lljnits, or IOBS of control could cause an emergency where abort would be desirable. Should sufficient Zi.v remain from the over-design of the lunar launch stage, and not he used during Moon-Earth transit this vould he used to attain an earth orbit where rescue could be achieved. Ho separate abort capability is required for this phase, hut availability of pro-pellant should be considered.
2.5 EXPEDITION PLAHNIHG
A detailed plan must be prepared for the complete Lunar Expedition operation. This plan must start from the first time man lands on the lunar surface and account for every single effort, or objective he is to accomplish during his stay on the surface, A crew of three nien will be sent into a new and hostile environment where rescue or assistance from other human beings will be extremely difficult, if not impossible, for the first mission. Time will be at a premium and all items of equipment must be planned, designed and delivered in the Cargo Payloads so that they can be used in the easiest possible manner.
The procedures for first exploring the surface and then for constructing the expedition facility must all be derived, demonstrated and proven by earth operations prior to attempting the desired operation oh the moon. An environmental facility that simulates the lunar surface with sufficient Work area to test out equipment and procedures will be required.
The actual landing operation and the first effort by men on the surface requires detailed data about the moon's surface. The following chart represents the best available data. The chart is a portion of a Lunar Sectional having a scale of 1:1,000 (l inch equals 16 miles) produced by the USAF Aeronautical Chart and Information Center, St Louis, Missouri. Present plans call for the eventual production of lUh charts to cover the complete lunar surface.
The best photographic resolution to date is around one-half mile on the lunar surface, which provides adequate data for charts having a scale of 1:1,350,000, Good astronomical telescopes can be used to Improve on the photographic data and obtain sufficient detail to prepare sectional charts like the one included. However, larger
2 > l i TOLAR-S-I*58
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scale, accurate lunar charts will be required to complete detailed plane- Data can be obtained for such charts from a lunar orbiting photographic satellite which vill provide sufficient resolution and overlap to enable Btereographic compilation of contours and elevations. The NASA proposed Lunar Orblter program Is a possible source of the required data.
Planning for construction of the expedition facility can begin only after detailed surface information becomes available. Examination of returned lunar core samples vill be necessary before plans can be completed.
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2.12 WDLAR-S-U58
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p - « . < _ ? d - ' - 1
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uoar LUINAK LnAM SCALE 1:1,000,000
rUWISHED 1Y IHE AE«ONAUTICAt CHA*T AND INFORMATION CENTER.
UNITED 5TATES * ' » fOKCE ST. IOUI5 la. MO.
KEPLER
LAC 57 Mtrcotor Projection
State 1<1,000,0M o M i * 0 0 ' « "
1ST EDITION DECEMBER 1960
NOTES Thii chart wat prepared with advisory owslonce from Dr. Q. P. Kulpar gnd hit coHoboralon, 0. W. G. Arthur and t". A. WhitaJier.
CONTROL The position of featurei an fhft chart *as determined
Through the uie of lelenographic conlrol eitabtiihed primarily from the mwiure* of J, From and S. A. Sounder. A collated listing of thh control wo* pubfished under the auipicas of the fnternationof Agronomical Union in 1935, (Named Lunar Formation* - BJagg and Mfiller).
VERTICAL DATUM
Vertical datum is bawd on on ossumed spherical figure of the moon and a lunar radius of 1738 kilometers. The datum plane wot subsequently adjusted to 2.6 kilometers below the surface described bf the 1738 kilometer rodiui to minimize the extent of tuner surface or minus elevation value. Gradients of mojos1 surface undulations were established by interpolating Schrulko - Rechtenstomm computations of J. From'* measurements of ISO moon craters. The probable error of comparative devotion values it evaluated at 1000 meters. Vertical datum, so established, is considered interim and wilt be refined as soon as an accurate figure of the moon is determined,
ELEVATIONS All elevations are shown in meters. The ntfalive heights of crater rims and other prominences above the moria and depths of craters were determined through photographic measurement utilizing the 1. Kopal and G . Fielder Shadow Progression Technique. Relative heights thus established, have been referenced to the assumed vertical doluai and have been integrated with the gradients of the surface undulation*, The probable error of the localized relative heights is 100 meters. Inherent with measuring technique used, relative height determinations In general E-W direction are more accurate than in the N-S direct ion.
Spot Elevation (referenced to datum) .1100
Crohtr Elevations
Rim (referenced to Datum) 300
Depth of crater (rim to floor) (400)
CONTOURS
All contours arc approximate Contour interval js 300 meters
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M.»7 TOBIAS MEYER
SECTIOK I I I
MASTER ECHEDUIES
LDNAR E3CPKDITION ( u )
(LUNEX)
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TITLE RAGE *- 3 . 1
RECORD CF CHANGES 3.2
INDEX 3 . 3
3 . 0 INTRODUCTION 3 - 5
3 - 1 MASTER PROGRAM PHASING CHART 3 - 5
3 - 2 LUNAR EXPEDITION PROGRAM SCHEDULE 3 . 6
3 - 3 LUNAR EXIEDITION MANAGEMENT MILESTONES JT60-FY63 3 . 6
3-h LUNAR EXPEDITION TEST SCHEDULE 3 - 7
3 - 5 LUNEX SPACE LAUNCHING REQUIREMENTS 3^7
3.6 PERSONNEL AND TRAINING 3 .8
3-7 LUNEX CIVIL ENGINEERING FACILITIES SCHEDULE 3 .8
ATTACHMENTS
I I I - A LUNAR EXPEDITION MASTER PROGRAM SCHEDULE
I I I - B LUNAR EXPEDITION PROGRAM SCHEDULE
I I I - C LUNAR EXPEDITION MANAGEMENT MILESTONES F T 6 2 - F Y 6 3
I I I - D LUNAR EXPEDITION TEST SCHEDULE
I I I - E LUNEX SPACE LAUNCHING REQUIREMENTS
I I I - F LUNEX CIVIL ENGINEERING FACILITIES DEVELOPMENT PROGRAM
I I I - G LUNEX TRAINING SCHEDULE
VDLAR-S-U58
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It***
3.0 INTRODUCTION
The establishment of the Lunar Expedition Program as a National objective will provide a worthy goal for the. United States industrial and governmental organizations. The lunar Expedition program has been based on extensive study, design and research writ during the past three years.
A lunar Expedition program will require the use and centralized control of a major portion of the present military space capability. M e will have the effect of giving the military program a Bcheduled long-range objective, and still provide useabla military capabilities throughout the period. As an example, manned re-entry vehicles for orbital operations will be available in early 1965- This will be followed by a manned lunar re-entry vehicle in 1$6S.
Propulsion and Space launching systems will be required to support the LUNEX program. This program will set orbital and escape velocity payload requirements ranging from 20 to 350 thousand pounds in a 300 mile orbit and from 2*f,000 to 13^,000 pounds at escape velocity. Shis capability will be obtained at an accelerated pace for the LUNEX program and as a result the same capabilities will be available for military use much earlier than could be achieved if the start of the development programs had to be Justified at this time entirely on the basis of military usefulness.
The accomplishment of the LUNEX program will require mpy^mnm use of several presently programmed efforts and reorientation of others. Dae major programs of direct interest to the Lunex are the SAINT and BOGS programs. Therefore, these efforts have been coordinated and Integrated with the LUNEX program. *me BOGS shots will provide the necessary orbital primate test data to allow the manned life support package for the lunex Re-entry Vehicle to be designed, The SAINT unmanned and manned program will provide additional orbital information on rendezvous, docking, and personnel and fuel transfer. In the event that the direct shot approach for the Lunar expedition requires reorientation in future years to use orbital assembly techniques this capability will be available from the SAINT program.
3.1 MASTER HtOGBAM IEASISG CHART
This schedule presents the Integrated military program required to accomplish the Lunar Expedition mission and to develop techniques for operating In the earth orbital and lunar areas. It was prepared to indicate the Interface between this Lunar Expedition System Package Plan and the Space Launching System. The major national objective of this integrated program Is to land men on the moon and return than In August of 1967.
WDIAR-S-Jl58
This document rortfsint irtffififlatioft afivcling the national tManf f £>t th* United States within the manning of the Eiptonap*/ Law*, TiiU"
I I . U-SC., Stifton 793 and 7W. the rranunluiwi or nuatoion fif which in any mannvr » an unaurtwriwd p a w n H proh&iftd by l#«*
sww CONHLtLlV'llAL. 3-2 " LUNAR EXPEDITION PROCBAM SCHEDULE
This schedule presents the major Items t o be accomplished as a re su l t o f the VJNBX program. She cost ing as shovn on the schedule does not include the cos t of developing the Space Launching System since t h i s i s provided under a separate System Package plan. However, the cos t of purchasing the f l i g h t veh ic les i s included.
Ihe major "prestige" milestones of the program can be summarized as fo l lows:
F i r s t Manned Orbital F l ight April 1965 (3 Man Space Vehicle)
F i r s t Lunar landing (Cargo) July 1966
Manned Circuffllunar F l ight Sept. 1966
Manned lunar landing & Return Aug. 1^67
penaanently Manned Lunar Expedition Jan. 1968
3-3 LUNAR EXPEDITION MANAGEMENT MILESTONES FY62 - FT63
.This schedule Indicates the major LUHEX program e f for t s required during f i s c a l years 1962 and 1963. 3be time a l locat ion for management and Ai 'orce technical evaluations have been kept to a minimum i n order t o meet the end objective of "man on the moon" In August 1967.
f Several c r i t i c a l major decis ions are required and are summarized
below:
Program Approval & Funding July 1961
Development-Production Funding Sec. 1962
Design Concept Decision Jan. I963
Approval f o r Hardware Go-Ahead Feb. I963
Delays i n providing the funding Indicated, or In rece iv ing not i f icat ion of dec is ions required, w i l l have the d i r e c t e f f e c t of delaying the end o b j e c t i v e s . This problem could be e f f e c t i v e l y solved by a streamlined management structure having a minimum number of reviewing author i t i e s . The present AFSC procedures are a s tep i n the r ight d irect ion but^ more .direct channels .are, des irable a t the higher command l e v e l s . , t , „ - ' ^ - - . V ,
^ • ^
WDLAR-S-458
Thii docwnent lenuim i n f o ™ * ' * * •Hading th* rutienal delenu of ihc United Sr*tes within tfw mewing, of ihe [ipiontge l a m , Title
I t , U.S.C Seclnn 793 end 7V4, th* Ireiumiuion or revelelron o l which hi any manner k> p i uneiflhorixed penon l l protiibiled by law.
> » *
n 3 A LUHAR EJCHKDITION TEST SCHEDULE * •
This schedule p resen t s t he major t e s t Items requ i red f o r t he LUHEX program. Upon completion of t he program manned t r a n s p o r t and unmanned cargo veh ic les w i l l be a v a i l a b l e t o support the Lunar expedi t ion . . The cargo veh ic le v i l l be capable of t r a n s p o r t i n g approximately ^5,000 pound "cargo packages" t o t h e lunar sur face fo r support ing t he expedi t ion . This same vehic le would be capable of t r a n s p o r t i n g fu ture m i l i t a r y payloads t o the luna r surface t o support space m i l i t a r y ope ra t i ons .
A d e t a i l e d high-speed r e - e n t r y t e s t program and an a b o r t system t e s t program i s scheduled t o provide b a s i c r e - e n t r y d a t a and t o insu re t he safety of t he men In t he Lunex Re-entry Veh ic le .
P r i o r t o t he f i r s t "manned l u n a r landing and re tu rn ' ' f l i g h t , a s e r i e s of t e s t and check-out f l i g h t s w i l l be r e q u i r e d . These w i l l i n i t i a l l y cons i s t of o r b i t a l f l i g h t s , and then very h igh a l t i t u d e (50,000 mi les or more) e l l i p t i c a l f l i g h t s fo r t e s t i n g t he veh ic les under r e - e n t r y c o n d i t i o n s . When these have been completed, the f i r s t f l i g h t s w i l l be made around the moon (circumlunar) and r e t u r n t o an ea r t h base . With a completely man-rated v e h i c l e , and unmanned lunar landing f l i g h t s completed, man w i l l then make the f i r s t landing on the moon f o r t he purpose of s e l e c t i n g a s i t e f o r the Lunar Expedit ion F a c i l i t y .
3.5 LUNEX SIACE IAUNCHTNG REQUIREMENTS
"The purpose of t h i s schedule i s t o summarize the space launching vehic le requirements and I n d i c a t e when the launches w i l l be needed.
The THOR-ABLE-STAR b o o s t e r s w i l l be used f o r t he r e - e n t r y t e s t program. The Space Launching System boos te r s des ignated as A, AB and BC, and so l i d s as r equ i red , w i l l be needed as i nd i ca t ed and t h e i r payload c a p a b i l i t i e s a re es t imated a s fo l lows :
Booster
A ItlO
AB 625
AB 825
BC 2720
Payload
20,000 pounds (300 mile o r b i t )
87,000 pounds (300 mile o r b i t )
24,000 pounds (escape v e l o c i t y )
13^,000 pounds (escape v e l o c i t y )
WDIAR-S-458
X&&
Thli dQcunwflf confiiru information effecting Ihe national d > f i n u of Iha Un<i«d State* within the moaning of Ih* Espionage Lewi, Title
IB, U-5-C, Section 793 ond 794, (ho tranuniiiion Or revelarion of which in ony manner to on unauthorized person is prohibited by low.
. *
^ r 3.6 PERSONNEL AND 1RAINING c
The Lunar Expedit ion program w i l l r e q u i r e m i l i t a r y personnel and a m i l i t a r y t r a i n i n g program- D e t a i l s of t h i s program a re p resen ted i n Sect ion XX and summarized on t h e Uraex Tra in ing Schedule inc luded i n t h i s s e c t i o n .
• & •
The number of personnel r equ i r ed w i l l i nc rease from a l i m i t e d s t a f f i n the e a r l y ft-ogram Office t o a t o t a l of 6,000 personnel I n t he a c t i v e expedi t ion y e a r . This t o t a l does no t include " in p l a n t " con t rac to r personnel -which i s es t imated t o be on the order of 66 thousand.
Training of m i l i t a r y personnel t o meet t h e requirements of t h e LUMEX program v i l l be done by con t rac to r and m i l i t a r y t r a i n i n g pe rsonne l . Maximum use v i l l be made of program equipment tfeen I t can be scheduled for t r a i n i n g purposes and i n addi t ion} a l l o c a t i o n of product ion equipment i s necessary t o meet toainlng requ i rements .
3-7 XUNEX CIVIL ENGINEERING FACILITIES SCHEDULE
The f a c i l i t i e s development and cons t ruc t ion program I s shown on t h i s schedule . The f i r s t i tem t o be accomplished i s a s i t e survey t o determine t he ex ten t t h a t t he LUNEX program can be supported by AMR and B4R. When t h i s has been accomplished i t i t i . l l be poss ib le t o deteimine i f the e a r l y LUNEX t e s t launches can be accomplished by using presen t f a c i l i t i e s . F u l l cons ide ra t ion i t i l l be given t o the p o s s i b i l i t y of bu i ld ing the Lunex Lranch Complex a s an expansion of the AMP or fMR. A more d e t a i l e d p r e sen t a t i on of t he f a c i l i t i e s program i s contained i n Sec t ion VIII C i v i l Engineer ing.
3-8 WDLAR-S-J*58
* *
Thii document contain! information (Heeling th* national ( M m i : of the Uniitd Stem within the meaning of Ihe Eipionege Uw>, Title
IS, U S . C , Section 793 and 794, the IteruniitiiOn 01 revelation of which in any manner B an unauthorind pemon i> prohibited by law.
• . - , - - 3 - - - B - - -
~c MASTER PROGRAM 6CHEDUXE
P R O G R A M SCHEDULE . J
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DATE CYtt CY| TOTAL PRIOR 1 F M A M ) i , » | » Q N D J F M A M J J
i k . HIGH SPEED RE-ENTRY f t i b T m I g | ? ' X % *
BOSS SUPPORT iWI1
-i ABORT SYSTEM TESTS
ORBITAL ,, UHMAHHED
. MASHED
CIPCUHLUHAR UHMAHHED HASHED
•
LOBAR IAHDIHG & RETURN UHMAHHED
'• MANNED -*
LUHAH EXPEDITIOH
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• BOOSTER REQUIREMENTS
i I RE-EHTRY TEST i I I i .-.T A-U.0
i i "*? AB-825 1
BC-2720 i
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J F M A M i i A S 0 H I ] F M A M T\ FYB . FYK 1
9
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^ CY IS C Y * C
V i ' O N D J F M A M J J A S O N D j F M A M I J A S D N D J F M A M J 1
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| FY 15 FYK FYt7 FYW
- • - \ * N . WDLAR-S-458
- . ^ - - v — •
4
CHART m - 8
LUNAR EXPEDITION PROGRAM MILESTONE SCHEDULE
CALENDAR 1961 1962 1963 1964
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MANNED LUNAR LANDING ANO RETURN
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LUNAR EXPEDITION FUNDING REOUIREMENTS(MILLIONS) 27 112 350
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SECTION IV
lEVELOFMENT - TEST - ERODUCTIOU
LUNAR EXPEDITION ( u )
(LUHEX)
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TITLE PAGE
RECORD OF CHANGES
TSDE3L
4.0 INTRODUCTION
4 . 1 EEVELOPMEHT OBJECTIVES
4 . 1
4.2
4-3
4-5
4.5
4.1-1 High-Speed Re-Entry 4.1.2 Manned lunar Fayload 4.1.3 Cargo Bayload 4.1.4 Abort System 4.1.5 Space launching System
4 . 2 SUBSYSTEM IEVELOPMENT
4.2-1 Re-4.2.1.3-1 4.2.1-3.2 4.2.1.3.3 4.2.1.3-4 4.2.2 4.2-3 4.2.4 4.2-5 4.2-5-2 4.2.5-3 4.2.5-4 4.2-5-5 4.2.5.6 4.2.5.7 4.2.6 4.2-7 4.2.8
4.2-9
4.3 TEST PLAN
4-3 4-3. 4.3-4.3. 4.3-4.3. 4.3.3.3
Entry Vehicle Aerodynamics Materials Structures Dynamics Propulsion life Support Flight Vehicle Power Guidance and Control System Inertlal Platform Star Tracker
Long Baseline Radio Navigation Doppler Radar Re-Entry Guidance Adaptive Autopilot Computer Communications Environmental Data Materials
Test Categories Research Tests Design Evaluation Tests Flight Testing High-Speed Re-Entry Flight Test lunex He-Entry Vehicle Flight Test lunar launch Stage Flight Test
4.4 HKXEUCTION PLAN
4, 4, 4. 4, 4,
5 6 7 7 8
4.9
4-9 4 . U 4 . U 4.12 4.13 4-15 4.17 4.19 4.20 4.20 4.21 4.21 4.22
22 22 24 26
4.27 4.32
4.34
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4 . DEVELOFMEHT - 2EST - PRODUCTION
4.0 IHTflODUCTIOH
Implementation of the lunar Expedition v l l l require a completely Integrated program Involving the development, t e s t , and production of Items based on almost every known technical d i s c i p l i n e . These technical d i s c i p l i n e s are presently being invest igated under a multitude of programs and organixations • The Lunar Expedition program v i l l require these technical e f f o r t s to be immediately organized and re-or iented where necessary. This can bes t be accomplished by preparing a detai led development, t e s t , and production program. Vben t h i s program i s completed each technical area can be evaluated by comparing I t s present program object ives and I t s required output t o meet the Lunar ' Expedition program requirements. In the following paragraphs the Lunar Expedition development object ives and technical performance requirements are presented. The scope of the major ex is t ing technical programs and the necessary re-or ientat ion i s discussed.
4 . 1 DEVELOPMENT OBJECTIVES
4-1 .1 HIGH-SPEED RE-SNORT
At the present time high-speed re-entry data In the v e l o c i t y spectrum from 25,000 f t / s e e . t o 1*5,000 f t / s e e . I s non-exis tant . In order to meet the Lunex Re-entry Vehicle development schedule I t " • w i l l be necessary t o have high-speed re-entry data during the engineering design program for the manned re-entry v e h i c l e . Thus a compressed and coordinated teBt program for both ground t e s t f a c i l i t i e s and f l i g h t t e s t i n g i s necessary*
Immediate act ion Is necessary t o schedule and design the high-speed wind-tunnel t e s t program. This v i l l show the type of information that can only be achieved by means of f l i g h t t e s t i n g .
The High-Speed Re-entry f l i g h t t e s t program scheduled for the Lunex program i s necessary t o provide basic data on re-entry as well as t o f l y spec i f i c shapes In the l a t e r period of the t e s t program. This s e l ec t ed shape program v i l l be coordinated with the Lunex Re-entry Vehicle design e f f o r t .
In order t o accomplish the High-Speed Be-entry f l i g h t t e s t program i t w i l l be necessary t o design and develop a t e s t v e h i c l e . Oils vehic le most use e x i s t i n g boost systems due t o time l i m i t a t i o n s , but the payload v l l l have t o be designed e spec ia l ly for t h i s program since none e x i s t s a t t h i s time. I t I s be l i eved that the At las booster v l l l prove adequate for these t e s t s , but a decis ion must ava l t the t e s t payload des ign.
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fc.1.2 MANNED LUNAR PAYLOAD *V -9
The largest single development objective for the LUTO3C program is to provide a payload capable of transporting men and equipment to the lunar surface and returning them to a selected earth base, nils payload would consist of a Lunar landing Stage, a lunar Launch Stage and a 3-man Lunex Re-entry Vehicle.
A typical Manned lunar Payload is shown in a cut-away view in Figure h~\. Ike characteristics and General Arrangement of the Manned Lunar Payload are shown in Figures k-2 and k-3. This payload is 52 feet U inches long, has the e.g. located 33 feet 8 inches from the nose of the re-entry vehicle and the interface diameter with the Space Launching System is 25 feet. The complete payload weighs 13^,000 pounds at escape velocity, and a 20,205 pound Manned Re-entry Vehicle is returned to the earth.
The Lunex Re-entry Vehicle must be capable of entering the earth's atmosphere with a velocity of approximately 37,000 ft/see. At the present time, basic re-entry information for velocities Of this magnitude does not exist. Therefore, engineering design effort for this re-entry vehicle must be accomplished concurrently with other major sub-systems developments and integrated with the High-Speed Re-entry test program and the Abort System test and development program. This requires close management control of these programs by the LUHEX Program Office.
Another major problem facing the re-entry vehicle development program is the life support package. The planned schedule will require tbe manned life support package to be designed on the basis of earlier primate shots. Mercury shots and the Discoverer series. These programs lead toward a manned capability, but this re-entry vehiwie requires the first truly space life support package.
. The lunar landing Stage must be capable of landing the Lunar Launching Stage and the Lunex Re-entry Vehicle on the lunar surface. At the present time this is considered a difficult design problem because little is known about the lunar surface. Actually the best photographic resolution to date is approximately <§ mile. Many theories exist on the formation of the moon and therefore, the characteristics of its present surface. When these two factors are considered the only practical design approach is to provide an alighting system capable of landing on an extremely rough surface. An automatic leveling, orientation and launching system is required for system check-out prior to manned flight. Therefore, any assumption that the Manned Lunar Payload can be moved about on the lunar surface or that the payloads might initially transfer fuel on the lunar surface, might be entirely erroneous and Jeopardize the complete Lunar Expedition effort. The landing stage will also, have to be developed so that It is capable of landing the Cargo Payloads on the lunar surface.
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The Lunar launching Stage must be developed with a different philosophy than the previous sub-systems. First, It only operates in 4. vacuum of space and on the lunar surface. Secondly-/ it vlll be required to function after It has been located on the lunar surface for an extended period varying from several days to many months. Therefore, the stage must be developed to launch the re-entry vehicle after being subjected to a better vacuum then available In our best earth laboratory facilities, following possible temperature variations of hOO to 500 degrees, following possible meteorite bombardment and from a less than optimum launch angle. Specifically the stage development must consider propellent boil-off, automatic check-out, self-erection and remote (earth-moon) launching procedures.
Die lunar launching Stage represents the major reliability problem of the system because an abort capability is planned for evexy phase of the LUIfflX mission except during launch from the lunar surface. During the early lunar flights an abort capability for this phase Is just too expensive payload-viBe for the Space Launching System. An abort capability during Lunar Launch essentially requires a duplicate lunar launching capability because the man must still be returned to the earth by either this system, or a special rescue flight. Therefore, until lunar support facilities are available a separate system for abort during lunar launch does not seem practical. This creates the requirement to develop an extremely reliable Lunar Launching Stage.
IM.3 CARGO BttLOAD
She successful support of the Lunar Expedition vill require a capability to deliver relatively large Cargo Packages to the lunar surface. These Cargo packages vlll be soft landed at the desired lunar sites by the Lunar Landing Stage. Each Cargo package vlll weigh approximately 45,000 pounds and vill be specifically designed to carry the items desired to support the expedition. Development of the Cargo Payload and the specific packages vill depend upon the Lunar Landing Stage design and the receipt of lunar environmental data. The actual design of the Lunar Expedition Facility vill only be possible vhen detailed Information on the lunar surface is available. Then vtth the facility design information the required materials, equipment, and procedures can be determined and a payload delivery sequence derived. The required payload delivery sequence is essential before the Individual payloads can be designed and developed, but timely development of major Items of equipment must proceed as their individual requirements become known.
k.l.k ABORT SXSTEM
The philosophy of abort has been presented In the Program Description section of this document. The development of the abort equipment will require an integrated effort with the re-entry vehicle
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The lunar launching Stage must be developed with a d i f ferent philosophy than the previous sub-systems. F i r s t , i t only operates i n a„ vacuum of space and on the lunar surface. Secondly, i t w i l l be required t o function a f t er i t has been located on the lunar surface for an extended period varying from several days t o many months. Therefore, the stage must be developed t o launch the re-entry vehic le a f t er being subjected t o a bet ter vacuum then available i n our bes t earth laboratory f a c i l i t i e s , fol lowing poss ib le temperature variat ions of 400 t o 50Q degrees, fol lowing poss ible meteorite bombardment and from a l e s s than optimum launch angle. Spec i f i ca l ly the stage development must consider propellent b o i l - o f f , automatic check-out, s e l f - erec t ion and remote (earth-moon) launching procedures.
The Lunar Launching Stage represents the major r e l i a b i l i t y problem of the system because an abort capabi l i ty i s planned f o r every phase of the LUNEX mission except during launch from the lunar surface. During the ear ly lunar f l i g h t s an abort capabi l i ty for t h i s phase i s Just too expensive payload-vise for the Space Launching System. An abort capabi l i ty during Lunar Launch e s s e n t i a l l y requires a duplicate lunar launching capabi l i ty because the man must s t i l l be returned to the earth by e i ther t h i s system, or a specia l rescue f l i g h t . Therefore, u n t i l lunar support f a c i l i t i e s ere avai lable a separate system for abort during lunar launch does not seem p r a c t i c a l . This creates the requirement, t o develop an extremely r e l i a b l e Lunar Launching Stage.
fc.1.3 CARGO BftTLOAD
The successful support of the Lunar Expedition -will require a capabi l i ty to del iver r e l a t i v e l y large Cargo packages t o the lunar surface. These Cargo packages v i l l be so f t landed a t the desired lunar s i t e s by the Lunar Landing Stage. Each Cargo Package w i l l weigh approximately ^5,000 pounds and w i i l be s p e c i f i c a l l y designed t o carry the items desired to support the expedition. Development of the Cargo Payload and the s p e c i f i c packages w i l l depend upon the Lunar Landing Stage design and the rece ipt of lunar environmental data. The actual design of the Lunar Expedition F a c i l i t y w i l l only be possible when de ta i l ed information on the lunar surface i s ava i lab le . Then with the f a c i l i t y design information the required materia ls , equipment, and procedures can be determined and a payload del ivery sequence derived. The required payload del ivery sequence i s e s s e n t i a l before the individual payloads can be designed and developed, but timely development of major items of equipment must proceed as the i r Individual requirements become known.
It.1.4 ABCfiT SYSTEM
The philosophy of abort has been presented In the Program Description sect ion of t h i s document. The development of the abort equipment w i l l require an integrated e f f o r t with the re-entry vehic le
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design and the test program must be conducted concurrently to provide a reliable and safe system for supporting manned operations.
It is essential that the re-entry vehicle development be conducted so that the life support capsule csn also meet the requirements Imposed by the abort system. Additional structural and propulsion items must be developed to provide for abort during the earth ascent phase of the lunar mission. She computing and control equipment on the Manned Lunar Payload must be capable of selecting the desired abort mode of operation and initiating the desired actions at any required time throughout the lunar mission.
1**1.5 SPACE LAUNCHING SYSTEM
The Lunar Expedition requires an extensive space launching capability- The development of this capability is a necessary part of the LUTJEJf Program. At present this development is being included under the Space launching System program. It is designed to support the lev altitude test, orbital, circumlunar, and full lunar flights.
The major problems facing the design and development of the LUHEX payloads vlth reference to the Space Launching System, concerns the interface characteristics, trajectory considerations, and earth launch facilities.
The present prime interface characteristics for the Manned and Cargo lunar Payloads are as follows:
Interface Diameter 300 inches Escape Payload Weight 13^,000 pounds . Payload Length 6y? inches Center of Gravity kok inches
(Measured from top of payload) The Space Launching System is required to provide timely
launching capabilities for the Lunar Expedition as follows:
Payload Weight Pounds
20,000 87,000 2^,000
13^,000
Unmanned Manned Trajectory Flight ' Flight
300 mile orbit Aug 6k April 6? 300 mile orbit Dec 65 - -Escape Telocity Dec 65 Aug 66 . Escape Velocity July 66 Aug 6f
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k.2 SUBSYSTEM BEVELOFMEHT
The development of a manned lunar payload and a cargo package requires the development of subsystems and applied research in many technical areas. Studies have established that the advances In performance In these technical areas can be accomplished to meet the overall program schedules and that no scientif ic breakthroughs are required. She Important point i s that items requiring development be identified, that necessary funds be allocated, and that effort be Initiated without delay. Die following sections discuss major subsystem requirements, present capabilities, and development required. Completed studies conducted by the Air Force and Industry have established subsystem requirements in sufficient detail to outline development programs which should be init iated Immediately. Present studies wil l refine these specifications further.
>>-£. 4.2-1 RE-ENTRT VEHICIB
«*&si lr.2.1.1
The manned re-entry vehicle i s a cr i t ica l item in the development of the manned payload packages. This vehicle must be
- capable of returning from the moon and re-entering the earth's (_ atmosphere at earth escape velocity (37*000 f t /Bee . ) . I t must
also have the capability of supporting three men on a 10-day round tr ip earth-moon mission. This mission would include boost from earth, coasting in earth orbit, ba l l i s t i c f l ight to the moon,
...^ deboost and landing on the moon's surface, remaining on the moon • < • for one to five days, launch from the moon's surface, re-entering
the earth's atmosphere and landing at a pre-selected base on the ' ~ ~ earth. Structural requirements imposed by inert ia! and pressure *~*— loading during boost, abort, trajectory correction, landing, re
entry, ground handling, and wind loading on the launch pad, have been considered in analyzing desired vehicle characteristics-. These studies have also included the heating and i t s effect on
- vehicle design as vei l as the effects of space and lunar environment including particles and radiation, meteorite penetration, and hard vacuum. Present deslga studies have estimated the total re-entry vehicle weight at 20,205 pounds. The weight breakdown
^"^f is as follows;
a. Body 7500 (1) Structure 3500 (2) Heat Shield U000
b. Wing Group 2000 (1) Structure ****• -fiOa.-„ v (2) Heat Shield * 1200 ' "— - •
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c." 'ControlSystem"***' TJ5 (1) Aerodynamic 600 (2) Attitude 175
d. Environmental Control 1530 (1) Equipment Cooling 138 (2) Structure Cooling 9^0 (3) Cryogenic Storage ^52
e. Landing Gear 700
f. Instruments & Displays 200
g. Electric Pover system 600
h. Guidance & Navigation 400
1. Communi cations 250
J. Furnishing & Equipment 850 (1) Seats fc Restraints 225 (£) Decompression Chamber 175 (3) Equipment Compartment 300 (k) Miscellaneous 150
k. life Support hoo
1. Crew (3 men) 800
m. Radiation 1200
n. Abort System 3000
4.2.1 2
Present re-entry and recovery techniques are outgrovths of the ballistic missile program utilising ballistic re-entry and parachute recovery. 3hey are not compatible vlth the velocities associated with re-entry from the moon, vlth controlled landing, or vith manned operation. Present engineering data associated vith high speed re-entry is not adequate for vehicle design.
4.2.1.3
A development-test program i s required to obtain generalized data on re-entry phenomena and to test scale models
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of selected vehicle configurations so that final selection and design of an optimum vehicle can be made. Concurrently with this test program the projects within the applied research program will be directed so as to carry out the following investigations to provide necessary data for the Lunex Re-entry Vehicle Design.
4.2.1.3.1 AERODYNAMICS
(1) Study hypersonic-low density aerodynamics including dissociation and ionization, non-equilibrium flow phenomena.; and the influence of radiation non-equilibrium on vehicle aerodynamic and heat transfer characteristics.
(2) Initiate an extensive ground based facility program directed at obtaining aerodynamic and heat transfer data up to Mach Ho- 25 (the maximum useable available capability). ttiese tests would Include the G.E. hypersonic shock tunnel in the M = 18 - 25 range; Cornell Aeronautical Laboratory hypersonic shock tunnel If = 12 - 18; Cornell Aeronautical Laboratory heated hydrogen hypersonic shock tunnel at M - 20; AEDC tunnel "B", "C", at M = 8 - 10; AEDC E-l and E-2, M = 1-5 - 6; AEDC supersonic and subsonic facilities. Ibis effort will be coordinated with the Lunex Engineering Design program and the High-Speed Re-entry test program-
(3) Correlation of wind tunnel tests in ve-uns of prediction of free-flight vehicle performance characteristics in order to provide correlation between ground tests facilities and free-flight vehicles-
(k) Complete vehicle static and dynamic stability analysis.
(5) Investigate local critical heat transfer problems Including those associated witli flaps and fins. The use of reaction controls, in order to alleviate critical heating areas, for vehicle stability and control, will be investigated-
4.2.1.3-2 M&IERIALS
(1) Materials Develoratent
(a) Low conductivity p las t i c material development.
(1) Uniformly distr ibuted low conductivity.
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(£) Tailoring conductivity d is t r ibut ion in material in order to obtain high ablation performance a t -surface and lov thermal conductivity in s tructure bond l i n e .
(3.) Develop materials with low ablative temperatures -
[h) Investigate bonding of mater ia l ! to . ' hot structure.
(b) Develop minimum shape change materials for aerodynamic control surface and leading edge applicat ions. flieee materials will include pyrolytic graphite, al loys of pyrolytic graphite, and ceramics.
(2) Materials Analysis
(a) For selected materials above, develop analytical model to predict ablation performance and Insulation thickness.
(b) Experimentally study material performance under simulated f l i gh t environments with the use of high enthalpy arc f a c i l i t i e s (b/RT0 = 700 t o 800).
(c) Study the influence of space environment on selected mater ia ls . This wil l include the influence of vacuum, u l t rav io le t radiat ion, and high energy pa r t i c l e s .
4 .2.1.3.3 STRUCTURES
(1) Primary effort will be in the development of load-bearing radiating structures. For this structure, the following areas will be investigated.
(a) Ihermal s t ress analysis and prediction.
(b) Dynamic budding
(c) Strain gage applications t o high temperatures .
(d) Experimental simulation on large scale structures of load temperature d is t r ibu t ion , and h is tory . She WflBD Structures f a c i l i t y would be the one most appropriate to these t e s t s .
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li.2 1.3A DYNAMICS
(l) Analytical studies In the following areas should be undertaken.
(a) Unsteady aerodynamic forces at hypersonic speeds.
(b) Aeroelastic changes In structural loading and aerodynamic stability derivatives.
(c) F lu t te r
(d) Servoelastlc coupling with guidance system.
(e) Fatigue due to random loading-
(f) Transient dynamic loading.
4 .2 .1 .k
Present projects -within the Air Force applied research program wil l be reviewed and reoriented or ef for t increased, as appropriate, to provide the necessary data. Projects which can be used for th i s purpose are l i s t e d below;
6lT3*(U) Study of Controlled Final Deceleration Stages for Recoverable Vehicles.
1315 (U) Bearings and Mechanical Control Systems for Fl ight Vehicles.
1366 (U) Construction Techniques and Applications of Mew >feterials.
1370 (U) Dynamic Problems in F l igh t Vehicles.
1395 (U) Fl ight Vehicle Design.
6lU6 (U) Fl ight Vehicle Environmental Control.
1309 (U) Fl ight Vehicle Environmental Investigation.
6065 (u) Performance and Designed Deployable Aerodynamic Decelerations
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4.2.1.5
In addition to the applied research efforts referred to in Paragraph 4.2.1.1* an intensive study of re-entry vehicle characteristics required for the tunex mission is being accomplished under project 7990 task 17532- 2fcis study will define an optimum vehicle configuration and present the most feasible technical approaches to solving the various re-entry problems. For example, the desirability of ablative and/or radiation techniques for cooling will be determined.
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4.2.2 HIOFULSIOH
4.2,2 .1
me Manned Lunar Payload requires a booster capable of placing ft 134,000 pound package a t escape velocity on a se l ec t ed lunar t rajectory. This booster development has been included in the Space Launching System package Plan and i t s development will be done for the Lunex program.
4.2.2.2
Propulsion systems for the Manned Lunar Payload which vill be developed under this plan are those required for the following operations:
lunar Landing
Lunar Launch
Trajectory correction
Attitude control
Abort
4.2.2.3
The Lunar Landing Stage must be capable of soft landing a t approximately 20 f t / s ec . a 50,000 pound payload on the moon. This payload consists of the Lunar Launching Stage and Lunex He-entry Vehicle. Preliminary design data from studies completed to date show tha t the manned re-entry vehicle will weigh approximately 20,000 pounds and a launch stage of 30*000 pounds wil l be required. Similar estimates for the Lunar Landing Stage indicate tha t i t wi l l weigh 85,000 pounds- During lunar landing, i f an i n i t i a l th rus t to weight r a t i o of ,45 i s assumed as consistent with the deceleration desired and time of deboost, an i n i t i a l re t ro th rus t of 60,000 pounds i s required. At f ina l touchdown on the moon, with a l l & v cancelled and assuming essent ia l ly a l l deboost propellent consumed, approximately 10,000 pounds of thrust i s required: Some t h r o t t l i n g or gimballing of the engine may be required a t the 10,000 pound leve l t o reduce the axia l component of th rus t . The requirements on the landing engine are for a 60,000 pound engine with a 6 t o 1 th ro t t l ing r a t i o , or a c luster of four engines of 15,000 pounds thrus t and a t l e a s t one with a th ro t t l ing range of 1.5 to 1. Assuming a thrust to weight r a t i o of 1.5 (Moon weight) for the Lunar Launch gtage, a 12,000 pound thrust engine i s required for lunar launch. "An engine of the
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4.2 .3 I2FE SUPPORT
4.2 .3-1
The l i f e support package for the Manned lunar Rtyload vLll be required to function for a "ilplitniw of 10 days* Bile i s based on the premise that a one-nay t r ip to the noon wil l require 2^ days, and the stay on the lunar surface wil l be on the order of 5 days. Die l i f e support system must be capable of supporting three men during high acceleration boost, approximately 2 i dayB of weightlessness, one to f ive days of l / 6 earth weight, 2f days of Weightlessness, re-entry deceleration and return to fu l l earth gravity- At the sane t ine i t mist provide a shirtsleeve cabin environment under the space and lunar environments, including extreme temperature gradients, absence of oxygen, radiation, e tc .
4.2.3-2
Studies of the l i f e support system weight requirements indicate that the l i f e support package can be provided within the weight allocation for the 20,000 pound Lunex Be-entxy Vehicle. She l i f e support system weight analysis was based on physiological experiments under simulated space f l ight conditions such as confinement, special d ie t s , reduced pressure, e t c At the present time approximately 65 to 70 percent of the knowledge required to design the three man package i s available. However, to obtain the additional data experimental laboratory and f l ight test ing i s required. Most information i s presently obtained by piggyback testing aboard experimental vehicles but to support the lunex program and to meet the desired schedules the BOSS primate program must be in i t ia ted and adequately supported.
4.2.3-3
Most of the data available today consists of physiological support (nutrition, breathing oxygen, pressure su i t s , and restraints for l imited periods), but there i s a lack of knowledge on prolonged weightlessness and the biological effects of exposure to prolonged space radiations. One BOSS program i n i t i a l l y wi l l support a chlmpan-xee for periods up to 15 days and has been programed to provide a l i f e support package of sufficient else and sophistication to support a man. Ems, with the BOSS^xrogram the data wi l l become available so that the Lunex program can design and construct the l i f e support package as required for April 965^
4-17 VDLAR-S-458
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4.2.3.4
Shroaghout this development all life support knowledge and techniques will be fully exploited. Techniques, learned In the work with the Discoverer package were utilized in building the Mercury package. In turn, experience end knowledge gained from Mercury is being fully exploited in the development of the present BOSS package,
4.2.3-5
The l i f e support program (BOSS) i s v i ta l t o meet the objections of the lunex program. However, other AFSC programs bust be considered for possible application to Lunex and the following are nov being evaluated:
6373 (0) Aerospace l i f e Support
7930 (U) Bib-Astronautics
4,18 KDLAR-S-458
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4.2.4 FLIGHT VEHICIB ?OWEfi
4.2.4.1
Electrical pover will be required to operate the Lunex Re-entry Vehicle subsystem such as l i f e support, navigation and guidance. Instrumentation, and communications. She pover requirement for these subsystems has been analysed and determined to je approximately 3 kv average during a ten-day manned tr ip to the moon and return. Jteak power requirements will be approximately 6 lev.
4.2.4.2
Solar, nuclear, and chemical powered systems were evaluated against these requirements. Vhile all of these systems may be capable of meeting these requirements the chemically powered systems have been selected for early adaptation Into the program. Specifically, fuel cells and turbines, or positive displacement engines appear to offer the most advantageous' solution. The final selection will be made during the final re-entry vehicle design when a detailed analysis of the trade' offs between various available systems considering relative velgit, efficiency, reliability, and growth potential la available. The optimum system may be a combination of fuel cells and chemical dynamic systems with one system specifically designed to supply peak demand. MLth this approach the system to provide peak load capacity, will also provide backup power in the case of equipment malfunction during a large part of the mission. A battery supply may be used to furnish emergency power required for crev safety during critical periods in the flight.
4.2.4.3
Present level of technology i s such that a satisfactory f l ight vehicle pover system wi l l be available when required for the LUNEX mission. Additional development effort should be Initiated In certain specific areas, such as a re l iab i l i ty evaluation program for fuel ce l l s and an Investigation of the problems of operating chemical dynamlc^systeafi la-a-zero-**0" environment. "
Close coordination must also be maintained with the manager of project 3145 (U) Energy Conversion, to Insure the availabil i ty of the required secondary power sources.
4.19 WDLAR*S-45fl
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fc.2.5-1
A study of the guidance and control requirements far toe lunar vehicle indicates that the mission can he accomplished by reasonable extensions at present state-of-the-art equipment. The complete lunar vehicle guidance package should be capable of furnishing guidance and control during the following phases of the lunar mission.
Ascent and Injection
Outbound Mid-course
lunar Landing
Lunar Ascent
Inbound Mid-course
Earth Be-entrjr
Earth Landing
present state-of-the-art equipment i s capable of handling portions of the guidance and control problem associated villi the above phases of f l ight . However, in order to obtain s complete guidance and control system, i t i s f e l t that development of the following items should be undertaken.
4.2.5,2 ITJERTIAL PLATFCRM
Guidance requirements for both the manned and unmanned vehicles can be met with the use of guidance concepts based on the use of inert ia! and corrected inert ia! data in a combination of explicit and perturbation computations of present and predicted trajectories. Consequently, an Inertia! platform con" figuration suited to the space environment I s needed. This platform should be l ight In Height, hifdtfy rel iable, and capable of maintaining a space-fixed reference over a long Interval of time. Rresent gyroscopic devices and accelerometers are neither accurate nor reliable enough to accomplish the space mission. An inertlal platform which holte great jirpmise^MMise In lunar missions-is one rtGlzing^Iectrlcally suspended gyros in conjunction with advanced accelerometera capable of operating in a space environment. Present e lectr ica l ly suspended gyros are capable of operating with a dri f t rate of .0005 deg/ar/g, and I t i s anticipated that by 1966, a drift rate cf .0001 deg/hr/g
H>LAB-S-1*5Q
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will be attainable. Also, no di f f icul t ies are foreseen In maintaining suspension of the rotating member In an acceleration f i e ld of 1? g's with 30 g's being possible. Developaent of a small inertial platform ut i l i z ing e lectr ical ly suspended gyros will be required for the lunar mission.
4.2-5-3 STAR 5RACKKR
In order to Increase the reliability- and the accuracy of the inertial platform, a compact star tractor for use vitb the platform during the outbound and Inbound mid-course phases of the lunar f l ight I s desired. Also, the star tracker should be capable of operating in a lunar environment so that I t can be used for s te l lar alignment during the lunar launch portion of the mission. The accuracy of present so l id state star trackers i s approximately 10 seconds of arc and their wight I s approximately 15 pounds. However, these trackers are' untested In a space environment and must be developed for the lunar mission and for use with the small inert ia l platform. In particular, tile star tracker must be capable of furnishing accurate s te l lar alignment Information to the inertial platform during the lunar ascent portion of the mission- I f I t I s possible to develop a controllable thrust engine In time to meet the launch schedule, the boost and Injection guidance problem for the lunar ascent wil l be simplified as i t wi l l be possible to time-control a predetermined velocity path, abit development could possibly reduce the accuracy requirement of the star tracker.
4.2.5-4 LONG BASHJKB RADIO MAVIGATICfr,
Since manned as ve i l as unmanned f l ights are planned fox the lunar mission, i t Is necessary to have a navigation system to back-up the inertial system and to Increase the over-all accuracy of the guidance and control techniques. Long baseline radio/radar tracking and guidance techniques offer great possib i l i t i e s for tracking and guiding vehicles in cislunar space. ftresent studies show that there are a number of problems yet to be solved to give the long baseline radio navigation technique the desired accuracy. Among these problems are l ) the accuracy with which coordinates can be determined for each tracking stat ion, 2) the accuracy vith which corrections can be made for tropbspberic and ionospheric propagation effects on the^rstea_ measuremejits^_and_3D_t^-aco4ira^^ can be synenr^Szeo^at^the several stations. Reasonable extensions of the state-of-the-art should be able to overcome these problems however, and i t i s f e l t that the development of a long baseline radio navigation system wi l l be necessary for the lunar mission.
k.21 v<**'
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TOLAR-S-458
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4.e .5-5 DOPPUK RASAS
Anticipation that radio beacons iti.ll be In place on the lunar surface has somewhat simplified the lunar landing phase of the mission. She use of mid-course guidance wi l l enable the vehicle to approach the noon within llne-of-sight of at least one of the radio beacons, and the beacon can be ut i l l i ed for the approach phase of the lunar landing. However, for f inal vertical velocity measurement, a sensing technique particularly sensitive to snail velocity changes Is required. A small CM doppler radar Is ideally suited for this requirement- Therefore development of a small, reliable doppler radar which can operate in the lunar environment i s needed. In order to decrease the power requirement for the radar i t should not be required to operate at a range of over 300 miles.
-1.2.5-6 RE-OHBT amuses
Major emphasis must be placed on the guidance requirements for the re-entry phase of the lunar mission. Position, velocity, and attitude can be measured by the inert ial system, however, other measurements i n i t i a l l y required wi l l be temperature, temperature rate, structural loading and air density. Extensive further study i s needed to define these measurements villi any accuracy. Early earth return equipment Bhould furnish the data necessary to develop the required re-entry guidance package for the lunar mission.
*.2.5-7 ADAPTIVE AUTOPILOT
The control of the re-entry vehicle will require an adaptive autopilot due to the vide variation in surface effectiveness. Adaptive autopilots such as used In the X-15 are available, but extensive development i s needed to ready them for use in the lunar mission.
4.2.5-8
TJie following projects or specific tasks within these projects can be ut i l ized to provide the development required for the LUNHX program.
klkk (0) Guidance and Sensing Techniques for Advanced Vehicles
JfOl6"5"ttf) BataTiConversion Techniques
508^5 (U) Guidance Util izing Stable Timing Oscillators
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50899 (u) Molecular Amplification Techniques
W27 (u) Self-Contained Electromagnetic Techniques for Space Navigation
4431 (U) Ine r t i a l System Components
H169-II (U) Space Adapted Celest ia l bracking System
W169-III (U) J t t l t l -Headed Solid State Celes t ia l Tracker
WI69-IV (U) Solid State Celest ial Body Sensors
5201 (u) Ine r t i a l Systems Technique
5215 (U) Military Lunar Vehicle Guidance
50320 (U) Mili tary Lunar Vehicle Guidance Systems
58321 (U) Military lunar Vehicle Terminal Guidance
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4.2.6 COMPUTER
4.2.6.1
The United states has the ability to provide a suitable computer facility at the present tine to support the LUNEX mission. As the milestones in the program are realized and requirements become more complex, the computer capability will improve to meet the Be more stringent requirements. Detailed studies on the specific needs of the missions, time-phased, will be conducted to determine trade-offs among possible techniques to insure that machine sophistication does not become an end unto itself. 3be following guidelines providing adequate flexibility, have been followed in arriving at -the required development recommendations:
a. Manned vehicles will require extensive data reduction to give an operator real-time display of the conditions around him and solutions to problems such as, velocity and attitude corrections, etc.
b. Sensor control (aiming and sampling rate} and data processing will be accomplished on the vehicle either on ground command, or by operator direction.
c. Kid-course and terminal guidance requirements will make severe demands upon vehicle-borne computational systems.
d. Badlatlon hazards and effects which are unknown at present could influence the technology that will be utilised for lunar missions.
e. Emergency procedures must be available in the event that the operators become incapacitated and Incapable of returning to earth at any time during the mission.
4.2.6.2
me Computer Capability can be expanded in two basic ways by improved hardware, or nev concepts. Examples of nev approaches which wil l be reviewed prior to selection of the final vehicle design are the following:
a. Standardized computer functions incorporated into modules so that they can be used t o "build" the capability each mission requires. Such e concept would allow a vehicle designer to fabricate a coatputational^facllity without resorting to extensive redesign and/or re-packaging. The modularized concept noted above I s particularly adapted to unmanned missions.
4.24 WDIAB-S-458
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b. For a manned mission two fixed programs could be permanently placed in storage; these would be an overall command, or executive routine to direct the sequences of operation, and the other vould be an emergency return-to-base routine that could be actuated by the master control, thus a 5~pound tape unit vould replace a larger core memory and provide a higher degree of flexibility. 3ne principal advantage In this system is that the computer is general-purpose in design and therefore useable on a large variety of missions and unnecessary capabilities will not be carried on a particular mission.
c. An optimumlzed hybrid of analog and digital devices combined to use the better features of each, i.e., speed of problem solution from the analog and precision, flexibility, and data reduction from the digital.
4.2.6.3
Substantial Improvements in computer capability, developments, reliability, volume, weight, and power consumption will be available for the LUHHC program by effort expended in toe following areas:
a. Core-rope memories to be used in fixed memory applications.
b. Functional molecular blocks. By 1963, the date of earth orbit, it is expected that more than 80$ of all computer functions can be performed by this method. Advantages are numerous; high memory densities, extremely small size, small weight and proper consumption.
c. Self-healing, or adaptive programming techniques as a means for back-up on component reliabili-ty.
d. Electrolumiaescent-photoconductive memory devices should be considered for their radiation and magnetic invulnerability. In this regard, pneumatic bl-stable elements should be considered for the same reason.
e. Pbotochromic storage devices have advantages In high storage densities, 1 billion bits/cubic inch. Certain applications, such as Bend -permanent storage could benefit from this feature.
4.2.6J»_ _
The following projects In the Applied Research Area will be utilized to obtain Improvements in computer technology;
3176 (U) Space Borne Computation fc Control Techniques
4421 (U) Digital Computation Methods & techniques
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4.2-7 COMMtflOCATTOBS
4.2.7-1
Die manned lunar mission vill require coramuni cations channels between the vehicles and earth and on the lunar surface for telemetry, T.V., voice, and vehicle control. Specific system parameters vill depend on the characteristics of the ground tracking network and communications stations vhich vill be used to support the lunar missions.
4.2-7-2
There are no significant technical problems associated v i th the development of equipment to perform the required communications operations. One exception to t h i s general statement i s tha t during re-entry radio transmission may not be possible a t the lover frequencies u t i l i zed elsewhere in the mission because of the plasma shield se t up by aerodynamic heating. One possible solution may be t o provide a separate system operating a t 10,000 mcs for re-entay. Overall savings i n equipment weight, and pover requirements will r e s u l t from careful analysis and ident if icat ion of requirements for information transfer and naxinmm u t i l i za t ion of system components In a dual ro l e . This v i l l be done during the vehicle design phase. While not a requirement for early missions the capabi l i ty to Txrovide a secure communications l ink i s desirable and wi l l be considered during f inal design of the communications systems. A secure communications l ink wil l be a :-*=.uirement i n l a t e r missions, throughout a l l phases, communications l inks c r i t i c a l t o mission success should Incorporate a high degree of protection against natural or man-made interference, or del iberate Jamming.
4.2.7-3
Ihe following Air Force projects vill be revleved and used to provide the necessary results required for the Iunex mission:
4335 (U) Applied Communications Research for Air Force Vehicles
4519 (17) Surface & Long Range Communications Techniques
5570 (U) Communications Security Applied Research
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4.2.8 EWIROHMEimL DATA
4 .2 .6 .1
ft-esent knowledge of the lunar environment le extremely limited end it is necessary to obtain detailed information concerning the lunar composition., subsurface structure, surface characteristics, meteorite flux, level of BOlar and cosmic radiation, and magnetic field. This knowledge is required to design the equipments for the lunex program so that personnel nay be protected and the mission accomplished.
4.2.8.2
The importance of lunar composition in manned exploration of the moon lies largely In the ability of the moon to provide fuel for vehicles and secondary power, as veil as to supplement life support systems vith additional water, radiation shielding material, and semi-permanent shelters. Of these lunar resources, water appears to be of major importance both as a fuel and in life support. Water vill probably be present both as ice in permanently shadowed zones and as water of hydration in certain minerals such as serpentine.
4.2.8.3
iYesent knowledge of lunar composition is almost entirely theoretical. The relatively low lunar density (3-34) indicates low metal content. By analogy with the compositions of meteorites it is generally assumed that the moon is composed of ehan-dritic (stony meteorite) material. That this assumption is only partially valid is demonstrated by the fact that chondritic meteorites would have to lose about 10J6 of their iron content in order to attain this lunar density.
4.2.8.4
The Air Force and NASA are presently trying to determine th lunar composition indirectly through study of tektltes, which may be fragments of the moon, and through study of micrometeoritic dust captured above the atmosphere. (Air Force efforts are funded under project 7698).
4.2.8.5
The Air Force I s trying-to-determine the lunar composition di rect ly by means of spectrometric analysis of the natural X-ray fluorescence of the moon due t o the bombardment of the lunar surface by solar radia t ion . The f i r s t knowledge of lunar compos* i t l o n i s anticipated i n March of 1962. (This work i s a lso funded under Rroject 7698).
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4.2.6.6 C
NASA intends to measure the lunar composition directly by means of Its Surveyor lunar probe now scheduled for Bid I963.
4.2.8.7
Neither Air Force measurements of overall lunar composition; nor NASA measurements of spot compositions will satisfy the requirement for location of lunar resources. Una NASA Prospector vehicle scheduled for 1966 wil l obtain store widespread data, but vti&t Is urgently needed i s detailed knowledge of the variation of lunar composition over the whole surface. Ohis can only be accompli shed by & lunar orbiting vehicle with appropriate instrumentation. NASA presently has this planned for 1965 and the appropriateness of their Instrumentation remains in doubt. Also this i s too late to meet the requirements of the LUHEX program.
4.2.8.8
2he Importance of lunar subsurface structure in exploration of the moon lies largely In a possible collapse hazard under vehicles and personnel, and in the possibility of utilizing -subsurface structures as shelters and storage facilities.
Present knowledge of lunar subsurface structure 1B based on a theoretical extrapolation from the presumed origin of the surface features. The majority of lunar geologists believe that lunar craters vere formed by means of the impact of large meteorites, and that only limited volcanlsm has occurred in the lunar highlands. 3he maria, en the other hand, are thought to be giant lava pools; although the melting is assumed to have been triggered by asteroldal impact.
Based on these theories of origin for the lunar surface features, it is thought that the subsurface structure of the lunar highlands will consist largely Of overlapping layers of debris ejected from the impact craters. One collapse hazard of such material is negligible. 3he maria should be covered by no more than kO feet of vesicular (bubble filled) lava, -with "«^"i"" vesicle (bubble) size about six feet in diameter. Such terrain could present a collapse hazard, the severity of which will depend- upon-actual rather than maximum) vesicle size.
It should be noted, however, that a rival theory for the origin of lunar craters holds that they were produced by volcanlsm as calderas. Should this theory be correct, the collapse hazard in the highlands would probably exceed that on the maria.
TOLAS-S-458
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is necessary to place instruments on the noon. 31ms, the Air Force, although contributing theoretical evaluations as described above (under Project 7698), has no program for directly determining lunar subsurface structure. NASA plans to place seismometers and a coring instrument In the Surveyor vehicle In mid-1963 to determine these parameters. Again, point measurements are not sufficient, and geophysical instrumentation adequate for determining subsurface structure from the lunar orbiting vehicle (1965) should be developed.
k.Z.B.9
2ne importance of lunar surface characteristics lies In their critical importance in design of both rocket and surface vehicles and in lunar navigation* Critical Burface characteristics include gross topography, microtopography and the nature of the lunar dust. Of these characteristics, knowledge of gross topography will be Important In overall rocket design end in design and operation of rocket landing and navigational equipment. The microtopography (relief less than 20 feet) will be important in the design of rocket landing equipment and the vehicle for surface exploration. The nature Of the surface dust will be most important in design of the vehicle for surface exploration.
Present knowledge of gross topography shovs that slopes are generally gentle, and topographic profile have been determined over a limited amount of terrain. Present knowledge of microtopography is very limited. Radar returns, once thought reliable indicators of low microrelief, are nov considered by most space scientists to be so poorly understood that conclusions may not be drawn from them. Photometric data appears to Indicate a rather rough surface, but this data is also subject to more than one interpretation. Present knowledge of the nature of the lunar dust is entirely theoretical. The leading school of thought holds that the dust is compacted and sintered. An opposing school holds that the dust bears an electrostatic charge. Should the dust bear an electrostatic charge, it would be very loose and probably subject to migration. The hazard to surface vehicles and even personnel is apparent.
Gross lunar topography on the visible~face is presently being mapped by the Aeronautical Chart and Infoxnatlon Center based on techniques developed under Project 8602. Maximum resolution is about 1/3 mile, and average resolution is about one mile. Higher resolution photography and photography of the back side of the moon will be obtained by the lunar orbiting vehicle planned by NASA for 1965. A cooperative effort by ACIC and NASA is presently envisioned to produce the necessary topo-graphic lunar charts.^ ^ . m i ^ r U ^ l * . U |
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Mlcrotopograpby 1 B being studied by the Army Corps of Engineers through radar experiments, (The Air Force work is being done on the Millstone radar equipment) The nature of the lunar dust is being studied primarily by the Air Force under Projects j6$Q and 6602 by means of radiometric studies from high altitude unmanned balloons and results are anticipated early 1962. NASA anticipates obtaining at least partial data on the nature of the dust from Surveyor {mid 1963) by television observation ot the lunar surface and by the landing characteristics of the vehicle.
k.2-8.10
The meteorite flux and level of solar and cosmic radiation near the lunar surface are important for the survival of personnel either on the lunar surface or in vehicles and shelters -
Present knowledge of these parameters is fairly precise as a result of satellite and deep space probe experiments by NASA and the Air Force- Only the radiation environment within the first fev meters of the lunar surface is still speculative as a result of uncertainties in our knowledge of the interaction of solar and cosmic radiation with the lunar surface materials. It seems likely that a cloud of ions will be produced by radiation bombardment as veil as secondary X-rays. Dae density of the electron cloud is unknown, and may be critical for lunar communications.
The Air Force is studying the lunar and cislunar radiation environment under Projects 6687, 6688, 7601, 7&9, and 7663 hh means of satellites, deep space probes, and vertical sounding rockets. The NASA Surveyor vehicle (mid-1963) should give detailed knowledge of the radiation environmeiit at the lunar surface.
k.2.8.n
The lunar magnetic f i e ld may be important to space and lunar surface navigation, and In i t s ef fects on ionized lunar materials .
The Russian lunik I I indicated tha t the lunar magnetic f i e ld must be very small. ' The Russians were not c lear on how small, but I t i s generally thought t h a t the moon does not possess a magnetic f i e ld . Thus, a l l magnetic ef fects should be derived from the very low in tens i ty Interplanetary f i e l d and magnetic f i e lds , "frozen" In to solar plasmas.
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4.2.9 MATERIALS
4.2-9-1 the Lunar expedition imposes rigid requirements on materials to maintain their characteristics vfaile subject to radiation, vacuum, temperature- extremes, and meteorites. Ibis problem must be considered by the individual subsystem design. It is intended to point out here the overall material problem and programs which will contribute tt>. its solution*
4.2.9.2 The absence of an atmosphere on the moon increases the radiative flux (particle and electromagnetic) from the sun and as such potentially Increases the possibility of damage to man and light-weight plastic structures through the formation of free radicals and subsequent depolymerization. 5he need for light-weight shielding is apparent. The vacuum conditions of the moon would aggrevate the problems associated with moderately volatile constituents of plastics, lubricants, etc. Tor instance, the relatively volatile plastlcizers la a plastic material could evaporate and interfere with the plastic function. Finally, the results of impact of mlcrcmeteorltes
on structural materials must be determined* All desirable properties must be acquired without penalty of weight. In addition to the problems encountered on the Moon, similar problems are encountered while In transit. In particular the heating encountered on re-entry into the earth's atmosphere at 37.000 feet per second presents a severe material problem.
4.2.9.3 Sane of the specific material requirements that can be identified are:
a. Lubricants that will function for long periods of time In a vacuum and temperature conditions such as exist In the moon.
b. Jfaterials that will not sublimate In a vacuum at moon temperature.
c. Light-weight shielding material against meteorites.
d. light-weight, radiation shielding.
e. Shock-absorbing material that will function at 3309P,
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f. Coatings that will resist radiation, especially during periods of solar flares-
g. Glues and adhesives that viU function with lunar materials.
V.2.9-^ Present projects to raise the level of technology in materials are listed below, Ihey will be supported as required to insure success of the lunar mission.
7312 (U) Finishes and Materials Preservation.
7320 (U) Air Force fltextile Materials.
73*10 (U) Non-Metallic & Composite Materials.
7351 (U) Metallic Materials.
7371 (u) Applied Research in Electrical, Electronic, and Magnetic Material.
7391 (V) Energy Transmission fluids.
if.2.9-5 While work in the basic research program cannot be counted on to provide technical break through within the time schedule of the LUHEX program, materials study of this type Vill be monitored so that all technical advances can be integrated into the IWMEX program. Specific examples Of projects of this type are:
8806 (U) Research on Materials at High Temperature.
7022 (U) Surface and Interface Phenomena of Matter.
9760 (U) Research in Properties of Matter.
U.33 WELAR-S-U58
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k-3 TEST PLAN
The development and production of the equipments for the Lunar Expedition will require a concurrent end detailed test program.
She test program vill be carried out on the basis of research tests to establish design criteria, materials, tests, component • tests and finally, a progressive series of tests as components are assembled into subsystems and major systems and structures. Integration tests for flight suitability vill be conducted for all functioning systems and the complete vehicle. Fayload effects on the booster structure will be determined vlih a simulated payload. Subsequently, a flight-type payload vill be used to demonstrate booeter-payload system compatibility, reliability, crew- safety, and mission performance.
Emphasis vill be placed early In the program on research tests to derive basic design criteria, define the configuration and determine aerodynamic parameters.
Tests are to be run at progressively higher levels as the design evolves- 3hus, entire subsystems, combined subsystems and complex major structures are to be subjected to evaluation tests as necessary to investigate component end subsystem interactions, or to prove out complex structural designs.
A captive-test-vehicle firing program vill be the culmination of ground development testing. 3he over-all objective of the captive-firing program is to demonstrate satisfactory integration of the propulsion system vith other vehicle systems that have an interface, direct or indirect, vith the propulsion system* Ihe early tests vill be conducted in a simulated vehicle vith the airborne vehicle systems Installed on a heavy-vall propellent tank section. She tanks vill be supported by a test stand structure vhich vill also restrain the tanks against propulsion system thrust forces- For final testing a flight-type configuration vill be used during captive tests.
Flight testing of the High-Speed Re-entry Test Vehicle, ths Abort System and Orbital, Circumlunar and unmanned lunar Lending and Return Vehicles vill complete the development program.
4.3*1 TEST CATEGCRIES
4.3.1.1 RESEARCH ZESTS
Tests vill be run in appropriate research laboratories to define basic designvcriterla In at least the folloving technical areas: * - -, .
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a. Propulsion
b. Heat transfer
c. Aerodynamic forces and pressures
d. Materials
e . S ta t ics (structures)
4 .3 .1 .1 .1 Propulsion Tests—Wind and vacuum tunnel t e s t s will be conducted t o Investigate the problems of multiple r e - s t a r t In a vacuum environment, to develop throt t leable techniques, to determine lunar landing problems, and to determine the des i rab i l i ty of using the same engines for lunar landing and lunar launching.
Tests v l l l be made to evaluate the propulsion stage for the clrcumlunar f l igh ts and to determine the capabili ty of the abort propulsion system t o accomplish i t s objective-
4.3.1.1.2 Heat Transfer Tests—Testing wil l be required on the Insulation for the l iquid hydrogen tanks to determine:
a. Optimum material thicknesses and velght
b . Bie amount of l iquid hydrogen bolloff
c- The a i r leakage through seals
d- The airload effect on s t ruc tura l in tegr i ty
- e . The thermal bowing of insulat ion panels
f. Toe separation distance between panel and tank skin
Scale-model or modified fu l l - sca le air-conditioning t e s t s v l l l be conducted on engine compartments, adapter sections and f l i g h t equipment storage areas .
Heat t ransfer character is t ics for selected mater ials , s t ructures , and surfaces wil l be required t o support the engineering design.
4*3*l-l-3 Aerodynamic Force and Pressure Wind-Tunnel Tests—Wind-tunnel model t e s t s of the launch vehicle and payload configuration Will be required t o accurately determine the aerodynamic forces and moments imposed on the vehicle during the boost t ra jec tory .
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2heee t e s t s v i l l provide data for determination of structural design c r i t e r i a , aerodynamic s t a b i l i t y and control parameters, and the per formance penally incurred by aerodynamic drag. She t e s t program w i l l include both force and pressure measurements through the f l i g h t Mach number range for which these e f f e c t s are s i g n i f i c a n t .
Hind tunnel t e s t ing of s e l ec ted shapes a t v e l o c i t i e s never before studied w i l l be necessary t o determine re-entry veh ic l e characteri s t i c s . particular emphasis w i l l be placed on control surface capabi l i ty and heating problems. Maneuverability l i m i t s * g loadings, re-entry corridor character i s t i c s and subsonic landing character i s t i cs must be determined i n support of the engineering design program.
Integration and correlat ion of the ground vind-tunnel t e s t i n g with the high-speed re-entry f l i g h t t e s t program i s e s s e n t i a l .
U - 3 - l ' l ' ^ Material Tests--A materials development t e s t program V i l l be undertaken t o determine the allowable design strength values and provide design information on the se l ec ted structural materials over the appropriate temperature ranges f o r the base metals , ablat ive surfaces, and welded Jo int s . Particular emphasis w i l l be placed on tendency toward b r i t t l e fracture under service conditions and i n se lec t ing materials f o r re-entry a t 37.000 f t / s e c . The t e s t i n g program w i l l consist of at l e a s t the fol lowing:
a. Smooth and notched s t a t i c t e n s i l e t e a t s of the se l ec ted materials .
b . S ta t i c t e n s i l e t e s t s of welded Jo ints , both fus ion-ana resistance-welded, for the se l ec ted Joint configuration f o r each type of sheet material .
c . Smooth and notched s t a t i c t e n s i l e t e s t s of the s e l ec t ed extrusion end forging materia ls .
d. Notched impact t e s t s of the extrusion and forging materie ls .
e . Low-cycle, high s t r e s s fat igue t e s t s of welded Joints made by the fusion and res istance methods f o r the se lec ted Joint con" f igurations i n sheet mater ia l s .
This data v i l l be accumulated for the appropriate temperature ranges, i . e . , from e levated re-entry temperatures to the cryogenic temperatures i n the tanks, as d i c ta ted by the projected environmental requirements. In addi t ion , supporting t e s t s such as metallographic examinations and chemical composition determinations v i l l be made as reouired-
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4*3-1-1.5 Static Vests—The static-test program will include design and structural substantiation testing to demonstrate structural integrity of the Manned lunar and Cargo Fayloada.
Structural substantiation testing to design loads and temperatures will be accomplished on a full-size stub tank, identical (except for length) to the Lunar Landing Stage tank, this will ensure that load introduction and takeout will be representative of the flight article.
One complete interstage adapter will be tested to ultimate design loads under appropriate environmental conditions, The adapter will be attached to a stub tank Identical to the Lunar Launching Stage tank section in every respect except length, to ensure realistic load introduction and takeout-
A stub tank will also be used to demonstrate the integrity of the Lunar Launch Stage tank construction under design loads and environments. Methods of introducing the payload vehicle loads into the adapter section and thus the Lunar Launch Stage tanks will be determined.
Tests will also be run on full-size tank bulkheads. These will be attached to a segment of typical tank structure, adequate to allov the bulkhead behavior to be representative of that of the flight article under design conditions. These bulkheads will be tested to ultimate design loads to ensure their structural reliability at all points within the fligit regime.
Ground handling equipment tests will cover critical fittings and Joints for structural substantiation of these items under design conditions.
4.3-2 DESIGN EVALUATION 3ESTS
Component design evaluation testing is defined here as Informal testing conducted by the vehicle contractor, or vendor test labs, for the purpose of basic design evaluation prior to production release, and to pinpoint critical areas in prototype packages.
Qualification testing is defined as those formal tests performed on flight-type hardware to demonstrate compliance with design specifications. A qualification test plan will be prepared approxi-mately_9Q_days-after engineering-go-ahead outlining the" qualification test conditions. The qualification tests are to be performed in strict accordance with written and approved detailed test procedures, and witnessed by the Air Force, of an approved representative.
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She vehicle contractors test laboratories will conduct these tests, or subcontract and supervise then at an Independent testing agency. Components to be tested ""111 be determined daring the engineering design effort'
Controlled environmental conditions will simulate conditions that airborne and ground support equipment are expected to experience during manufacturing, shipping, storage, prefllght and flight.
Environmental testing conditions vill be established based on data already obtained in research and development programs on large rocket-powered vehicles and associated support equipment. Conditions for shipping, storage and handling environmental tests are established in current military and commercial specifications, Subsystem, combined subsystems, and structural evaluation tests will be run in appropriate laboratory facilities to Investigate component and subsystem interactions, and to prove out structural designs. Acceptance test procedures will also be developed for use in the factory on deliverable hardware.
A test plan describing the basic conditions and test objectives of each factory system test, along with the checkout parameters and recorded evaluation data, will be prepared.
A final acceptance test will be required .t the time the contractor delivers the vehicle to the Air Force. lest conditions will be as close to the flight conditions as is feasible and. safe. All systems will be energized and operated simultaneously.
A final acceptance test evaluation document will be prepared for use by the Air Force and the contractor in determining compliance with test requirements.
Systems acceptance test procedures will be based on all critical parameters required to determine proper functioning of each system in accordance with design specifications and drawings. M s will assure a coordinated effort of vehicle design,. test equipment design and factory acceptance testing.
fc-3*3 FLIGHT 5ESTISG
Ihe LUNEX flight test program represents a long and expensive effort leading to the first manned landing on the moon, it requires basic research flights, equipment checkout flights., capability demonstration -flights ana finally the manned and cargo Lunar Expedition flints. This type of effort can only be achieved efficiently and at a minimum cost if the end objective Is always clear and the program is designed to meet this objective.
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The Lunar Expedit ion f l i g h t t e s t program w i l l provide many side* b u t important space c a p a b i l i t i e s , f o r example; i n Apr i l 1965 the f i r s t o r b i t a l f l i g h t c a p a b i l i t y i n a t r u e space vehic le w i l l be p o s s i b l e ; i n September 1966, man v i l l make h i e f i r s t f l i g h t around the moon i n a f u l l y maneuverable and recoverab le r e - e n t r y v e h i c l e ; and i n August 1967 the f i r s t man w i l l l and on t he moon- E s s e n t i a l l y these can a l l be ca l l ed t e s t f l i g h t s , bu t i n each case t h e system i s only a t t h e beginning of i t s c a p a b i l i t y Ins tead of being a dead-end I tem. Each of these c a p a b i l i t i e s may r e a d i l y be expanded t o provide a m i l i t a r y c a p a b i l i t y i f necessa ry .
The f l i g h t t e s t program i s summarized on t he Lunar Expedi t ion Test Schedule. The following major ob jec t ives w i l l be accomplished i n the i n d i c a t e d . p a r t of the t e s t program.
1*.3*3-1 HIGH-SPEED RE-ENTRT FLIGHT TEST
Since presen t -wind-tunnel c a p a b i l i t i e s a r e l i m i t e d t o approximately 18,000 f t / s e c , i t i s necessary t o perform r e - e n t r y f l i g h t t e s t i n g a t v e l o c i t i e s t h a t range from 25,000 t o ^5,000 f t / s e e . The major o b j e c t i v e s of t h i s t e s t program a re t o :
a . Verify or disprove p resen t t h e o r i e s on b a s i c r e - e n t r y techniques a s ex t rapo la ted t o t he s t a t e d v e l o c i t y r ange .
b . Determine problem a r e a s and develop nev fundamental t heo ry , numerical procedures and t e s t i n g techniques vhere r e q u i r e d f o r t h i s r e - e n t r y range .
c . Ident i fy the fol lowing:
(1) Items t h a t can be i n v e s t i g a t e d f u r t h e r on a l abora tory s c a l e -
(2) Spec i f i c l a b o r a t o r y f a c i l i t y r e a u i r e n e n t s .
(3 ) Addi t iona l f l i g h t t e s t s t h a t must be performed.
d. Support t h e engineer ing design program fo r t h e LUHEX by providing t he above da t a and s p e c i a l shape t e s t i n g i f r e q u i r e d .
4 . 3 . 3 . 2 LUNEX KE-EHTRT VEHICLE FLIGHT TEST
The Lunex Be-ent ry Vehicle -will be f l i g h t t e s t e d by var ious techniques and i n varying environments. Each t e s t w i l l be designed t o al low the veh ic le t o proceed t o t he nex t more
4-39 WDIAR-S-U58
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difficult step. Jhe major testing steps axe presented below with the major test objectives for each step.
a. Prototype Drop Test
Prototype vehicles will be drop tested from a B-52, or equivalentj. In both an unmanned and a manned series of tests. Bach series will be designed to;
(1) Establish landing characteristics.
(2) Measure inherent subsonic, transonic, and hypersonic s tabi l i ty and control characteristics of the vehicle.
(3) Explore the f l ight characteristics of the re-entry vehicle in every possible portion of the Mach number spectrum.
(It) Train LtfflHC Crews.
b- Orbital Test:
Maximum use wil l be made of SMBT orbital t e s t information and unmanned and manned f l ights wi l l be accomplished. These tests wil l demonstrate:
(1) One capability of the Lunex Re-entry Vehicle to operate In the orbital area.
(2) Re-entry capability at ve loci t ies of 25,000 f t / s e c .
(3) She maneuverability of the re-entry vehicle and i t s capability to land at a preselected earth base.
c. Circumlunar Test
This f l ight w i n use the Circumlunar Propulsion Stage and the Lunex Re-entry Vehicle. The major teBt objectives are:
( l ) To send an unmanned and then a manned vehicle around the moon and return far an earth landing at a selected base.
(g) To check out guidance, f l ight-control, communis cations and l i f e support sub-systems in a true space environment prior to landing on the lunar surface-
(3} R> perform manned reconnaissance of the lunar surface.
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d. lunar Landing -and Return
The unmanned vehicle flights will check out the Manned Re-entry Vehicle and related systems to provide a completely automatic system before man first tries the most difficult step In the LUNEX program. Hie major test objectives for these flights will be to:
(1) Check out the lunar landing and lunar launching Stages.
(2) Check out the Cargo Payload's ability to deliver cargo packages to & preselected site on the lunar surface-
(3) Place three men on the lunar surface so that the initial surface reconnaissance can be accomplished prior to the arrival of the lunar Expedition.
fc.3-3-3 IUKAR MUNCH STAGE FLIGHT TEST
The Lunar Launch Stage vill be Initially checked under orbital conditions to:
a. Demonstrate space environment operation.
b- Demonstrate engine restart after "soaking" in space for an extended period.
c. Demonstrate automatic checkout, communications, and remote control capability.
The Lunar Launch Stage vill then be flight tested with the complete Manned Lunar Payload for the unmanned and manned Lunar Landing and Return Missions.
h.3.3.h LUNAR LANDING STAGE FLIGHT TEST
The Lunar Landing Stage will be initially checked out by drop testing. These tests will;
a. Demonstrate landing techniques and the capability of the selected landing system.
b. Evaluate the effects of unexpected .terrain variation.
c. Determine the effects of malfunctioning equipment during the landing maneuver.
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a. Evaluate the effects of engine b las t on landing surfaces similar t o the predicted lunar surface.
The lunar Landing Stage v i l l receive i t s f i r s t space evaluation in orb i t . The major objectives a r e :
a. Correlate drop-test data with orbi ta l or space operations*
b . 5b determine the effects of space environment on the stage.
The f i r s t Lunar Landing vi th the Lunar Landing Stage wi l l be accomplished vi th a cargo package as the payload. When t h i s has been completed a Lunex Re-entry Vehicle v i l l be landed unmanned. The t e s t objectives axe t o :
a. Demonstrate the feas ib i l i ty of landing large cargo packages on the lunar surface.
b . Demonstrate the f eas ib i l i t y of automatically landing a "manned vehicle" vhile unmanned.
c. Provide a man-rated system for the Lunar Expedition.
4.3-3-5 CARGO BACXftGB CONFIGURATION FLIGHT TEST
Various configurations for the Cargo Package of the Lunex Cargo Payload v i l l be tes ted . . The objectives are t o :
a. Determine the Cargo Payload aerodynamic charac te r i s t i c s .
b . Demonstrate tha t the Cargo packages can be delivered vhere desired on the Lunar surface.
4.3.3.6 ABCRT SISTEM FLIGHT TKST
The fact tha t a system of t h i s magnitude must possess some measure of "unrel iabi l i ty" i s recognized and a "fai l safe" abort system Is required t o Insure the survivabi l i ty of the crev. The t e s t objectives for the Abort System Flight Test Program are t o :
a. Demonstrate tha t crev members in the manned Lunex Re-entry J^icle_caaJje__recoyered-safeIy in the-eveat-of—ft^alfunctjoo.
b . Demonstrate tha t the Space Launch System i s capable of shirt-dovn, or th rus t vector change, so t h a t crev abort i s possible .
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wmrnr k.^.k CHECKOUT AMP TEST BJUHMBJT
The test equipment will be fully automatic -with quantitative readout capability for all critical functions. The Lunex checkout equipment will be the same, or compatible with the Space Launching System checkout equipment. The equipment vlll be capable of checking
mmmm out the complete booster and payload system as veil as any individual, •--..ji.;.' or Isolated component, or subsystem. It shall be fully capable of
checkout of any one stage, or the re-entry vehicle, as an isolated ;=::;-:-.-;- unit, and vlll mate with the stage Interface functions and furnish
appropriate operational or simulated error inputs to the stage systems.
For the time period of interest, it Is entirely practical to incorporate malfunction prediction capability for preventative maintenance. This will entail a computer function which will accurately control and record the input and output signal values to each system
~" or component. Variations in operation will be recorded and compared to predetermined failure values, or characteristics and will forecast
;>$*«, the remaining service life of the system under test.
The checkout equipment shall be installed In each blockhouse and it may °e usc& In conjunction with the launch area. This same
( equipment shall be utilized in the vehicle manufacturing checkout and test functions, as veil as In the launch complex, receiving, inspection, and maintenance facilities.
The blockhouse equipment will monitor the launch control system commands and Inputs as veil as those of the payload. Because the launch control equipment will display only go/no-go signals, the checkout and test system will furnish quantitative displays of any function under question for human appraisal and decision.
When the systems are flown unmanned and on the early manned lunar flights it -will be necessary to provide automatic checkout where appropriate via a telemetry link. As an example, prior and during lunar launch the checkout procedures will be monitored at the earth control station via the telemetry linjt.
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At the present time a detailed Production Elan is not available. However, the present preliminary design study.will be completed on 30 June I96I and the final report to be provided by six Independent contractors will include their proposed Production Plan. When the study results have been evaluated a Production Plan for the Lunar Esgwditlon will be prepared.
Several points are apparent at this tine and they are presented for completeness In this plan.
k.k>l QUANTITY
Limited quantities of early equipments will be required until the test program improves and Increases the capability of each item and production quantities become possible. Thus, as development and testing proceeds the equipments will become more standardized and production techniques will become more applicable. When the Lunar landing and Return flights are initiated it will be necessary to launch vehicles at rates that vary from one to two flights per month. When the Lunar Expedition is actually underway the launch rate will remain at a rate of two per month for an extended period. Considering the size, weight, complexity and importance of these vehicles this represents production rates even when compared to past aircraft or missile production programs.
K.k.S QUALITy
The inherent reliability of the systems required for the Lunar Expedition program will be maximized by good design practice. Reliability testing represents a major effort of the test program, but the achieved reliability of these systems can only be maintained during production by an excellent quality control program. Ufcis means that good organization, adequate manning and early recognition of the quality control problem is essential. Close coordination is required between the quality control personnel and the reliability personnel in _the jfleBlgn^deVelopment, and test prcgr&m-lf the reliability program and the test results are to provide the proper guidance so that quality Qggi be maintained throughout the production effort. ;_..- "'
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4.U-3 LOCATION
It is anticipated that most of the major systems and sub-systems can be manufactured at facilities, or locations presently l» existence and available to the aerospace industry. However, the possibility does exist that certain items, such as the first stage solid propellant stage, may be manufactured at the lunar launch Complex due to its size and transportation limitations. 5hese particular items have not been specified at this time, but this will be done as soon as possible.
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TITLE PAGE 5 . 1
RECCED OF CHANGES 5.2
INDEX 5.3
5.0 INTRODUCTION 5.5
5-1 BUDGET ESTIMATE AMD FINANCIAL PLAN- 5.5
5-2 COST ESTIMMES- 5 .6
5-3 FT 62, 63 FINANCIAL PLAN 5.7
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5- BUDGET AND FINANCIAL
5.0 IN3BODUCTTOH
The funding estimates for the Lunar Expedition Program are based on results obtained from previous concept, feasibility, and preliminary design studies. These results were published in the Lunar Observatory final Report, Volume I - Study Summary and Program flan, numbered AFBMD TR 60-hk and dated April i960. Hie costing of this program was accomplished by the Rand Corporation and was based on a completely integrated program.
One funding estimates for the Lunar Expedition represent all the costs of establishing a habitable facility on the moon except the cost of developing the Space Launching System.
---- This funding would include s. Lunar Transport Vehicle de-""- velopment program that would give the U.S. the capability of
using the moon and space. Then if the need should develop in the ^&& future, the Lunar Expedition Facility could be expanded to support l™*"-*7 military operations. Studies have shown that the moon possesses
real military potential and it could support a recallable deterrent
C capability. Bie development of the Lunar transport Vehicle repre
sents a minimum program for the Air Force to obtain control of the cislunar volume and the lunar surface. 5.1 BUDGET ESTIMATE AND FINANCIAL H A H
A preliminary design for the Lunar Transport Vehicle is presently being accomplished by six contractors on an active study program. This program was funded for $300,000 in FY 6l and three of the contractors are each performing the design under a $100,000 contract. The other three contractors ere participating on a voluntary basiB. * Tile final reports for this preliminary design will be submitted to the SSD on 30 June 1961. Evaluation of these reports will follow immediately and the results will be used to revise this document where necessary. The LUNEX program has an Engineering Design competition scheduled for initiation in January 1962. This competitive effort would be evaluated and a decision on the manufacturing approach would be possible by January 1963- To accomplish this program the following funds will
. be required:
FY-62 FY-63 S f f i W H i "26T9 112.2 ^ - - . . ,.
Should the above funds not be made available, the schedule for establ ishing the Lunar Expedition wi l l be delayed proportionally t o the delay In funding.
5-5 WDLAR-S-45B
TM> rfacmnmr ceatn'M lnfe«natlan atfadiBt ft* HMioMil 4 * t a « * of N H U n l M Stem w M I * Hw M a s i M • ! Hw E i p i w i M l m » , TIN* t l . U. I .C, b c H n 7 M and 794, M* hanmtutaa m i t l a l l e o «f wtirch in any Honnr M * i iMNtlnrliad p*ran H prahibftid to tow.
• * *
5-2 COST ESTIMATE^.
5he funding requirements for the complete LUNEJC program are as follows:
w
R £ D
Launch Fac i l i t ies
Expedition Costs
Annual Total
Program Total
F.Y. COSTS (In m m ions)
1962 1963 19& 1965 1966 1967 1968 1969 1970 1971
Ig6.9 IfA 335 660
8 6k 6b
ja6.9J US 399J 1&
108W 1608
1131
108411608' 1135
1053, 798; 631 j
1Q23J 798 631 '
• 751*3
To accomplish the LUNEX Program, additional information about the lunar surface is required at an early date. This means lunar surface photographs from a lunar orbiting vehicle and the delivery of a radio-light beacon to the lunar surface by a soft landing vehicle. Present MSA programs vill provide some information and capability. However, to meet the KMEX program schedule, the following additional funding will be required by either the XIASA or the Air Force:
Unmanned Vehicles P.Y. COSTS (In millions)
Lunar Photographs and Radio-Light Beacon
Recovery of Lunar Core Sample
ANNUAL TOTALS
1961 1962 1963 196k 1965 1966 1967
15 75 85 i i !
15 I I :
i 12 35 85 J
1 ' l
»85 !265 .85 ! 21*
! 27 '.no 175 300 .265 - 85 ! *
5.6
WDLAR-S-lt58
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*:1 -—">"
5-3 FY 62, 63 FINANCIAL PLAN
MANNED LUNAR PAYLOAD Lune'x Re-entry Design & Mockup
(2 cont'r, 8 M ea) Lunar Landing Stage
(2 cont'r, 1 M ea) Lunar Launching Stage
(2 cont 'r, 1 M ea)
SECONDARY POWER Manned Vehicle power System Surface Vehicle Power System (15 kw) Nuclear Lunar Facility Power (300 kw)
(Spur Program Support)
GUIDANCE Mid-course System Lunar Terminal System Lunar Ascent System Earth Return System
LIFE SUPPORT Crew Compartment Design Ecological System Moon Suit or Capsule
COMMUNICATIONS & DATA HANDLING. Manned Vehicle Video System Design Wide Band Moon-Earth Link Design Secure Narrow Band Link Study Man-Man Lunar Surface
Materials and Resources Re-entry Materials Research Lunar Natural Resource Dev-
$ In Thousands FY-62 FY-63
16,000 80,000
2,000 10,000
2,000 10,000
600 100
1,000
1,000 300
1,500
200 300 100 200
450 450 300 500
too 1,000 500
1,000 1,200
800
too 200 100 300
1,000 llOO 300 650
1,000 500
1,300 1,000
26,900 112,150
5-7 WDLAR-S-^56
Tkli < « « M «Malm JotoiMotiHi nfbcMni * • notional driMit of MM United Stetoi -IDtln tk* H » I I « •! rtv Eiplono** 1 m , Tttto II, U.J.C., Stafen 7M «id T», It* tranniubn m imtotSwi of which rn an? •ornwr K> in nnoultnuiwo M M it BTMIMM by tow.
I
CONFIDENTIAL
DIVISION OF LUNAR EXPEDITION PROGRAM - LUNEX WDLAR-S-45B
.:,fcc<wn^-73 • * w
EECTIOH VI
PROGRAM MANAGEMENT
LUNAR EXPEDITION (U)
(LUHEX)
6.1
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• ;42££*#» . -RECCRP OP CHANGES e
VHUR.S-U58
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INDEX
TITLE PAGE .- 6 . 1
RECORD OP CHANGES 6 - 2
INDEX 6.3
6 - 0 MANAGEMENT FOCAL POINT 6 - 5
6 .1 RESPONSIBILITIES 6.5
6.2 PROGRAM OFFICE MANNING 6 . 6
6 - 3 ORGANIZATIONAL RELATIONSHIPS 6 . 7
6.fc AIR FORCE DEVELOPMENT AND SUPPORT 6 - 7
6.5 OTHER AGENCIES 6 .8
6.6 MANAGEMENT TOOLS 6 .6
6.7 PEP 6 .8
6 .3 WDLAR-S-U58
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TJTWT- "»
£ i
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* - . * • *
6.4
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WKLAR-S-1*58
wWiht H» I B X H I I H af ftto batomaa Ivan, 1 M * la on wiairittariiMJ aanaa h araMWM by law.
' -* - -.•'-. _ _ > . . , _ f-
->f- . - - r - - ' . I - ' . .
6 . ' HUX3RAM MANAGEMENT
6.0 MANAGEMENT FOCAL POUTT
Tie focal point for management of the Lunar Expedition program will be a Lunex program Office within the Space Systems Division, AFSC. The Director of the Program Office will coordinate, integrate. monitor and direct all activities of the Lunar Expedition Program. Subordinate to the Director vill be managers fox major parts of the program. A tentative organizational chart fox the Program Office is show in Figure 6-1.
6.1 RESPONSIBILITIES
a. The Earth Launch Complex Office v i l l be responsible for the c iv i l engineering aspects of building up the earth launch base. The immediate problem of this office wi l l be a s i t e selection surrey.
b. The Earth launch Vehicle Office wi l l be responsible for a l l earth launch boosters required for this program.
c. The Lunar Landing and Launch Vehicles Office wil l be responsible for a l l development and testing of the lunar Trifling Stage and lunar launch Stage.
d. The Manned and Cargo Payloads Office wi l l be responsible for the development of the 3-man Lunex Be-entacy Vehicle and. the Cargo Package. This wi l l be one-of the key offices i n the entire program since i t v i l l be concerned with such major technical areas as l i f e support equipment, re-entry problems, secondary power and structures.
e. The Communications and Data Handling Office v i l l be responsible for establishing the ccnmunications network and centralized, data handling organization. I t wi l l a lso concern Itse l f with communications problems between the earth, the moon, and the lunex Re-entry Vehicle and. point-to-point on the lunar surface.
f. Guidance and Flight Control Office wil l be responsible for developing: ascent, mid-course, terminal, lunar ascent, and re-entry guidance equipment.
g. The Lunar Expedition Faci l i ty Office block (shown In dotted outline) indicates that that office wi l l be established, at a later time since the problems associated with the expedition f a c i l i t i e s are not of immediate concern.
6-5 W)LAR-S-fc58
IWi demMM (Minim mfnimtiwi aKadtiii Ha) national aahiua •* Mw UniM b e t a wbaln nW M I I I I I af It* b p l « n | i tawi, nil* II. U.S.C.. SKfiw 7V3 and 7M, tka tnmnaSiiten ar nnlarnu af whick in any aanaar M on BMattwiiad aansa li prohibited' hf low.
h. 5he Flans Office wil l be responsible far examining other potential uses of equipment developed for the lunex Program. For example, - the Bflme equipment could be used far sending sen eround Mare and Venus, or perhaps effecting a landing on Pboboe. Considerable planning also needs to be done regarding the exploratory phase of toe lunar Expedition.
i . Programming Office will be responsible for scheduling and budgeting of the entire program. This office will have under i t s control a network of computers designated as the H3p program.
J. The Technical Integration and Support Office wil l be responsible for insuring the technical compatibility of a l l components of the system, such as, that the vibration Is within to ler able limits during the boost phase when a l l components of the system have been put together. This office wi l l also provide technical assistance to each of the main component off ices . The component office such as the Manned and Cargo Payloads Office will not rely entirely on the Technical Integration and Support Office for assistance, but wil l be free to obtain the best technical advice available in the nation from whatever source i s necessary, such as other government laboratories or universities. This Technical Integration and Support Office wil l be manned by Air Farce officers *ho wil l be responsible for the various disciplines and for technical support from the Aerospace Corporation.
k. The Reliabil ity Office will insure that a strong rel iabi l i ty and safety program i s followed by a l l contractors throughout the program. Since re l iab i l i ty and safety i s of such extreme importance in this program every effort must be made to insure the re l iab i l i ty of the final equipment- Shis can only be done by giving proper recognition to the problem at a high organisational level where policies and recommendations can be recognized and implemented.
6.2 HHX31AM OFFICE MAHNEKJ
A Program Office must be established immediately after program approval i f planned schedules are to be met. I t i s estimated that an in i t ia l buildup to 72 officers plus 35 secretaries wil l be required. A requirement for 100 MIS wi l l be established with the Aerospace Corporation. In view of the magnitude of the program, which wil l bulla up to more than one b i l l ion dollars a year* a larger Program Office wi l l be required. .Planning for these Increased manpower requirements wil l be accomplished by the Program Office, after i t i s established. Suggested Ini t ia l distribution
Kill a x w H i caalahn intonation affecting tha aatiaBal dafaiua af Ida Unltad I toMi wiAiit Ida M e a l M at rha E|«tana*a I s m , Till* I I . U. I .C, ftttlan 793 mi 7*4. Ik* tiaanalittaa a . maloHaa a( wtikt ia any aiannar ta aa saavHwrliad aafwn H amMWtad by I t * .
V"? personnel within the Rrogram Office Is as follows:
a. Lunex Program Director k
b. Plans k
e. Programming 6
d. Technical Integration and Support 20
e. Reliability 2
f. Earth launch Complex 5
g. Garth Launch Vehicle 5
h- lunar Landing and launch Vehicle 5
i. Manned and Cargo Reloads 15
j. Communications and Data Handling 3
k. Guidance and Flight Control 3
6.3 CBG/iNIZATIONAL RELATIONSHIPS
There will be a continual and energetic exchange of direction and Information between personnel of the Lunar Program Office and development contractors• Because of the complex nature and magnitude of the program, the Program mrector will be required to deal with many contractors from diverse technical areas. It is envisioned that an associate contractor will be selected fotr each major portion of the program, who will, In turn* use many supporting contracting various technological capabilities. Technical Integration and support vill be accomplished by the Aerospace Corporation under the overall guidance and control of the Program Office.
6.k AIR KQRCE BEVELOBMBNT AMD SUPPCM
Toe Lunex program office will work with the Technical Area Managers within AFSC. The Technical Area Managers have project responsibility for development of solutions to technical problems such as those associated with guidancej materials, rocket engine propulsion, life support, etc. Each Technical Area Manager will identify and emphasize those critical technical, problems to vhlch specific effort must be directed in order to attain a capability required by the Lunex program.
6 , 7 WDIAB-S-45Q
. - M l * ' " *
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(
^* J-iUKi
6.5 OTHER AGENCIES
Specific arrangements vill be made vith other agencies as requirements arise in the development of the Lunex program.
6.6 MANAGEMENT TOOLS
Die basic philosophy of developing all elements of this program on a concurrent basis Introduces rigid scheduling requirements. Specific tasks must be defined and scheduled. However, -when development problems dictate that many factors be varied to keep abreast of advancing state-of-the-art, concurrency and even the end objectives are affected and possibly delayed. A management tool vhich uses an electronic computer vill be used to support the Program Director in planning, operating, and controlling the Lunar Expedition Program. It vill be initiated in the early stages of the Program and will continue to be used throughout the expedition phase. Ibis management tool called Program Evaluation Procedure * (PEP) vill assist the Director by providing:
a. A method of handling large masses of data quickly, efficiently and economically.
b. The capability to locate, identify and this correct trouble spots.
c. A capability of integrating the many varied and complicated facets of the Lunar Expedition Program.
6-7 PEP
Die PEP management tool i s made possible through the use of an electronic digi tal computer. The scheduling and monitoring of many thousands of items required in the Lunar Expedition Program make the use of th i s computer technique imperative. Hie PEP approach employs linear programming techniques with a s ta t i s t i ca l concept in conjunction vith the electronic computer. Diis procedure faci l i tates the analysis of interrelationships of many thousands of program elements. Uhe results axe presented as program summaries upon which the Director can base decisions. (See Pig. 6-3)
3he f i r s t step In using the PEP management tool i s to make a detailed analysis of the overall Lunex Program. Each major event, milestone, or accomplishment that must be achieved i s l i s t e d i n chronological order. 2he events must be ve i l defined and should occur at an instant of time union can be identified. A network, or "a program plan chart, i s laid, out in vhiclTtne events are shown as points or c irc les whose positions roughly represent their chronological order. Interrelationships between the events (c ircles)
6.8 WDLAR-S-458
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. , * • : • - . •'--'~---:' '•". . - - ; .-=-s-.;v - - - . ' . - . 6 - i -
c and sequence of events are Bbow by connecting lines. The line between the events represents work that must be done to proceed from one event to the next (See Figure 6-U). 5he computer then totals all of the expected activity times along every possible (in the thousands) route of the netvork from start to the end event. Die rep computer then examines the total times of the large number of paths in order to find the longest nhich ifi called the critical path. The critical path defines the sequence of events which vill require the greatest expected tine to accomplish the end event.
•3K effects 01 a delay for any particular milestone or event an the entire program or on any other event can be quickly and efficiently determined so that corrective action can be taken if required.
6.9 HDLAR-S-1*58
Tth cammant tonMlM infotMallea sHattim th* RtfftMl oafroa af tka ItalMd Statai wlthla tH innantna of HM lipionaf. Lam, rnl* II. U.S.C, tertian 793 and 7*4, Hm HtomHtlm ar iwrietla* ef vaidi in any manna, to an •noaHiariml panan Ii Biaklbirad by law.
*SJffi
7W
-V'-
mirv
PLANS
r ^ 1 I LUNAR i
EXPEDITION • I FACILITY |
LUNEX PROGRAM
DIRECTOR
PROGRAMMING
MANNED a CARGO PAY LOADS
EARTH LAUNCH COMPLEX
TECHNICAL INTEGRATION a SUPPORT
EARTH LAUNCH VEHICLE
COMMUNIS. . J N S B DATA HANDLING
RELIABILITY
LUNAR LANDING
a LAUNCH VEHICLE
GUIDANCE B FLIGHT CONTROL
c
fc
FIGURE 6-1 LUNEX P R O G R A M OFFICE
WDLAR-S-456
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" ? ^ r » ' ^ ^ ^ ^ ^ 7 - ^ S f t r ^ - ^ s ^ j j T f n — T a i i T * r '*v*j*»j^ii!iiu»jii"»jofcw«ii -••-
' ' " * "- - ~ - - 3 t j ^ - :L ' - " ""•• '.^'-\
vunrraoffifiL
I MATERIALS |
I
?* ATER1ALS l**;*
FACILITY DESIGN
AND CONSTRUCTION PROPULSION
CONSTRUCTION ION I
MANUFACTURING
GOVERNMENT AGENCY
CONTRACTOR
FIGURE 6 ^ PEP INFORMATION FLOW RATTERN
: , , r . : [ WDLAR-S-458
SECTION V H
MATERIEL SUPPORT
IHNAR EXPEDITION (U)
(LUNEX)
M WDLAB-S-1J58
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fjAMHffiT''"'" .\','. A—-J-S*'-*: .• RECORD OF CHANGES
CHANGE NO.
: IESCRIPTIOH OF CHANGS 21AIS OF CHANGS REFERENCE 1 0 BASIS
PART
,->
; * • • ;
7-2 WDLAR-S-1*58
• - * • £ *
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«**'.w-i - * * * .
nnsx
TITLE PAGE 7 .1
RECORD OF CHABGES 7 .2
INDEX 7- 3
7.0 INTRODUCTION • 7^5
7 . 1 SUPPLY 7-5
7.2 DISTRIBUTION 7-7
7 .3 STORAGE 7-7
7.U REAL PROPERTY INSTALLED EQUIPMENT (RPIE) 7-8
7-5 MAINTENANCE \ 7-8
7 .6 MAHUFACTORIN3 FACILITY CRITERIA. 7-8
•Cfl.VriDHffilk
7.3 ^WDLAR-S-^58
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l*J* , . ! . . . - . " - • • • ••
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WDIAR-S-1»56
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7- MATERIEL SUPPORT
7.0 IHTflODUCTION
It is intended that this program use two significant concepts that will result in better management of the materiel support program. These are the Delayed Procurement Concept and the Responsive Production Concept. Under tiie Delayed Procurement Concept, the ordering and delivery of high-cost insurance-type spares is deferred until the final production run must be made, allowing for the accumulation of maximum operational experience with the new item before a final spares order must be placed. Under the Responsive Production Concept, a portion of the requirement for high-cost operational spares Is procured In unfabricated, unassembled form. When the spares demand can be more reliably predicted, based on actual usage experience, additional complete spare items can be produced within a very short lead-time period. When experience fails to justify a requirement for additional complete spares, the materiels and parts involved can be utilized In end article production. The policy shall be to buy minimum quantities of high-value spares and maintain close control over their transportation, storage, issuance, and repair until they finally wear out, or are no longer required. Simplification of procedures and relaxing of restrictions on low-value items will provide the means (man-power, machine time, etc.) for more precise management of high-value items.
7-1 SUPPLY
Maximum utilization will be made of existing assets. Where practical, equipment and parts will be reclaimed from completed test programs, repaired, modified and overhauled to suitable condition for use in later tests and operational tasks. The procedures and paperwork Involved with procurement of spare parts must be streamlined to permit maximum flexibility in planning and responding to a continually changing configuration^ Immediate adjustment or inventories and reorder points must result from test program and engineering changes. Selection of spare parts should be made at the time of initial design to enable procurement of spare and production parts concurrently to eliminate reorder costs resulting from separate procurements.
7-5 -VDLAB-S-l^B
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"Stal^
Determination of quantities, reparable-cverhaulHBodiflca-tlon planning, control etc., shall be accomplished and directed by a permanently organized and active groin) composed of personnel representing the engineering, production, materiel, reliability, quality control, procurement and contract departments, and the
mm various affected sections within these departments such as , design, test, planners, etc., attending as required. Die A U K
vlll have a member assigned to this group for surveillance i\i purposes and to provide logistic guidance on problems which may __ require advice from the Air Force.
Persons assigned to the group shall be veil qualified by - reason of experience and technical ability.
Ihe procedures and paperwork involved shall be streamlined, taking due cognizance of the powers and capabilities of the
- :; above group to permit maximum flexibility in planning and the ~*~ quickest possible response to changes and emergency situations.
J^ Ihe group will pay particular attention to control of hi-value items and Items critical to the needs of the expedition and test program. Such items, particularly those potentially subject to imminent redesign, will be rigorously screened to assure economical Inventory and the best possible repair, overhaul and modificai v.on planning at all times.
She group shall be responsible for the following:
a. Immediate adjustment of inventories and reorder points resulting from changes to the delivery schedule, the test program, and for engineering changes.
b. Inventory review and adjustment of initially established stock levels and/or reorder points in light of latest experience gained from the test program every time reorder or minimum stock levels are reached.
c. Review of stock levels, and adjustment and/or disposition of non-moving Items on a continuing basis, but at intervals not to exceed sixty (6*0) days for any individual hi-TftlUe i t ems and 180 d a y s f o r otft™* j **>!«, w «••*-. n t V r Intmrmla.
"as agreed upon by the Contractor and the Contracting Officer. Shis i s t o Include the return to production of axqr surplus quantities for^jework t o later design requirements.
VDUR-&-k5Q
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d. Control of repalr-overhaul-modlfication planning.
7 - 2 DE5THIBUTI0B
The Contractors shall develop Internal working procedures vhlch encompass the following requirements;
a. Inventory levels snail be programmed to vary with anticipated utilization. Shipments In advance of estimated requirements will not be made except when it is clearly In the best Interest of the program to do so.
b. Stock levels shall be minimized by maximum economical reliance on repair, overhaul, and modification of reparable items. Repair, overhaul, and modification turnaround time will be a prime determinant in establishing the minimum stock-level period for each Item.
c. Where feasible (vlth particular emphasis on hl-value and critical Items), inventory cost will he minimized by stockage of repair, overhaul and modification bits, pieces and components (relatively low-cost items) In conjunction with a pre-planned and flexible expedited repair, overhaul, and modification program, as opposed to stocking sub-assemblies and end items themselves "(the relatively high-cost items).
d. Stock levels will be determined on basis of overall program needs and will be independent of the site location of the stock. Maximum utilization will be made of available contracted air transportation to minimize "pipeline" time.
7.3 STORAGE
Farts whether required for the test or expedition programs should not be segregated from production stock. This merely adds an unnecessary stockage' cost-burden. By combining storage facilities with a co-mingling of stock, considerable cost savings can be effected. Spares and production stock serve as buffer stocks for each other. If multiple activities such as Tnanufaeturing, test, and tne expedition are supplied from a single storage facility the chance of stockout would be
7*7
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minimized •
7 .k REAL PROPERTY INSTALLED EQUIPMENT (RPTE)
Each contractor Is charged vith the responsibility of identifying, as veil as determining the criteria for all items required for successful mission accomplishment. When the requirements have been determined the responsibility for accomplishing the required HPIE materiel support program vill be assigned. This materiel support vill include the necessary selection of spare parts to be stored at the manufacturing facility or at the launch site.
7-5 MAINTENANCE
The proposed operational mode of the ItfREX program is unique in that it retains all the features of a research and development program. In the time period designated as "expedition", it can be expected that in addition to a variety of missions the systems vill be modified and improved.,, the launch facilities and support equipment may require modification, and technical development may force program changes. Since the expedition period Is actually a continuation of the development and test program it is apparent t&at the systems and techniques developed during testing may also be continued for the Expedition.
An evaluation vill be made to determine the feasibility of having contractors support the program throughout its entire life. However, in determining the total task, consideration must be given to the available Air force manpower, equipment and facilities that may be used to support the LUNEX program.
7 .6 MANU7ACTORING PAClLITr CRITERIA
The equipment production facilities vill preferably consist of an existing large aerospace plant convertible to LUMEX production vith a minimum modification program. It nay be necessary to find a facility that is adjacent to, or easily accessable to navigable waterways. The facility should obviously be located in an area containing an abundance of skilled manpower.
: *.--.-
Manufacturing Test faci l i t ies adjacent to the manufacturing facil i t ies would be very desirable to reduce transportation problem.
TOLAR-S-lf58
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Certain Items, such as the large liquid and solid boosters and propellant, will probably be assembled at the Lunex launch Complex and special facilities for manufacturing these items will be required at the launch complex. Thus checkout and acceptance test facilities vill also be required at the launch complex.
Many major manufacturing items, such as the Lunar Landing Stage and the Lunar launch Stage, will be produced at the manufacturers' facility. This will require propellant storage, or a propellant manufacturing capability at the plant, plus various test and check out facilities to support manufacturing.
As an example, the following test facilities will be required to support the manufacturing of the Lunar Landing and lunar Launching Stages:
a- Configuration—Far each of the two stages a Propulsion Test Vehicle Test Stand and two Flight Acceptance Firing Stands will be required. In addition, cold flow-test facilities conslstelng of one pad and three structural towers will be required.
Two separate test complexes will >? .needed - one for each of the two stages. There will be only one centrally located blockhouse with control and instrumentation capability for operating both complexes. Each hot firing stand would be located in accordance with a 2 psi explosion overpressure criteria. An explosive force calculated on equivalent LHp caloric content to TKT, shows that the hot stands should be no closer than 2000* to any other hot or cold stand.
b. Test Pad Configuration and arrangement — Each hot test pad will consist of a concrete pad containing the launcher structure. The stage is erected by a mobile eonmeVcial type crane, and personnel access for maintenance is by work stand and ladders, or a cherry picker. Ho service tower will be required.
c. Thrust Level Measurement - - Thrust l e v e l s w i l l be detcrmined-by measuring the chamber pressure and applying •Hie result to the engine manufacturer's calibration curve. Tanking level Is determined by the Propellant Utilization System.
7.9 WBLAfc-8-458
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HJIEX
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TITLE PAGE
RECORD OF CHANGES
IKDEX
8.0 nnRonjcnoN
8 . 1 LUNAR LAUNCH COMPLEX
8.2 LOGISTICS
8.3 AEROSPACE GROUND EKVIBOHMEBT
8 . 1
8.3
8.5
8.6
8.7
8-7
-J&3,
8.3 WDIAR-SA58
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d. Altitude Simulation Unit - - A plenum chamber, containing steam jets up stream of its exhaust bell, shall be attached to each engine for altitude simulation.
e. flame Deflector - - The design is a conventional configuration elbow shaped, shield cooled with a firex water injection system.
f. Propellent Storage and Handling Equipment - - A central LOg storage and transfer facility shall be provided for each of the two test facilities. The Lunar Landing Stage facility shall store 350,000 lbs. of LQa- Spherical, vacuum Insulated devars shall be used. Ihe transfer unit shall be a motor operated centrifugal pump vith 500 gpm and 100 psi discharge head capacity. Die lunar launch Stage Vest facility LCU storage shall contain 18,000 gallons in spherical devars vith a transfer pump capability of 200 gpm and 100 psi discbarge head. Distribution lines for both complexes would be prefabricated, static vacuum, insulated steel pipe.
An LHjj storage and transfer facility will be provided at each hot firing test stand and the cold flow test pad. One transfer system Is an LHg gas generator system vith air being the thermal source. Pressuring level in each tank would be 100_ psi. The LH 2 storage capacity requirement for each lunar Launch Stage facility is. 15,000 lbs. and at each Landing Stage Site is 35#000 lbs. Again the storage facilities would be spherical devars vith segmented, prefabricated, static vacuum insulated stainless steel pipe distribution lines.
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8.4 WDIAR-S-U58
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8. ' CIVIL ENGHJEERIBG
8 .0 nnBOKJcnoN :
As part of the Lunar Transport Vehicle study, consideration vas given to the facilities required for the launch and support of the Space Launching System and the Lunar Bayloads. It vas assumed that the manufacture of all boosters and the payload vould be accomplished at existing factories, facilities and equipment required for the manufacture of large boosters may be readily Installed at factories having clearance sufficient to handle the booster. Large boosters such as required for this prograis must necessarily be transported over long distances by specially constructed barges, By selecting manufacturing facilities and launch sites adjacent to navigable waters, a minimum of overland transport vould be required. A significant savings may be effected by providing launch capabilities at selective areas where existing support facilities, personnel housing, and assured tracking capabilities are available.
The logistic support for the launch rates indicated in this plan dictates that new propel! ant manufacturing facilities be constructed at the launch site and that transport barges and other vehicles be available to 'transport vehicle components from the manufacturing plants.
A modified Integrated Transfer Launch System is envisioned for the Lunar Transport Launch System. The size and weight of the Space Launching Vehicle, designated the BC2720, precludes the transfer of the entire Lunar Transport Vehicle after assembly, but the Integrated transfer of upper stages and lower stages separately with a minimum mating and checkout on the launch pad may provide increased reliability and appreciable cost savingt
In order to achieve the highest launch pad utilization possible and to make maximum use of specialized capital equipment and highly skilled manpower, the application of operations research technology will be required. To handle the test load and the complex sequencing requirements presented by the three-stage Space launching Vehicle plus the Lunar Payload, a computer controlled, integrated launch sequencing and checkout system will be needed. It 1B desirable to accomplish the maximum amount of systems testing In a protected environment prior .-to locating the vehicle on the launch pad, and to use the launch pad, in so far as Is possible, for its prime purpose, that of preflight servicing and launching the vehicle.
8 .5 ^WDLAR-S-fcsa
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8.1 LUHAR LAUNCH COMPLEX
The Lunar Transport Vehicle System has a requirement for launch and support facilities suitable for maimed lunar flight of a vehicle using a BC 2720 Space Launching System. Investigation of the launch pad requirements for a launch rate of two per month indicates that from k to 6 launch pads vould be necessary depending on the launch site location and the means available for handling the booster- There are no existing launch pads capable of handling this vehicle, nor are there, at this time, facilities capable of conducting static testing of the "C" booster and the launch of the complete Lunar Transport Vehicle. It is possible that by combining the capabilities for both static firing and launch in two of the pads required, a significant coat saving may be gained and an accelerated test program may be effected. This vould provide a capability for the launch of the "C" booster with or without solid boost during R&D flight test and for early test missions of the Lunex Re-entry Vehicle- The development and flight test of the "B" booster is planned at AMR during the development program.
It was assumed in the Lunar Transport Vehicle study that the manufacture of all boosters and the payload vould be accomplished at existing factories. New and added facilities and equipment such as large forming brakes, special welding Jigs, fixtures and machines, and large processing facilities vould be required. In plants of sufficient size these facilities and equipment could reau-ly be installed. Further Investigation comparing the relative economics of manufacture at the launch site versus manufacture at existing facilities is required to insure an economical choice.
Assemblies having a diameter exceeding 12 feet or veighing over 200,000 pounds cannot be transported over United States railways. A load of 78,000 pounds is considered to be the limit over selected highway routes. In as much as both the "B" and "C" boosters of the Space Launch Systems have diameters In excess of Ik feet, transport from manufacturing plant to the launch site must be by barge. The large quantities of boosters and the special environmental protection required suggest that specially designed barges be constructed to transport these assemblies. Harbors and docking facilities vould be required near the manufacturing facility and at the launch Bite.
By locating the launch facilities at or near Cape Canaveral for an easterly launch significant savings may be
8.6 WELAR-S-458
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effected. The use of existing administrative capabilities, personnel housing, assured tracking facilities, and technical support areas will provide a saving In costs and in leadtime required for construction of support facilities. Similar gains Bay he made hy locating launch facilities at Point Arguello for polar launch- This does not mean that Cape Canaveral and Point Arguello are the only reasonable locations for the launch site. In fact, by extending the Atlantic Missile Range in a westerly direction across the Gulf of Mexico it is conceivable that a launch site in the vicinity of the Corpus Christ! Naval Air Complex would provide the full use of AMR Range facilities with minimum overfly of foreign land masses. Likewise, extension of the AMR Range In a northerly direction to the coast of South Carolina would provide a similar accommodation.
8.2 LOGISTICS
The logistic support for the launch rates indicated in this study dictates that new propellant manufacturing plants he constructed at the launch site. Existing propellant manufacturing plants are inadequate and the launch rates mentioned would use the full capacity of a separate propellant manufacturing facility.
a. Propellant use rates for a 2 per month launch rate are estimated as follows:
(1) Liquid Hydrogen manufacture 50 tons per day.
(2) Liquid Hydrogen storage . @ launch pad 1-5x10° pounds.
(3) Liquid Oxygen/Nitrogen Manufacture 120 tons per day.
{k) Liquid Oxygen storage -@ launch pad U x 10° pounds.
Barges will he required for transport of boosters from the manufacturing plant to the launch complex-
8.3 AEROSPACE GRQUHD ENVIRONMENT
A modified Integrated-Transfer-Launch System is envisioned for the Lunar Transport launch System. This approach would allow the complete integration and checkout of the "B" booster together with the lunar Transport Payload in a protected
8.7 TOLAR-S-lt58
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environment simultaneously with the assembly and checkout of the C2720 booster combination at the launch pad. The else and weight of the BC2720 Space Launching Vehicle precludes the transfer of the completely assembled Lunar Transport Vehicle from an integration building to the launch pad. It Is feasible^ however, to mate and Integrate the "B" booster with the lunar Transport Payload Inside the protected environs of an Integration building and vhen completed transfer the "B" booster and payload assembly to the launch pad for mating with the C2720 assembly. (See Figures 8-1 and 8-2). This can best be accomplished by a ellffslde location or extending a ramp from the integration building to an elevation at the launch pad approximately equal to the height of the C2720 stage. The assembly and checkout of -the nC2720n vehicle may be accomplished in two vays depending on the specific location of the launch pad and its accessibility to navigable waters. For a launch pad having no direct access to navigable waters, the assembly and mating of the solid segmented motors to the "CM booster would be accomplished at the launch pad. The extended time necessary to accomplish this assembly and checkout accounts for the difference in the numbers of pads required. It is estimated that 6 launch pads would be needed for this plan. For a launch pad having direct access to navigable waters,- the assembly and mating of the solid segmented motors to the "C" booster could be accomplished at an interim integration building located some distance away from the launch pad. After assembly and checkout, the "C2720" combination would be transported by a barge to the launch pad and mated to the "B" booster and payload assembly. By using this approach it Is estimated that k launch pads would be adequate for the 2 per month launch rate. Final confidence checks and Integration of the booster and facility interface would be accomplished at the launch pad.
The TNT equivalent of vehicle propellents was estimated in the following manner. The THT equivalent of the liquid propellents was taken at 60$ of the total LOX/lSjj load for all stages. This is the figure currently used at AMR for TNT equivalence for LOX/lflg. In this case, because of "the great quantities of propellant Involved, this degree of mixing Is unlikely and the 6o# figure would be conservative. Solid prppellants are taken at 100$ of the propellant velght. It Is also considered that detonation of the solid propellants may cause the subsequent detonation of liquid propellants and vice versa; but, the simultaneous detonation of all propellants
WDLAR-S-U58
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e 1E not likely to occur. Skis philosophy resolves to consideration of THT equivalents of liquid propellants and solid propellants separately and they are not additive. Ihe THT equivalent of one of the four segmented solid assemblies is 680,000 pounds. The 60$ TNT equivalent of the total liquid propellant load 1B approximately 1,300,000 pounds. Using the highest TNT equivalent (1,300,000 pounds) the inhabited building distance must be approximately 2| miles from the launch pad and minimum pad separation must be approximately 1 mile. For an inhabited pad adjacent to a launch operation, pad separation would be Q§ miles. It Is obvious that the real estate problem will be extensive. For a coastal location of "C" launch pads up to 18 miles of continuous coast line would be required, for a distance of 3 miles inland. 3hese distances can be decreased by creating a buffer between the pads. Locating the launch pads in ravines or indentations In cliff side launch locations might substantially reduce the land areas required. The selective location and orientation of the Integration building and other support facilities to take best advantage of topography would do much to decrease distances and reduce costs.
Hie repeated launching of similar payloads in the lunar Transport Launching System and the extended time between launches from each pad indicates that a central launch control for all pads might tt desirable• To avoid analog signal- line driving problems and to allow greater distances than normal between the pads and the common blockhouse it is possible to use digital control for launch pad checkout and launch. Analog to digital conversion would essentially be accomplished at each launch pad and transmitted to the blockhouse via digital data link. With vertical mating, assembly and detailed checkout In the vertical assembly integration buildings, only gross, survey type testing or a simulated countdown and launch would be performed at the launch pad, since test and vehicle subsystem sequencing systems could be Installed in both areas. Present day checkout methods, because of the many manual controls and long-time spans involved would not provide sufficient assurance of the high reliability of the complex Integrated systems expected In the Lunar Transport Vehicle.
8.9 WDDAR-S-U58
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SECTION IX
PERSONNEL AND ORAIRING
LUTJAR EXPEDITION (U)
(UWEX)
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RECORD OF CHANGES .
CHANGE NO.
IESCRIPTIOH OF CHARGE DAUB OF CHANGE REFERENCE TO BASIC
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TITLE PAGE • * 9 . 1
RECORD OF CHARGES 9.2
INDEX , , 9.3
9.0 HJTROEUCTION , , . „ 9.5
9-1 PERSOHHEL , , 9.5
9.2 TRAINING PROGRAM 9.6
9.3 PLANNING FACTCBS AMD GROUND RULES , $.f
9.k TRAINING 9-10
9.5 TRAINING PERSONNEL , 9-H
9.6 TRAINING EQUIPMENT PACKAGE , 9 . 1 1
9-7 FACILITIES , 9-1^
9.8 HJDGET AND FINANCE 9 - 1 5
ATTACHMENT
IX - A PROJECTED MANNING AFSC'S , , , 9-l6
IX - B EUNEX/SPACE LAUNCHING SYSTEM , 9 , 2 0
IX - C RE-ENTRY VESICLE
IX - D LUNAR LANDING STAGE
IX - E' LUNAR LAUNCH STAGE AND CARGO PAYLOAD PACKAGE
K - F INTEGRATED SYSTEMS -
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9-3 WDLAR-E-U58
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9 . PERSQHHEL AND HtAHttJB
9.0 IHBTOEUCTOQH
Oils section of the Lunar Expedition Program Plan (Lunex) Includes estimated personnel requirements to support the program and presents the training required to Accomplish the end objective.
The personnel requirements were derived on the basis of the scope of the complete program and the personnel would be comprised of civilian and military personnel-
The training program was prepared by the Air Training Command and based on the Lunar Expedition Program Plan.
9.1 PERSOHHEL
The accomplishment of the Lunar Expedition Program vill have a manpower Impact on the Air Force that is quite different than previous programs. The number of personnel actually on the expedition will be relatively small compared to the number of personnel required to support the operation. The actual contractor "in-plant" personnel required to accomplish this program are not Included in the following figures. However, a general estimate of the total contractors' effort, based on the average estimated annual expenditure for the complete Lunex program, would be the equivalent of one of our larger manufacturing companies with 60 to 70 thousand personnel. It should also be stated that this effort would undoubtedly be spread throughout the Industry and not concentrated in one company and the previous statement is only for comparison.
The military and civilian personnel required to support the lunex program is estimated as follows:
Space Personnel 1^5
Lunar Expedition 1^5 • (21 men at expedition facility, crew rates of 5)
Ground Personnel 3677
lunar Squadron 100 launch Squadron 873 Instrumentation S q u a d r o n 2 9 X Assembly & Maintenance Squadron 660 Supply Squadron 562 Bane Support Units 639
Administration 350
9 . 5 WDLAR-S-U58 Orhhr-r U.UJUJ*» ' ' -A-.^-yi
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; £.*. te^Ltj^r&& Personnel *(Space plus Ground)
Overhead 1£87
Range Tracking 9I4O Logistic Support Organization 3kf
Grand Total Personnel 5109
9-2 TRAINING PROGRAM
The remaining portion of this section of the lunar Expedition Program Flan (lunex) presents the Training Program. It is based on the limited data and information available at the time of preparation. The knowledge gained from the state-of-the art development of tbis program vlll of necessity have to be applied directly to the training areas to insure "concurrency" of the programs training development. lurther, the training knowledge and experience acquired from current research and development programs must be studied for application to this program.
The concepts and plans projected in this part of the PSPP will be subject to constant revision and/or updating. Use of various simulators and synthetic training devices must be a part of the training program. Identification of the required ' twining equipment and real property facilities to house them must be accomplished early in the program development to Insure training equipment and facilities being available to meet the training need dates-
The unique mission of the Lunex program requires a comprehensive and timely source of personnel equipment data (FED). Tais information is required for space crew and support positions required to operate and maintain the space vehicles and support equipment. Development of such data must be initiated as part of the design effort to reduce the time element for follow-on personnel sub-system requirements.
Ho effort is made in this section to specify requirements for the Space Launching System since they are delineated in the Space Launching System Package Program.
This section of the Proposed System Package Program was developed under the premise that Air Training Command would be assigned the individual aerospace crew and technical training responsibilities for this program- Therefore, ATC must develop their* capability concurrent with hardware development through the engineering design phases to support the expedition.
' 9 . 6 WDLAB-S-^58
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C6KUPIUUU* 9.3 PUNNING FACTORS AND GROUND RUI£S
a. Scope;
Ibis section is conceptual In nature at thiB time and embodies the basis for the training to be accomplished in support of the lunar Expedition Program. It includes guidance for individual, field, unit and crew training.
b- Definitions:
(1) Aerospace Crey Personnel:
Personnel performing crev duty in the lunar Transport Vehicle.
(2) Cadre Personnel :
Those personnel necessary for logistic planning, AH? 80-lU Testing Programs, and ATC instruction and preparation of training materials. The requirements for participation In the testing programs will include test instruments for category testing in accordance vith paragraph 5 & (l) and (2), APR GO-Xk, end Job Training Standards for the Integrated Systems Testing Program in accordance with paragraph 8 g (3)> AIR 80-1^.
(3) Main Complement Personnel:
Personnel employed in the receipt , check-out, Ins ta l la t ion , repair , maintenance and operation of the system.
(10 Support Personnel:
Air Force Logistic Command personnel required for support functions as v e i l as other agencies' supervisors and planners 1
(5) Types of Training:
(a) Type I (Contract Special Training) • Special t raining courses conducted by contractors a t an ATC ins ta l l a t ion , contractor f ac i l i t y or any other designated s i t e .
(b) Type I I . (ATC Special Training) Special T r a i n i n g Cffflrfiftfi flOT?ifll)EtPfl b y ATC t r a i n i n g RffTrhwrs* Ing-h-HifftwH a t an ATC ins ta l la t ion , contractor f a c i l i t y , or any other designated s i t e .
(c) Type H I . Career t ra in ing . toTwnrMTIBi
9.7 . HDLAR-S-458
' • • • . ; « '
'~*3!-.,..,..•-..... ;X*) ^ype IV. Special training provided by ATC training detachment Instructors at the Bite of the organization requiring the training.
(6) TeBtlnq Programs:
(a) Component - the testing of the components of a sub-system, such as the guidance package, or ecological package.
(b) Subsystem - components assembled Into a subsystem as the Re-Entry Vehicle Subsystem and tested as a unit.
(c) Integrated System - the Re-Entry Vehicle, lunar Launching Stage and lunar landing Stage assembled together and tested as a whole system.
c. Assumptions:
(1) Die man-rated lunar transport Vehicle vlll be available for use by the lunar Expedition In I968.
(2) ATC personnel -will observe, participate and study the training programs developed for current research and development programs conducted under other government agencies and/or contractors. x
(3) AJH 80-lU vill be used at a guide for accomplishing the program testing.
(k) The terminology for normal levels of maintenance, i.e., organizational., field, depot, and shop, vehicle assembly and maintenance as specified in AFW (AMC) letter MM, dated 25 July i960, subject: Standard Maintenance Terms and Maintenance Facility nomenclature for Missile Weapon Systems frill apply.
(5) The Air Force Maintenance policy of maximum maintenance at the lowest feasible level vlll prevail.
(6) Sue to the time phasing of the subsystems, special consideration must be given to the training facilities requirements funding for the Re-Entry Vehicle technical training programs^
(7) Testing Pates:
->-. . »>>~*^&) Start of Component Testing Dates are:
t He-Entry Vehicle - June 1963-
^2. lunar launch Stage -February 1965-
9 3 ^ ' *" WDLAR-Swfc58
oHId
2- Lunar lending Stage - Wr.y I965.
(b) Start of Subsystem Testing Dates Are:
1. Re-Entry Vehicle - November 196k.
2. Lunar launch Stage - May 1966.
3. Lunar landing Stage - July 1966.
d. Peculiar Requirements and/or Limitations:
(1) The unique mission of this progrom mrOtes it mbnde-tory that the following actions he accomplished concurrent vith the development of the hardware:
(a) The contractors vlll develop the Personnel-Equipment Data information concurrent vith the design of the hardware. This information must be available to ATC personnel for early planning purposes.
(b) Type I training dates reflected in the time phasing chart viU require the use of R&D and test equipment as training equipment.
(c) Production schedules for R&D and Expedition equipment vill include the training equipment required to support Type II and. Type III training. Allocation and delivery priorities vill be in accordance vith AFB 67-8.
(2) An identification of personnel necessary to support this system has been made in order to assist in defining the training parameters* Changes to these estimates vill be made as more conclusive information becomes available. See Charts IX A and B.
(3) Jfaximum Cross-Training vill be provided es required to all personnel associated Vith this program.
(k) The requirement for follow-on training and "Uie value of past experience is recognized and maximum retention of personnel is mandatory.
(5) Hew and peculiar training problems are envisioned for the-tecfanical personnel.
(6) -The training of the aerospace crew personnel vlll require the development of a program which is unique to the Air Force.
9.9 WDLAR-S-U58
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•
e. Qualitative and Quantitative Personnel Requirements Information
(1) A QQPRI prepared in accordance with Mil Spec 26239A vlll be required to develop the training courses, course material and substantiation for the Personnel Classification changes.
(2) ATC and other applicable commands vlll furnish personnel for the ftQPRI integration team and provide technical guidance to the contractor during preparation.
0.4 TRAINIIJQ
a. Training Responsibilities and Concepts:
(l) Engineering Design Effort
(a) ATC vlll participate in the engineering design effort to insure that technical data is collated vith , the personnel sub-system for follow-on training program requirements.
(b) ATC will be responsible for training required in support, of the R&D effort under AER 50-9-
(c) Selection of the initial aerospace crew personnel and ATT .erospace crew training Instructors for the lunar Transport Vehicle will commence 8 months prior to the . start of Category I Testing-
(d) All lunar Transport Vehicle crews and military space launching support personnel will be phased into special training (Type i), 6 months prior to Category I Testing.
(e) Environmental space training for the selected crews and instructor personnel will start 9 months prior to the start of Category II testing and will be conducted by tile Aerospace Medical Center, Brooks AFB, Texas.
(f) ATC Lunar Transport Vehicle crews will be phased out of training 30 days prior to the requirement for Type XI or III aerospace crew training to provide follow-on training capability in this area.
(2) flight Testing & Expedition Program:
(a) ATC will be responsible for all individual training, i.e., technical, aerospace crev, AGE and additional job tasks as required..
^p'nF
c ttCDEL . * * * .
« * *
(b) All requirements for Type I Special Training, APR 50-9, In Bupport of this effort will be contracted, for by ATC.
(c) ATC will maintain liaison with the contractor concerning engineering changes in the program during its develop* ment to keep training information in coneonance vita the program sub-program configurations and other concepts having a direct implication, to training.
(d) flight Testing & Expedition Crew proficiency will be the responsibility of the Lunex Program Director unless ATC is requested to furnish this training.
9-5 TRAINIHC PERSONNEL
a- Field Training Detachment (FTD)
The number of personnel required to provide training for lunar vehicle personnel will be determined during Hha training programming conference. QQFRI, TBI's, Personnel Plan, Operational Plan and Maintenance Plan will be available at this time-
b. Contractor Technical Service Personnel (AFR 66-18)
Contractor technical service personnel may be initially required to augment Field Training Detachment (FTD) personnel. CTSP requirements in support of this program will be phased out as blue suit capability is achieved.
c . Trained Personnel Requirements (TPR)
TPR will be developed by commands concerned upon approval of QQPRI, and will be tabulated as gross requirements by command, by AFSC and by fiscal quarter. These requirements will be phased on anticipated need dates for personnel to be in place at the testing sites, launch sites, and maintenance areas, and will be furnished Hq. ATC in sufficient time to allow proper planning for required training.
9.6 TAMHUVG EQUIPMENT PACKAGE
a. General;
Training equipment requirements will be developed to support:
( l ) Check-out and ground maintenance to be performed by the direct support personnel for the Lunar Transport Vehicle.
9.11 TOLAR-S-U58
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(2) flight test operations and maintenance to be performed by the responsible crews. In consideration of this, present and near future systems experience gained in the aerospace area vill be applied to the Lunex program to assist in the identification of training equipment. She training for this program must be conducted in the most realistic environment practicable.
(3) Post mission maintenance and test equipment.
b. Equipment Selection:
Selection of training equipment will be based on the following general rules:
(1) Maximum utilization will be made of training equipment programmed for other missile and space system training programs.
(2) During the initial phases, equipment programmed for test, development, and the expedition programs will be used to the maximum extent practicable when regular training periods can positively be scheduled In the use of that equipment. The lack of availability of such equipment will result in degradation of training.
(3) Equipment selection will be made in consideration of future and/or subsequent programs to provide maximum training capability in similar systems with m-<"•*"•""• cost,
(k) Maximum use and development of training films, training graphics, and synthetic training aids, and devices will be made to reduce requirements for critical operational items during the Initial phases of the program.
(5) Training equipment will be identified in sufficient time to enable procurement and delivery In advance of equipment for use in the flight test and expedition program.
c. Harming lactors:
Planning factors for determination of Training Equipment Requirements:
presently available, definitive planning factors upon which over-all equipment requirements may be based cannot be provided. However, for preliminary planning, the following factors may be applied to subsystems of the program to determine order of
M 9.12 VDLAR-S-U58
A M M M
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magnitude. Provided Control Centers used for other space vehicles will be applicable to the Luna*- Transport Vehicle, category *I, **II, and ***III training equipment requirements as specified in USAF letter dated 30 January 1961. subject: Weapon System Training Equipment Support Policy will be as follows:
Major Vehicle Sections Per cent of Sub-System Cost Required for Training Items
(a) He-entry Vehicle 250#
1- Complete R/V - 1 ea
2. Sub-systems of R/V - 1 ea
^. Major components of each sub-system for Bench Items - 1 ea
(b) Lunar launch Stage 150^
1. Sub-systems of Launch Stage - 1 ea
2. 50# of Major Components "~ for Bench Items
(c) lunwr Landing Stage 100 6
Major Components - 1 ea
(d) Cargo Package 2JQ0#
Complete Cargo Package
(e) Aerospace Ground Equipment 200jt
1. Complete set for handling and testing vehicle sections and included equipment
2. Complete set as bench items _ _ . . for maintenance training * Cat I Trainers — - — — — ^ ** Cat II Barts/Components/End Items
*#* Cat III Training Aids/accessories
9.I3 WDLAR-S-^58
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e (2) Training films and transparencies requirements
will be developed as soon as possible.
(3) Spare parts support will be required for ell Category I and II training equipment.
(k) A continuing requirement vill exist for the modification of training equipment. These modifications should be provided by review and processing of training equipment change proposals concurrent with operational equipment change proposals.
(5) Funding of V-kOO money will be omitted in consonance with AFR 3X5-**, Para 12.
9-7 FACILITIES
a. General:
The needs for training facilities should be est= bllshed approximately three years prior to the d?,tes at which Type XI training equipment will be required. Facilities must incorporate sufficient flexibility to accommodate future updating of training equipment resulting from program configuration changes.
b. AeroBpace Crew Training Facilities: ^ ~
(1) Initial training for aerospace crew personnel will -require toe use of existing space training facilities. Joint-use agreements between NASA and other USA.F agencies and the Air Training Command will be required to insure maximum utilization of these facilities. Aerospace Medical Center1s facilities (Brooks AFB, Texas) -will be utilized to the fullest. Inter-service agreements with the Navy for use of specific training device facilities should be considered for crew training.
(2) The establishment of a centralized space training facility would have a direct bearing on the over-all specific requirements for this type of training. The results of the System Study Directive (SSD) Hr 7990-17610, titled: "Centralized Space TralniTy; nwr.-mty," win h»w iM-p-**. Tw^-Mug m t>>» posture of the training facilities of the future. For this reason, facilitarjeauirements for follow-on training are not
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c. Other Training f a c i l i t i e s :
. I t i s anticipated tha t technical Training Centers now inTexlstence can absorb the additional technical t ra in ing load
lout increasing the f a c i l i t i e s . However, modification of Lsting f a c i l i t i e s to provide t ra ining laboratories v i th jcialized pover and environmental systems t r i l l be necessary. [E requirement must be identif ied In sufficient time to permit
f ac i l i t y programming through normal procurement cycles.
9-fi HTOET ABB FUJAHCE
i a. Training Equipment Costs
Flmdlng v i l l be required for 'braining equipment ident i fied In Section 9.6, Training Equipment lackage.
b. Training facilities Costs
funding and costs of training facilities will be determined once the decision is made whether to build a Centralized Space Training Facility or to continue vith decentralized procedures. Funding can then be determined for the required facilities and modifications,
f
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Thil sofuntnt tMMlni informaHwi aHactlna n * lutianol daftm* of Hit UMNd wan wftfcin lt» naaaiag af Hw EtplMiaw L a n , TIIH IB. U:S,C., S«l!vi 793 and 7W, Hw fruminiiaiDfi e* nrwIallM mt wtrica iii any Mannar fo an HAOHlBariiad naru" It oraBtbftad ay lew-
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* Proposed «* Numbers are estimates for
Type I Training Cp.4re
CHART DC - A PROJECTED MAJTNnC AJSC'e
FOR ttJNAH TRAHSPORT VEHICIE PROGR
1 Major Segment * of System
* Vehicle Crev
vWtfL < • *
Vehicle Support
Cadre Requirement AFSC ABM 35-1 Title
PART A
1 (AP5C) 13XX *Aerospace n i g h t Test Pi lot
1 (ATC) 13XX Aeroape.ce Pi lot
1 (AFSC) 15XX *Aerospace Performance Engineer Se Bavlgator
1 CATC) 15XX
1 (AFSC) 3OXX *Aerospace Communications Electronics & Computer Specialist
1 (JOB) 3OJ0C
PARTB
**Z (AFSC) 30551/ Electronic Digital Data 71 Processing Repairman/
Maintenance Technician
1 (ATC)
9.16
1 »
r*
Major Segment of System
Cadre Requirement AFSC
Vehicle Support (Continued)
a (AFSC)
1 (A!K)
29373
^ a (AFSC) '12250/
70
2 (AFSC)
1 (ATC)
l»225l/ 71
-
2 (AFSC)
1 (ATC)
30151/ 71
1 (AFSC) 30150/ 70
1 (AFSC) 30153/ 73
1 (AFSC) U6250/ 70
fe >
AFM 35-I Title
Airbor-e Radio and Elect: .iic Counter-measure Operator Technician
Instrument Repairman/ Technician
Mechntfiical Accessories and Equipment Repairman/Technician
Aircraft Electronic Ife.vigf.tlon Equipment Hepaiman/lfalntenance Technician
Aircraft Radio Repair-man/ftolntenance Tech.
Aircrnft Electronic Counterme&&ures/ Maintenance Technician
Weapons Mechr\nlc/ Maintenance Supervisor
9.17
^ , -
System
Operat and r&
Vehicl
Ma Inte access
Mainta equipm
SHFj U
Repair Elint
Capsul loadin
Major Segment of System
Vehicle Support (Continued)
? w*#
Cadre Requirement AFSC
1 (AFSC)
1 (ATC)
2 (AFSC)
1 (ATC)
2 (AFSC)
1 (ATC)
2 (AFSC)
2 (AFSC)
1 (ATC)
2 (AFSC)
1 (ATC)
2 (AFSC)
56850/ 70
53^50/ 70
U2152/ 72
1*2353/ 73
31150/ 70
tfUM* ATM 35-1 T i t l e
Liquid fuel Systems feintenance Spec ia l i s t / Technician
Airframe Repsirman/ Technician
Aircraft end Missile Pneudrexilic Repsir-man/Technlcien
Flight Control/Auto P i lo t Systems Repe.Ir-man/Technicir>j3
Guidance Systems l>fechsnic/Technici>;n
31250 Control Systems Mechanic/ 70 Technicir-Ji
00370 /bor t System Vehicle Technician
System
Liquid Air systems.
Airframe in
Repeirs Hyd Systems.
Checks out pilot syste
Maintains e guidance sy detections equipment,
Maintains ? control sy
r-fcdnttins •;bort syst
Major Segment Cadre of System Requirement AFSC
Vehicle Support 2 (AFSC) (Continued)
^3351/ 71
1 (ATC)
2 (AFSC) 42350/ 70
1 (AFSC) "56650/ 70
1 (ASSC) 30152/ 72
1 (ATC)
2 (AFSC) 27250/ 70
1 (APSC) 30551/ 71
1 (ATC) •
Additional Specialist 62271
90150/ 70
58250/ 70
92250/ 70
1 * '•
AJM 35-1 ratafee;**
Missile Engine Mechanic/Technician
Aircraft and Missile Electrical Repairman/ Technician
Refrigeration Specialist/ Supervisor
Aircraft Early Warning Radar Maintenance Repair-man/Technician
Air Traffic Control Operator/Technician
Electronic Digital Data Processing Repairman Operator/Technician
Diet Supervisor
Aeromedical Specialist/ Technician
Fabric, Leather and Rubber Products Repairman/Repair Supervisor
Personal Equipment Specialist/Supervisor
»:&
Syst
Propulsio rockets.
Electrica
Maintain vent i la t i
Radar Dop Equipment
Operates precision
Insures p repair of
Supervis
Sub-prof physical
I. ••- '
'ft
ttr»*M*w
CHABT EC - B
LUHEX/SPACE LAUNCHING SYSTEM
1. lhe estimates for the launch system ere not included in view o
Launching System (SL5) study. It can, however, be estimated that
personnel utilized in both the liquid/solid propellant type booster
a team for support of this system.
2. At such time as the S.L.S. 1B designated as the primary launch
will be made for the launch vehicle Mid support AFSC's as a part o
9.20
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MOOKAM SCMBMM
RE-ENTRY VEHICLE CY 61 CY 6i
Chart IX-C 1ATC Input to PSPP
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4 ATC SPO Rep Appointed .yprlme Training Center Selected
j I SSP Prepared. Finalized I Contractor Selected n
j I PSS Data Contracted 1 u
f PEP Effort Starts M Training Facil i t ies Requirements
B II OQPRI Effort Starts (Components) g TEPI Effort Starts (Components)
u n Test Directive Coordinated H OQPRI Integration Team (Component) II OQPRI Review (Component) M Draft QQPRI Received (Components) » Prel im OQPRI Approved fComponents) II Draft TEPI Received (Components)
" i
N If Test Plan Prepared H M Training Parts Pre-provisioning
II Tyaitdtij P^gi-fTTi Conference II Training Program Requirements a Training Parts Provisioning H Crew Selection g Mock-Up and DEI M Tech.Spec! Tng (50-9) for Component Tes t p Test of Components M Type II Tng Effort Starts » Subsystem QQPRI Integrated M Subsystem TEPI Integrated II Subsystem QQPRI Approved B Subsystem TEPI Received M Subsystem Testing Begins 14 Evaluation of Tng Starts fiat. XL i.-i?
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n Training P r o g r a m Requirement a M Training P r o g r a m Conference M Training P a r t s Prov i s ion ing H Mock-Up and DEJ H Tech Spec ! Tng (50-9) Component Teat p Teat of Componenta a '^raining F a c i l i t i e s Requirements » oubayatem QQPRI Integrated
SubayBtem TEPI Integrated II Subavstem QQPRI Approved P Subavatem TEPI Rece ived H Type II Training Effort Starts H Sub By B tern Test ing Beg ins M Eval of Tng Starts
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CARGO PAYLGAD PACKAGE J J S J J
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n -L I .
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a n Training Facilities Requirements ll Training Program Conference H Training Parts Provisioning B Mock-Up and DEI M Tech Spec! Training (50-9) Component Test V Teat Component Starts M Subsystem QQPRI Integrated W Subsystem TEPI Integrated y Subsystem QQPRI Approved 31 Subsystem T E P | Received M Typg n Trig Effort Starts II Subsystem Testing Starts M Eval of Tng 1L
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Chart DC-F
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COMPUTt 6-30-61
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FACILITIES ft GSE S~\ FACILITY AND GS
COMPONENT EVALUATION OPROTO COMPONEtrt^N
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VSTRUCT. i 'S-ASSY. F
LUNAR SOFT LANDING AND RETURN
FLIGHT TESTING
RELIABILITT ASSESSMENT
DESIGN
% &
REVIEW
*?f FIGURE 6-4 PRELIMINARY
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ON-LAUNCHER
ASSEMBLY
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SECTION X
" :SS=7-
INT2TIJGENCE ESTIMATE
<&.*
LUHAS EXPEDITION (U)
(LUNSX)
SSSi*
,c 10 .1 TOWR-S^S*
Tali AuuiMtit (anistni infernal! M aflatting | | * nHianal dafanu al A* Unilwl Stotat within H M massing at Ma Eipianata Lawt, TlMa I I , U.S.C. Sadlon 783 and 794. * • hamnriiiisn ar nnlotlan af vhldi In any mnnnar la an unaaiketind pmnmK h erekibHad by • « • -
RECORD OP CHANGSS
CHANGE NO.
DESCRIPTION OF CHANCE DA1E OF CHAHOE REFERENCE TO BASIC
PARI
i t . . VDLAR-S-U58
* * V , Tkii BBCaawm (ealaim lahnaatla* offadlaa HM iatianal A n n * * af Iha UfiHad »ah» wHtita Hw nwrniiii af H M Eiplaaata law!, TUIa I I , U.J.C.. WrKw 7*3 and 7 M . laa rnaimlulen *r lavaletiaa af wkkh la ajfy,.i«ninar M an aaaaHiarivd panan ii oranlbltad a» lew.
• J * . -
INDEX
TITIE PAGE. 1 0 , 1
RECORD OP CHANGES * 1 0 * 2
INDEX 1 0-3
10-0 ijmiODUCTIOK 1 0 *5
1 0 . 1 FOREWORD 1 0 * 5
10.2 PERFORMANCE CAPABILITY . . . . . • • • 10-5
10-3 SUMMARY AND CONCLUSIONS 1 0 ' 6
10.3
'Vt
IM> dvcBHant «Motm lafanaNan aHactlng ttm H K I H I o a f m * • ' ln» UnlMd S m u wMiln th» • .onint •* the Eielsneta U w i , Till* I I . U.S-C. Section 7V3 and TV4, the hsnmiuioa •> wralet'HHi »F which In an<r monnni to AD HMMhsiIuri OWIM i l prali lUM by '<••>•
•T'Z •
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This page intentionally l e f t blank
Site1-
WDLAS-S-^56
» h I K I I I I M nfttatm tabrimHaa offxtlnt «W Ht iwn l d a l m * st Hw Ih i lM Stolw W M I B Ifc* Manias <f t t * Elpfenaaa 1 m , THto I I , U.S.C., SadlM 7*3 and 79*. Ifct hanuaiii lM ar mvataHaa af «kidi in any * m < i i r* an •uwflMtin^ nanail h sraklblM W low.
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c
10. INTELLIGENCE ESTIMATES
lo.o" INTRODUCTION
The purpose of this section of toe program plan is to estimate the foreign threat in terms of technical capabilities and probable programs which may affect the establishment of a lunar expedition. The threat vill he defined in terms of major performance capability and dates of operational availability.
10.1 FCREWCRD
The fo l lov ing da ta was obta ined from DCS/In te l l igence , Hq AKDC and published I n t e l l i g e n c e e s t i m a t e s .
10.2 PERFORMANCE CAPABILITY
The Soviets have flown geophysical and component'equipment payloads on the i r ver t ica l rockets for the development, modification, and acceptance t es t ing of instrumentation for use on the i r s a t e l l i t e and lunar a i r c r a f t . They developed and used complex sc ient i f ic instrumentation on Sputnik I I I , and s t a b i l i zation, orientation and control equipment on Lunik H I and Sputnik IV. Presently, by using t h e i r ve r t i ca l rockets, the Soviets are t es t ing infrared equipment, in addition to col lect ing data on the background noise level of the ea r t h ' s surface. I t i s believed tha t a development program exis t s -uhich eventually could lead t o detection and reconnaissance s a t e l l i t e s . The development program •which led to the photographic system used in Lunik I I I i s e;q«cted to continue, vith an eventual application in photographic reconnaissance and weather s a t e l l i t e s .
The Soviet space launch capabil i ty i s shown i n the following table of Sputnik end Lunik booster th rus t l eve l s :
Sputnik I 300,000 pounds
Sputnik I I 300,000 pounds
Sputnik I I I • 432*000 pounds
Lunik I , I I , and I I I 456>000 pounds
Lunik IV, V, and VI 466,600 pounds
There i s also evidence of a c lus ter of f ive 140,000 pound un i t s . The Soviets are developing engines of 1 t o 2 j mil l ion
10.5 WKLAR-s-458
Tkh aocnwat cMHahn k ihnMlH i a f t e t W t t * H t t n o l M « K of H» UniMd SMIn wMIn Urn M a i l s * at * a E i » : « m * U w i . TM* l i , U.S.C., Sartlon 793 and T M , I t * •nmniuion m m a t a t M af tnMia In any • • • • • ' ta •» ••aalfcialjaJ * » ' ! • • b •MftlbBrt fcr • * .
pound t h r u s t . The es t imated t i n e fo r a boos ter t o mctch t h i s I engine i s as fo l lows :
S ing le engine boos t e r - 1963
Clus te red engine boos t e r - 1965
In genera l , i t t a k e s approximately h a l f the time fo r development r equ i r ed i n t h e U.S .
The rn^yiimm Sovie t o r b i t c a p a b i l i t y , v i t h p resen t ICBM boos te r s us ing f i v e ( l4o,000 pound t h r u s t ) engines and four (6,600 pound t h r u s t ) engines i s 10,000 pounds i n low a l t i t u d e o r b i t . Al l Lunik and Sputnik v e h i c l e s u t i l i z e d a t h i r d s tage having 12,500 pound t h r u s t engine burning fo r approximately 420 seconds.
By us ing h igher energy chemical p rope l l en t s i n modified Upper s t ages , t h e payload can be increased up t o 15,000 or £0,OCO pounds during 1961 . However, approximately 50,000 pounds of payload may be a t t a i n e d by 1962 i f ICBM launch veh ic l e t h r u s t i s Increased .
In the 1965-1970 pe r iod , a new c lu s t e r ed chea ica l boos t e r should allow t h e Sovie ts t o p lace 5° to 100 tons i n o r b i t j n ind iv idua l l aunches . This u i l l permit lending a rsan on the upon. _
10 .3 SUMMARY ADD CONCLUSIONS
Very e a r l y t he Sov ie t s r e a l i z e d the propaganda value o b t a i n able from space adventures and, accord ingly , b-p.ve s t r i v e n cont inuous ly fo r " f i r s t s " . This has apparent ly inf luenced the d e t a i l e d p a t t e r n f o r t h e i r space p l ann ing . Even though the Soviets have achieved " f i r s t s " i n :
1 ) Establ ishment of an a r t i f i c i a l e a r t h s a t e l l i t e
2 ) Rocketing p a s t t he moon and p lac ing a veh i c l e i n t o a s o l a r o r b i t
3) Hard impact on t h e moon
k) Photographing t he s i d e of t h e moon no t v i s i b l e from the e a r t h _____
5) Safe ly r e t u r n i n g mammals and men from o r b i t
i t seems obvious t h a t t h e Sovie t a t t empts t o score " f i r s t s " w i l l cont inue .
• # • *
; " 10-6 * WDLAR-S-^56
Thii dotsmmf coM.au WibniuribA iffeclina the u i ioni l detenu of * « Unilcd Staiei within the meaning of Ihe Etpienege Lewi. Till*
IB. U.S.C., Section 793 Hid 744. the ujntmiuion or iival.iion of which in iny mennei to en i*i*uthorintt perion is prohibited by law.
^*^
Although large orbiting spacecraft appear to be the prime Soviet technical objective during the period of this estimate, it is believed they will continue to uBe and Improve their current lunar probe capability since there are many "firsts" yet to be accomplished in the exploration of the moon. These include lunar satellites, lunar soft landings, lunar soft landings and return •with actual samples of the lunar surface, and, finally, a tankette for a true lunar exploration.
It is expected that the Soviets will continue to launch iss:-;:s- unmanned lunar rocket probes for the purpose of reconnoitering ^ the moon and near moon environment for the application of this
knowledge to the development of manned lunar exploration systems.
Since soft landings are essential for obtaining data on the lunar surface, it is believed that the Soviets definitely will have to develop techniques for achieving lunar soft landings, especially soft landings and return to earth, to establish the procedures to
"'/,'_*' be employed in accomplishing the main objective of establishing a manned lunar station. The first of these test vehicles could be very similar to their Arctic automatic weather stations that presently are Jettisoned from aircraft. This vehicle would be able to record temperature, micro-meteorite impact, various types of radiation, particle concentration, seismic disturbances, solid resistivity, and depth of probe penetration. As landing techniques are improved, larger payloads with increased instrumentation for terminal control and lunar re-start ft-".d launch capabilities will undoubtedly be developed.
•IS;-*
c Circumlunar flights by manned space vehicles, and eventually
"7" lunar landings, will be required in order to know more precisely the environmental situation preliminary to the eventual establish-
•< ment of a lunar base and the complete conquest of this body. This j_.-_ is considered to be a more distant objective of the Soviet program
and its attainment w i n appear, if at all during this decade, toward the end of the period.
Although the landing of a "tankette" on the moon falls under the category of a soft landing, the size and weight of such a vehicle mates it a sufficiently worthy subject for special consideration.
—- The Soviets have published extensively on such a vehicle, and =*a Yu D. Kbelbtsvieh, Chairman of the Science Technical Committee for
Hadio Remote Control of Cosmic Rockets, has published his preliminary design of a lankette laboratory for lunar exploration. Graduate
c
students of Moscow High Technical School now are experimenting with models of a tankette in layers of powdered cement to simulate powdered soil conditions which might be expected on the moon.
WDLAR-S-^58
thi i dDcim>ent conta in* information jflecling Ihe najtonal tfefemj of (ha United 5 l * t « within tht meaning of *he Eicnonagc Law*. Till*
IS, LL5X*, Section 793 and 794, the trantmiHtan of revelation of which in any manner to en unautharfcied partem h prohibited by lew,
V
Actual accomplishment of the project will have to await the availability and flight testing of the new booster with thrust in the millions of pounds category in the 1965 time period.
The Soviets do not differentiate between military and non-military space systems. They have talked of a peaceful Intent of their space program but there are many pounds of payload in their eatellites ufaich cannot be accounted for on the basis of data given out. It should be presumed that this could be military payloads. With this in mind, it can be stated that during the early 1970'B it is possible that space weapon systems will be developed as a supplement to earth-based delivery systems- It is also possible that military facilities may have been established on or in orbit around the moon. Atmospheric and climatic conditions will demand an air conditioned environment for moon-based delivery systems. For increased survival security and decreased requirements for "imported" construction material, it seems reasonable to assume that these would be constructed under rather than above the moon's surface.
IDETifTiAL 10-8 WDIAR-S-U58
-ftvlt document cenraint Hifomation aflecting Hie national defend of Hie United Mam wilhin Hie meaning af the Espionage Law!. Title
18, U.5.C., Section 793 and 7*4, Hw lnmmi»lon or revelation of which in any manner to an unauthoiiied pcnon i i prohibited by law.
nFKTfJil
MANNED LUNAR
PAYLOAD
LUNAR RE-ENTRY VEHICLE ( 3 MEN )
r~s CARGO PACKAGE
LUNAR LAUNCH STAGE
LUNAR LANDING STAGE
— SPACE LAUNCHING SYSTEM-(BOOSTER COMBINATION)
(•)
(t)>
CARGO PAYLOAD
VEHICLE M VEHICLE C
FIGURE A-l LUNAR TRANSPORT VEHICLE
iTOHiiramH WDLAR -S-4S6
cam
c
MANNED 'LUNAR PAYLOAD
LUNAR RE-ENTRY VEHICLE ( 3 MEN)
CARGO PACKAGE
LUNAR LAUNCH STAGE
LUNAR LANDING STAGE
SPACE LAUNCHING SYSTEM' (BOOSTER COMBINATION)
CARGO PAYLOAD
FIGURE 2-2 LUNAR TRANSPORT VEHICLE
WDLAR-S-4S8
*• *
FIGURE k-2 MANNED VEHICLE SYSTEM
CENTER OF GRAVITY, AXIS SYSTEM AND STATION DIAGRAM
ENTRY VEHICLE AT LANDING
VEHICLE PRIOR TO ENTRY
VEHICLE AT BEGINNING OF LUNAR LAUNCH
VEHICLE AT BEGINNING OF LUNAR LANDING
MANNED VEHICLE AT EXIT
SW. itOii
HDIAR-S-^58
S K ^ - ^ i S B l * ! - - 1 — . • - a | j g " * y ~ » " ' ' i r " ' - - - - r T ' T - .- - r l i i ' - *.-*:
; - = * f t -•*TTF «. . . s.'. \ , '-•
Cargo Factoge
The Lunar Cargo Package (See Figure A-l , item e) i s tha t p w t of the Cargo Payload vhich represents a package consisting of supplies, equipment, e t c . , needed on the lunar surface. Preliminary design data indicates tha t an amount in excess of 40,000 pounds must and can be delivered to the lunar surface.
Cargo payload
n » Cargo Payload i s th=,t psxt of the Lunar Tr°-nspprt Vehicle vhich i s placed on a selected lunar trajectory 8* ,d i s bonsted to earth escape velocity, i t consists of tvo sajor pa r t s . These are:
Lunar Landing Stage
Caxgo Package
This division i s schematically represented in Figure A-l by the parts labelled b end e . The cargo payload does not in* elude a Lunar Launch Stage since the cargo pacfc&ge regains on the lunar surface. The -weight Of the Cargo package i s equivalent t o the combined veight of the Lunex Re-entry Vehicle (3 men) and the Doner Launch Stage, The Cargo Payload weighs 13^,000 pounds a t earth escape-
Circumlunax
- A highly e l l i p t i c a l t ra jectory tha t goes around the moon and d t ' " returns to the ear th .
Circualunar proTMlsion stage
A stage attached to the Lunex Re-entry Vehicle to provide a, suitable propulsion and control capabil i ty for maintaining the Re-entry Vehicle on a circumlunar t ra jec tory .
Delayed Procurement Concept
k s,s- Concept of deferring the f ina l ordering and production of high-cost insurance type spares un t i l mariimrn f l igh t
-***i- experience i s available^
p.- -fti-nw
High-Speed Re'-e'ntry Test
A t e s t program using a special Re-entry Test Vehicle designed "**'""**fcQJSpbtaln fundamental re-entry data and specific configuration
data i t re-entry veloci t ies of 25 to k5 thousand_feet per second.
fth aViimtM (MtalM infermaHan eHatliiw Mn natianl riafana of tbt Unirad Stafai wHhln Iha uteulm ^ «h« Eiptanat* low., l i l la I I , U.&.C., 5.ctl.B 7*3 and 794, ttm traaamiitlofi sr rawttaiian af'whith la any Mannar to an unaaHiarlkan bartaa H praliibhad bv law-
•JW"S
V . Lunar Expedition F a c i l i t y
A f a c i l i t y designed to be constructed under the lunar surface and to support the Lunar Expedition. Ib is f a c i l i t y w i l l be designed BO that i t can be readi ly expanded t o support future mi l i tary requirements
lunar Landing Stage
The Lunar Landing Stage 1 B that part of the Manned Lunar Payload that v l l l land the Manned Lunar Payload at a se lec ted s i t e on the
r.K-*r-. ' surface of the moon. The expended portion of t h i s stage i s l e f t —-— on the lunar surface when the Lunex Re-entry Vehicle i s launched
for the return t r i p t o earth (See Figure A- l , item b . ) .
Lunar landing Stage - Cargo
The Lunar Landing Stage of the Cargo Payload (See Figure A- l , item b' ) i s ident ica l t o the landing stage of the manned Lunar
"_,;: Payload. i t provide the capabi l i ty of so f t landing the Cargo package a t a preselected s i t e . The Cargo Payload i s unmanned and
jg^;,. the landing operation i s automatic. The Lunar Landing Stage r e -;_ mains on the lunar surface v i t h the Cargo rayload-
^
Lunar Launch Complex
The Lunar Launch Complex cons i s t s of the base f a c i l i t i e s , i n t e gration bn J dings, check-out bui ldings , launch pads, propellant manufacturing p lants , the complex control center and a l l of the equipment required t o earth launch and support the Lunar Expedition.
Lunar Launching Stage
The Lunar Launch Stage (See Figure A - l , item c ) i s tha t part of the Manned Lunar Payload that w i l l boost the lunex Re-entry Vehicle t o lunar escape ve loc i ty on a moon-to-earth trajectory -I t w i l l be ejected prior t o earth re-entry.
Lunar Te*mi
The Lunar Team consists of Air Force technical personnel from - various Air Force System Command organizations and the various &&& Air Force Command organizations. This team was formed to assist ",", the BSD in establishing a sound Lunar Expedition program. The
. membership during the past two years has varied from 30 to 50 personnel;
Lunar Transport Vehicle
C **--•-• flhe Xunazh.'Xranspjprt Vehicle i s required to transport men and
materials for the L^ihar/Expedition. The Iimar^QaMaaafaVehicle
* * * & * - WBUR-S-458 Tfcii dwaiaant tanfeiai kifariMllaa affactlng nW Mttonol (tetania af Nia United StaJti within l*a w » i " » erf rh* Eipionna* Lewi, T»ia I I , U.5.C.. Saclim 793 and 7 W . tto tianiinhtiea at nnkiHan of ohldi In any •aannai ta on unoirtheritad parian •> pfahibitad br low,
***** (JUBMFU u . ' i -* _ _ ^ ^ '**if * * • _ *
consists of 8 Hpace Launching Vehicle end one of two pay loads. ^" One pay load 1B the Manned Lunar Payload and the other is the Cargo rayload (r«e Figure A-l)
_ _ ? _ .
LUNEX I s s short t i t l e for the Lunar Expedition Program
Tunex Rrogrem Director
'-•'-• -'-v- The Lunex Program Director is the individual responsible for t_. directing and controlling a l l facets of the Lunar Expedition
4" ' '"' Program.
Lunex Re-entry Vehicle
The Lunex Re-entry Vehicle (gee Figure A - l , item d) i s the only part of the Manned Lunar Fsyload t h a t returns to the earth. - I t carries three men and a l l the necessary l i f e support, guidance, and common!cation equipment that i s required. I t re -enters the
•'•••-' earth's atmosphere and uses aerodynamic braking to slow down and land l ike a conventional airplane- The preliminary design
^ ^ of the Lunex Re-entry Vehicle calls for a vehicle 52 f t . long "**••" with a return weight of 20,000 pounds.
i
Han-rated £
A vehicle, or system is considered to be "man-rated" when sufficient ground and flight test data has been accumulated to determine that the reliability objectives for the item have been achieved and that the abort system satisfactorily compensates for the inherent unreliability of the system.
Manned Lunar Fayload
The Manned Lunar rsyload is that part of the Lunar Transport vehicle which is placed on a selected lunar trajectory and Is boosted to an earth escape velocity of approximately 37,000 feet per second. It consists of three major parts. These are:
- Lunar Landing Stage
Lunar Launch Stage
lunex Re-entry Vhlele (3 men)
. „ * *
This division Is schematically represented in Figure A-l by t i e parts labelled b , e, and d. The complete Manned Lunar Payload reigns 13^000 pounds at earth escape.
.--\*-; _m_P<lPRrTI_>£Jis * l'
TW. tfocsmwit C M M D lab—alitt afbcHng Mv avHcuBl dt f t tM af Hw. Unitod Stain wnkln KM Marina al Ik* Eiptonnaa' law), Til l* I I . U.S.C., I H I I M 7*3 and 7W, flit MniMlulan m moalaHaa a l wliick ia any m a m r a> an MHaH_r_d panan b piabiblM by law.
Responsive Production Concept
A concept iftuereby long lead portions of high-cost operational spares are purchased. unassembled to reduce costs until final decision is made on spares procurement.
Space launching System
•MM The complete system, including ground facilities, propellent manufacturing facilities, etc., as required to launch the boosters required for space operations.
— - siaiTOARp TERMINOLOGY
AGE
A term used to describe the Aerospace Ground Environment required for a specified system.
Abort. System
**** The Abort System includes all the equipment required to remove, or return the crew members of the Lunex Re-entry Vehicle to a
\
position of safety in the event of a malfunction of the Lunar
Transport Vehicle. * PEP
'i -L
P-E-P. are the initials for "Program Evaluation Procedure". It is a management tool tfiich uses an electronic digital computer. It has the capacity to handle large masses of data quickly. The PEP system provides information that will enable the lunex Program Director to quickly identify, locate, and consequently, correct program trouble spots-
9am. A term used to describe Qualitative and Quantitative Personnel Requirements Information that is required to properly plan for personnel training.
* • * *
'-.r 3 ^ A term meaning Real Property Installed Equipment that 1B synonymous with Technical f ac i l i t i e s . Technical Facil i t ies are those structural and related items vhich are buil t and/or installed by the Corps of Engineers and then turnedcwerto the Air Force or an Air .Force contractor.
WXMR-S-Jf58
Tab dKHBanl ceMaln hforaialJan •ffatlin* (ha natiaMl aafam. af tha Uniwd Stain wHWa Urn amntna •> Ih* Eiplsaaa* l a m , tttla t l , U.S.C, S*c«ifn 7*3 9*4 79*, Hw traf»"ii»iM * mrtlBtion af vMrti in m r monmi to M Mautkorliwl pan** h pnh lb tM br tov.
{l.lifllL
tf
"*.9)-
• . , ;•• - »
*SS-
TTAT Lunar Chart
A, chart prepared to a scale of 1:1.000,000 and covering the lunar Burface. Present plans call for the preparation of lkk individual charts to cover the complete lunar surface.
HiOGRVM TITLES
BOSS
BOSS i s the designation for "Biomedical Orbiting f-atell i te System" - The BO.T5 program uses primates to provide l i f e science data for designing manned space systems.
SftlHT
The rAIHT program vill develop and demonstrate orbital rendezvous and satellite inspection techniques. It vill further demonstrate the capability of closing, duelling, and refueling.
/ '
-" y?*1*!7 <•>•*.. 2M£H>. v ^rv*
A1.6
WDLAR-S-458
Tkh rfaumnt witsiai SntanMfwn aftattfna I k . aatianal M H H at f*. UnHao1 Storm within tfta naming al rba EieiSfMtt Lowi, Tttb I I , U,S:C, Saitlon 793 and 794, i*t tiBtu>iiii»iwt ar Mialatiaa a l wkid ia anr nariiwr fa an *n«(harli*d parts. a aroklbrted by taw.
