SECTION V. BUDGET AND FINANCIAL

5.0 INTRODUCTION

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 Lunar Observatory Final Report, Volume I - Study Summary and Program Plan, numbered AFBMD TR 60-44 and dated April 1960. The costing of this program was accomplished by the Rand Corporation and was based on a completely integrated program.

The 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 a Lunar Transport Vehicle development program that would give the US 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 military operations. Studies have shown that the moon possesses real military potential and it could support a recallable deterrent capability. The development of the Lunar Transport Vehicle represents a minimum program for the Air Force to obtain control of the cislunar volume and the lunar surface.

5.1 BUDGET ESTIMATE AND FINANCIAL PLAN

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 61 and three of the contractors are each performing the design under a $100,000 contract. The other three contractors are participating on a voluntary basis. The 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: $ 26.9 million

  • FY-63: $ 112.2 million

Should the above funds not be made available, the schedule for establishing the Lunar Expedition will be delayed proportionally to the delay in funding.

  • Launch Facilities

  • Expedition Costs

5.2 COST ESTIMATES

The funding requirement for the complete Lunex Program are as follows:

FY COSTS (in millions of dollars)
Item 1962 1963 1964 1965 1966 1967 1968 1969 1970 1971
R & D 26.9 104 335 660 1084 1608 -- -- -- --
Launch Facilities -- 8 64 64 -- -- -- -- -- --
Expedition Costs -- -- -- -- -- -- 1135 1023 798 631
Annual Total 26.9 112 399 724 1084 1608 1135 1023 798 631
Program Total 7541

To accomplish the Lunex Program, addition 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 NASA programs will provide some information and capability. However, to meet the Lunex program schedule, the following additional funding will be required by either the NASA or the Air Force:

Unmanned Vehicles - FY COSTS (in millions of dollars)

Item 1962 1963 1964 1965 1966 1967 1968 1969 1970 1971
Lunar Photographs and Radio-Light Beacon 15 75 85 15 -- -- -- -- -- --
Recovery of Lunar Core Sample 12 35 85 285 265 85 24 -- -- --
Annual Totals 27 110 175 300 265 85 24 -- -- --

5.3 FY 62, 63 FINANCIAL PLAN

ITEM FY-62 FY-63
MANNED LUNAR PAYLOAD
Lunex Re-entry Design & Mock-up
-- (2 cont'r, 8 M ea) 16,000 80,000
Lunar Landing Stage
-- (2 cont'r, 1 M ea) 2,000 10,000
Lunar Launching Stage
-- (2 cont'r, 1 M ea) 2,000 10,000


SECONDARY POWER
Manned Vehicle Power System 600 1,000
Surface Vehicle Power System (15 kW) 100 300
Nuclear Lunar Facility Power (300 kW)
-- (Spur Program Support) 1,000 1,500


GUIDANCE
Mid-course System 200 450
Lunar Terminal System 300 450
Lunar Ascent System 100 300
Earth Return System 200 500


LIFE SUPPORT
Crew Compartment Design 400 1,000
Ecological System 1,000 1,200
Moon Suit or Capsule 500 800


COMMUNICATIONS & DATA HANDLING
Manned Vehicle Video System Design 400 1,000
Wide Band Moon-Earth Link Design 200 400
Secure Narrow Band Link Study 100 300
Man-Man Lunar Surface 300 650
Materials and Resources
Re-entry Materials Research 1,000 1,300
Lunar Natural Resource Dev. 500 1,000

--------------------------------------------------------------------------------

Total In Thousands 26,900 112,150

 

VI. PROGRAM MANAGEMENT


6.0 MANAGEMENT FOCAL POINT
The 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 co-ordinate, integrate, monitor and direct all activities of the Lunex Expedition Program. Subordinate to the Director will be managers for major parts of the program. A tentative organisational chart for the Program Office is shown in Figure 6-1.

6.1 RESPONSIBILITIES

a. The Earth Launch Complex Office will be responsible for the civil engineering aspects of building up the earth launch base. The immediate problem of this office will be a site selection survey.

b. The Earth Launch Vehicle Office will be responsible for all earth launch boosters required for this program.

c. The Lunar Landing and Launch Vehicles Office will be responsible for all development and testing of the Lunar Landing Stage and Lunar Launch Stage.

d. The Manned and Cargo Payloads Office will be responsible for the development of the manned Lunex Re-entry Vehicle and the Cargo Package. This will be one of the key offices in the entire program since it will be concerned with such major technical areas as life support equipment, re-entry problems, secondary power and structures.

e. The Communications and Data Handling Office will be responsible for establishing the communication network and centralised data handling organisation. It will also concern itself 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 will be responsible for developing: ascent, mid-course, terminal, lunar ascent, and re-entry guidance equipment.

g. The Lunar Expedition Facility Office block (shown in dotted outline) indicates that that office will be established at a later time since the problems associated with the expedition facilities are not of immediate concern.

h. The Plans Office will be responsible for examining other potential uses of equipment developed for the Lunex Program. For example, the same equipment could be used for sending men around Mars and Venus, or perhaps effecting a landing on Phobos. Considerable planning also needs to be done regarding the exploratory phase of the Lunar Expedition.

i. Programming Office will be responsible for scheduling and budgeting of the entire program. This office will have under its control a network of computers designated as the PEP program.

j. The Technical Integration and Support Office will be responsible for insuring the technical compatibility of all components of the system, such as, that the vibration is within tolerable limits during the boost phase when all components of the system have been put together. This office will also provide technical assistance to each of the main component offices. The component offices such as the Manned and Cargo Payloads Office will not rely entirely on the Technical Integration and Support Office for assistance, but will be free to obtain the best technical advice available in the nation from whatever source is necessary, such as other government laboratories or universities. This Technical Integration and Support Office will be manned by Air Force officers who will be responsible for the various disciplines and for technical support from the Aerospace Corporation.

k. The Reliability Office will insure that a strong reliability and safety program is followed by all contractors throughout the program. Since reliability and safety is of such extreme importance in this program every effort must be made to insure the reliability of the final equipment. This can only be done by giving proper recognition to the. problem at a high organisational level where policies and recommendations can be recognised and implemented.

6.2 PROGRAM OFFICE MANNING
A Program Office must be established immediately after program approval if planned schedules are to be met. It is estimated that an initial build-up to 72 officers plus 35 secretaries will be required. A requirement for 100 MTS will be established with the Aerospace Corporation. In view of the magnitude of the program, which will build up to more than one billion dollars a year, a larger Program Office will be required. Planning for these increased manpower requirements will be accomplished by the Program Office, after it is established. Suggested initial distribution of personnel within the Program Office is as follows:

a. Lunex Program Director 4
b. Plans 4
c. Programming 6
d. Technical Integration and Support 20
e. Reliability 2
f. Earth launch Complex 5
g. Earth Launch Vehicle 5
h. Lunar Landing and Launch Vehicle 5
i. Manned and Cargo Payloads 15
J. Communications and Data Handling 3
k. Guidance and Flight Control 3

6.3 ORGANIZATIONAL 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 end magnitude of the program, the Program Director will be required to deal with many contracts from diverse technical areas. It is envisioned that an associate contractor will be selected for each major portion of the program, who will, in turn, use many supporting contractors of various technological capabilities. Technical integration and support will be accomplished by the Aerospace Corporation under the overall guidance and control of the Program Office.

6.4 AIR FORCE DEVELOPMENT AND SUPPORT
The 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 guidance, materials, rocket engine propulsion, life support, etc. Each Technical Area Manager will identify and emphasise those critical technical problems to which specific effort must be directed in order to attain a capability required by the Lunex program.

6.5 OTHER AGENCIES
Specific arrangements will be made with other agencies as requirements arise in the development of the Lunex program.

6.6 MANAGEMENT TOOLS
The 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 which uses an electronic computer will be used to support the Program Director in planning, operating, and controlling the Lunar Expedition Program. It will be initiated in the early stages of the program and continue to be used throughout the expedition phase. This management tool, called Program Evaluation Procedure (PEP) will assist the Director by providing:

a. A method of handling large masses or data quickly, efficiently and economically..
b. The capability to locate, identify and this correct trouble spots.
c. The capability of integrating the many varied and complicated facets of the Lunar Expedition Program.

6.7 PEP
The PEP management tool is made possible through the use of an electronic digital computer. The scheduling and monitoring of many thousands of items required in the Lunar Expedition Program make the use of this computer technique imperative. The PEP approach employs linear programming techniques with a statistical concept in conjunction with the electronic computer. This procedure facilitates the analysis of interrelationships of many thousands of program elements. The results are presented as program summaries upon which the Director can base decisions. (See Fig. 6-3)

The first step in using the PEP management tool is to make a detailed analysis of the overall Lunex Program. Each major event, milestone, or accomplishment that must be achieved is listed in chronological order. The events must be well defined and should occur at an instant of time which can be identified. A network, or a program plan chart, is laid out in which the events are shown as points or circles whose positions roughly represent their chronological order. Interrelationships between the events (circles) and sequence of events are shown by connecting lines. The line between the events represents work that must be done to proceed from one event to the next (See Figure 6-4).

 

The computer then totals all of the expected activity times along every possible (in the thousands) route of the network from start to the end event. The PEP computer then examines the total times of the large number of paths in order to find the longest, which is called the critical path. The critical path defines the sequence of events which will require the greatest expected time to accomplish the end event.

The effects of 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.
 

SECTION VII. MATERIEL SUPPORT

7.0 PRODUCTION
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 the 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 materiel and parts involved can be utilised 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 utilisation 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 of 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.

Determination of quantities, reparable-overhaul modification planning, control etc., shall be accomplished and directed by a permanently organised and active group composed of personnel representing the engineering, production, materiel, reliability, quality control, procurement and contract departments, and the various affected sections within these departments such as design, test, planners, etc., attending as required. The AFPR will have a member assigned to this group for surveillance purposes and to provide logistic guidance on problems which may require advice from the Air Force.

Persons assigned to the group shall be well qualified by reason of experience and technical ability.

The procedures and paperwork involved shall be streamlined, taking due cognisance 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.

The 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 modification planning at all times.

The group shall be responsible for the following:

a. Immediate adjustment of inventory 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 or disposition of non-moving items on a continuing basis, but at intervals not to exceed sixty (60) days for any individual hi-value items and 180 days for other items, or at other internals as agreed upon by the Contractor and the Contracting Officer. This is to include the return to production of any surplus quantities for rework to later design requirements.

d. Control of repair overhaul modification planning.

7.2 DISTRIBUTION
The Contractors shell develop internal working procedures which encompass the following requirements:

a. Inventory levels shall 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 minimised by maximum economical reliance on repair, overhaul, and modification of reparable items. Repair, overhaul, and modification turn-around time will be a prime determinant in establishing the minimum stock level period for each item.

c. Where feasible (with particular emphasis on hi-value and critical items), inventory cost will be minimised by stockage of repair, overhaul and modification spares, 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 utilisation will be made of available contracted air transportation to minimise "pipeline" time.

7.3 STORAGE
Parts, 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 commingling of stock, considerable cost savings can be effected. Spares and production stock serve as buffer stocks for each other. If multiple activities such as manufacturing, test, and the expedition are supplied from a single storage facility the chance of stock-out would be minimised.

7.4 REAL PROPERTY INSTALLED EQUIPMENT (RPIE)
Each contractor is charged with the responsibility of identifying, as well as determining the criteria for all items required for successful mission accomplishment. When the requirements have been determined the responsibility for accomplishing the required RPIE materiel support program will be assigned. This materiel support will 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 Lunex 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 will 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 that the systems and techniques developed during testing may also be continued for the Expedition.

An evaluation mill 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 MANUFACTURING FACILITY CRITERIA
The equipment production facilities will preferably consist of an existing large aerospace plant convertible to Lunex production with a minimum modification program. It may be necessary to build a faculty that is adjacent to, or easily accessible to navigable waterways. The facility should obviously be located in an area containing an abundance of skilled manpower. Manufacturing Test Facilities adjacent to the manufacturing facilities would be very desirable to reduce transportation problems.

Certain items, such as the large liquid and solid boasters 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 will 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

-- For 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 consisting of one pad and three structural towers will be required.

The separate test complexes will dedicated 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 LH2 caloric content to TNT, 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 commercial type crane, and personnel access for maintenance is by work stand and ladders, or a cherry picker. No service tower will be required.

c. Thrust Level Measurement

-- Thrust levels will be determined by measuring the chamber pressure and applying the result to the engine manufacturer's calibration curve. Tanking level is determined by the Propellant Utilisation System.

d. Altitude Simulation Unit

-- A plenum chanter, containing steam jets upstream 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. Propellant Storage and Handling Equipment

-- A central LO2 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 LO2. Spherical, vacuum insulated dewars shall be used. The transfer unit shall be a motor operated centrifugal pump with 500 gpm and 100 psi discharge head capacity. The Lunar Launch Stage Test Facility LO2 storage shall contain 18,000 gallons in spherical dewars with a transfer pump capability of 200 gpm and 100 psi discharge head. Distribution lines for both complexes would be prefabricated, static vacuum, insulated steel pipe.

An LH2 storage and transfer facility will be provided at each hot firing test stand and the cold flow test pad. The transfer system is an LH2 gas generator system with air being the thermal source. Pressuring level in each tank would be 100 psi. The LH2 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 dewars with segmented, prefabricated, static vacuum insulated stainless steel pipe distribution lines.
 

VIII. CIVIL ENGINEERING

8.0 INTRODUCTION
As part of the Lunar Transport Vehicle study, consideration was given to the facility required for the launch and support of the Space Launching System and the lunar payloads. It was assumed that the manufacture of all boosters and the payload would 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 program 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 would be required. A significant saving 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 propellant 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 saving.

In order to achieve the highest launch pad utilisation possible and to make maximum use of specialised capital equipment and highly skilled manpower, the application of operations research technology will be required. To handle the test load and the complex sequencing requirement 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 is 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 pre-flight servicing and launching the vehicle.

8.1 LUNAR LAUNCH COMPLEX
The lunar Transport Vehicle System has a requirement for launch and support facilities suitable for manned lunar flight of a vehicle using a BC2720 Space Launching System. Investigation of the launch pad requirements for a launch rate of two per month indicates that from 4 to 6 launch pads would 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" boaster 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 cost saving may be gained and an accelerated test program may be effected. This would 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 would 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 would be required. In plants of sufficient size these facilities and equipment could readily 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 weighing 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. Inasmuch as both the "B" and "C" boosters of the Space Launch Systems have diameters in excess of 14 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. Harbours and docking facilities would be required near the manufacturing facility and at the launch site.

By locating the launch facilities at or near Cape Canaveral for an easterly launch significant savings may be effected. The use of existing administrative capabilities, personnel housing, assured tracking facilities, and technical support areas will provide a saving in costs and in lead-time required for construction of support facilities. Similar gains may be made by 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 Christi 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 rate as indicated in this study dictates that new propellant manufacturing plants be 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 at launch pad: 1.5x10^6 pounds.
(3) Liquid Oxygen/Nitrogen Manufacture: 120 tons per day.
(4) Liquid Oxygen storage at launch pad: 4 x 10^6 pounds.

Barges will be required for transport of boosters from the manufacturing plant to the launch complex.

8.3 AEROSPACE GROUND ENVIRONMENT
A modified Integrated Transfer launch System is envisioned for the Lunar Transport Launch System. This is approach would allow the complete integration and checkout of the "B" booster together with the Lunar Transport Payload in a protected environment simultaneously with the assembly and checkout of the C2720 booster combination at the launch pad. The size 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 when 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 cliff-side 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 C2720 vehicle may be accomplished in two ways 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 "C" 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 4 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 propellants was estimated in the following manner. The TNT equivalent of the liquid propellants was taken at 60% of the total LOX/LH2 load for all stages. This is the figure currently used at AMR for TNT equivalence for LOX/LH2. In this case, because of the great quantities of propellant involved, this degree of mixing is unlikely and the 60% figure would be conservative. Solid propellants are taken at 100% of the propellant weight. 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 is not likely to occur.

 

This philosophy resolves to consideration of TNT equivalents of liquid propellants and solid propellants separately and they are not additive. The TNT equivalent of one of the four segmented solid assemblies is 680,000 pounds. The 60% TNT equivalent of the total liquid propellant load is approximately 1,300,000 pounds. Using the highest TNT equivalent (1,300,000 pounds) the inhabited building distance must be approximately 2 1/2 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 2 1/2 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. These distances can be decreased by creating a buffer between the pads. Locating the launch pads in ravines or indentations in cliff aide launch locations might substantially reduce the land areas required. The selected 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.

The 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 be desirable. To avoid analogue 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.

 

Analogue 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.


SECTION IX. PERSONNEL AND TRAINING


9.0 INTRODUCTION
This 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 PERSONNEL
The accomplishment of the Lunar Expedition Program will 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: 145
Lunar Expedition (21 men at expedition facility, crew rates of 5): 145
Ground Personnel: 3677
Lunar Squadron: 100
Launch Squadron: 873
Instrumentation Squadron: 293
Assembly & Maintenance Squadron: 860
Supply Squadron: 562
Base Support Units: 639
Administration: 350

Total Direct Personnel (Space plus Ground): 3822
Overhead: 1287

Range Tracking: 940
Logistic Support Organization: 347

Grand Total Personnel: 5109

9.2 TRAINING PROGRAM
The remaining portion of this section of the Lunar Expedition Program Plan (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 this program will of necessity have to be applied directly to the training areas to insure "concurrency" of the programs training development. Further, the training knowledge and experience acquired from current research and development programs must be studied for application to this program.

The concepts and plane 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 training 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 (PED). This information is required for space crew end 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.

No 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.

9.3 PLANNING FACTORS AND GROUND RULES

a. Scope:

This section is conceptual in nature at this 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 Crew Personnel: Personnel performing crew duty in the Lunar Transport Vehicle.

(2) Cadre Personnel: Those personnel necessary for logistic planning, AFR 80-14 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 with paragraph 5 a (1) and (2), AFR 80-14, and Job Training Standards for the Integrated Systems Testing Program in accordance with paragraph 8 g (3), AFR 80-14.

(3) Main Complement Personnel: Personnel employed in the receipt, check-out, installation, repair, maintenance and operation of the system.

(4) Support Personnel: Air Force Logistic Commend personnel required for support functions as well as other agencies' supervisors and planners

(5) Types of Training:

(a) Type I (Contract Special Training). Special training courses conducted by contractors at an ATC installation, contractor facility or any other designated site.
(b) Type II. (ATC Special Training) Special Training Courses conducted by ATC training centres' instructors at an ATC installation, contractor facility, or any other designated site.
(c) Type III. Career training/
(d) Type IV. Special training provided by ATC training detachment instructors at the site or the organisation requiring the training.

(6) Testing Programs:

(a) Component - the testing of the components of a sub-system, such as the guidance package, or ecological package.
(b) Sub-system - components assembled into a sub-system, such 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) The man-rated Lunar Transport Vehicle will be available for use by the Lunar Expedition in 1968.
(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.
(3) AFR 80-14 will be used as a guide for accomplishing the program testing.
(4) The terminology for normal levels of maintenance, i.e., organisational, field, depot, and shop, vehicle assembly and maintenance as specified in AFLC (AMC) letter MCM, dated 25 July 1960, subject: Standard Maintenance Terms and Maintenance Facility Nomenclature for Missile Weapon Systems will apply.
(5) The Air Force Maintenance policy of maximum maintenance at the lowest feasible level will prevail.
(6) Due 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 Dates:

(a) Start of Component Testing Dates are:

1. Re-Entry Vehicle - June 1963.
2. Lunar Launch Stage - February 1965.
3. Lunar Landing Stage - May 1965.

(b) Start of Subsystem Testing Dates are:

1. Re-Entry Vehicle - November 1964.
2. Lunar Launch Stage - May 1966.
3. Lunar Landing Stage - July 1966.

(c) Peculiar Requirements and/or Limitations:

(1) The unique mission of this program makes it mandatory that the following actions be accomplished concurrent with the development of the hardware:

(a) The contractors will develop the Personnel Equipment Data information concurrent with the design of the hardware. This is information must be available to ATC personnel for early planning purposes.
(b) Type I training dates reflected in the time phasing chart will require the use of R&D and test equipment as training equipment.
(c) Production schedules for R&D and Expedition equipment will include the training equipment required to support Type II and Type III training. Allocation and delivery priorities will be in accordance with AFR 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 will he made as more conclusive information becomes available. See Charts IX A and B.
(3) Maximum Cross-Training will be provided as required to all personnel associated with this program.
(4) The requirement for follow-on training and the value of past experience is recognised and maximum retention of personnel is mandatory.
(5) New and peculiar training problems are envisioned for the technical personnel
(6) The training of the aerospace crew personnel will require the development of a program which is unique to the Air Force.

(d) Qualitative and Quantitative Personnel Requirements Information

(1) A QQPRI prepared in accordance with Mil Spec 26239A will be required to develop the training courses, course material and substantiation for the Personnel Classification changes.
(2) ATC and other applicable commands will furnish personnel for the QQPRI integration team and provide technical guidance to the contractor during preparation.

9.4 TRAINING

a. Training Responsibilities and Concepts:

(1) Engineering Design Effort
(a) ATC will participate in the engineering design effort to insure that technical data is collated with 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 AFR 50-9.
(c) Selection of the initial aerospace crew personnel and ATC aerospace 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 the Aerospace Medical Centre, Brooks AFB, Texas.
(f) ATC Lunar Transport Vehicle crews will be phased out of training 30 days prior to the requirement for Type II 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 crew, AGE and addition job tasks as required.
(b) All requirements for Type I Special Training, AFR 50-9, in support 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 development to keep trainee information in consonance with 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 TRAINING PERSONNEL

a. Field Training Detachment (FTD)
The number of personnel required to provide training for lunar vehicle personnel will be determined during the training programming conference. QQPRI, TPR's, Personal 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 TRAINING EQUIPMENT PACKAGE

a. General:
Training equipment requirements will be developed to support:

(1) Check-out and ground maintenance to be performed by the direct support personnel for the Lunar Transport Vehicle.
(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 will be applied to the Lunex program to assist in the identification of training equipment. The 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 utilisation 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 minimum cost.
(4) 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. Planning Factors:
Planning factors for determination of Training Equipment Requirements:

(1) In view of the limited program information presently available, definitive planning factors upon which over 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 magnitude. Provided Control Centres used for other space vehicles will be applicable to the Lunar Transport Vehicle, Category I (Trainers), Category II (Parts / Components / End Items), and Category III (Training Aids / accessories) 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: Percent of Sub-System Cost Required for Training Items

(a) Re-entry Vehicle: 250%
Complete R/V - 1 ea
Sub-systems of R/V - 1 ea
Major components of each sub-system for Bench Items - 1 ea

(b) Lunar Launch Stage: 150%
Sub-systems of Launch Stage - 1 ea.
50% of Major Components for Bench Items

(c) Lunar Lending Stage: 100%
Major Components - 1 ea
Cargo Package: 100%
Complete Cargo Package

(e) Aerospace Ground Equipment: 200%
Complete set for handling and testing vehicle sections and included equipment
Complete set as bench items for maintenance training

(2) Training films and transparencies requirements will be developed as soon as possible.


(3) Spare parts support will be required for all Category I and II training equipment.

(4) A continuing requirement will 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 charge proposals.

(5) Funding of P-400 money will be omitted in consonance with AFR 375-4, Para. 12.
 

9.7 FACILITIES

a. General:
The needs for training facilities should be established approximately three years prior to the dates at which Type II training equipment will be required. Facilities must incorporate sufficient flexibility to accommodate future updating of training equipment resulting from program configuration changes.

b. Aerospace Crew Training Facilities:

(1) Initial training for aerospace crew personnel will require the use of existing space training facilities. Joint Use Agreements between NASA and other USAF agencies and the Air Training Command will be required to insure maximum utilisation of these facilities. Aerospace Medical Centre's facilities (Brooks AFB, Texas) will be utilised to the fullest. Interservice agreements with the Navy for use of specific training device facilities should be considered for crew training.
(2) The establishment of a centralised space training facility would have a direct bearing on the overall specific requirements for this type of training. The results of the System Study Directive (SSD) Nr 7990-17610, titled: "Centralised Space Training Facility," will have direct bearing on the posture of the training facilities of the future. For this reason, facilities requirements for follow-on training are not projected.

c. Other Training Facilities:
It is anticipated that Technical Training Centres now in existence can absorb the additional technical training load without increasing the facilities. However, modification of existing facilities to provide training laboratories with specialised power and environmental systems will be necessary. This requirement must be identified in sufficient time to permit facility programming through normal procurement cycles.

9.8 BUDGET AND FINANCE

a. Training Equipment Costs
Funding will be required for training equipment identified in Section 9.6, Training Equipment Package.

b. Training Facilities Costs
Funding and costs of training facilities will be determined once the decision is made whether to build a Centralised Space Training Facility or to continue with decentralised procedures. Funding can then be determined for the required facilities and modifications.
 

CHART IX-B
LUNEX/SPACE LAUNCHING SYSTEM

1. The estimates for the launch system are not included in view of the status of the Space Launching System (SLS) study. It can, however, be estimated that the launch complex personnel utilised in both the liquid/solid propellant type boosters will be integrated into a team for support of this system.

2. At such time as the S.L.S. is designated as the primary launch support system, a PSPP will be made for the launch vehicle and support AFSC's as a part of this program.
 


SECTION X.  INTELLIGENCE ESTIMATES

10.0 INTRODUCTION
The purpose of this section of the 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 will be defined in terms of major performance capability and dates of operational availability.

 

10.1 Foreword
The following data was obtained from DCS/Intelligence, Hq ARDC, and published intelligence estimates.

10.2 PERFORMANCE CAPABILITY
The Soviets have flown geophysical and component equipment payloads on their vertical rockets for the development, modification, and acceptance testing of instrumentation for use on their satellite and lunar aircraft. They developed and used complex scientific instrumentation on Sputnik III, and stabilisation, orientation and control equipment on Lunik III and Sputnik IV. Presently, by using their vertical rockets, the Soviets are testing infrared equipment, in addition to collecting data on the background noise level of the earth's surface. It is believed that a development program exists which eventually could lead to detection and reconnaissance satellites. The development program which led to the photographic system used in Lunik III is expected to continue, with an eventual application in photographic reconnaissance and weather satellites.

The Soviet space launch capability is shown in the following table of Sputnik and Lunik booster thrust levels:

  • Sputnik I: 300,000 pounds

  • Sputnik II: 300,000 pounds

  • Sputnik III: 432,000 pounds

  • Lunik I, II, and III: 456,000 pounds

  • Lunik IV, V, and VI: 466,600 pounds

There is also evidence of a cluster of five 140,000 pound units. The Soviets are developing engines of 1 to 2 1/2 million pounds thrust. The estimated time for a booster to match this engine is as follows:

  • Single engine booster: 1963

  • Clustered engine booster: 1965

In general, it takes approximately half the time for development required in the US


The maximum Soviet orbit capability, with present ICBM boosters using five (140,000 pound thrust) engines and four (6,600 pound thrust) engines is 10,000 pounds in low altitude orbit. All Lunik and Sputnik vehicles utilised a third stage having 12,500 pound thrust engine burning for approximately 420 seconds.

By using higher energy chemical propellants in modified upper stages, the payload can be increased up to 15,000 or 20,000 pounds during 1961. However, approximately 50,000 pounds of payload may be attained by 1962 if ICBM launch vehicle thrust is increased.

In the 1965-1970 period, a new clustered chemical booster should allow the Soviets to place 50 to 100 tons in orbit in individual launches. This will permit landing a man on the moon.

10.3 SUMMARY AND CONCLUSIONS
Very early the Soviets realised the propaganda value obtainable from space adventures and, accordingly, have striven continuously for "firsts". This has apparently influenced the detailed pattern for their space planning. Even though the Soviets have achieved "firsts" in:

1) Establishment of an artificial earth satellite
2) Rocketing past the moon and placing a vehicle into a solar orbit
3) Hard impact on the moon
4) Photographing the side of the moon not visible from the earth
5) Safely returning mammals and men from orbit

It seems obvious that the Soviet attempts to score "firsts" will continue.

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 use 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 unmanned lunar rocket probes for the purpose of reconnoitring 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, micrometeorite 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 restart and launch capabilities will undoubtedly be developed.

Circumlunar flights by manned space vehicles, and eventually lunar landings, will be required in order to know more precisely the environmental situation preliminary to the eventual establishment of a lunar base and the complete conquest of this body. This is considered to be a more distant objective of the Soviet program and its attainment will 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 makes it a sufficiently worthy subject for special consideration. The Soviets have published extensively on such a vehicle, and Yu D. Khelbtsvlch, Chairman of the Science Technical Committee for Radio Remote Control of Cosmic Rockets, has published his preliminary design of a tankette laboratory for lunar exploration. Graduate 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.

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 satellites which 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's 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.
 


Appendix #1 - Glossary

Cargo Package
The Lunar Cargo Package (See Figure A-1, item e) is that part of the Cargo Payload which represents a package consisting of supplies, equipment, etc., needed on the lunar surface. Preliminary design data implicates that an amount in excess of 40,000 pounds must and can be delivered to the lunar surface.

Cargo Payload
The Cargo Payload is that part of the Lunar Transport Vehicle which in placed on a selected lunar trajectory and is boosted to earth escape velocity. It consists of two major parts. These are:

Lunar Landing Stage

Cargo Package
This division is schematically represented in Figure A-1 by the parts labelled b and e. The cargo payload does not include a Lunar Launch Stage since the cargo package remains on the lunar surface. The weight of the Cargo Package is equivalent to the combined weight of the Lunex Re-entry Vehicle (3 men) and the Lunar Launch Stage. The Cargo Payload weighs 134,000 pounds at earth escape.

Circumlunar
A highly elliptical trajectory that goes around the moon and returns to the earth.

Circumlunar Propulsion stage
A stage attached to the Lunex Re-entry Vehicle to provide a suitable propulsion and control capability for maintaining the Re-entry Vehicle on a circumlunar trajectory.

Delayed Procurement Concept
Concept of deferring the final ordering and production of high-cost insurance type spares until maximum flight experience is available.

Hi-Speed Re-entry Test
A test program using a special Re-entry Test Vehicle designed to obtain fundamental re-entry data and specific configuration data am re-entry velocities of 25 to 45 thousand feet per second.

Lunar Expedition Facility
A facility designed to be constructed under the lunar surface and to support the Lunar Expedition. This facility will be designed so that it can be readily expanded to support future military requirements.

Lunar Landing Stage
The Lunar Landing Stage is that part of the Manned Lunar Payload that will land the Manned Lunar Payload at a selected site on the surface of the moon. The expended portion of this stage is left on the lunar surface when the Lunex Re-entry Vehicle is launched for the return trip to earth (See Figure A-1, item b.).

Lunar Landing Stage - Cargo
The Lunar Landing Stage of the Cargo Payload (See Figure A-1, item b) is identical to the landing stage of the Manned Lunar Payload. It provides the capability of soft landing the Cargo Package at a preselected site. The Cargo Payload is unmanned and the landing operation is automatic. The Lunar Landing Stage remains on the lunar surface with the Cargo Payload.

Lunar Launch Complex
The Lunar Launch Complex consists of the base facilities, integration buildings, checkout buildings, launch pads, propellant manufacturing plants, the complex control centre and all of the equipment required to earth launch and support the Lunar Expedition.

Lunar Launching Stage
The Lunar Launch Stage (See Figure A-1, item c) is that part of the Manned Lunar Payload that will boost the Lunex Re-entry Vehicle to lunar escape velocity on a moon-to-earth trajectory. It will be ejected prior to earth re-entry.

Lunar Team
The Lunar Team consists of Air Force technical personnel from various Air Force System Command organisations and the various Air Force Command organisations. This team was formed to assist the SSD in establishing a sound Lunar Expedition program. The membership during the past two years has varied from 30 to 50 personnel.

Lunar Transport Vehicle
The Lunar Transport Vehicle is required to transport men and materials for the Lunar Expedition. The Lunar Transport Vehicle consists of a Space Launching Vehicle and one of two payloads. One payload is the Manned Lunar Payload and the other is the Cargo Payload (See Figure A-1).

Lunex
Lunex is a short title for the Lunar Expedition Program

Lunex Program Director
The Lunex Program Director is the individual responsible for directing and controlling all facets of the Lunar Expedition Program.

Lunex Re-entry Vehicle
The Lunex Re-entry Vehicle (See Figure A-1, item d) is the only part of the Manned Lunar Payload that returns to the earth. It carries three men and all the necessary life support, guidance, and communication equipment that is required. It re-enters the earth's atmosphere and uses aerodynamic braking to slow down and land like a conventional airplane. The preliminary design of the Lunex Re-entry Vehicle calls for a vehicle 52 ft. long with a return weight of 20,000 pounds.

Man-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 Payload
The Manned Lunar Payload 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 Vehicle (3 men)

This division is schematically represented in Figure A-1 by the parts labelled b, c, and d. The complete Manned Lunar Payload weighs 134,000 pounds at earth escape.

Responsive Production Concept
A concept whereby 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
The complete system, including ground faculties, propellant manufacturing facilities, etc., as required to launch the boosters required for space operations.
 

STANDARD 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
P.E.P. are the initials for "Program Evaluation Procedure". It is a management tool which uses an electronic digital computer. It has the capacity to handle large masses of date quickly. The PEP system provides information that will enable the Lunex Program Director to quickly identify, locate, and consequently, correct program trouble spots.

QQPRI
A term used to describe Qualitative and Quantitative Personnel Requirements Information that is required to properly plan for personnel training.

RPIE
A term meaning Real Property Installed Equipment that is synonymous with Technical Facilities. Technical Facilities are those structural and related items which are built and/or installed by the Corps of Engineers and then turned over to the Air Force or an Air Force contractor.

USAF Lunar Chart
A chart prepared to a scale of 1:1,000,000 and covering the lunar surface. Present plans call for the preparation of 144 individual charts to cover the complete lunar surface.
 

PROGRAM TITLES

BOSS
BOSS is the designation for "Biomedical Orbiting Satellite System". The BOSS program uses primates to provide life science data for designing manned space systems.

SAINT
The SAINT program will develop and demonstrate orbital rendezvous and satellite inspection techniques. It will further demonstrate the capability of closing, docking, and refuelling.

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