Proyecto horizonte 12

UVE SOCIETY Fernando de Monreal Clavijo

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Volume I SUMMARY AND SUPPORTING CONSIDERATIONS

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1 InclDraft Requirement

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1.

General

2.

Operational Concept.

3*

Background of Requirement.

A.

References: CD

NSC policy on outerlspace.

(2) b.

Reason for Requirement.

UNCLASSIFIED

UNCLASSIFIED

5.

Degree of Urgency.

6.

Maintenance and Supply Implications.

7.

Training and Personnel Implications.

8.

Additional Items and Requirements.

VOLUME I

9 JUNE 4959

A. GENERAL,

B.

JUSTIFICATION 1.

2.

space.

The B r o a d R e q u i r e m e n t

P u r p o s e of the Lunar Outpost

3. A Realistic Objective

4. Scientific Implications

5. Political Implications

6.

Security Implications

7.

C.

Summar y

CONCLUSIONS

A. OBJECTIVES AND SCOPE OF THE STUDY

B. RESUME OF THE TECHNICAL PROGRAM

C.

OUTPOST

1.

Location

2.. Design Criteria

a. b.

3.

Essentially no atmosphere.

Figure 1-1 shows the HORIZON outpost as it would appear in late 1965, after about six months of construction effort. The basic building block for the outpost will be cylindrical metal tanks ten feet in diameter and 20 feet in length. (Details of typical tanks are shown in Fig. 1-2.) The buried cylindrical tanks at the left-center of Fig. 1-1 constitute the living quarters of the initial construction crew of nine men who will arrive in July 1965. (Details in Fig. 1-3.-) During the construction period, this force will be gradually augmented until a final complement of 12 men is reached. The construction camp is a minimum facility and will be made operational within 15 days after the beginning of active work at the outpost site. Two nuclear reactors are located in holes as shown in the left portion of Fig. 1-1.

These provide power for the operation of the preliminary quarters and for the equipment used in the construction of the permanent facility.

The main quarters and supporting facilities are shown being assembled in the open excavation to the right-center of the figure. These cylinders will also A number ultimately of factors be covered influenced with lunar the decision material.toEmpty locate cargo the main and structures propellant beneath containers the surface. have been Among assembled these were andthe areuniform being used temperfor storage ature available of bulk supplies, (approximately weapons., - 4 0and 째 Flife ) , protection essentials such from as meteoroids, insulated oxygen/nitrogen security, good insulating tanks. Two properties typical surface of the lunar vehicles material, are shown: and radiaone istion a construction protection. Each vehicle of for the lifting, quartersdigging,scraping, and cylinders will etc. be, athe special other isdouble-walled a transport The basic vehicle "thermos completed for more bottle outpost extended type"isvacuum shown distance in tank Fig. trips with 1-4. needed a Significant special for insuhauling, lating additions material reconnaissance, beyond in the thespace items rescue, between illustrated and theinlike. walls.

Fig.In1-1 (Vacuum theare lefttwo background, is additional easily amaintained lunar nuclear Landing power simply vehicle supplies, by venting is cold settling storage the on tank the facility, tosurface. the lunar andAthe void. lightweight conversion ) Despite paraof the bolic ambient the original antenna subsurface construction has been temperature erected campnear quarters of -the 4 0main 째toFa,quarters bio-science the heat to losses provide andfrom physicalthese communications special sciencetanks laboratory. willwith be remarkably earth. low. Investigations 10 show that the

F i g . 1-1.

Fig. 1-2.

_ Fig. 1-4.

4Âť Personnel Equipment

(4) durability against abrasive lunar surface; (5) cleansing and • erilization. Figure 1-5 shows a cutaway and "buttoned up" concept ior such a suit. It should be borne in mind that while movement and dexterity are s e v e r e problems in suit design, the earth weight of the suit can be allowed to be relatively substantial. For example, if a man .nd his lunar suit weigh 300 pounds on earth,_they will only weigh 50 pounds on the moon.

A comprehensive program will be undertaken to provide special hand tools, load-handling gear, and dining to meet In choosing appropriate trajectories to useequipment in this program, the requirements. will be pre-cooked; oneunusual must strike a balance Initially, between all thefood low-energy paths and thehowhigh ever, as water supplies increase with the introduction of a reclaiming energy curves. The low energy trajectories give the highest payload system, dehydrated and fresh-frozen will be used.

Early atcapability, but are sensitive to small foods variations in the injection contention will be given to hydroponic culture of salads and the develop-* ditions and can also lead to unacceptably long transit times.

The ment of energy other closed-cycle foodfaster product higher trajectories are and systems. are not as sensitive to deviations In order in to thecorroborate injection conditions, essential environmental but they resultdata, in payload a series of penalties unmanned and experiments higher terminal are velocities planned. There whichare in early turn require data requiregreater 5. Environmental Research ments braking Several in/the energy areas different at the of radiation, termination trajectorymeteoroid schemes of the trip. impacts, willAbe good used temperatures, compromise in Project magnetic appears HORIZON. tofield, beThey a surface trajectory include conditions, which trajectories will ionization, yield for transit: a transit radio (1)time propagation direct from from earth and biological D. to themoon SPACE earth *• Flight of to effects.

TRANSPORTATION approximately the Mechanics moon, (2) from 50 toearth 60SYSTEM hours.

(307 nautical mile 15 rto a 96-minute

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Fig.

1-5.

T y p i c a l L u n a r Suit

altitude) orbit of the earth, (3) from this 96-minute earth orbit to the moon, and (4) direct from the moon to earth. In addition, there are special considerations for the terminal phase of each type trajectory.

Figure 1-6 illustrates the two basic schemes of transporting man and cargo from earth to the moon.

The first scheme (1 above) is the direct approach, that i s , a vehicle would depart the earth's surface and proceed directly to the lunar surface using a retro-rocket or landing stage for the final landing maneuver.

Since approach the moon would has norequire appreciable rocket The direct a six atmosphere, stage vehicleawith a lifttype propulsion system will be required for the landing.

The second off thrust of 12 million pounds, as compared to a two-million-pound scheme (2 and 3for above) showns cishthat an stage earth and thrust vehicle the orbital e mfor e sproceeding . By placingfirst theinto upper orbit and later departing the orbitthrust for the flightinto to the lunar payload of two-million-pound vehicle orbit, andsurface, with additional again using a landing stage.

In either scheme, the flight time from vehicles as shown, performing a fuel transfer and checkout operation, the ormission, earth moonlarger willtwo be the same. theearth same In the orbitalorbit scheme, thattoofthe transporting much payloads men tocan thebe moon transported and into returning orbit, To illustrate them assuming to earth, this thepoint, vehicle couldit be has size accomplishedbeen to beassumed constant, in and the study by accumulatthat ing the,payloads The first It should direct meninarriving be scheme, orbit, pointed iton which is the out, possible jnoon however, is thetowill most transport that bestraightforward, provided if the a payload United with to an States has the immediate two moon is advantages: on return to have the capability. order a manned first, of tenitFigure lunar times offersoutpost 1-7 (and thedepicts shortest more by 1966, ifthe flight desired) vehicular andtime atthe the from requirements capability same the time earth's ofprovide afor surface single the two first vehicle to schemes. men the arriving lunar flyingsurface directly on thesince moon to the anwith moon. orbital thestopover desired return is not capability, required.

17

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Earth - Moon Transportation Schemes

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2.

Orbital Carrier and Space Vehicles

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First SUgc (Booster)

Second Stag*

third stage will utilize two 100,000-pound thrust H^/O^ engines, a fourth stage will use one such engine.Present feasibility studies inducate a SATURN II payload capability of 70, 000 pounds into a 96minute orbit using three stages and 26,750 pounds to earth escape velocity using four stages. The development of such a vehicle will provide ;e nation a new-optimum vehicle for the utilization of the SATURN booster. The prime requirement for the development of such a vehicle'is an expansion of current high-energy O^/H- engine programs to include development of 100 K and 500 K engines.

Using this orbital system, individual payloads of 48,000 pounds mayAs be Figure mentioned soft-landed 1-12 isearlier, aonconceptual the 6,000 moon.pounds view This of value oftheuseful is operations especially cargo in can significant, the beequasoft-landed torial since earth it represents on orbit. theThe moon theoperation approximate with theindirect orbit minimum method. is principally weight As presented one required of propelherein, for a only lant complete transfer cargo earth will andbe return istransported not vehicle, as assembly inwhich thisjob. manner, is The already vehicle although assembled being there fueled and is aloaded is discussion the with third propellants stage of how of and apersonnel SATURN is capable could II with of also returning a lunar be transported landing several men. and to and return Thus, from vehicle in the moon attached. orderutilizing to provide The third theadirect preassembled stage method. of the SATURN return The second vehicle II was form on used the of conveyance in lunar bringing surface the requires combination during the twotime steps. intoframe orbit Initially and under has theconsideration, required thus expended payloads, it is itsmandatory propellants. which willtoconsist This go ofstage through one is main fueled an initial lunar in rocket orbit earthby orbit. vehicle a crew In and addition of approximately several to providing additional tenapropellant men largeafter which tankers, the individual vehicle willpayload then be placed proceeds capability, in a-96-minute on thethe moon. orbital orbit, It is transportation of planned the earth. to send system At this all offers time, the personnel other propellants important and in approximately advantages. orbit will beAmong 1/3 transferred of the these cargo toare theto that main thethemoon lunar totalby rocket number the orbital of vehicle. method. firings to deliver the same amount of payload 29 to the moon is l e s s and

Fig. 1-12.

payloads may be fired for orbital rendezvous at any given pass every day of the month. This alleviates the launch site scheduling problems which are associated with the restricted firing t i m e s of direct flights.

There are two versions of the lunar landing vehicle. The first type wil1 be used for direct trips from earth to the lunar surface. This vehicle has a gross weight of 26,750 pounds and will soft land some 6,000 pounds of payload. The second vehicle will be used for flights via orbit. It will have a gross weight of 140, 000 pounds which gives it a capability of soft landing approximately 48, 000 pounds of payload An investigation of the guidance problems concerned with Proon the moon. Each type of vehicle will have suitable payload compartject HORIZON indicates that the necessary accuracies and reliabilities ments to accomplish different mission requirements. The lunar landing can be met by adaptations, combination and slight extensions of known vehicle shown in Fig. 1-13 has an earth return vehicle as a payload. and available To sustain guidance the orbital hardware stationand crew techniques. and to provide Final for injection their safe For such return vehicle payloads, the structure of the expended braking" velocity, return to which earth, an marks orbital the return beginning vehicle of the such coast as shown phase of in Fig. the trajectory 1-14 stage will serve as a launching platform when it i s time to begin the to will thebemoon, provided. will be This controlled vehicle may by conventional be used in'conjunction means. Mid-course with another return journey to earth. guidance established will United assureStates that the orbital lunarstation, landingorvehicle it may would be usedcome as a basis within approximately for a minimum20 orbital km (11 station nautical needed miles) to support of the selected Project point.

HORIZON. The It terminal is capable guidance of carrying system, fromwhich 10 to would 16 men. beIttarget will be oriented, carriedwould into orbit reduce by a the SATURN three standard I duringdeviation the first part errorofatthe landing program to approximately and replaced by a SATURN 1.5 km.3. IIGuidance in 1967. and Control 33

in •5

Fig. 1-13.

Lunar Landing Vehicle

E.

TRANSPORTATION SYSTEM INTEGRATION

The development and integration of the space carriers to support HORIZON have been carefu^y outlined and various considerations as to compatibility, size, development schedule, and overall mission have been incxuded and discussed in detail in Volume II. Personnel space transportation requirements to support HORIZON are shown on Fig. I- 15. By the end of 1967 some 252 persons will have been transported into an earth orbit, 42 will have continued to the moon, and 26 will have returned from the moon. The orbital station strength is approximately ten; however, the crew will be rotated every several months. The space transportation system will deliver some N The communications required for Project HORIZON are logically 756,000 pounds oftouseful cargo tocommunications the lunar complex. surface byEach the system, end of 1967. divided Ininto addition an earth-based the 24-hour and lunar-based satellite of these the In order to accomplish this, 229 SATURN vehicle firings will be complexes current"maybe development considered program as having of a world-wide two functions surveillance - communications net will required.

A schedule of launching the broad mission assigned each and surveillance. provide spaceOf surveillance particular significance for and the United forStates the earth-based during the complex I960 era. vehicle isbasic shown in Fig. and I- 16.

Usatellite should system be noted that, to thedevelopsavings is theThe 24-hour communications hardware techniques used in presently this netdue are under directly incurred byillustrated thetobooster recovery system which will be used, total ment." applicable As Communications HORIZON. in Fig. on the 1-17 Figure lunar such1-18 surface a system illustrates will will pose provide schematically special theproblems how number SATURN boosters required to support the program isinnot capability such dueof in aof world a constant largenet part station communications to thecould lack of be atmosphere expanded with bothtospace and support the vehicles relatively HORIZON transit high by the 229 but only 73. and the addition F. curvature lunar COMMUNICATIONS of outpost. of two theadditional surface. However, 85-foot ELECTRONICS antennas careful investigation and35other equipment. reveals no

Fig. 1-15.

Project HORIZON Personnel Space Transportation Requirements

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TRANSPORT VEHICLE

problems which cannot be solved by an appropriate research program.

In a number of areas, current developments appear almost directly applicable; for example, the small helmet-mounted radio currently in production and troop u s e . A microminiaturized version of this, presently r advanced development, will provide a basis for personal communication between individuals clad in lunar suits. As the lunar outpost expands, radio relay stations will extend the radio horizon as conceived in Figure 1-19.

In to voice communication between of the lunar Theaddition equatorial location of the new launch sitemembers would provide very party, a number of other electronic devices will be used at the outreal advantages in terms of payload capability, guidance simplicity, post.

These include TV receipt and transmission, transmission of of and operational launching schedules in terms of increased latitude still photographs, location devices, selfappropriate firing homing t i m e sand . Two sites stand out instantaneous when compared to others contained emergency communications packs (for distress signals to Brazil and Christmas Island. Both of these ' c*locations appear feasible; earth), infrared detectors, and radar detectors. however, A survey more was made detailed to determine criterial will the have adequacy to be of established the Atlantic to make Missile the best Range choice. and Cost Pacific andMissile early availability Range for the mayaccomplishment ultimately be the of Project governing The HORIZON. results factors. of The this It is results study emphasized are of this discussed that survey site in indicated acquisition detail in that, Volume and all initiation things II and G. LAUNCH SITE ,_ being ofillustrated launch considered, site in construction Fig. neither 1-20.site A total is was one suitable. ofofeight the most launch Sincecritical apads new are items launch required. insite the prowillgram This be required, with facility respect will a study support to leadtime. was the made requirements For to the determine purposes ofthe HORIZON ofoptimum this study and location itwould has also andbeen provide requirements assumed additional that for such the capacity Brazil a site.-„•__-_. for siteother would United be used.

States 39~")programs. ~~

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Fig. 1-19.

Lunar Communication Net

Fig. 1-20.

Terrestrial Launch Site

H. PROGRAM LOGISTICS

I. RESEARCH AND DEVELOPMENT

1.

2.

Basic and Supporting Research

Project HORIZON Development Program

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Fig. 1-22.

A.

SCOPE OF OPERATIONS 1.

General

2.

Terrestrial Launch Site

3.

Orbital Station

b.

Space laboratory for equipment.

c.

Materiel storage space.

d.

Low-altitude communication relay.

f.

Space surveillance.

g.

Meteorological surveillance.

h.

Survey/geodesy data collection.

i.

4.

Lunar Outpost

a.

V

b.

c#

Construction

B. 1. Gene ral

c. nations.

3.

Staff Organization

A.

GENERAL

B.

POLICY

330 • Appendix

C. 1.

Political and Psychological

(5) Utilization of knowledge gained during first phases of outpost operation.

(6) Extent to which national policy requires attainment of specific military or scientific capabilities.

(7) State-of-the-art improvement in rocket booster engines, particularly in specific impulse, thrust, and weight.

2. National Security

(2) Evaluation of the significance of lunar operations within the broader framework of the total national defense.

62