fifteenth semiannual report to congress, jan. 1 - jun 30, 1966

8/7/2019 Fifteenth Semiannual Report to Congress, Jan. 1 - Jun 30, 1966

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FifteenthS E M I A N N U A L

R E P O R T T OC O N G R E S S

JANUARY I - JUNE 30, 1966

NATIONAL AERONAUTICS AND SPACE ADMINIST

WASHINGTON, D. C.20546


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Surveyor I (cover) and other illustrations prepared by AlfredJordan, Visual Aids Branch, Office of Administration, NASAHeadquarters.

__~ ~~ ~~~_ _ .I'or salr hy th o Suprrlntrndent of Documents. U.S. Government PrlntlnR OffICO

WnRhington, D.C. 20402 - Prlee $1


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Contents

HIGHLIGHTS . . . . . . . . . .ACTIVITIES AND ACCOMPLISHMENTS.. . .Chapter 1-Manned Space Flight- _ _ - _- _ _ __ _ _ __ _ _ _ _ __ - - _ -

Gemmi Program _ _ _ _ _ _ _ _ - _ _ _ _ _ - _ _ _ _ _ _ _ _ _ _ _ _ _ _Gemmi VI11 _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ __ _ _ _ _ _ _ _ _ _ _Gemini VI11 Experiments--_ _ __ __ _ - __ - - _ _Gemmi IX-A _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ __ _ _ _ _ _ _ _ _ _ -Gemini IX-A Experiments- - _- _ - - _ _____ _Medical Results of Gemini VI11 and IX-A- -Development, Production, and Test _ _ ____ _Gemini Mid-Program Conference- - - __ __ _ _-

Apollo Program- - - - _- - _ _- - - - _ _ _- ___- - _- __ _ _ _Specific Missions and Objectives _ _ __- - - - - -Development and Testing of Spacecraft- - - -

Launch Escape System _ _ _ _ _ _ __ _ __ __ __ _ _ __Launch Vehicles-_ - _ _ _ _- - - _- - - _- _ __- _- - - -Uprated Saturn I (Saturn IB) _ _ _ _ _ _ - -Saturn V _ _ _ _ - _ - _ _ _ _ _ _ _ _ _ - _ _ _ _ _ _ _ _ _ _Saturn V Dynamic Testing- _ _ _ _ __ _ - _ -

Apollo Lunar Surface Experiments Package(ALSEP) _ _ _- - - ___ _- - - - _ ___- - _- _- - - _-

Astronaut Actinties - - - - - - - - _ __- - - _- - - - ___- -Apollo Applications- - - - - - _ ___- - - - - _- - _ _- _ _ _ _-

Program Management __- _ __ _- - _- - _- - - - - -Flight Hardware- - - - - - - __- - - - - - - - ______ _Experiments - ___- - - - _ _- _ - - - __- - - - _- _- - - -Program Obi ectives- - - - - - _- - - - - - - _- _- _- _ _Mission Objectives _ _ _- - - - - - _- - - - - - - - - - - -

Advanced Manned Missions- _ - _- - - - - - - - - - - - - -Construction of Facdities- _ - - - - - - - - - - - - - - - - __-Space Medicme- - - _- _ _- - - - - _- - - _- - _ __- - - - - - -

Military Medical Personnel Requirements- -Cooperation with USAF in MOL Program- -Reorganization of Medical Capabilities a t

MSC- __ __- - - - - - _- - - _ _- - - - - - - __ - - - - - -Medical Data Analysis Program_- - - _- - _- -General - _ - - _ _- - - - - - - - _- - - - - - - - - - - - - - _

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HIGHLIGHTS

Gemini VIII, the sixth manned Gemini mission, was conducted onMarch 16. Wi th Astronauts Neil A. Armstrong and David R. Scottaboard the spacecraft, Gemini VI11 accomplished th e second rendez-

vous and the first docking mission of the program.The Gemini IX-A spacecraft, with Astronauts Thomas P. Staffordand Eugene A. Cernan aboard, was successfully launched on June 3.

Gemini IX-A successfully rendezvoused with the AT DA (Aug-mented Target Docking Adapter) during the spacecrafts third revolu-tion (but did not dock because the ATDA shroud did not completelyseparate).

Astronaut Cernan carried out extravehicular activity for 2 hoursand 5 minutes on the th ird day of the Gemini IX-A mission.

The first uprated Saturn I (Saturn IB) mission w as completedon February 26. This was an unmanned suborbital flight.

The first alt itude testing of the complete Lunar Module descentpropulsion system was carried out at White Sands Test Facility(WSTF) .

The Apollo Launch Escape System w as declared qualified for flightfollowing the final test in January at WSTF.

The Manned Space Fl ight Center-built first S-IC flight stage was

acceptance tested on the single position test stand in February. Thesecond flight stage was successfully acceptance fired on June 6.The first flight unit of the Saturn V th ird stage (S-IVB-501) was

successfully acceptance fired on May 26.On May 26, the Crawler Transporter lifted the Launcher Umbilical

Tower and the Apollo/Saturn 500F and moved the combined unitsto Pad A in a nine-hour trip.

Nineteen new pilot/astronauts were assigned to the Manned Space-craft Center in May.

The last major laboratories were completed at the Manned Space-craf t Center in Houston.

0

I n June, Surveyor I soft landed on the moon and began to transmithigh-resolution pictures of the lunar surface. The thousands of pic-tures will be used in planning for manned lunar landings.

Two observatory type satellitas were launched: the first OrbitingAstronomical Observatory in April, and an Orbiting Geophysical

Observatory carrying 21 scientific experiments in June.Preparations were also underway for launching the first Biosatellite(an orbiting biological laboratory) and the first Lunar Orbiter whichwill make photographs of the moons surface for use in selectingpotential landing sites for manned spacecraft.

I n May, Explorer X X X I I was orbited to observe and report on theneutral components and the charged ions of the upper atmosphere.

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4 NASA FIFTEENTH SEMIANNUAL REPORT TO CONGRESS

Mariner I V (which flew within 6,118 miles of Mars in Ju ly 1965)transmitted data as it passed behind the sun a t a distance of 219 millionmiles from the earth. This was the first time that coherent radio-frequency energy has passed through the solar corona and been

monitored by earthbased receiving stations.Pioneer VI-launched December 16, 1965, to survey interplanetary

space during a complete solar cycle-collected and returned substan-tial data covering 900 hours of flight time.

I n ,June, PAGEOS-I, the second spacecraft in the U.S. geodeticsatellite program was orbited. It serves as an orbiting point of lightas bright as the star Polar is for use in precision mapping of the earthssurface.

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A highly sophisticated, completely-instrumented Nimbus I1 space-craft was launched in May to furnish data for more accurate weatherforecasts; in February, the launchings of ESSA-I and -11 markedthe opening of the national operational weather satellite system.

Two second-generation commercial communications satellites(INTELSAT-11) were being rmdied fo r launch by NA4SA for theCommunications Satellite Corporation late in 1966. Positioned ingeostationary orbit-ne over the Atlantic, the other over the

Pacific-the satellites will provide earth coverage in both the Northernand Southern hemispheres.A Gravity Gradient Test Satellite was launched in Jun e to help de-

termine if the gravitational pull of the ear th can be used t o stabilizespacecraft in high orbits.

Prototypes of instruments which will be used in NASAs earth re-sources survey program were evaluated in airborne remote sensor tests.

The first Applications Technology Satellite (ATS)-which willconduct experiments in communications, meteorology, and geophysics-completed major qualification tests and was scheduled to be launchedin December.

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The three Pegasus satellites continued to return valuable meteoroidpenetrations data which are used in the design of advanced spacecraft.

The reentry E experiment of the Scout reentry heating project wasflown in February. It provided useful data on nosecap material be-havior under reentry heat conditions and information on scaling laws.

NASA received the second of it s two lifting-body research vehicles,the HL-10, and began wind tunnel tests of the craf t. The M-2 madethree captive flights (two of them manned) and several tax i tests.

Research was conducted on a concept for a radio telescope n i d e upof a parabolic shaped network of fine wires about one mile in diameterorbi tinga t an altitudaof 3700 miles.


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HIGHLIGHTS 5

A visual aid, the standoff cross, was developed for astronaut use inrendezvous and docking maneuvers and incorporated into the Apollolunar module design.

Measurement devices developedto

determine human response to thespace environment included radio transmitters small enough to beswallowed or implanted under the skin, spray-on electrodes, and pocketsize data recorders.

A second 260-inch solid motor was test fired in February, producinga peak thrust of over 3.5 million pounds, burning for 114 seconds nearpeak thrust, and delivering useful thrust for a total of 130 seconds.

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The Nations first nuclear rocket system, a breadboard enginecalled the NRX/ ES T, was power tested.

Two significant NJXX-A5 reactor experiments were conducted(Jun e 8 and June 23), with the reactor operating in general accordancewith design predictions.

The first 35 KWe S N A P 4 breadboard power conversion system,using the first generation of components, was operated for the firsttime.

Work was underway to develop a small (15-watt) ion engine for the14pplications Technology Satellite.

I n he electric thrustor area, one ion engine, under endurance testing,had accumulated over 4500 hours as of the end of this report period.

A mercury bombardment engine had also been tested for about 4000hours.

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STADAN (Space Tracking and Data Acquisition Network) sup-ported 43 satellite programs during the period, eight of which were

launched since January 1 (four NASA satellites, four belonging toother government agencies).

The first Apollo Instrumentation Ship, the USNS Vanguard, wascompleted and testing started.

Th e eight Apollo/Range Instrumentation Aircraft were undercontract.

The 210-foot antenna located at Goldstone, California, was dedi-cated in April and became operational shortly thereafter.

The Deep Space Network provided continuous control of SurveyorI dur ing its flight to the moon and after its landing.

Nine countries cooperated with NASA on scientific sounding rocketexperiments, and agreements for new experiments were concludedwith Germany, the Netherlands, and Spain.


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Arrangements were made with seven countries for operational sup-port of new o r continuing NASA projects.

Over 2700 foreign nationals from 92 locations visited NASA facili-ties for scientific and technical discussions or general orientations.

Under the NASA International University Fellowship Program, 38graduate students completed their studies while 53 either entered theprogram or continued their studies.

By June, 164 grants or contracts had been awarded to 153 institu-tions for advanced training under NASAs sustaining university pro-gram. Predoctoral training program grants were awarded to 152 uni-versities, 10 entering the program for the first time. By the end of

.June, 272 NASA trainees had earned the Ph.D.I n a program enabling postdoctoral investigators to conduct ad-

vanced research at a NASA field center, 104 individuals were on tenureat 6 centers and the Goddard Institute for Space Studies.

Support or multidisciplinary space-related research in science andtechnology was provided to 48 educational institutions, an increase of12 over the last period.


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I

FLIGHT

M A N N E DSPACE

I

During the first half of 1966, significant manned space flight achieve-ments included two Gemini missions and the Apollo Saturn missioninitiating the flight phase of the Apollo program. The Gemini VI11and IX-A missions were completed, and the first suborbital flight testof the uprated Saturn I launch vehicle with the unmanned ApolloCommand and Service Module spacecraft (AS-201) was conducted.

The Apollo Sat& I flight, one of a number of major Apollo pro-gram milestones, was completed on schedule after more than threeyears of program development effort. Future milestones include thefirst manned flight of the Apollo/uprated Saturn I and the first un-manned flight of the Apollo Saturn V, both scheduled for 1967; andaccomplishment of the Apollo lunar mission, scheduled to t,ake placebefore 1970.

Construction and activation of necessary facilities in support of theApollo program continued on schedule. On May 25 the crawler-transporter for the first time moved a fully assembled Apollo Saturnspaca vehicle from the Vehicle Assembly Building (VAB) to thelaunching pad A a t Launch Complex 39.

The overall objectives of the Apollo Applications program werefurther defined and additional major effort was directed toward es-tablishing NASAs later post-Apollo space program goals.

I n April, organizational changes in the Kennedy Space Center were,approved, including establishment of a new position of Deputy D i m -

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tor, Center Operations and formation of an Executive Staff in supportof the Center Director. The changes resulted from the rapid buildupof KSC in the past three years, the assignment of both manned andunmanned launch program responsibilities, and the quickened paceof Apollo program launch preparation.

In addition, nineteen new pilot/astronauts were assigned to themanned space flight program and began their tra ining activities.

Gemini Program

I n the five manned Gemini flights of 1965, the investigation of theeffects of long duration flight was completed, extravehicular activity

was demonstrated, and the first rendezvous of two spacecraft in spacewas achieved. Two of the manned Gemini flights were conducted tocontinue the development and investigation of rendezvous techniquesand procedures, and to extend our knowledge of manned extravehicularoperations. During the Gemini VI11 mission in March, the first dock-ing of two spacecraft in space was successfully accomplished. I n thecourse of the Gemini IX-A mission in June, extravehicular activitywas conducted for more than two hours, and three methods of rendez-vous were executed and evaluated.

Gemini Vlll

The Agena Target Vehicle test program, instituted by NASA andthe Department of the Air Force in October 1965 to confirm t he causeof the Gemini VI-Agena failure and t o test corrective modifications,was successfully completed in March. The Gemini VIII -Agena Tar -get Vehicle was consequently modified to a new configuration anddelivered to Cape Kennedy for the Gemini VI11 mission.

The sixth manned Gemini mission (Gemini V I I I ) was the secondrendezvous mission and the first docking mission of the program. TheAi2gena Target Vehicle was launched from Complex 14 at 0 : O O a.m.(e.s.t) on March 16. The Gemini spacecraft, with Astronaut Neil A.Armstrong as command pilot and Astronaut David R. Scott as pilot,was launched oiie hour and 41 minutes later from Complex 19. (Fig.1-1.) Rendezvous and docking with the Agena Targe t Vehicle \vas ac-complished as planned during the fourth revolution of the spacecraft.

The rendezvous phase of the mission mas completed aft er five hoursand 58 minutes of spacecraft flight, and nine spacecraft maneuvers,when spacecraft VI11 was 150 feet, from the Agena Target Vehicleand all relative motion between the two vehicles had stopped. (Fig.

After station keeping for 36 minutes (fig. 1-3), spacecraft VI11docked with the Agena Target, Vehicle, and the Target Docking

1-2.)


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Figure 1-1. Gemini Vlll launch, March 16, 1966.


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Figure 1-2. The Agena Target Docking Vchiclc seen from Gemini VIII.

Adapter was rigidized, combining the two vehicles into one spacevehicle. This docking event marked the attainment of another Gemi-ni program objective, a vital step toward the Apollo lunar mission.

The stability and control of the docked vehicles were excellent for27 minutes afte r docking, until the combined vehicle began to de-velop unexpected roll and yaw rates. Subsequently, the crew foundit increasingly difficult to control these rates without excessive use ofOrbit Attitude nad Maneuvering System (OAMS) propellants.

To isolate the problem, the crew undocked the spacecraft from theAgena Target Vehicle. After undocking, spacecraft roll and yawrates continued to increase. When these rates reached 300 degreesper second, the crew completely d e a c t h t e d the OAMS and activatedthe Reentry Control System (RCS) . Using malfunction analysisprecedures, the crew determined that a thruster in the OAMS wasmalfunctioning.

Inasmuch as the primary function of the Reentry Control Systelrl(RCS) s to control the spacecraft dur ing reentry and the system hadbeen used to gain control of the spacecraft, the Mission Director de-cided to terminate the flight in the seventh revolution.

The crew made a controlled reentry and landed within seven milesof the planned landing point in the recovery area in the Western Pa-


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Figure1-4.

GeminiVll l

Astronauts Armstrong and Scott afte r splashdown in Pacific O cea n.

Nuclear Emulsion. A fourth experiment, Si-l&Agena Micromete-orite Collection, was installed on the Gemini VI11 Agena TargetVehicle; plans call for retrieving this experiment during the extra-vehicular activity period of the Gemini X mission. Six other experi-ments were incomplete because of the short duration of the mission.

Gemini IX-AA4fter a

successful countdown and liftoff of the Atlas/Agena Target Vehicle,a malfunction occurred in the Atlas Launch Vehicle that resulted in anerratic trajectory and loss of the -4gena Target Vehicle.

The US AF Space System Division investigation to determine thecause of the Gemini I S Atlas malfunction concluded that the probablecause \vas an electrical short in the guidance and control system. I n -dications were that the short cnwed one of the booster engines to go to:I pitch down position. The other booster engine reacted norm:~lly y

going to a pitch lip position, resulting in a rapid pitch down/rollmaneuver. During thi s m:uieiiver the ground based guidance W:LS lost,:md R normal switch over to the backup guidtince system \vas made.Although the backup system operated, its reference was lost during theinitial maneuver. The Atlas continued to fly but iissumed nn incorrectflight p:Lth, and the flight WLS terminated prior to ignition of the

The Gemini IX mission \vas first attempted on May 17.


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M A N N E D SPACE FLIGHT 15

Agena main engine. The malfunction was considered a random fail-ure unique to the Gemini IX Atlas vehicle, requiring no vehicle designchanges.

As described in NASAs Fourteenth Sentiannual Report (p. 22) , naugmented target docking adapter (ATDA) was added to the Geminiprogram as a backup for the Agena Target Vehicle. The availabilityof th is vehicle along with a pre-arranged turn-around plan allowedNASA to recycle the Gemini I X mission (redesignated IX-A) in14 days fo r a planned June 1 launch. From Complex 14 at KSC, theATDA was launched at 1O:OO a.m. (est.) on June 1, attaining thecircular orbit of 161 nautical miles. Countdown of the Gemini IX-Aspacecraft continued to T minus 3 minutes (a planned hold, wherefinal ground corrections for spacecraft orbit insertion are made). A tthe resumption of the countdown, the spacecraft would not acceptits launch azimuth update information. The optimum time for launch-ing the spacecraft for the planned rendezvous was exceeded and space-cr af t launch was rescheduled to Ju ne 3.

On June 3, at 8:39 a.m. (e.s.t.), the Gemini IX-A spacecraft waslaunched with Thomas P. Stafford as command pilot and Eugene A.Cernan as pilot. The crew executed a number of rendezvous ma-

neuvers and rendezvoused with the A TDA as planned during th e thi rdspacecraft revolution. As the spacecraft completed its terminal phaseof rendezvous, the crew confirmed visually what telemetry had par-tially indicated to the ground during the ATDA insertion into orbiton June 1. The shroud that protects the ATDA from aerodynamicforces and heating during the launch phase had not completely sep-arated, thus preventing completion of the docking maneuver. (F ig .1-5.) Based on the crews in-flight observations of the partiallyopened shroud and a ground analysis of the separation mechanisms,

the problem was traced to improper rigging of lanyards used toseparate electrical wiring between the shroud and the ATDA. Sincesimilar lanyards are also used on the Agena vehicle, corrective meas-ures were taken to prevent a recurrence on later Gemini missions.

The initial rendezvous simulated the planned Apollo Lunar Modulerendezvous with the Command and Service Module. Two additionalrendezvous maneuvers were later executed by the Gemini IX-A crew.The last of these was a Lunar Module Abort Simulation. Althoughextremely difficult to execute, this rendezvous simulation was com-pleted successfully and provided significant experience for the crewand the flight controllers at the Mission Control Center.

On the thi rd day of Gemini IX-A, extravehicular activity (EVA)was conducted for 2 hours and 5 minutes. (Fig. 1-6.) This EV Aprovided the second step in the understanding and development ofmans proficiency in extravehicular operations. During th is EVA,

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Figure 1-5. The "Angry Alligator"-ATDA with pa rtia lly opened protective shroud stillattached.

evaluations were conducted of tether dynamics, umbilical operations,dark side operations, Velcro hand holds, and mechanical hand rails.

A major pa rt of the EV A planned for this mission w as to includeexperiment D-12, Astronaut Maneuvering Uni t (A MU) . This unitw as stowed in the adapter section of the spacecraft where it \vas tobe checked out and donned by Astronaut Cernan. Af ter the checkoutand donning were completed, the astronaut would conduct variousmaneuvers with th e AMU while attached to the spacecraft by a 100foot tether.

The amount of work required of the astronaut to perform his as-signed EVA tasks w as much greater than anticipated and resultedin fogging of his helmet and visor. Checkout of the AMU was satis-factorily completed; but hecause of the limited visibility resultingram the fogged visor, the command pilot ordered Astronaut, Cernan

to return to the spacecraft cabin without, conducting the experiment.An antifogging compound will be used on the remaining EVA mis-

sions to eliminate visor fogging.As in Gemini V I I I , a controlled reentry \VRS flown and the space-

craf t landed within 2.8 miles of the planned landing point. Th is wasthe best executed controlled reentry of any mission to dtite, and was


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17ANNED SPACE FLIGHT

,Figure I d . Astronaut Ccrnan during EVA.

the four th successive time the Gemini spacecraft had landed within 7miles of the planned landing point.Gemini IX-A Experiments

The Gemini IX-A mission made highly important cmtributions inthe field of scientific experiments. All three of the principal scientificinvestigators with experiments originally planned for this flightpraised the astronauts and other members of the Gemini team f or the


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08 NASA FIFTEENTH SEMIANNUAL REPORT TO CONGRESSdata obtained during the flight. Seventeen high quality photographswere obtained for the Zodiacal Ligh t Photography experiment. TheZodiacal light is believed to result from sunlight reflecting on smallparticles in orbit about the sun.

Approximately 45 photographs were obtained for the Airglow Hor-izon Photography experiment. (Fig. 1-7.) The night airglow layercan be seen as a narrow br ight band lying above the night-time hori-zon. Caused by sunlight excitation of the upper atmosphere, the re-sulting airglow persists into the nighttime.

Eighteen hours of exposure time, including a 10-hour bonus result-ing from the flight plan changes, were obtained for the s-12 Micro-meteorite Collection experiment. The purpose of th is experiment was

to expose biological samples to the space environment, collect micro-meteorite particles, and examine craters caused by micrometeorites.Another experiment, the S-10 Agena Micrometeorite Collection ex-periment, w as rescheduled to the Gemini X mission which was plannedto include E V A to he Target Vehicle.

Real time flight plan changes made it possible t o add an experimentand obtain approximately 50 photographs of the South Americancontinent for the S-5 Synoptic Terrain Photography studies. (Fig.1-8.) Before the Gemini IX-A mission, very few synoptic terrainphotographs of the South American continent had been obtained.

Medical Results of Gemini Vlll and IX-A

The significant medical features of these flights were primarily theunique stress environment encountered in Gemini VI11 and the extra-vehicular activities in Gemini IX-A.

The Gemini VI11 crewman performed satisfactorily throughoutthe emergency caused by the failure in the spacecraft Orbit Attitude

and Maneuvering System. Roll rates during this period exceeded 180'per second for approximately 4 minutes with maximum rates in therange of 300 degrees per second, lasting a t least 1 minute. During theperiod of maximum roll, the crewmen were able to see the circuitbreaker panel by holding the head back and turning slowly to theappropriate side. Neither nausea nor other physiological problemswere induced by this activity, although the head movement usuallyused to see the circuit breakers-a forward, twisting motion-causedvertigo dur ing this period of extreme roll. Hear t rates were increwed

slightly dur ing the emergency period.After landing, nausea and vomiting, induced by a relatively rough

sen, were experienced by the crew. Medical examinations followingthe landing failed to reveal any notkeable effects of the flight.

n a t a for Gemini IX-A were still being analyzed at. the end of theperiod. However, the crew members were in excellent condition a t the


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20 NASA FIFTEENTH SEMLANNUAL REPORT TO CONGRESS 0~~

Figure 1-8. Central coastal are a of Peru showing pat h of 1962 avalanche.

problems and showed the crews physiological status to be good for theEVA.

Th e pilot left the spacecraft without difficulty. The extravehicular

activity followed the flight plan fo r approximately 52 minutes; a t thattime the pilot, reported R fogging of the visor during checkout of theAstronaut Maneuvering Unit. Approximately 27 minutes later, thepilot reported that his visor was still fogging. H e then returned to thespacecraft umbilical an d mnq h c k in the spacecraft within the nesthalf hour. The total EVA time was 2 hours and 5 minutes.

During the EVA, the pilots heart rate was typically higher than tha tof the command pilot. Following the extr:ivehiculnr :Lctivity, thecommand pilots heart rate quickly returned to normal levels; that ofthe pilot declined slowly over :I period of 8 hours. 7V:iter intake fol-lowing the extrnvchiculnr activity increased for hoth the crewmen,with the pilot drinking about three times as much as the commandpilot.

Th e third nights sleep W R S scheduled for 8 hours, but both crewmenslept lightly for less than that time. However, following the sleep


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period, both sounded alert during voice communications and their bio-medical da ta were normal. Both were in excellent physical conditionafter completion of the flight.

Development, Production, and Test

The Gemini space vehicle consists of a spacecraft and a modifiedTitan I1 launch vehicle. The target vehicle used f o r a rendezvous mis-sion consists of an Atlas Standard Launch Vehicle (SLV-3) and theGemini Agena Target Vehicle. Development and qualification of thesemajor elements have been completed, with production and deliveryscheduled to be completed i n the 3d quarter of 1966.

Spacecraft V I II , IX, and X were delivered to Cape Kennedy dur-

ing this period. Spacecraft XI completed systems test and was to bedelivered in July. Spacecraft XI1 was in assembled systems test.

Gemini Launch Vehicle (GLV) 8 was delivered in January. GLV9 was delivered in March, and GLV 10 was delivered in May. GLV11 was to be delivered in July, and GLV 12 was i n final systems testin the Vertical Test Facility.

Atlas 5303 for the Gemini I X mission was delivered in February.Atlas 5304, originally planned f o r Gemini X, was used to launch theATDA for the Gemini IX-A mission. Atlas 5305, scheduled forGemini X, was delivered in June. At las 5306 was .to be delivered inJuly. This vehicle wasadded t o the program to replace the Atlas used to launch the ATDAon the Gemini IX-A mission.

Agena 5003 was delivered in January and launched in March as therendezvous and docking target fo r the Gemini VI11 Mission. Agena5004 \vas delivered in March, Agena 5005 was delivered in May, andAgena 5006 was to be delivered in July. Agena 5001, planned for use

on Gemini XII, was in final phases of production and assembly.Gemini Mid-Program Conference

A 3-day (Feb. 23-25) Gemini Mid-Program Conference a t theManned Spacecraft Center reviewed f o r representatives of govern-ment, industry, and the scientific community, administrative and oper-ational achievements of the program through missions VI-A and VI I .Proceedings of the conference were published in KASA SP-121 (avail-able from the U.S. Government Printing Office, Wnshington, D.C.

20402, $2.75). The second and final conference will be held early in1967, following completion of the Gemini program.

Atlas 5307 was in final stages of assembly.

Apollo ProgramThe momentum of the Apollo Program increased rapidly during the

first. half of 1966, midpoint in the program which will culminate in


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manned flights to the moons surface and safe return to earth of theApollo astronauts. I n February, the flight test phase of the upratedSaturn I (Saturn I B ) Program opened with the successful mission ofAS-201. This mission was the first in a series of unmanned flightsto test the Apollo Saturn I space vehicle and to qualify the combinedvehicle systems for manned flights in earth orbit.

A t the end of the period a Saturn launch vehicle stood on each of thethree Apollo launch complexes at Cape Kennedy. AS-203, the nextvehicle to be launched in a test of the launch vehicle only, stood onLC-37; AS-202, a fully assembled Apollo uprated Saturn I spacevehicle, was on LC-34; and the fully assembled Apollo Satu rn Vfacility checkout vehicle (AS-500F) was on Pad A of LC-39.

Specific Missions and ObjectivesThe first uprated Sa turn I (Sa turn I B ) mission, an unmanned sub-

orbital flight, was successfully completed on February 26. (Fig. 1-9.)This marked the beginning of a major new phase in Apollo FlightOperations.

The major objectives of this mission were to prove out the launchvehicle, to demonstrate the compat ibility and structural integrity ofthe CommandPService Module (CSM ) and the uprated Sa turn I

vehicle, to verify the spacecraft subsystems, to demonstrate spacecraftheat, shield performance, and to demonstrate the adequacy of themission support facilities.

Lift-off from Launch Complex 34 at Cape Kennedy occurred at11 :12 a.m., e.s.t. The first stage functioned according to design, cut-ting off after 2% minutes to complete a successful first phase of theflight,. The second stage ignited and burned fo r over 7 minutes.Guided by the Instrument Unit, it placed the spacecraft into theproper trajectory, culminating a highly successful performance bythe launch vehicle. The trajectory had an apogee, or high point, ofapproximately 300 miles.

After spacecraft/launch vehicle separation, the spacecraft propul-sion system was fired twice, a verification of its stop/start capability.I t propelled the command module back into the atmosphere a t a speedof approximately 27,000 feet per second. This imposed reentry con-ditions more severe than in either Mercury or Gemini and provideddata important for the Lunar Mission reentry. The command module

impacted some 4,500 miles downrange in the South Atlantic nearAscension Island (fig. 1-10) and w as recovered by the U.S.S. Bomr,the primary recovery ship, a t 2 :20 p.m., e.s.t,.

During the mission, the spacecraft systems functioned within designspecifications, although the propulsion system performance was some-what irregular. The spacecraft heat shielding experienced greater


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24 NASA FIFTEENTH SEMIANNUAL REPORT TO CONGRESS e

!

Figure 1-10. Apollo spacecraft in South Atlantic.

ablation than expected in three spots ; however, it prevented interiortemperatures from exceeding human limits and essentially provedthat the basic design was sound and men would have returned safelyfrom earth orbit.

The second Apollo/uprated Sa turn I launch development mission, tobe launched a t Cape Kennedy early in Ju ly 1966, is to be a unique

engineering study of liquid hydrogen behavior in the launch vehicleupper stage during orbital flight. The primary purpose of th is un-manned mission is to observe operation of the two-stage launch vehiclesS-IVB second stage prior to its use as the third stage of Saturn V inthe manned lunar landing program.

Development and Testing of Spacecraft

I n the Apollo Command and Service Module spacecraft groundtest program, many critical hardware tests were completed and othermajor tests were still underway. Propulsion testing a t Whi te SandsTest Facility (WSTF) ,New Mexico, using Service Module (SM) 001,was essentially completed. This testing culminated in R series of in-tegrated tests of fuel cells, cryogenic systems, and the service propul-sion system. The Block I service module engine and the Block Ipropellant gaging system both completed qualification during this


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M A N N E D SPACE F L I G H T 25

period. Meanwhile CSM 011 subsystem factory checkout was com-pleted, the heat shield was fitted, and the CM (Command Module)mated to the SM. Following integrated testing, the modules wereseparated and delivered to KSC for flight on the second Apollo/up-rated Satur n I mission, AS-202.

The lunar configured Block I1 Command and Service Module under-went a critical design review during the period. Apollo programpersonnel from the Manned Spacecraft Center and Headquartersconducted an intensive review with the spacecraft contractor to makesure the design would satisfy the requirements for a lunar mission.Particular attention was given t o the design features required for alunar mission but not included in the Block I spacecraft, especiallythe docking equipment and a thicker heat shield. A period of intensivetesting was underway to qualify the Block I1 spacecraft fo r flight in1967.

Manufacture of the first three Block I1 spacecraft was nearly com-pleted. One of these is to be used fo r thermal vacuum testing a t theSpace Environmental Simulation Laboratory a t the Manned Space-craft Center, one is scheduled to fly on an uprated Saturn I launohvehicle, and the third is to be launched by a Saturn V launch vehiclein 1967.

The Lunar Module (LM ) design was essentially complete, withdelivery of the first flight vehicle, L3-1, scheduled in the second halfof 1966. A critical design review of the LM was successfully completedin March. The final significant design decision was the selection ofa radar system to be used for rendezvous in lunar orbit.

The first altitude testing of the complete LM Descent PropulsionSystem was carried out on a descent propulsion test rig at White SandsTest Facility. Altitude testing of the L M Ascent Propulsion System

began, and the first series of propellant flow tests mere successfullycompleted. The second phase of the LM Descent Propulsion Systemaltitude testing was started, and combined system tests were com-pleted before the. beginning of propellant flow testing.

The L M Structure Test Vehicle, a structural mockup of the L Mascent and descent stages with simulated equipment, was successfullyused in the initial L M launch vehicle dynamic tests conducted atMSFC. Following these tests, the vehicle was being refurbished forflight on AS-5Q2.

During the period, the Thermal Analysis Verification Vehicle, afull-scale thermal model of the LM , was undergoing thermal vacuumtests. Results of these tests vere leading to thermal design improve-ments expected to be verified on the LM Thermal Vacuum Tests Vehiclewhen testing is initiated.

(Fig. 1-11.)


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06 NASA FZFTEENTH SEMIANNUAL REPORT TO CONGRESS

Figure 1-1 I. Crated Command Module 01 I arrives at KSC.

An essential part of the equipment required for a lunar mission isthe space suit. Modified Gemini suits to be used for early Block Iea rth orbital spacecraft missions were undergoing Apollo qualificationtesting, and the first flight suits were scheduled fo r delivery in August.-1 ritical design review fo r the Block I1 Extravehicular Mobility Un it

( E M I J ) w as completed in ,June nnd no significant deficiencies werefound. The EMU, consisting of the ,Ipollo Block I1 space suit andportable life support system, is designed for use in the lunar landingmission aiid will be tested in earth orbi t in 1967. (Fig. 1-12.)

Launch Escape System

A significant milestone achieved early in the period was the flightqualification of the Apollo Launch Escape System. The rocketpowered system is designed to separate the spacecraft commandmodule from the space vehicle and propel it to safety in th e eventof an abort situation on the pnd or in early powered flight.

The flight on which qualification was completed took place in Ja n-unry at WST F, as shown in fig. 1-13. The launch vehicle. was theLittle Joe I1 which had been used in fou r previous tests under varyingnbort conditions. With the successful completion of this final test, an


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Figure 1-12. The Apollo Block II space suit.


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Figure 1-1 3. Intermadiute al t i tu de abo rt test.


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M A N N E D SPACE FLIGHT 29II intermediate altitude abort simulation, th e Launch Escape System was

declared qualified f or manned missions.

Launch VehiclesDevelopment and testing of the up-rated Sa tu rn I and the Saturn

V continued satisfactorily during the period.Uprated Saturn Z ( S a t u r n ZB).-The uprated Sa tu rn I is the

launch vehicle to be used in the first Apollo manned mission, whichwill be flown in earth orbit. Its liquid oxygen/liquid kerosene firststage (S-IB.) is similar to the original Saturn I first stage but itweighs less and has greater thrust (1,600,000 pounds). The liquid hy-drogen/liquid oxygen second stage (S-IVB) is totally new. It hasa thrust of 200,000 pounds, greater than any previously flown hydro-gen/oxygen stage. Powered by the J-2 engine, it is the same as thethird stage of Saturn V. The Instrument Unit ( I U ) is similar t othat of the original Saturn I and almost identical to that of theSaturn V.

authorized hardware was being manufactured and tested. Compo-nent qualification programs were essentially complete with the ex-

ception of some items of the second stage and the IU which requireadditional tests for Saturn V environments.The most significant milestone during the period was the previously

mentioned successful flight of the first vehicle. I n this mission the allup principle of flight testing was used; tha t is, all stages were fullyoperational and committed to flight together in the first flight test.The high degree of success achieved was made possible by a thoroughground test, qualification, and checkout program. Several firsts wereaccomplished with this flight : the first flight of the uprated 200,000-

pound-thrust H-1 engines ; he first flight of the 200-000-pound-thrusthydrogen/lOX 5-2 engine; the first flight of the first stage; the firstflight of the second stage; the first firing of a service propulsion sys-tem engine in space; and the first flight of an Apollo spacecraft on aSaturn vehicle.

Final predelivery checkout for the launch vehicle stages of AS-202was completed and both stages were delivered to KSC. T he I U wasalso delivered to KSC. The vehicle mas erected on LC-34 on March9 and checkout began 9 days later. A delay in the availability of theCSM payload for AS-202 prompted a decision to reschedule thelaunch of AS-202 af te r that of AS-203.

Postacceptance firing checkout of the first stage of AS-203 pro-ceeded without difficulty at Michoud Assembly Facility near NewOrleans, and the stage was delivered to KSC in April. The second

I The design of the uprated Saturn I has been completed and all


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stage was acceptance fired a t the contractors test site in Sacramento,Calif., and also delivered to KSC. Assembly of the IU was com-pleted in February, and after checkout it, too, was delivered to KSC.By the end of April all stages were erected on LG 37B . Bince thisvehicle will not carry a CSM, a nose cone manufactured a t MSFC wasinstalled a top the IU.

Both the first and second stages for AS-204 completed successfulacceptance firing tests, he former at MSFC and the latter a t Sacra-mento. Af ter the firing, the first stage was moved to Michoud for p a tfiring checkout.

Critical design reviews were held f or the first manned configurationof the uprated Saturn I, SA-204. The designs of the first and sec-

ond stages and the Instrument Unit were reviewed by the MarshallSpace Flight Center with the respective contractors to make sure thatthe design would meet the requirements of the mission. The reviewdisclosed no major discrepancies. All launch vehicle stages for AS-204 were to be delivered to KSC in August to support the currentlaunch schedule.

A t the end of the report period, the stages for the remaining eightuprated Saturn I vehicles were in various phases of manufacture andtest, ranging from fabrication t o statictests.

Roturn T.-Extensive testing of all stages of the Saturn V launchvehicle continued. During February, the MSFC-built first S-ICflight stage (S-IC-1) mas acceptance tested on the single position teststand. The stage underwent two stat ic firings, one of approximately40 seconds and the other of approximately 80 seconds. Followingthese firings, the stage static firing instrumentation was removedand post static checkout was started. After checkout, the stage wasto be shipped to ICSCs Launch Complex 89. The second MSFC-built, flight stage in the S-IC series (S-IC-8) was successfully accept-ance fired on ,June 6. Post firing activities were in progress at theend of the period.

,Qssembly and checkout of the facility checkout stage was completedat Michoud, and the stage was delivered to ICSC. Also, the thirdS-IC flight stage (S-IC-3) WRS fabricated and asscmhled.

Major ground tests to support, the second stage of Sa turn V (S-I1stage) were conducted during the period. Seven full duration (360second) firings of the S-I1 battleship were attempted, and five of these

were successful. The remaining two were prematurely terminatedbecause of overheating. After the seventh firing, the bnsic 53-11 bat-tleship program mas concluded. However, the test faci lity was kepton a standby basis, available for use as hackup.

The S-11-T, n test stage, which more closely tipproximates aflight stage than the battleship, \vas successfully fired a t M T F for 15


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XI1 CONTENTS

Crawler Transporter with L UT and 500F on way to Pad A- - -Mockup of ALSEP on Lunar Topographical Simulation Area- -Nineteen new astronauts: Edward G. Givens, Jr., Edgar D.

Mitchell, Charles M. Duke, Jr ., Don L . Lind, Fred W. Haise,Jr., Joe H. Engle, Vance D. Brand, John S. Bull, BruceMcCandless 11, John L. Swigert, Jr., William R. Pogue,Ronald E . Evans, Paul J. Weitz, James B. Irwin, Gerald P.Carr , Stua rt A. Roosa, Alfred M. Worden, Thomas K.Mattingly, and Jack R. Lousma- - - - - - - - - - - - - -

Centrifuge in the Flight Acceleration Facility, M S C - - - - - -Interior of Environmental Testing Laboratory- - - - - - - - - - - - - -Th e Orbiting Astronomical Observatory- _ _ - - - - - - - - - - -Surveyor

Iphotographs foot-long lunar rock- _- - - _- - _- - - - - - -

Surveyor footpad on the moons surface _ _ _ _ _ _ _ _ - - _ - - - _ - - - - -Lunar Orbiter spacecraft.. - - - - - - - - - - - - - - - - - - - -Improved miniaturized Gillliver life detector.. - - - - - - - - - - - - - -Biosatellite undergoes qualifying tests- - - - - - - - -ESSA-I and ESSA-I1 spacecraft - - - - - - - - - - - - - -Kamchatka Peninsula (U.S.S.R.) photographed by ESSA-I - -Mexico and Lower California as seen by ESSA-IT- - - - - ~ - - - -Nimbus I1 photographs the Great Lakes- - _ _ _ _- _ __ - _ - - - . -Flight model of ATS cloud camera- - . . ~ - _ _ _- _ _ _- - _ - .PAGEOSI Geodetic Satellite- _ __ __ _ ~ _ _ _ _ _ _ _ - _ _ _ _ _ - - - - -Infrared aerial survey of an active volcano in Hawaii.. - - - - . -The reentry E experiment spacecraft- - - . . - . - . - - - - -Proposed orbiting radio telescope- - - - - - - - - - - - - -Segment controlled space telescope - - - - - - - - - - - - - - - - -Standoff cross__ - - - - - - - - - - - - - - - -

_- - - -

. .

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Life support system test chamber- - - - - - - - - - - - 94-95.~

The advanced space suit- - _ _ _ _ _ _ _- . __ _ _ _ _ _ _ _ _ _ - - - - -The Endoradiosonde in the hand and in the intestine- - - - - . -Cardiovascular monitormg device- - - - - - - - - - - - - - - - - - - - - - - -Tes t apparatus for foot controlled ast ronaut maneuvering unit -Spin test apparatus-_.. - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - -Solar heat distribution on a rotating satellite- - - - - - - - - - - - - -Nozzle to be used on the X E engine- - - - - - - - - - - - - - - - - - - - - - -Breadboard power conversion system- - - - - - - - - - - - - - - - -The ion engine being developed for the ATS- - - - - - - - - - - - - - - -

Transportable station to be operated a t Toowoomba, Aus-- - - - - - - - - -

Apollo Instrumentation Ship-USNS Vanguard- - - - - - - - - - - -IAaunching from USNS Range Recoverer near Koroni, Greece -Clinical Sciences Research Building, Stanford University

Medical Research Center- - _ _ _ _ _- - . - . . - - - - - -NASA organization chart (January 2, 1966) - - - - - - - - - - - - - - - -

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CONTENTS

TIROS highlights through May 24, 1966 _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _Spacecraft-acquired data applied to earth resources surveys

(May 13, 1 9 6 6 ) _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ - - - - - - _ _ _ _ - _ _ _ _ - - _ _ _ _ _ _Natural resources activities (March 11, 1966) ___- - - __ __ _- _-Summary of power tests of first U.S. nuclear rocket engine

system (February-March 1966) __ _ ____- - - - __ __- - - __ _ _- _-Appropriation authorizations, fiscal year 1967- __- ___- - - - _ ___Status of appropriations as of June 30, 1966 _ _ _ _ _ _ _ _ _ _ _ _ _ _ _Comparative consolidated balance sheet, June 30, 1966 and

December 31, 1965- _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _

Resources provided and applied, six months ended June 30,1 9 6 6 _ _ _ _ _ _ _ _ - _ _ _ _ _ _ _ _ - - - _ _ _ - - _ _ _ _ _ _ - - - - - - - _ _ _ - _ _ - _ - _ _Net change in working capital, six months ended June 30, 1966-

Appendixes

A-Congressional Committees on Aeronautics and Space(Jan. 1-June 30,1966) _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _

B-National Aeronautics and Space Council (Jan. 1-June 30,1 9 6 6 ) _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ - _ _ _ - - - _ _ _ - _ _ _ _ - _ _ - - - _ _ _ _ _ _ _C-Current Official Mailing Addresses for Field Installa-

tions (June 30, 1966) _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _D-Principal NASA Officials a t Washington Headquarters

(June 30,1966) _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _E-NASAs Historical Advisory Committee (June 30, 1966) _ _F-NASAs Inventions and Contributions Board (June 30,

1 9 6 6 ) _ _ _ _ _ _ _ _ - _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ - _ _ _ - _ _ _ _

G-Patent Waivers Granted and Denied for Separate In-ventions upon Recommendation of the AgencysInventions and Contributions Board (Jan. 1-June 30,

H-Patent Waivers Granted and Denied for All InventionsMade during Performance of Contract upon Recom-mendation of the Agencys Inventions and Contri-butions Board (June 30, 1966) _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _

I-Scientific and Technical Contributions Recognized by theAgencys Inventions and Contributions Board (Jan. 1-June 30, 1966) _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _

J-Awards Granted NASA Employees under Provisions of theIncentive Awards Act of 1954 (Jan. 1-June 30, 1966) _-

K-Educational Publications and Motion Pictures (June 30,1 9 6 6 ) _ _ - _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ - - _ _ _ _ _

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X IV CONTENTS

I,-Technical Publications (Jan. 1-June 30, 1966) - - - - - - _- _- -M-Major NASA Launches (Jan. 1-June 30, 1966) _ _ _ _ _ _ _ _ _N-NASA Launch Vehicles_-- __ _- _____- - _ _ _ ____ __ _ _ __ __ _

0-NASA International Activities Summary (cumulativethrough June 30, 1966) _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _P-Grants and Research Contracts Obligated (Jan. 1June 30,

1966) __ __ _ __ _ __ __ _ _ _ _- _ __ _ _ _ _ _- _- __ _ _ __ __ _ _ - _ __ _Q-Institutions Currently Participating in NASAs Pre-

doctoral Training Program (June 30, 1966) - _ _- - _- __- -

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seconds on Apri l 23. On May 17, a 150-second firing mas successfullyconducted; then on May 20 it underwent a successful fu ll durationfiring (354.5 seconds). (Fig. 1-14.)

On May 25, an attempt t o achieve a second full duration firing wascut off after 198 seconds because leakage in an engine-start fuel linecaused a minor fire. On May 28, the stage was inadvertently over-pressurized with helium dur ing a leak test and was destroyed. Thisaccident not only resulted in loss of the stage for fur ther testing butalso caused damage to the A-2 stand a t M T F which is needed to testthe first S-I1 flight stage (23-11-1). T o reduce the impact of thisloss, possible revisions to test sequences and schedules were beingstudied as the report period ended. Meanwhile the S-11-1 wasundergoing factory checkout a t Seal Beach before shipment to MT Ffor it s acceptance tests.

The first flight uni t of the Saturn V third stage (S-IVB-501) wassuccessfully acceptance fired on May 26 in the test facility at Sacra-mento. Since this stage must have a restart capability in orbit, thetest consisted of a 150-second firing, a 105-minute simulated coastperiod, followed by a restart and 305-second firing. The stage wasundergoing post acceptance firing checkout as the period ended.

The first Instrument Unit (IU-501) was undergoing checkout atHuntsville, with shipment t o KSC scheduled for August. Th e nextthree Instrument Units were in various phases of fabrication andassembly at Huntsville.

Preparations and tests, vitally important to the success of theSaturn V flight program, were being carried out at the Kennedy SpaceCenter. Stages for a Sa turn V facilities checkout vehicle, AS-BOOF,were delivered early in the period and stacked on the Launcher Umbil-ical Tower (LUT) in the high bay of the Vehicle Assembly Building.Power was applied on May 13, and the vehicle was used to check outthe ground support facilities and procedures in the VAB which willlater support Saturn V flight vehicles.

On May 25, a Crawler Transporter lifted the LUT and 500F andmoved the combined units out to Pad A. (Figs. 1-15 and 1-16.)The t rip required 9 hours. On June 8, in the face of hurricane warn-ings, 500F was taken back to the VAB aboard the Crawler, thenreturned to P ad A on June 10. These operations verified the mobile

assembly/launch concept employed a t Launch Complex 39.Saturn 'v Dynamic Testing.-Dynamic testing in the Sa tu rn Vprogram is the test verification of the vehicle design in terms of itsresponse to the flight loads that are imposed upon it. This testingis performed on a nonflight Saturn V space vehicle, designatedAS-500D, built to simulate the weight, center of gravity, momentof inertia, and stiffness of t he flight vehicle. The space vehicle is


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02 NASA FIFI'EENTH SEMIANNUAL REPORT TO CONGRESS

Figure 1-14. Static test firing of S-IC-1 at MTF.

flexibly supported in a dynamic test stand and subjected to the kindsof vibration caused by wind forces, engine ignition, liftoff, enginecutoff, stage separation, and control force application.

Near the end of the reporting period, the data acquisition systemmns delivered and installed in the Saturn V Dynamic Test Facility.

Checkout, of the entire facility began, using the first stage of the

Testing of the launch configuration (Configuration I ) is scheduledto start late in 1966; in this configuration, the first stage is thrusting.Early in 1967, testing of Configuration I1 is to begin; thi s one sirnu-latcs the spaco vehicle when the second stage is thrusting. (Con-figuration 111, which simulates the thrusting of the third and findstage, was completed in November 1965. as one phase of the upratedSaturn I dynamic program.)

Apollo Lunar Surface Experiments Package (ALSEP)

The scientific objectives of the Apollo lunar landing missions areto study tho moon, the physical characteristics of its surface, and theinterior down to its core. NASA plans to achieve these objectives bycollecting and returning luna r samples, by car rying out a field geology

AS-5OOD (S-IC-D) .


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ftl

1

I

IcIB

1.

L

/

I i

I . . . -Figure 1-16. Crawler Transpder with LUTand SOOF on woy te Pod A.


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Figure 1-17. Mockup of ALSEP on Lunar Topographical Simulation Area.

experiment, and by using a lunar surface experiments package.(Fig. 1-17.)

The experiments package is being developed in two configurations.The first contains a scientific payload consisting of four primary andthree backup experiments. The primary experiments are a passiveseismometer, a magnetometer, a solar wind measuring device, and asuprathermal ion detector. The primary experiments of the secondconfiguration are the passive seismometer, the suprathermal detector,the lunar heat flow, and the active seismometer.

I n February, a 6-month program definition phase was completed.Also in February, N,QSA determined which experiments would bedeveloped and appointed the principal investigzztors who mould con-duct the experiments. By June, substantially all interface relation-ships between the scientific experiments and the Central Station meredefined.

Astronaut Activities

Nineteen new pilot/astronauts were assigned to the Manned Space-craft Center during May of this year. (Fig . 1-18.) This increasesthe total number of NASA astronauts to 50. Twenty-three astronauts

258-738 0-67---4


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36 NASA FIFTEENTH SEMIAIVNTJAL REPORT TO CONGRESS

are flightready and most of them have crew assignments. Fivescientist/astronauts completed approximately half of their generaltraining. Astronauts Slayton, Shepard, and Carpenter are assignedto key managerial positions in a nonflight status.

General training for the newly assigned pilot/astronauts wasoriented to the Apollo and Apollo Applications programs since theGemini program will be completed before these astronauts achieveflight-ready status. A combined academic, field training, and opera-tional familiarization program gives each astronaut a solid technicalbase and thorough Apollo program orientation. This program willenable each to resolve specific mission crew problems and develop mis-sion flight test techniques when he is assigned as a crew member to aspecific flight. This type of general background training has provedinvaluable in both the Mercury and Gemini programs.

Crew assignments for the first two Apollo manned missions weremade previously, and intensive flight readiness activities were under-way. Following several weeks of briefings and seminars on vehiclesystems, the Apollo flight crews engaged in systems and integratedtesting of the spacecraft to be flown on the first two missions.

The experience level of the astronaut force steadily increased duringtho past 6 months as NASA continued to make Gemini flights at ap-proximately 2-month intervals. The capability to substitute the back-up crew late in the prelaunch preparation period was demonstrated onGemini IX. Thc practice of providing backup crews fo r all missionsnot only precludes expensive launch delays but maintains the capabil-ity of our astronant force at a very high level.

Plans were completed for a second scientist/astronaut selection,which is scheduled to begin in the fall of 1966. Scientific screeningof candidates is to be done by the National Academy of Sciences.

Apollo ApplicationsSignificant accomplishments of the Apollo Applications program

during the report period involved the following aspects : management,flight hardware, experiments, and program/mission objectives.

Program Management

Overall objectives for the proposed program were previouslydefined. To support these objectives, project, organizations were estab-lished at MSC and MSFC, and key personnel were assigned. Theseorganizations are planned to be comparable in form to those of Apollo.-1 draf t program development plan W:LS completed. This is the b:Lsicin:anagement, plan which describes the program and the ititinner inwhich i t is to be managed and executed.I


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MANNED SPACE FIJIGET 37

Figure 1-18. Th e new astr ona uts : (sea ted left to righ t) Edward G. Givens, Jr.,Edgar D. Mitchell, Charles 31. Duke, Jr., Don L. Lind, Fred IF. Haise, Jr.,Joe H. Engle, Vance D. Brand, John S. Bull, and Bruce McCandless II-(standing left to ri ght) John L. Swigert, Jr., William R. Pogue, Ronald l0,Evans, Paul J. Weitz, James B. Irwin , Gerald P. Carr, Stuart A. Roosa, AlfredI f . Worden, Thomas K. Mattingly, and Jack R. Lousma.

Flight Hardware

Preliminary definition of candidate space vehicle configurations forattaining long-duration flights was completed. Procurement planswere partially completed t o continue production of Apollo flight hard-mare needed to meet NASA requirements for long-duration flightsand t o support the experiments program. Test plans were partiallycompleted for testing portions of the Apollo space vehicle that millrequire qualification for long-duration flights beyond the 14-daymissions.

Experiments

Identification was completed and plans were being prepared for thedefinition, development, and integration of experiments to fulfill therequirements of the scientific and engineering communities. Revisionswill be made as studies continue. Two contractors were selected forthe award of Payload Integration Definition contracts.


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Program Objectives

The purposes of th e Apollo Applications program, :is discussed inthe 13th Sewitrnnuu? Report (p . 42), are to exploit fnrtlier develop

the basic capabilities of the Saturn-Apol lo System. The major flightmission objectives of tlie program fall into two pri1icip:Il categories :(1) Long-duration flights to determine the effects on men :mtl systems,ancl (2) space flight experiments. The space flight experiments cate-gory includes life sciences (both biomedical and biascience/tech-nology) , astronomy and space physics, extended lunar exploration,applications (including tnetrorology, communications, earth re-sources), and technology (e.g., spent stage utilization, ac1v:inced extrx-vehicular activity, propellant handling in space, :tiid orhitnl :tssembly: nd ma ntenance .

Extended duration manned flight experience is required to establishtlie basic capabilities of the projected m:tnned space flight goals (e.&wrth orbital space station, lunar station, or manned p1nnet:tx-y ex-ploration). Fligh ts lasting as long as a year \vould be attained in.\pollo Applications through the use of modified Apollo hardwitre\v i t h resupply.

The experiments in the areas listed would be responsive to specificneeds, as defined by the scientific :tnd engineering commiiiiities and asravie\vcd and approved by the cogniz:tnt N A S A program offices. A11experiments proposed for flight on manned missions would be reviewed:ind approved by the joint NASA/DOD Mnnned Space Fl ig ht Exper i-inrnts Board.

Experiments in the areas of astrononiy and space physics, and ex.tended-lunar exploration, would support, tlie N:ition:tl AstronomicalObservatories objectives proposed in the 1965 Woods Hole SummerStiidy and the extended lunar exploration as recommended a t the 196.;Ihlmouth Summer Study.

These proposed prograni objectives are based on certain assumptions :The Gemini and Apollo programs, before 1970, will have providedthe capability to explore space out to 250,000 miles f rom earth andto conduct mnnned operations and experiments on flights of up tot w o weeks.The npriited Saturii I aiid Satiirn V boosters will have denion-strated the capability to inject 20 and 125 tons of payload perl:tuncli, respectively, into ne:w-e:trtli orbit.rhe Saturn V will have sent 48 tons to the vicinity of the moon.The -ipol lo sptcecraft will have sustained :L three-man crew fo r 2wet.ks i i i it t\vo-c.onip:i1.tii~eiit, iodiiI:kr, ninneuvernble vehicle, wil ll ~ v e: \ i i t l t d t w o nieii o i i tlie moon, :inti wil l have returned to earthwit I1 s:ui~pIes f Iiinar mnteri:iI.


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M A N N E DSPACE FLIGHT 39

U.S. astronauts will have flown over 500 man-days in space. Dur-in g this time, data and experience mill have been acquired fromapproximately 100 in-flight experiments in response to the needs

of the scientific and technological communities.The currently approved Apollo mission objectives can be accom-plished with the currently planned flight vehicles. If the approvedApollo objectives can be achieved with fewer flights, the remainingflight, vehicles can be used for alternate missions during 1968-71.Follow-on missions requiring procurement of flight hardware be-yond that now planned for Apollo mould continue the mannedspace flight effort, based on Apollo systems, beyond that time. I fall of the presently funded hardware is required for the basicApollo lunar missions, the program content of the alternate mis-sions can be appropriately phased into the follow-on period.

Mission ObjectivesMission plans were under continual study to identify and trade off

!alternative modes of accomplishing mission objectives. Approxi-mately 2 years prior to the scheduled launch date fo r each mission, theobjectives and flight assignments for that mission should be firmlyestablished, and a period of intensive mission planning must beginthrough the NASA organization and its contractors. Apollo Appli-cations missions planned for 1968-69 should enter this 2-year missionpreparation phase during fiscal year 1967. The post-1969 missionswill be subject to fur ther definition studies and long-lead-time develop-ment effort.

The total process of identification, definition, selection, hardwaredevelopment, flight qualification, and procurement of experiments cantake a total of 3 to 4 years. This process must be initiated long

enough in advance to be in phase with the schedule requirements fordetailed mission planning and launch. Similiarly, adequate lead timesmust be allowed for procurement of basic space vehicle hardware.

Advanced Manned Missions

The major effort of the Advanced Manned Missions Program hasbeen directed toward establishing NASAs post-Apollo space Frogramgoals and developing program alternatives that support the goals.

The primary considerations for possible new goals have been that theygive promise of satisfying scientific and national needs in order tomerit strong public support.

The most recent activity has focused on the development of a planfor a n integrated space program with logical, well-defined milestonesof progress. Such an integrated space exploration plan would beginwith AAP, progress to a space station, develop into a Mars/Venus


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flyby, and possibly include in its long-range gods manned surfaceexploration of Mars and Venus. Eventual implementation of th isplan would depend on the previous development of a long-durationEarth orbital space mission module and the inf ormation obtainedabout, the planets from uninaniied probes and manned flyby missions.This module would initially be utilized as an Earth orbital station forapplications potentially beneficial to such economically importantareas as agriculture, forestry, oceanography, and hydrology.

The program alternatives being developed to achieve these goals arebased on a continuing program of advanced studies covering Earthorbital, lunar, aiid planetary missions, :is we11 as the hiinch vehiclesrequired to support these niissions.

The major study effort continued to be in the Earth orbital areasince this activity, in its early stages, is closely tied t o the Apollo Appli-cations Program (AAP) Studies were being conducted of a numberof advanced-AhP aiid post-AAP spacecraft configurations fo r coli-ducting scientific :uid :ipplications experiments and for extending thetime in Earth orbit. Configurations studied included those derivedfrom Saturn/Apollo technology and directed at achieving 1-year andlonger duration in orbit with a compiitible logistic systeiii. Theseactivities sought to develop the essenti:tI predesign information forthe long-diirntion spice iriissioii module which could support il broadim ge of future space missiona. ,2nalyses were also tinderway todevelop concept11iil designs for appropriate space resciie systems tomeet emergencies.

Lunar mission studies which were underway support :tdvanced-XAP:uid possible follow-on exploration. These studies cover the generalcategories of mission requirements, Iiinnr explorat on systems. :~ndEarth-Moon traiisportixtion systems. Concepts for surface niobility.

siirvey probes, and scientific explornt ion systems are iwluded. Proni-king concepts for more efficient delivery systems for pl:u.ing cxrgo: ~ n dpersonnel on the 1iiii:ir surfnce, were being stndied, :is werethe E::wth-bnsetl rq ii irements to s i i p p r t possible extended lunaresplorntioii.

rlie third study :ire:i is cwnceriied with pssiblc fnture ~nnnned mis-sions to the planets. 1I:irs an d Yci i i i s are the niorc likely targets be-~ i ~ s ef tlieir relative proxiinitg t o tlie Eiirth. The llanetiiry niis-h i tudies coiit inued to corer the areas of niissioii requirements, sys-

tem studies, and operatiow a n t 1 sii1)por.t. The re1:itionships between1)ossible e:irlier f l g l ) ~ i i s s ions an(1 Inter 1:inding missions were being:tn:tIyzed.

1he l i ~ 1 l l 1 ( ~ l i chhiclesiintl h l ) i i ( v 1)rol)tilsion st:iges required t o supportthe possible fu ture EartIi-orbital, liin:ir, and plnnctxry missions werealso being studied. U n d e r consideration were possible upratings of

r ,


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MANNED SPACE FLIGET 41

Sa tu rn vehicles and stages, advanced stages and vehicles, and possiblereusable vehicles.

Construction of Facilities

Significant accomplishments were made in the construction and ac-tivation of facilities for the test, checkout, and launch of manned spacevehicles. A t Cape Kennedy, where the checkout and launch of spacevehicles are conducted, modifications to Launch Complex 37 were com-pleted and the facility was activated. I n addition, construction ofmajor elements of the Launch Complex 39, Vehicle Assembly Build-

ing, crawler-transporters, and launch pads was completed. Thesefacilities were being activated in preparation for erection and checkoutof the first Apollo Saturn V scheduled for launch in 1967.

At the Manned Spacecraft Center in Houston, the last major labora-tories were completed. The Flight Acceleration Facility, containinga large centrifuge for astronaut crew training (fig. 1-19), and the En -vironmental Testing Laboratory, housing the space chambers in whichflight conditions can be simulated (fig. 1-20), are now operational.

,4t the Mississippi Test Facility, the site for acceptance testing of theSaturn first and second stages, the first of two stands for testing secondstages became operational in April. This test stand was subsequentlyreadied fo r stat ic firing of the first Saturn V flight version of thesecond stage. Construction of the second stand \vas progressing sat-isfactorily. Capability for testing Apollo Saturn V booster flightstages (S-IC) at MTF should be achieved by the end of the year.

Space Medicine

I n the latter half of 1965, discussions were begun with the U S .Public Health Service concerniiig the possibilities of and the necessityfor precautionary action against harmful contamination of the earthby lunar organisms. The discussions were the result of recomendn-tions by the Life Sciences Committee of the Space Science Board.National *4cademy of Sciences. The recommendations, which stressedthe desirability of quarantining returning lunar landing crews andspacecraft. ; the need for biological studies of spacecraft., suits, andequipment ; and the requirement fo r examining lunar samples underrigid bacterial and chemical isolation and behind absolute biologicalbarriers, were based on R statement issued by the Space Science Boardin 1962 : The introduction into the Earths biosphere of destructivealien organisms could be a disaster of enormous significance to man-kind. We can conceive of no more tragically ironic consequence ofour search for extraterrestrial life.


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42 NASA FIFTEENTH SEMIANNUAL REPORT TO CONGRESS 0

. - s i

Figure 1-19. Centrifuge in the F light Acceleration Facility, MSC.

As a result of the USPHS-NASA discussions, an InterdepartmentalAdvisory Committee on Back-Contamination was formed in emly1966. The functions assigned to the Committee were (1) t o protectthe publics health, apiculture, and other living resources; (2) toprotect the integrity of the lunar samples and the scientific experi-

ments; and (3) to assure the least composite of the operatiomil aspectsof the lunar missions. Responsibility for the staff leadership of theCommittee w as assigned to the Division of Space Medicine.

\vas created under the Director of Space Medicine. The individualholding the new position was also named to serve as Executive Secre-t ary of the Interdepartmental Advisory Committee on Back-Con-tamination. This committee is made up of representatives from the I T SPublic Health Service, the Departments of Agriculture andInterior, and from the Ames Research Center, Manned SpacecraftCenter, and NASA Headquarters.

Committee actions included defining objectives; evaluating the siteselection and design criteria for the 1,unar Receiving 1,aboratory ;rmd reviewing stxndards, protocol, m d procedures for handling re-turned crews, spacecraft, equipment, and .wnples.

Subsequently, the position of Director, Lunnr Receiving Opera I olls


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MANNED SPACE FLIGHT 43

~~~~

Figure 1-20. Interior of Environ men tal Testing Loborotory.


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e4Military Medical Personnel Requirements

Together with representatives of the Surgeons General of the Armyand Air Force and the Chief of the Bureau of Medicine and Surgery,Navy, NASAs Space Medicine Division completed an evaluation ofNASAs requirements for military personnel in the biomedical area.This evaluation resulted in a reduction in the number of positionsrequiring mili tary personnel. I n several cases, i t led to a loweringof the professional education or experience requirements. It alsoestablished procedures to reduce the paperwork involved in NASAsrequesting the assignment of personnel by the Services. Such reviewsare to be conducted annually so that NASA requirements for militarypersonnel will be consistent with changing availabilit ies in civilian

skills.Cooperation With USAF in MOL Program

Biomedical scientists representing the Division of Space Medicineand the U SA F Manned Orbiting Laboratory Program Office partici-pated in a series of meetings to exchange information on proposedUSAF MOL and NASA medical experiments and requirements forbiomedical data. These exchanges were initiated to provide the AirForce with medical dat a for use in defining the medical and lifclsupport requirements for the Manned Oribiting Laboratory, to aidin establishing nonduplicating lines of investigation, and to makeknown to NASA the MOL medical data requirements.

Reorganization of Medical Capabilit ies at MSC

I n May, a reorganization at the Manned Spacecraft Center createdthe Directorate of Medical Research and Operations. Combined inthis Directorate were the medical functions of the Chief of CenterMedical Programs and Center Medical Office and the biomedical re-search functions of the Crew Systems Division, Engineering and De-velopment Directorate. This consolidation will make better use of theCenters medical manpower resources, establish within n single orga-nization the overall responsibility for identifying the medical prob-lems of irianned space flight, and help improve NASA career patternsin the medical and medically related fields.

Medical Data Analysis Program

I n Gemini V I I , the feasibility of automatically monitoring and ana-lyzing in-flight an electrocardiogram system WAS successfully demon-strated. During this period, fur ther progress mas made in patternrecognition, in waveform measurement, and in the development ofinterpretive and diagnostic routines. Before it is used operationallyin SA-205, the system will serve as an automatic collector of baseline

NASA FIFTEENTH SEMIANNUAL REPORT 0 CONGRESS


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MANNEDSPACE FLIGHT 45

data, as a vehicle for refining techniques and routines, and as a quasi-operational digital monitoring system.

Efforts to develop specifications for a contourographic display sys-

tem fo r electrocardiograms were continuing. This display systemrecords the analog waveform of each single heart cycle one below theother and provides a contourogram that appears t o have a third dimen-sion. This system compresses the data and allows a scanner to notesmall changes in rate and slight difference in waveform while main-taining the details in proper time perspective over long periods.

Plans were completed for the transfer of the Medical Data Analy-sis Program from NASA Headquarters Space Medicine to the Direc-torate of Medical Research and Operations, Manned Spacecraft Cen-ter. The program is being transferred because i t has progressed tothe point where its most effective implementation will be at the Center.

General

A NASA contract related to measurement devices for biomedicaltesting of orbiting research laboratory concepts was completed inMarch. A full-scale wooden mockup of a medical-behnvioral labora-tory for the Lunar Excursion Module ascent stage was delivered to

the Manned Spacecraft Center by the contractor. This mockup is tobe used to continue inhouse efforts pertaining to the medical-behavioralexperiments program.

Two comprehensive briefings on selected biomedical problem areaswere presented by the Space Medicine sLaff t o NASA management andengineering personnel. The first briefing, a review of space radiationproblems, included participants from the Oak Ridge Ins titute ofNuclear Studies, the Argonne National Laboratory, and the USAFAerospace Medical Division, as well as scientists from NASA Head-

quarters and various NA4SA Centers. The second briefing was di-rected to the life sciences support of manned space flight missions.


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h N SPACE

NASA launched two orbiting observatories during the first 6months of this year-its first Orbiting Astronomical Observatory anda third Orbiting Geophysical Observatory carrying 21 scientific experi-ments. Them large unmanned spacecraft were designed to studyultraviolet, X-, and gnmma rays, and ~nrth-Siin-interplnnetary p arelationships. They were joined in orbit, in May, by ExplorerXXXII which will observe the upper atmosphere.

On dune 2, Surveyor I soft landed on the moon and in about six daystransmitted over 3,500 TV pictures of the lunar surface. Data pro-vided by the spacecraft helped scientists understand the moonstopography and supplied vital information for Project Apollo.

To take pictures of the rim and floor of the crater in which SurveyorI landed, the *4gency has scheduled an August launching of the firstLunar Orbiter photographic laboratory.

Two other NASA lunar and planetary spacecraft continued theiroutstanding performances. Marking the first time that radiofre-quency energy from a spacecraft was received after traveling deepwithin the solar corona, Mariner I V transmitted signals from over 200million miles away after it had passed nearly behind the sun. PioneerVI, systematically measuring and monitoring interplanetary spaceduring n complete solar cycle, collected substantial data ten timesfaster than previous probes.

Exobiologists of the National Academy of Sciences, who evaluatedthe photographs of Mars taken by Mariner IV, reiterated for NASAtheir earlier recommendation that biological exploration of the planetshould be a high-priority objective of the Nations space program.

The %day flight of the Agencys first Biosatellite was scheduled forthe last quarter of 1966. This orbiting biological laboratory willcarry 13 experiments to study the effects of weightlessness, radiation,and the removal of the effects of the earths rotation on the plants,animals, and other life forms on board. While contributing to basic

46


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0 SCIENTIFIC INVESTIGATIONS IN SPACE 47biological knowledge, the Biosatellite should help defhe the dangersof prolonged space missions for astronauts.

Physics and Astronomy ProgramsOrbiting Obsenatories

Reaching above the earths atmosphere to observe celestial bodies,NASA launched its first Orbiting Astronomical Observatory (OAO-1) on April 8. The observatory carried four experi-ments that could not be performed on the ground. On board wereseven telescopes from the University of Wisconsin for broadbandultraviolet photometry, an experiment from Massachusetts Insti tute

of Technology t o measure the intensity and the direction of arrival ofgamma rays from nuclear reactions of matter in space, an experimentto extend the search for X-rays from the planets and other bodies,and an experiment of Goddard Space Fligh t Center to survey gammarays in the 2- to 180-kiloelectron volt energy ranges.

OAO-1 w as orbited as planned and carried out its first pointingoperation. However, during its second day in orbit faulky operationof a battery circuit deprived the spacecraft of power and it became use-less. A second attempt to launch an Orbiting Astronomical O k r v a -tory will be made in 1967.

The third Orbiting Geophysical Observatory (OGO-111) w aslaunched on June 6 to continue NASAs investigations of the com-plex Earth-Sun-interplanetary space relationships. Twenty-onescientific experiments are carried by the spacecraf t the largest num-ber ever flown by this country. ( OW - I , launched on September 5,1964, and OGO-11, on October 14,1965, are still in orbit.) The highlyelliptical orbit of OGO-I11 (apogee, 75,874 miles; perigee, 183 miles)was designed for measurements in interplanetary space and at theboundary of the earths magnetic field.

Seven observatories make up the OGO series. They carry a largenumber of experiments using the same basic structure, power supply,attitude and thermal controls, telemetry, and command systems.

Explorer SatellitesAn atmospheric

Explorer similar 10 the Explorer XVII launched on April 2, 1963,the satellite is one of several designed to study the neutral componentsand the charged ions of the upper atmosphere. An apogee of 1,629miles was achieved instead of the planned 750 miles; perigee \%-as earlyas planned at 173 miles. Adjustments mere made in the spacecraftscommands to compensate for the higher apogee. At first, all of itsexperiments functioned and returned da ta ; la ter there were difficultieswith the mass spectrometers.

(Fig. 2-1.)

On May 25, NL4SAorbited its Explorer XXXII.

I


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SCIENTIFIC INVESTIGATIONS IN SPACE 49

Lunar and Planetary ProgramsSurveyor

The first Surveyor engineering spacecraft was successfully launchedto the moon on May 30 and made a soft landing on its surface in theSea of Storms (Oceanus Procellarum) about 63 hours later. The per-formance of the 2,2200-pound spacecraft w-as outstanding in all phasesof the flight and the landing. As of June 8, Surveyor I had op em Mfor approximately 6 days and obtained more than 3,500 high-resolutiontelevision pictures of the lunar surface and parts of the spacecraft.(Figs. 2-2 and 2-3.) Included were wide-angle and narrow-angle

panaramic sequences, pictures of the spacecrafts landing pads andimpressions which they made in the lunar surface material, andphotographs taken through special color filters.

The spacecraft carried out successfully all of the objectives of itsmission. Data transmitted by Surveyor I have brought about a sub-stantial increase in scientists understanding of the nature of the moonssurface and provided essential data for the Apollo manned lunarlanding project.

Lunar OrbiterLunar Orbiter, scheduled to be launched by NASA in August, will

photograph the rim and the floor of khe ancient crater in the Sea ofStorms in which