Seventeenth Semiannual Report to Congress, 1 January - 30 June 1967

8/7/2019 Seventeenth Semiannual Report to Congress, 1 January - 30 June 1967

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To THE CONGRESSOF THE UNITEDSTATES:I am transmitting today the Sixteenth, Seventeenth, and Eighteenth

Semi-Annual Reports of the National Aeronautics and Space Adminis-tration covering the period between J ul y 1 ,1966 and December 31,1967.

The events recorded here are both tragic and encouraging ; soberingand inspiring.The eighteen-month period saw success and failure and then successagain as a proud agency moved forward with renewed determination.The Gemini missions were completed;Lunar Orbiters I and I1 trans-

mitted thousands of clear pictures of the moon ; new communicationsand meteorological satellites were orbited.

Then came tragedy. Three brave American astronauts were killed inthe Apollo fire.Initially stunned, NASA then went to work to overcome the flawsin the Apollo system. Soon, impetus was restored to this crucial part ofour space effort. Other great space achievements followed such as theApollo 4 light.

I commend these reports to your attention. They contain, I believe,concrete evidence that NASA is moving forward, and that America iscontributing mightily in the worldwide effort t o conquer space for thebenefit of all mankind.

THE WHITEHOUSE,Oct . 11,1968.


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SeventeenthS E M I A N N U A LR E P O R T T OC O N G R E S SJANUARY 1 -JUNE 30, 1967

NATIONAL AERONAUTICS AND SPACE ADMINISTRATIONWASHINGTON, D. C. 20546


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Cover: Artists sketch of Lunar Orbiter.

For sale by the Superintendent of Documents, U.S. Government Printing OfficeWashington, D.C., 20402 -Price $1.50


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THE PRESIDENTThe White HouseOctober 7, 1968

DEARMR. PRESIDENT:The Seventeenth Semiannual Report of the National Aeronautics

and Space Administration, covering the period January 1 throughJune 30 , 1967, is submitted herewith f o r transmittal to Congress inaccordance with section 206 (a ) of the National Aeronautics and SpaceAct of 1958.

This period was overshadowed by the Apollo fire which took the livesof three of our astronauts. The thorough investigation of thc accidentand the steps that were initiated to improve safety by changes in designand procedures have previously been made mat ters of public record.This report shows tha t the same period was also one of progress inaeronautics and space as evidenced, for example, by the successful flightsof Surveyor, Lunar Orbiter, and many other spacecraft. It was a diffi-cult time f o r NASA, but one in which the agency showed, I believe, thatit could react maturely t o failure as well as success, and continue todeserve the confidence and support of the nation.

Respectfully yours,JAMES. WEBBAdministrator


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ContentsACTIVITIES AND ACCOMPLISHMENTS-- -- _ _ _ _ _ _Chapter 1-Manned Space Fligh t_ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ - _ _ _ _ _ _

Gemini Program _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _Apollo Program _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ - _ _ _ _ - _

Apollo Management . . . . . . . . . . . . . . . . . . . . .Apollo-204 Accident _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ - _

Materials Selection and Substitution_--Hatch Redesign __-_____-____--___--Ground Communications _ _ _ _ _ -- _ _ _ _ _Spacecraft Communications ___-______Environmental Control System______-_Fire Protection __-__________- -____- -Electrical System - _____ - _____ - . - ___ -Launch Complex Emergency Equip-

ment__________--___-----_--_--_--Safety Organization _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ -Steps Toward the First Manned Apollo

Mission _ - _ _ _ _ _ _ _ _ _ _ _ - _ _ - _ _ _ _ -Design Status _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _Hardware Status _____--_____-_________--

Apollo 4 Mission . . . . . . . . . . . . . . . . . . . .Apollo 5 Mlssion . . . . . . . . . . . . . . . . . . . .Apollo 6 Mission_ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ - _Program Software _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _Spacecraft Status and Development

Problems - _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ - - _ -Lunar Module St ruc tura l Test Problem-Launch Escape System_ _ _ _ _ _ _ _ _ _ _ _ _ _ _Uprated Saturn I Launch Vehicles__-_-Saturn V _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _Dynamic Test Vehicle Test Program__ --

Apollo Science Program_ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _Apollo Applications . . . . . . . . . . . . . . . . . . . . . . . . .

Program Objectives . . . . . . . . . . . . . . . . . . . . .Program and Flight Mission Pla nn ing __ ___ _Flight Hardware . . . . . . . . . . . . . . . . . . . . . . .Experiments _ _ - _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _Program Management _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _

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CONTENTSi

Chapter 1-Manned Space Fl ig ht co nt in ue dAdvanced Manned Missions_ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _Construction of Facilities . . . . . . . . . . . . . . . . . . .

Kennedy Space Center_ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ - _ _Manned Spacecraft Center_ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _Mississippi Test Facility _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _

Supporting Systems and Operations_ _ _ _ _ _ _ _ _ _ _ _Launch Information Systems _ _ _ _ _ _ _ _ _ _ _ _ _Mission Control Systems _ _ _ - _ _ _ _ _ _ _ _ _ _ _ _ _Operations Support Requirements_ _ _ _ _ _ _ _ _Flight Crew Operations _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _

Space Med~cine _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _Interagency Committee on Back Contamina-

tion _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _Integrated Medical and Behavioral Labora-tory Measurement System_ - _ _ _ _ _ _ _ _ _ _ _ _ _Medical Information Analysis_ _ _ _ _ _ _ _ _ _ _ _ _US/USSR Project : Foundations of Space

Biology and Medicine_ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _Biomathematical Studies _-_-___________-_

2-Scientific Investigations I n Space _ _ _ _ _ _ _ _ _ _ _ _ _Physics and Astronomy Programs_ _ _ _ _ _ _ _ _ _ _ _ _ _

Orbiting Observatories _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _Pioneer _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _Explorer Satellites _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _San Marco and Ariel Satellites_ _ _ _ _ _ _ _ _ _ _ _Sounding Rockets and Balloons_ _ _ _ _ _ _ _ _ _ _

Lunar and Planetary Programs_ _ _ _ _ _ _ _ _ _ _ _ _ _ _Surveyor _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _Lunar Orbiter _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _Mariner _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _Voyager _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _

Advanced Programs and Technology_ _ _ _ _ _ _ _ _ _ _Lunar and Planetary Studies_ _ _ _ _ _ _ _ _ _ _ _ _ _Advanced Technical Development and Steri-

lization Program _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _Bioscience Programs _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _

Exobiology _ _ _ _ _ _ _ _ _ _ _ _ _ - _ _ _ _ _ _ _ _ _ _ _ _ _ _Planetary Quarantine _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _Environmental Biology _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _Depressed Metabolism _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _

Intravascular Catheters _ _ _ _ _ _ _ _ _ _ _ _ _ _

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CONTEXTS viiPageChapter %Scientific Investigations in Space-Continued

Bioscience Programs-ContinuedEnvironmental Biology-Continued. .Clmical Microanalysis _ _ _ _ _ _ - _ _ _ _ _ _ _ _

Acceleration-Radiation ; Vibration-Radi-ation Effects_ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _Biosatellites _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _Behavioral Biology _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ __ _ _ _ _ _Physical Biology _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _

Bio-information Retrieval _ _ _ _ _ _ _ _ _ _ _ _Apollo Lunar Surface Experiments Package-

Light and Medium Launch Vehicles_ _ _ _ _ _ _ _ _ _ _ _scout ____________________-- - - -__-- - - - -_Agena _________________________-_---___

Launch Vehicle Status _ _ _ _ _ _ _ _ _ _ _ _ _ _ _Atlas-Centaur _ _ _ _ _ _ _ _ _ - _ _ _ _ - _ - _ - - _ _

Chapter 3-Space Applications _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _Meteorological Satellites _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _

ESSA and TIROS . . . . . . . . . . . . . . . . . . . . . .Nimbus _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _Meteorological Sounding Rockets _ _ _ _ _ _ - _ _

Meteorological Sounding Rocket System-Field Experiment Support _ _ _ _ _ _ _ _ _ _ _

Communications Satellites . . . . . . . . . . . . . . . . . . . .Relay and Telstar_ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ - _ _Syncom _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _Intelsat _ _ _ _ _ _ - _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _Echo . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .Supporting Research and Technology___--__

Navigation-Traffic Control Satellites_ _ _ _ _ _ _ _ - _ _Applications Technology Satellites_ _ _ _ _ _ _ _ _ _ _ _ _

ATS-I Telecasts ___________-_______----_-ATS-I Experiments _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ATS-I1 _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _

Geodetic Satellites _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _PAGEOS _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ - _ _ _ _ - _ _GEOS _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _

Earth Resources Satellites . . . . . . . . . . . . . . . . . . . .Experiments for Apollo Applications Pro-

gram _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ - _ _Airborne Data Acqulsition_ _ _ _ _ _ _ _ _ _ - - _ - _ _Ear th Resources Data From Space____---__

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...V l l l CONTENTSChapter 3-Space Applications-Continued

Earth Resources Satellites-ContinuedFisheries and Oil Research_ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _Infrared Emissions Identify Rocks _ _ _ _ _ _ _ _

&Advanced Research and Technology____--_---__Space Vehicles Program_ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _

Space Radiation Shielding _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _Meteoroid Hazard . . . . . . . . . . . . . . . . . . . . . . .Spacecraft Thermal Control - _ _ _ c _ _ _ - _ _ _ - _Lifting-Body Flight Program _ _ _L _ _ _ _ _ _ _ _ _Advanced Gliding Parachutes _ _ _ _ _ _ _ _ _ _ _ _ _Planetary E ntr y Parachute Program-------High-Frequency Vibration - - - --- - -- - - ---Structural Analysis Computer Program-----

Spacecraft Electronics and Control___c_________Avionics Systems Studies _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _Communications and Tracking _ _ c _ _ _ _ _ _ _ _ _Spacecraft Attitude Control _ _ _ _ L _ _ _ _ _ _ _ _ _Guidance and Navigation _ - - _ _ _ _ _ _ _ _ _ _ _ - _ _Instrumentation _ _ _ _ - - _ _ _ _ _ -_ _ _ _ - _ _ _ _ - _ -Data Processing _______________L_________Electronic Component Development _ _ _ _ _ _ _ _

Aeronautical Research - _ _ _ _ - _ - - - - _ _ _ _ _ _ - _ _ _ _ _Aircraf t Aerodynamics _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _Aircraft Loads and Structure s _ _ _ _ _ _ _ _ _ _ _ _Aircraft Operating Problems _ _ _ _ _ _ _ _ _ _ _ _ _Fog _____________________ c _________

Rotor Burst Control Research _ _ _ _ _ _ _ _Lightning -- - - - - - - -- -- - -- - - -Noise Abatement _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _V/STOL Aircraft ______________________ cSupersonic Aircraft . . . . . . . . . . . . . . . . . . . . .

Propulsion/Airf rame Integration - -- -XB-70 Flight Research Program- --- - --

Hypersonic Aircraf t . . . . . . . . . . . . . . . . . . . . .Hypersonic Research Engine _ _ _ _ _ _ _ _ _ _X-15 Research Aircraft Program-_----

Biotechnology and Human Research_ _ _ _ _ _ _ _ _ _ _ _Advanced Concepts . . . . . . . . . . . . . . . . . . . . . .Life Support Systems _ _ _ _ _ _ _ - _ _ _ _ _ _ _ _ - _ _ _Hard Space Suit Developments _ _ _ _ _ _ _ _ _ _ _Human Research _ _ _ _ _ _ _ _ - _ - _ _ _ _ _ _ _ _ _ _ _ _ _Man-Systems Integration - _ _ _ _ _ _ _ _ _ _ _ _ _ - _ _

Chapter

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CONTENTS ixPage

Chapter &Advanced Research and Technology-ContinuedChemical Propulsion Systems _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ -Solid Propulsion Research and Technology--

Solid Propulsion Experimental EngineeringProgram _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _

Liquid Propulsion Research and Technology-Liquid Propulsion Experimental Engineering

Programs _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _Launch Vehicles . . . . . . . . . . . . . . . . . . . . .Space Propulsion _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _Auxiliary Propulsion _ _ _ _ _ - _ _ _ _ _ _ _ _ _

Basic Research _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ - - _ _ _ _ _ -Fluid Physics _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _Applied Mathematics _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ -Materials Research . . . . . . . . . . . . . . . . . . . . . .Electrophysics _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ - - -

5-Nuclear Systems and Space Power__ -_ -______ - -Nuclear Rocket Program . . . . . . . . . . . . . . . . . . . . .

Reactor Technology Development _ _ _ _ _ _ _ _ -Engine System Technology Development_---Other Development Activities _ _ _ _ _ _ _ _ _ _ - _ -NERVA Engine Development _ _ _ _ _ _ _ _ _ _ _ _ _Advanced Nuclear Rocket Propulsion Con-

cepts -_---______-_-___-_______-_-__-__SNAP-8 Development Project _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _Nuclear Electric Pow e r Research and Technology-

Rankine Turbo-Generator Technology- _ -- -Thermionic Conversion Technology _ _ _ _ _ _ _ _Low Power Brayton Cycle Equipment___--_Isotope Power _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ - - -

Electric Propulsion Program _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _Space Power Research and Technology_ _ _ _ _ _ _ _ _

Solar Power Generation _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _Electrical Systems Technology _ _ _ _ _ _ _ _ _ _ _ _Chemical Power Generation _ _ _ _ _ _ _ _ _ _ _ _ _ _ _

6-Tracking and Data Acquisition _ _ _ _ _ _ _ _ _ _ _ _ _ - - _Manned Space Flight Network_ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _Deep Space Network _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _Satellite Network _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ - - -NASA Communications System _ _ _ _ _ _ _ _ _ _ _ _ _ _ _

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Chapter 7-International affairs _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _Cooperative Projects _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _Australia _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _

Brazil _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _European Space Research Organization

(ESRO) _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _France _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _Germany - ----- - - - - --- _ - - - - -- -- - - --India _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _Italy _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _Japan---------__-----------_----_------Norway/Denmark ---- - --- - - --- - ---- - - - - -United Kingdom _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _Inter-American Experimental Meteorological

Rocket Network (EXAMETNET)------_Lunar Surf ace Sample Analysis_ _ _ __ - _ __ --United Nations _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _Operations Support_--_______-----_----------

United Kingdom _________________- -_ - - - -Convair 990 Flights . . . . . . . . . . . . . . . . . . . . .National Geodetic Satellite Program- ------ -Satellite Communications Experiments- - ---

Personnel Exchanges, Education and Training---International Conventions Relating t o Space----

8-Grants and Research Contracts Activities-------Sustaining University Program _ _ _ _ _ _ _ _ - _ _ _ _ _ _

Training - --- - - _ - - -- -- _ -- _ ------- _Research _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _Research Facilities _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _

Management of Grants and Research Contracts--9-Inf ormational and Educational Programs- - - _ --

Educational Programs and Services _ _ _ _ _ _ _ _ _ _ _Spacemobiles ---- - -- - - - - - - - - -- -- --- -Youth Programs _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _Educational Publications and Films--------Educational Television and Radio__-------_

Scientific and Technical Information _ _ _ _ _ - _ _ _ _ _Processing Information __________--_--___Technical Publications ___________-- - -__-_

Technology Utilization _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _Biomedical Application Teams ____--_-----

Chapter. .

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CONTENTS xi

Chapter 9-Informational and Educational Programs-ContinuedTechnology Utilization-ContinuedComputer Software Management Information

Center ___________________ -__c________Regional Dissemination Centers _ _ _ _ _ _ _ _ _ _ _Interagency Cooperation _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _Technology Utilization Conf erenee- _ - _ _ _ _ _Technology Utilization Programs Overseas- _

Historical Program _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ - _ _ _ _ _ _ _ _Chapter 10-Personnel, Management, Procurement, an d Sup-

port Functions _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ - -Personnel _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ - _ _ _ _ _ - - _ _ _ _ _ -

Training Activities . . . . . . . . . . . . . . . . . . . . . .Employee-Management Cooperation _ _ - _ -Key Executive Personnel Changes _ _ _ _ _ _ _ - _

Key Appointments _____-_____-_ - -__-Reassignments _ - _ _ _ - - -- - _ - --- --Terminations _ _ _ _ - - - - - _ _ _ _ - _ _ --

NASA Awards and HonorsL------L-----_--Statu s of Personnel Force_ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _

Inventions and Contributions Board_ _ _ - _ _ _ _ _ _ _ _Petitions for Patent Waivers_ _ _ _ _ - _ _ _ _ _ _ _ _Space Act (Section 306) Awards_ _ _ _ _ _ _ _ _ _ _Government Employees Incentive Awards___Hearings Before the Board_ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _

Organizational Improvements _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _Financial Management _ _ - _ _ _ _ - _ _ - _ _ _ _ _ _ _ _ _ _ _

Fiscal Year 1968 Program _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _Financial Reports, June 30, 1967 _ _ _ _ _ _ _ _ _Preprocurement Pa ten t License Policy__ _ _ _ _ _ _ _Cost Reduction _____________________L________procurement___^-^____^^^^_____^-____^^^^_^^

NASA Contractor Performance EvaluationProgram _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _

Use of DOD Contract Administration Serv-ices _______________________________ I__

Independent Research and DevelopmentCosts Allowance on Unsolicited Proposals-

Unsolicited Proposals . . . . . . . . . . . . . . . . . . . .Improved Procurement, Supply and Prop-

ert y Management __-_______-______-____Extension of Service Contract Act of 1965to Option Renewals _ - _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _

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xii CONTENTSPage

Chapter lO-Personnel, Management, Procurement, and SupportFunctions-Continued

Procurement-ContinuedProcurement Management Surveys _ _ _ _ _ _ _ _Incentive Contracting _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _Summary of Contracts Awards_ _ _ _ _ _ _ _ _ _ _ _Contracts Awarded to Private Industry_____Geographical Distribution of Prime Con-

tracts _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _Subcontracting - _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ - _ _ _ _ -Major Contract Awards _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _Major Contractors . . . . . . . . . . . . . . . . . . . . . . .

Labor Relations _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _Relationships with Other Government Agencies- _

The Aeronautics and Astronautics Coordi-nating Board _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _Interagency Agreements _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ - - -Personnel Affairs . . . . . . . . . . . . . . . . . . . . . . . .Exchange of Information _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _Mutual Support _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _

Illustrations

Redesigned hatch on Command Module mockup 28_ _ _ _ _ _ _ _ _ _ _ _Prototype emergency oxygen mask stowed in cabin___ -____ -_ -Simulated evacuation procedure ( tra ining) _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _LTA-8 being put in space simulation chamber for manned

thermovacuum tests _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _Launch Escape System being hoisted to top of service tower____Lunar Module ascent engine_ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _Saturn V in Dynamic Test St and for Configuration I1 testing__ALSEP central station crew engineering model in deployed

configuration _ _ _ _ _ _ - _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _The suprathermal ion detector (SIDE) deployed _ _ _ _ _ _ _ _ _ _ _Overall view, lef t side, of ATM_ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ATM X-ray telescope being removed from thermalvacuum

chamber____________--___________-___-________________Aerial view of Lunar Receiving Laboratory, MSC_ _ _ _ _ _ _ _ _ _ _ _S-I1stage being lowered into second S-I1 est stand_-_____ ___

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CONTENTS

Eleven new astronauts :Phillip I(.Chapman, Robert A. Parker,William E. Thornton, J o h n A. Llewellyn, Joseph P. Allen,Karl G. Elenize, Anthony W. England, Donald L. Holmquest,Franklin S. Musgrave, William B. Lenoir, and Brian T.0 Leary _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ ~ - - ~ ~

Overall view of Apollo simulator room, KSC_ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _Orbiting Solar Observatory (OSO-111) . . . . . . . . . . . . . . . . . . . .Explorer X XX IV undergoes thermalvacuum tests_ _ _ _ _ _ _ _ _ _ _ _The British Ariel I11_ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _Surveyor I11 digs a trench on the moon . . . . . . . . . . . . . . . . . . . .Lunar Orbiter I V with solar panels unfolded_ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _The Mariner V spacecraft_ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ESSA 111s24-hour world cloud coverage (January 6,1967) _ _Nimbus I1APT photograph of the Great Lakes (Ju ly 16,1966)-APT picture of the U.S. and Cuba from Nimbus I1 (June 7,1967) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .Radios and television sets in the world (1965-70) _ _ _ _ _ _ _ _ _ _ _ _Sketch of the potential navigation-traffic control experiment__-Instruments carried by an earth resources survey ai rc ra ft_ _____Nimbus I1earth resources data on the Columbia River Basin___TIROS IX revealed unknown geologic faults in northern

Norway _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ - -Rocks identified by their infrared emissions _ _ _ _ _ _ _ - _ _ _ _ _ _ _Using the Gamma Probe in the Apollo spacecraft _ _ _ _ _ _ _ _ _ _ _ _The X24A _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _Sailwing and Parawing _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _Parachutes fo r unmanned Mars entry and descent _ _ _ _ _ _ _ _ _ _ _Balloon-launched parachute test flight sequence _ _ _ _ _ _ _ _ _ _ _ _ _Data processing application to X-ray photos_ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _VTOL and STOL concepts studied_ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _Medical monitoring chair _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _The membrane diffusion method of water recovery_ _ _ _ _ _ _ _ _ _ _ _The AX-1 hard suit and joint concept_ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _Particle analyzer _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _Human balance control _ _ _ _ _ _ - _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _Gimbal suspension and water immersion systems__- _ _ _ _ _ _ _ -Work site restraint concepts_ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _Gauntlet concept hand tool_ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _The 260-inch motor____-_________-_-______-___---____-__-High pressure turbopumps . . . . . . . . . . . . . . . . . . . . _ _ _ _ _ _ _ _ _ _ _High pressure engine _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _Aerospike concept _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _

. .

...xlllPage

3536414344464748606162646569707172

74, 757677787982

86, 87909192939495, 96979799

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Implosive shock tube _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ 104


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Xi V CONTENTS

Calculating an aircraft trajectory- _ - _ _ _ - --- _ _ _ _ _ _ _ _ _ _ _ _ -The Phoebus 1-B reactor a t fu ll power_ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _Installation of the Phoebus 2 cold-flow reactor a t Test Cell C,

NRDS _______________________--__--_--_______________Ground experimental engine ( XE) _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _Engine remote installation equipment with Engine Mock-Up_-_Phoebus-2 U-tube nozzle__________--__-_-___-______--_____NFS-3b feed system for Phoebus reactor . . . . . . . . . . . . . . . . . . .Engine/Stage Test Stand 2 an d 3 Complex Site Plan __- ___ _-_Turbo-compressor fo r Brayton Gas Turbine Cycle- _ _ _ _ - _ _ _ _ _Nuclear thermionic converter _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _Resistojet experiment for ATS-C_ _ _ _ - _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _One kilowatt hydrogen-oxygen module_ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _NASA Tracking and Data Acquisition Stations- - _ _ _ _ _ _ _ _ _ _ _The SF OF , located at the Je t Propulsion Laboratory--___-_--Use of Intelsat f o r Apollo Communications _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _Launch of Sa n Marco I1 spacecraft from platform a t sea--_-__Ariel 111 being tested_ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _

. .. .

Page105109110112113115116117120121123125127130133138139

TablesP a g e

Nimbus I1 Experimental Results on Completing Orbit 4860,May 15, 1967__,_-______-___---_______________---_-____ATS-I Transmissions in Aircraft Tests (December 1966-June1967) _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ - _ _ _ - _ _ - _ _ _ _ _ _ _ _ - - - _ _ _ _ - _

Participation i n the GEOS-I and PAGEOS Projects_---------Research Facilities in Progress-June 30,1967 _ _ _ _ _ _ _ _ _ _ _ _ _ _Completed Research Facilities-June 30, 1967_ _ _ _ _ _ _ - - - - - _ - _NASA Appropriation Authorizations Fiscal Year 1968_--_--_-Sta tus of Appropriations as of June 30, 1967 _ _ _ _ _ _ _ _ _ _ _ _ _ _ _NASA Comparative Consolidated Balance Sheet, June 30, 1967

and December 31,1966 _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ - _ _ _ _ _ _ _ _Resources Provided and Applied Six Months Ended June 30,1967 ________________________________________-_ - -_____Net Change in Working Capital Six Months Ended June 30,

596667146147166167168169169


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CONTENTS

Appendixesxv

PageA-Congressional Committees on Aeronautics and Space

(Janua ry 1-June 30,1967) _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _B-National Aeronautics and Space Council (Januar y 1-

June 30, 1967)_ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _C-Principal NASA Officials a t Washington Headquarters

(Ju ne 30, 1967)_____________________-_____-__-____D-Current Official Mailing Addresses for Field Installations

(June 30, 1967)_____________________-__-__-_--____E-NASAs Historical Advisory Committee (J un e 30 , 1967)_ _F-NASAs Inventions and Contributions Board (Ju ne 30,

1967) _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ -G-Patent Waivers Granted and Denied f o r Separate Inven-

tions Upon Recommendation of the Agencys Inventionsand Contributions Board (Ja nuary 1-June 30, 1967)_ _ _H-Patent Waivers Granted and Denied f o r All Inventions

Made during Performance of Contract Upon Recom-mendation of the Agencys Inventions and ContributionsBoard (January 1-June 30, 1967)_ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _

I-Scientific and Technical Contributions Recognized by theAgencys Inventions and Contributions Board (January1-June 30, 1967)________-__________-_____________-

.J-Awards Granted NASA Employees Under Provisions of theIncentive Awards Act of 1954 (January 1-June 30 ,1967) _ _ _ _ _ _ _ _ _ _ _ _ _ __ _ _ _ _ _ _ _ _ _ _ _ _ __ _ _ _ _ _ _ _ _ _ _ _ _ _- _

K-Educational Publications an d Motion Pictures (June 30,1967) ____________________________________________L--Technical Publications ( January 1 J u n e 30, 1967) _ _ _ _ _ _

M-Major NASA Launches (Januar y 1-June 30, 1967)_ _ _ _ _ _N-NASA Launch Vehicles _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _0-Grants and Research Contracts Obligated (Jan ua ry 1-

June 30,1967)___-______________-__________________P-Institutions Current ly Partic ipating in NASAs Predoc-

toral Training Program (3une 30 , 1967)_ _ _ _ _ _ _ _ _ _ _ _ _

183184185186187188

189

192

195

196

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This period involved intensive development efforts on the Apollospacecraft and the Saturn V launch vehicle, and was marked by a fireduring a ground test of this spacecraft which claimed the lives of threeastronauts. The Gemini program was closed out.

The Gemini ProgramGemini Program activity consisted primarily of property disposition

and final reporting. At the end of the period, approximately 95 percentof all remaining property had been transferred to on-going governmentdevelopment programs o r to the Smithsonian Institution as artifacts.The Manned Orbiting Laboratory Program received about $103 millionworth of Gemini property (new cost prices), not including the cost ofspacecraft 11, 111, 111-A and VIII, which were also transferred. Nineprograms in the Department of Defense, other than MOL, receivedGemini equipment.

Within NASA, the Apollo Program, the Apollo Applications Pro-gram, and several unmanned satellite programs were using Geminiequipment. Seven NASA centers received Gemini surplus test equip-ment suitable fo r laboratory use. Gemini Spacecraft XI was transferredto the Electronics Research Center as a guidance and control researchtool and will be released to the Smithsonian when no longer needed. Theremaining spacecraft were being transferred as artifacts to the Smith-sonian, which will place three on exhibit, one at KSC, one at MSC, andone a t MSFC.

3


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4 NASA SEVENTEENTH SEMIANNUAL REPORT TO CONGRESSProgram documentation progressed routinely, with completion ex-

pected by years end. A summary report on Gemini extravehicularactivity, a catalog of Gemini anomalies, and supplements to missionreports were distributed. The proceedings of the Gemini SummaryConference were expected to be published in January, 1968. A publica-tion containing earth photographs from Gemini 111,IV, and V (SP-129,described in Appendix L of this report) was distributed, and a com-panion book including earth photographs from subsequent missionswas being prepared.

All costing against Gemini contracts was completed, and all contractswere either closed out or in final process of termination.

The Apollo ProgramThe goal of the Apollo Program is t o develop the capability for

exploration of space out to 250,000 miles from earth. This capabilitywill be demonstrated by a mission t o land men on the moon fo r limitedobservation and exploration and t o return them safely to earth. Sucha mission will climax a series of sub-orbital and orbital missions, eachwith specific objectives. However, all are t o be flown primarily t o ad-vance the state-of-the-art and to qualify systems f o r the ultimate luna rlanding mission.

The Apollo Program was preparing for the resumption of the flightphase at periods end. Both NASA and industrial management con-tinued to identify and solve problems which would impair the schedule,increase the costs, jeopardize the safety of astronauts o r otherwisehinder the performance of the Apollo team. Apollo flight programplanning is based on providing not only the capability t o capitalize onsuccess but also the capacity to respond to problems.

Flight missions were assigned and planned to assure flexibility inmanning the uprated Saturn I (Saturn IB) and Saturn V series andin providing f o r the orderly transition between the two flight series.NASA intends to transfer manned flights from the uprated Saturn Ito the Saturn V vehicle as soon as the latter is ready fo r manning, withthe earliest transfer point occurring after the first manned upratedSaturn I mission, AS-205/CSM-101. Such planning will allow the ApolloProgram to proceed in a deliberate manner despite the impact of theAS-204 accident which required extensive redesign of flight hardware.

The Apollo flights were rescheduled to accommodate the many pro-gram changes that were made following the accident. These changesreduced the number of flights available to achieve a lunar landing by theendof 1969.

One unmanned Apollo flight is scheduled f o r the second half of1967. It is to be the first launch of a Saturn V, AS-501 (Apollo 4 mis-


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MANNED SPACE FLIGHT 5sion), placing in orbit an unmanned Command and Service Module.It will be a launch vehicle development mission, including a demon-stration of the spacecraft heat shield at lunar return velocities and flighttesting the sealing technique of t he redesigned hatch.Apollo Management

The fundamental soundness of the Manned Space Flight Programsmanagement structure and process were demonstrated by the success ofthe Mercury and Gemini Programs and by the first thirteen successfulmissions of the Sa tu rn I vehicle in the Apollo Program. The managementreview carried out by the Apollo Program Office since the accident notedno areas requiring major organizational change. However, the reviewdid identify the need for greater centralization and clarification indocumenting and updating t he specific responsibilities of the organiza-tions within the Apollo Program.

Possible ambiguities in the assignment of program responsibilitieswere removed, an d control of waivers and deviations was reinforced.Specific management directives were prepared to replace or consolidateprevious directives concerning preparation of test and checkout plansand procedures at IZSC ; responsibilities in the Apollo Program atMarshall Space Center ; and functions and authority of the ApolloIrogram Office at NASA Headquarters .To further strengthen program management, NASA contracted with

The Boeing Company to assist and support the NASA Apollo organiza-tion in performing specific technical integration and evaluation func-tions, with NASA maintaining the final technical decision responsibility.The Boeing Company established and began maintaining organizationswithin the geographical locations of each of the Manned Space FlightField Centers and the Apollo Program Office f o r this purpose.Apollo management techniques and reporting systems were beingfur ther strengthened to meet the needs of the program, and a system wasbeing established to provide a continuous flow of information to al lCenters, to the Apollo Progrftm Office and top officials in NASA head-quarters, and t o the various contractor organizations.Apollo 204 Accident

On Janua ry 27, 1967, a tragedy occurred at Cape Kennedy when fireerupted inside the Apollo spacecraft during ground testing. The fireresulted in the deaths of IJt. Colonel Virgil I. Grissom, Lt. ColonelEdward H. White, 11,and Lt. Commander Roger B. Chaffee.

The Apollo-204 Review Board, comprised of NASA officials as wellas representatives of other government agencies and private organiza-tions, determined af ter 2M months of investigation tha t the most likelycause of the fire was electrical arcing from certain spacecraft wiring.


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6 NASA SEVENTEENTH SEMIANNUAL REPORT TO CONGRESS(The Report of Apollo 204 Review Board to the Administrator, Na-tional Aeronautics and Space Administration, was printed as Vol-ume 11, Parts 1,2, and 3, Hearings, Subcommittee on NASA Oversight,Committee on Science an d Astronautics, U.S. House of Representatives,April 10, 1967.)

Many changes were made in the Apollo hardware following the acci-dent, with design changes in the more advanced Block 11 Apollo space-cra ft reflected on the contractor manufacturing lines. Other changes, notresulting from the accident investigation, were also being made in theApollo spacecraft.

Spacecraft crew compartment material was a key consideration in thepost-accident review. Knowledge gained as a result of the fire and insubsequent testing led to alterations both in the selection of spacecraftmaterials and in their placement within the vehicle. This was probablythe most significant single technical change resulting from the accidentinvestigation. An account of changes in Apollo design, construction,and procedures made during the report period follows.

Materials Belection and Xubstitution.-An improved spacecraft ma-terial selection and substitution program was established to reduce therisk of fire in all manned spacecraft operations both on the ground andin Bight.

Ra tc h Bedesign.-Before the Apollo 204 accident, improvements werebeing made in the Apollo Command Module hatch, following th e extra-vehicular experience in the Gemini missions. The original hatch openedinward. Effort on hatch redesign was intensified as a result of the acci-dent, with emphasis on preflight and postflight crew egress. (Fig. 1-1.)The new design, which opens outward, offers operational improvementin normal preflight, spaceflight, and post-landing use. It also providesthe fastest emergency crew egress capability.

Emergency egress considerations were also applied to the facilitiesfor Apollo launches. The launch umbilical tower and access arm werebeing altered by (1)modifying the access-arm mechanism and changingthe pa rk position to shorten reposition time ; (2) eliminating stepsand protuberances in the egress path; and (3 ) providing positiveventilation, improved lighting, and fire-resistant materials in th e whiteroom.

Ground Cornnzunicatioiw-The operation of the ground communica-tions system was improved by reducing the number of stations oncritical loops. Access to the system is to be limited to stations that willbe essential for a n operation.

Steps being taken to assure the reliabil ity of the present system in-cluded design changes, improved operational procedures, controllingcircuit configuration, and adding intercommunication equipment. Thesemodifications and additions will permit fu ll duplex operation on critical


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MANNED SPACE FLIGHT 7

Figure 1 - 1 . Redesigned hatch on Command Module mockup 2 8 .circuits off the pad at Kennedy Space Center (KSC) and to other keyplaces such as the Mission Control Center at the Manned SpacecraftCenter, Houston. The changes are to be made before the next mannedspacecraft tests at KSC.

gpacecraft Communications.-Problems associated with spacecraftcommunication in the Block I spacecraft were solved and correctionswere made in the Block I1 spacecraft design; therefore, minimal space-cra ft changes were required.

Environmental Control Bystem.-After intensive study of the ApolloEnvironmental Control System, NASA determined that 100 percentoxygen at 5 psi will be used during space flight, including reentry. Thisrequires no changes in the spacecraft hardware. However, changes wereconsidered for the cabin atmosphere while the spacecraft is on theground and during launch. Fo r manned test operations on the ground,NASA will continue to use the 16.5 psi pure oxygen atmosphere unlessthe boilerplate fire-safety tests conducted with the new materials indi-cate that another system would be preferable. As an option, NASA willbe able to use either air o r 100 percent oxygen during ground tests,prelaunch, and launch.

Alterations were also being made in the oxygen plumbing within thecabin. The aluminum oxygen lines with solder joints were being changedto stainless steel, and protective covers are to be added to exposed oxygen


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8 NASA SEVENTEENTH SEXIANNUAL REPORT TO CONGRESSlines. Materials in the Environmental Control System which constitute afire hazard will be replaced, although the water-glycol coolant, which hassome inflammable properties, is to be retained. It is essential that an in-hibitor be used in the coolant to prevent corrosion, and the present in-hibitor was selected as the best possible one for the system. The principaleffort is to provide a leakproof coolant system and to minimize fire haz-ard to prevent spills. Leaking and spillage were being substantially re-duced or eliminated by using soft-metal washers, by employing improvedtorquing procedures, and by adding quick disconnects with fluid checkvalves to prevent water-glycol spillage during normal maintenance.It was determined tha t solder joints are acceptable if properly madean d not abused. However, the number of solder joints is to be reduced,armor is to be added to the water-glycol system joints exposed to struc-tural abuse, and protective covers are t o be added over all exposedplumbing.

Materials and procedures were developgd to clean up any spills whichdo occur without leaving a residue, and improved test procedures toverify proper clean up were worked out.Pire Protection.-Provisions fo r increased fire protection included anemergency breathing mask system t o permit crew operations if fireoccurs during the shirtsleeve mode of operation, (Fig . 1-2.) an enlarged

Figure 1-2. Prototype emergency oxygen mask stowed in cabin.


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MANNED SPACE FLIGHT 9pressure relief valve so the cabin can be depressurized rapidly, addi-tional oxygen surge tank capacity and associated plumbing so that thecabin can be repressurized rapidly, and a newly developed portablecrew-operated fire extinguisher for the Command Module.

Electrical Bystem.-In a major review of the spacecraft electricalsystem, the Block I and Block I1 spacecraft were examined t o determineif any of the components or subsystems were possible ignition sources,and then the design of the Block I1 spacecraft electrical system andthe adequacy of manufacturing, installation, and testing practices werescrutinized. In general, the Block I1 spacecraft electrical system designappeared to be satisfactory and the plan of implementation conformedt o acceptable practices. The improvements previously incorporated inthe Block I1 spacecraft solved most of the problems revealed in theinvestigation of the Block I spacecraft involved in the fire.

Changes were being made to ensure compliance with the propercriteria f o r circuit breakers, protective covers were being added overexposed wiring to prevent damage during installation and test, an dthe wiring on spacecraft already built was being inspected. Additionalmandatory inspection is now called f o r during the manufacturing andtesting of new spacecraft.

Launch Complex Emergency Equipment.-Adequate provisions f o rfire-fighting and other emergencies were also made by installing addi-tional launch-complex equipment.

Xaf ety Organization.-NASA placed renewed emphasis on all aspectsof its safety program. Kennedy Space Center established new criteria t odetermine which additional test-team personnel require emergency andpad rescue training (Fig. 1-3.), new safety training standards for allpersonnel and an individual certification program were being developed,and an Apollo spacecraft mockup containing new hatch provisions willbe used at KSC for training rescue and operational personnel. It is tobe movable so that it can be installed in the altitude test chamber fortraining exercises.

Xteps Toward the First Manned A p o l l o Mission.-A number of stepsmust be completed before the next manned flight. One-a ground testprogram (aircraft-drop, propulsion, st ructura l, and crew-compatibilitytests) f o r the Block I1 Command and Service Module t o qualify thespacecraft-was underway. Vibration and thermal-vacuum tests will beconducted on the ground, and the new hatch design will be tested on theunmanned Saturn V missions. Also required is the Command Modulefire test in the boilerplate spacecraft and requalification of the variousunits and systems being changed. Finally, all approved changes andmodifications must be incorporated into the flight spacecraft, which mustthen be tested at both the Downey (California) plant and the MannedSpacecraft Center.


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10 NASA SEVENTEE NTH SEMIA NNUAL REPORT TO CONGRESS

Figure 1-3. Simulated evacuation procedure (training).

During the necessary three- to five-month checkout period at the Cape,the Command and Service Modules are to be mated, and combinedsystems tests a re to be run. Following the first manned test at sea-levelconditions, there will be an unmanned test in the altitude chamber. Thelast of the vacuum chamber tests is to be conducted with the spacecraftmanned and the chamber simulating the changing environmental con-ditions from launch to orbit. The spacecraft is then to be moved to theLaunch Complex 34 pad and mated with the launch vehicle for furthertesting. Finally, the manned plugs in and plugs out tests and thecountdown demonstration tests will be carried out.

In 1968, NASA expects to be prepared to fly the Block I1 space-craft, the first of the manned Apollo series, in an open-ended missionof up to two weeks in earth orbit. The goal will be to verify the com-bined performance of the spacecraft and the crew.Design S k i u s

During the first half of 1967, the Apollo hardware design programprogressed as major portions of the Saturn V Launch Vehicle DynamicTest Program and various other test programs were completed.


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MANNED SPACE FLIGHT 11Following the investigation of the 204 accident, extensive redesign

and modification of the Command Module was made. Major areas ofchange include the hatch, materials, the earth landing system, cabinrepressurization, and protective coverings for exposed plumbing andelectrical harnesses. Redesign and modifications of the Lunar Modulewere not as extensive as those on the Command Module and primarilyinvolved material changes. Scheduled deliveries of both spacecraft weredelayed to permit additional testing, retesting, and requalification ofmodified hardware.Hardware SMus

Because of the 204 accident, the Apollo Program underwent extensivereplanning to accommodate the changes to Block I1 Command ServiceModules and Lunar Modules necessary for manned flight. Consequently,Apollo launches originally scheduled f o r the first half of 1967 had to bedeferred.

A p o l l o 4 iWission.-The unmanned Apollo 4 missions objectives areto qualify the Sa turn V Launch Vehicle facilities and procedures, to testthe S-IVB restart-in-space capability, to test the Block I1 spacecraftheat shield under lunar return velocities, and to test the new hatch seal.The launch vehicle for the Apollo 4 Mission will be SA-501 and theCommand Service Module will be CSM 017. A Lunar Module TestArticle, LTA-lOR, will be used in place of the LM. This mission has beendelayed by the Command Module CM 017 wiring rework, inspection,and validation j and by problems associated with the S-11-1 stage.

The S-IC-1 first stage of SA-501 was delivered to KSC on September17, 1966, and erected on the launch umbilical tower. The S-IVB-501and S-IU-501 arrived at KSC on August 14 and 25 (1966), respectively.Because of the unavailability of the S-11-1 second stage, an S-I1spacerwas employed to allow complete stacking of the launch vehicle. The CSM017 was erected on the launch vehicle on January 11, 1967. Partiallaunch schedule integrated testing with the S-I1 spacer was completedearly in February. The S-11-1 stage arrived at KSC on January 24.Afte r completion of low bay act ivity in mid-February, the S-I1spacerwas replaced by the S-11-1 ate in February.

I n early June, as a resul t of weldment discrepancies identified on theS-11-6 liquid hydrogen tank, the launch vehicle was disassembled so theS-11-1 stage could be inspected. The inspection was completed in mid-June and no serious problems were found. The launch vehicle was beingprepared for electric mate. During this time, extensive progress wasmade in the checkout of launch Complex 39 and Pad A facilities andequipment including swing arm validation of Launch Umbilical TowerNo . 1 (LUT-1). As a result of the 204 accident investigation, the Com-


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12 NASA SEVENTEENTH SEMIANNUAL REPORT TO CONGRESSmand Service Module 017 was moved to the Manned Spacecraft Opera-tions Building f o r wiring inspection, modification, and validation dur ingApril and May.

Apol lo 5 Missio?z.-The unmanned Apollo 5 mission objective is t overify the operation of the Lunar Module ascent and descent propulsionsystems and the L unar Module structure.

The launch vehicle f o r the Apollo 5 mission will be the SA-204, and thepayload will be the Lunar Module LM-1 and a nose cone. The launchvehicle was delivered t o KSC during 1966, and LM-1 arrived on June23, 1967. Early in April, the SA-204 launch vehicle was moved fromLaunch Complex-34 t o Launch Complex-37B. Launch Ccmplex-37B wasmodified t o accommodate the additional instrumentation on SA-204Iaunch vehicle.

LTAS (Thermal Vacuum Test Article) underwent modification andsystems validation in preparation for shipment t o MSC f o r thermalvacuum testing. (Fig. 14 . ) Testing of the Structural Test Vehicle,LTA-3, the descent Propulsion test vehicles, LTA-5D and PD-2, and theAscent Propulsion Test Vehicle, PA-1, continued through this period.All tests delaying the LM-1 mission were completed except the LTA-3

Figure 1-4. LTA-8 being pu t in space simulation chamber for manned thermovacuumtests.


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MANNED SPACE FLIGHT 13vibration acoustic test and the PD-2 malfunction and start tests, andthese were scheduled for September and October, 1967. The launchschedule was delayed by LM-1 propulsion plumbing system leak prob-lems and a helium heat exchanger fai lure which occurred du ring LTA-5D testing. The LM-1 helium heat exchanger was being replaced andleak problem solutions were being developed.

Apollo 6 Hission.-The mission objective of the unmanned Apollo 6is to qualify the Saturn V launch vehicle facilities and procedures andthe Block I1 CM heat shield, and to test the new Block I1 hatch design.The launch vehicle fo r the Apollo 6 mission is the SA-502 ; he CommandService Module is CSM 020.

I n February, the S-IVB-502 and the LTA-2R (Lu nar Test Article)were delivered to IZSC, in March the S-IC-2 stage and the InstrumentUnit (S-IU-502) were delivered and in May the S-11-2 was delivered.CSM 020 was being modified as a result of changes called f o r followingthe 204 accident, with delivery planned for November.Program Sof hare.-The launch vehicle and spacecraft flight pro-grams, and the Saturn launch computer complex software required tosupport the Apollo 4,5, and 6 missions were on schedule.

h'pacecraf t 8tatzrs and Development Problems.-As stated earlier,wiring inspection, rework, and modifications were delaying delivery ofBlock I1 ground and flight test Command and Service Modules. LunarModule production was also delayed during the first half of 1967 becauseof the fire-related changes.

Both the Command Module and Lunar Module were made heavier bythe changes, and the increased weight caused three basic problems.Fir st, the changes reduced the safety factor of th e Eart h LandingSystem, which was designed for an 11,000-pound Command Module. Anintensive effort was undertaken to reduce the growth in CommandModule weight. Also under investigation was a modification to the Ear thLanding System to increase the factor of safety by providing two-stagereefing main parachutes, and by using larger drogue chutes.

Second, because of the additional weight, the Command Module ra teof descent during earth landing increased from 35 feet per second to399$ feet per second for the design case. Struc tural adequacy of theCommand Module in a launch pad abort condition was under study. Asafe land landing could occur at the higher descent rate, however. Stepswere taken t o modify the astronaut couches to increase crew protectionto withstand a 40G impact load. Additionally, increased testing wasbeing planned to detesmine spacecraft structural capability under theworst possible pad abort land landing condition.Third, the Service Module and Lun ar Module propellant tank capac-ities were being severely taxed because of increased propellant require-


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14 NASA SEVENTEENTH SEMIANNUAL REPORT TO CONGRESSments. The additional propellant is required to maintain the spacecraftat necessary delta velocities which are most sensitive to decreases in thepropellant weight/hardware ratios. Necessary corrective actions beingtaken included examining the Lift/Drag ratio at re-entry to allow areduction in ballast requirements. Operational changes (such as restrict-ing lunar landing to pre-selected sites) which would minimize increasedhardware weight by reducing overall propellant requirements were alsobeing considered.

Lunar Module Structural Test Problem.-In February, during launchboost load testing of the St ructural Test Vehicle, LTA-3, two descentstage upper deck skin panels failed at about 100 percent limit load.The failure occurred during the first stage end-boost static test condi-tion. Other tests not affected by this failure cohtinued to be conducted.It was determined to be more economical to replace the LTA-3 descentstage with the LM-6 descent stage than to repair it. The LM-6 descentstage was prepared for structural tests an d shipped to MSC in May. TheLM-1 mission constraint was removed when the end-boost static test wassuccessfully accomplished in Jun e 1967. (Completion of the LTA-3Acoustic Vibration Tests in September should remove the last LTA-3/LM-1 mission constraint.) Struct ura l fixes were incorporate in LM-1 andsubsequent vehicles.

Launch Escape Systems.-The delivery of Launch Escape Systems tosupport Apollo launches was on schedule, with no development problemsapparent. (Fig. 1-5.)

Uprated Saturn I Launch Vehicles.-Apollo Sa tu rn launch vehicles205-212 were proceeding on schedule. The AS-205 launch was beingpaced by the availability of CSM-101, the first manned Block I1 CSM,with the remainder being paced accordingly. If required, the additionaluprated Satur n I missions will be dual launches involving both the CSMand the LM.

Sa tu rn V.-The Sa tu rn V consists of three stages-the S-IC (fir st),the S-I1 (second), and the S-IVB (third). The second S-IC stage, theS-IC-2, was delivered to KSC in March and was undergoing checkoutin preparation for the Apollo 6 mission. The S-IC-3 was successfullystatic fired a t MSFC in late 1966 and was in storage at Michoud at theend of this period. It is to be delivered to KSC during the four th quarterof 1967. The S-IC-T was fired at MTF in March 1967, marking the com-pletion of checkout of Position I of the S-IC acceptance test stand. TheS-IC4 completed its static firing test program at MTF in May. S-ICvehicles 5 through 15 were in various stages of fabrication, assembly, andcheckout a t the Michoud operation near New Orleans.The first and second S-I1stages, 5-11-1 and -2, were delivered to KSCduring the period, af ter acceptance testing in the S-I1 est stand A-2 a t


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Figure 1-5. Launch Escape System being hoisted to top of service tower.


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16 NASA SEVENTEENTH SEMIANNUAL REPORT TO CONGRESSMTF. The S-11-3 was in transit t o MTF for acceptance testing at theclose of the period. The S-11-4 through 15 were in various stages offabrication, assembly, and test a t Seal Beach, California.

On ApriI 15 , the 8-11-2 was static fired a t the M TF for a full durationof 367 seconds. This was the second static firing for the 8-11-2 stageand was a major milestone in the Confidence Program tha t was initiatedin 1966 after the 8-11-T failure. The Confidence Program consisted pri-marily of five battleship captive firings and two successful consecutivefirings on each of the 8-11-1 nd S-11-2 stages.

Two major problems paced the S-I1 Program. They were the welddefects in the propellant and pressurization lines and in the liquidhydrogen and liquid oxygen tanks. The problem with welded lines be-came apparent early in May when the final S-I13 inspection revealedten defective lines that had t o be replaced. Subsequent inspection ofS-11-1,-4, and -5 stages resulted in returning 43 welded lines to thevendor f o r rework. Manufacturing procedures and inspections werebeing upgraded t o eliminate weld defects of this type. The tanks of theS-11-4 and all subsequent S-I1s were inspected with dye penetrant andultraviolet light. Through this technique, inspectors discovered 104surface flaws on the S-11-6 liquid hydrogen and liquid oxygen tanks.Although only five of these flaws required rewelding, reinspection ofS-11-1,-2, and -3 was directed to insure the integrity of the welds on allthese stages. No serious flaws were detected i n these stages. Similar testsand inspections were carried out on the S-IC and S-IVB stages, withno discrepancies being found. Investigation of the causes of the highdefect ra te i n the S-11-6 was still underway at the end of this period.

The S-IVB-502 was received at RSC in February 1967, and numbers503 (new) through 515 (new) were in various stages of fabrication,assembly, and test. On January 20, 1967, the S-IVB-503 stage explodedon the Beta 3 test stand in California during countdown f o r staticfiring. The stage was completely destroyed and heavy test stand damageresulted. Investigation showed that the 8-IVB-503 helium tanks werefabricated with welding rods of pure titanium instead of the requiredtitanium/aluminum/vanadium alloy. Subsequent inspection of allhelium tanks indicated that this problem was confined t o the S-IVB-503stage.

The Instrument Unit 502 (S-IU-502) was received at KSC duringMarch. The S-IU-503 was available f o r shipment to KSC during thereporting period but was placed in storage until required at KSC.S-IU-504 through 515 were in various stages of fabrication, assembly,and test.

The F-1engine production program remained on schedule in support


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MANNED SPACE FLIGHT 17of the S-IC tage program. Eleven F-1 engines were delivered duringthe report period.

The 5-2 engine production program also remained on schedule in sup-port of the S-I1and S-IVB stage programs. Nineteen J-2 engines weredelivered during the report period.

During the first half of 1967, stability and chamber erosion problemsshowed up in the LM ascent engine. (Fig. 1-6.) At periods end, the

Figure 1-6. Lunar Module ascent engine.


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18 NASA SEVENTEENTH SEMIANNUAL REPORT TO CONGRESSsubcontractor had not been able to produce a stable injector compatiblewith the combustion chamber. A NASA evaluation team went to theplant to determine the basic problems and to aid in their solution.Actions were initiated to select another manufacturer to develop aninjector as a backup.

Extensive qualification testing of the LM descent engine continued ;plans call for the work to be completed during the th ird quarter of theyear.

Dynamic Test Vehicle Test Program.-The objective of the DynamicTest Vehicle (DTV) test program is to verify the mathematical tech-niques by comparing the dynamic characteristics derived from testsof a full scale prototype with characteristics derived mathematically.These characteristics, when updated to the flight configuration, are usedas input parameters in flight control and structural loads analyses,which a re then verified (flight control and structural) on the Sa turn/Apollo vehicles.The testing concept required simulating various conditions of flightusing a Dynamic Test Vehicle erected in a test stand. The stages of thevehicle were ballasted to simulate the vehicle at a specific point in thetrajectory.

The Configuration I dynamic testing program was initiated andcompleted at MSFC. Configuration I consists of all stages of the launchvehicle and all elements of the Command and Service Module, LunarModule, and Launch Escape System. Correlation with analysis forcenter line modes and frequencies was achieved. However, the analysisdid not accurately predict the response at the Flight Control Gyrolocation. Considerable local deformation was experienced at the Instru-ment Unit, resulting in slopes at the Control Gyro location that wereconsiderably greater than center line slopes of the vehicle. Because ofthis local activity, flight control stability margins were below designobjectives for several lateral Configuration I modes. To solve this prob-lem, engineers relocated the Control Gyro to the bottom of the cold plate111, an d redesigned the filter networks. Configuration I testing was thenextended to verify dynamic characteristics at the new location of theControl Gyro and also to identify a possible alternate location f o r it.Stability margins were substantially improved as a result of the designchange. With the redesign, all modes demonstrated stability marginsabove design objectives, and the SA-501 margin restraint was removed.

After undergoing the complete Configuration I testing, the DynamicTest Vehicle was disassembled so the test tower could be modified forConfiguration I1 tests. Configuration I1 consists of the 8-11and S-IVBstages and all elements of the Apollo Spacecraft. Configuration I1testing began in May and was in progress at the end of the period, withcompletion expected in the third quarter of 1967. (Fig. 1-7.) Initial


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Figure 1-7. Saturn V in Dynamic Test Stand for Configuration I I testing.


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20 NASA SEV ENT EEN TH SEMI ANNUA L REPORT TO CONGRESSConfiguration I1 esting results were indicating excellent correlation forcenter line modes and frequencies on the first three modes.The Apollo Science Program

The Apollo Science program consists of an in-flight program and alunar science program. Because of operational constraints, the in-flightprogram was being limited to essential medical experiments and synopticterrain and weather photography for which all equipment was available.

The objectives of the Apollo Luna r Science Program are t o investigatethe structure and processes of the lunar interior, to determine the com-position of and the processes modifying the surface of the moon, and toestablish the historical o r evolutionary sequence of events by whichthe moon has arrived at its present configuration.

For the first missions, four scientific activities were being programmedfor the astronauts :making observations to provide a qualitative descrip-tion of lunar surface features ;collecting samples to permit post-missionanalysis in geochemistry, petrology, geology, and bioscience;deployingthe Apollo Lun ar Surface Experiments Package (ALSEP) which willremain and obtain continued measurements of geophysical parametersf o r a year o r more; and performing field geology experiments t o obtaininformation on the geologic structure as it may be revealed by surfacefeatures and formations.

The ALSEP system acts as a scientific station capable of acceptingand supporting a variety of different experiments. (Fig. 1-8.) Power forthe system will be supplied by a P u 238 radioistopic thermoelectricgenerator.

The initial ALSEP experiments are a passive seismometer, a lunarsurface magnetometer, a solar wind spectrometer, a suprathermal iondetector, and a cold cathode gauge. Experiments for later missionsinclude an active seismic experiment with pyrotechnic seismic sources,a lunar heat flow experiment, and a charged particle lunar environ-ment experiment. A lunar surface dr ill is t o be used in conjunction withthe heat flow experiment and will also be used to obtain lunar coresamples.

Geology tools and a tool carrier developed f o r the Lunar FieldGeology experiment are to be incorporated i n to the Scientific EquipmentBay (SEQ) with ALSEP. Included with the tools are core tubes andaseptic samplers. Two Apollo Lunar Sample Return Containers and aHasselblad camera are pa rt of the Lun ar Field Geology experiment butare stowed separately.

Qualification testing for ALS EP I is to be started by early October,1967, with flight hardware planned for delivery in the summer of 1968.The following sections briefly describe the initial ALSEP experi-


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Figure 1-8. ALSEP central station crew engineering model in deployed configuration.

ments. The passive seismometer is designed t o determine the naturalseismicity of the moon, and t o provide data on the physical propertiesof the lunar interior. Data is to be obtained by using a 10 to 15 second.three-axis orthogonal seismometer for long-period, low-frequency, seis-mic energy and a short-period (yz to one second) seismometer for thehigh frequency portion of the seismicity signal spectrum.


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22 NASA SEVENTEENTH SEMIANNUAL REPOBT TO CONGRESSThe lunar surface magnetometer is a magnetic station which will usea tri-axis flux-gate magnetometer to measure the magnetic field vector

and temporal variations a t the lunar surface as well as to measure fieldgradients at the sensor site. Three booms, each with flux-gate sensors,will be separated to form a rectangular coordinate system and gimballedto allow paralle l o r orthogonal alignment.

The solar wind spectrometer is designed to measure the temporal,spectral, and directional characteristics of the interaction of the solarwind and the moon. The experiment will measure the number ofcharged particles impinging upon it, and their energy (electrons to 1376electron volts, protons to 9600 ev). Directional origin of the particleswill be determined by observing which of the seven oriented sensorsindicates their flow. Energy selection is made by modulating the flow ofparticles in the energy interval being measured.

The suprathermal ion detector (SIDE) is designed to measure theflux, energy, and velocity of positive ions in the lunar ionosphere. (Fig .1-9.) The instrument has a velocity selector composed of crossed electricand magnetic fields followed by a curved plate analyzer. Velocity and

Figure 1-9. The suprathermal ion deteclor (SIDE) eployed.


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MANNED SPACE FLIGHT 23energy sort ing of the particles entering these detectors covers ions in therange from one to four AMU per unit charge, from 2 ~ 1 0 ~o 2 ~ 1 0 ~cm/sec., and from 0-2 KEV. A second curved plate analyzer withouta velocity filter detects solar wind particles. Associated with the SIDEis a cold cathode gauge t o determine the pressure of neutral particlesby measuring the density of the ambient lunar atmosphere.

Apollo ApplicationsThrough its Apollo Applications Program (AAP),NASA continued

to refine program objectives, plan program and flight missions, develophardware concepts and designs, identify experiments to be used, andestablish its program management structure.Program Objectives

The program has four primary objectives: to conduct long durationmanned space missions (up to one year) ; to conduct extended lunarexploration ; o carry out scientific investigations in earth orbit ;and tomake space applications in earth orbit.

Long durat ion space flights will include evaluation of habitability,systems development, and usefulness of man. Space applications in earthorbit will include experiments in meteorology; communications andnavigation ; and earth resources. The last-named will apply to agricul-ture and forestry, geology and minerals, geography, cartography, man-made resources, hydrology and water, and oceanography. Scientificinvestigations in earth orbit are t o include solar astronomy, earth ob-servations, and stellar astronomy.Program and Flight Mission Planning

The AAP missions were being planned t o gain experience, testtheories, perform experiments, and collect data. Multiple objectives werebeing established f o r each flight mission in order to obtain maximumresults at a relatively low cost.

Key elements in this planning include the decision to use, modify,and expand present Apollo systems capabilities rather than initiatewhole new developments; the concept of reusing basic hardware f o rmany missions by storing it in orbit and returning later with freshcrews and a resupply of expendables ; he approach of designing experi-ments that will gather important data while simultaneously testingthe experimental concepts themselves; and the anticipated use of theopen-ended mission philosophy of allowing each mission t o proceed asfar as it is capable.


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24 NASA SEVENTEENTH SEMIANNUAL REPORT TO CONGRESSThe first three missions were more clearly defined. The first mission

(AAP-la) is to be manned and is to carry out science, meteorology, andearth resources experiments. This one should last u p to 14 days. Thesecond (AAP-1 and AAP-2) is to be a manned dual launch mission of u pto 28 days duration which will demonstrate the feasibi lity of orbitalworkshop operations. This mission is also expected to conduct biomed-ical, science, and technology experiments. The third mission (AAP-3and AAP-4) is also to be a manned dual launch mission but should lastup to 56 days. It is to carry out ATM operations, demonstrate thefeasibility of reuse of the workshop, a nd conduct biomedical, science,and technology experiments. Detailed mission planning was in progressat periods end.

The Agency issued a formal version of the AA P flight mission assign-ment document for the early flights. This document, which authorizesthe missions, describes in general terms the primary objectives of eachflight, the flight profiles, the space vehicle configurations, the identityof experiments to be carried, and the space operations to be conducted.

Following issuance of the flight mission assignment document, NASAissued flight mission directives for the early flights. These define in moredetail the missions purpose and objectives, the general flight plan, theflight hardware configuration, the experiments, the ground tests, thereliability and quality assurance requirements, and the organizationalresponsibilities.

Additionally, a configuration definition document was issued. Thisprovides detailed descriptions of the flight hardware for the earlymissions. For later flights, studies were started, or continued, to definethe requirements and problems associated with atta ining A AP one-yearmissions.Flight Hardware

NASA continued its efforts to develop or modify major flight hard-ware required for the early missions. This hardware includes the orbitalworkshop, the airlock, the Apollo Telescope Mount (ATM), he launchvehicles, and the command and service modules.

The orbital workshop, for use in AAP-1 and 2, will permit astronautsto outfit, inhabit, work, and perform experiments in the empty hydrogentank (Workshop) of a spent S-IVB stage by means of a 65-inch diameterairlock between the spacecraft and the hydrogen tank. A hatch in theairlock will permit egress into space without depressurization of theworkshop or the spacecraft. In orbital flight, the command and servicemodules will dock with the airlock, and the crew will activate systemsto pressurize the spent hydrogen tank f or habitation.

Preliminary design of the orbital workshop was completed, a nd a


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M A N N E D SPACE FLIGHT 25full-scale mockup was delivered to MSFC. A thorough and well docu-mented astronaut walk-through was conducted, followed by a prelimi-nar y design review. Plans were approved to provide an additional workarea for the installation of more experiments and habitability equipmentfor future revisits after the initial use.

An Airlock Development Plan was prepared. A contractor defined theairlock and multiple docking adapter interfaces and began designanalyses fo r incorporating a two-gas (nitrogen and oxygen) orbitalworkshop environmental control system. Reviews indicated that theairlock design was proceeding satisfactorily.

The Apollo Telescope Mount (ATM) provides a new capability fora variety of solar scientific experiments to be performed above theearths atmosphere. It has a stabilized platform to accommodate experi-ment instruments requiring finely controlled pointing and scientificinstruments and supporting systems mounted in a structural rackattached to the ascent stage of an Apollo lunar module (LM) .The ATMrack will have a pointing control system consisting of control momentgyroscopes, fine control vernier gimbals, electronic control circuitry, andappropriate astronaut controls and displays. A thermal control systeman d a communications and data handling system are also to be included.Electrical power is to be furnished by a solar array mounted t o theATM rack, with rechargeable batteries t o maintain system loads duringdarkness.

ATM systems contracts were awarded for a three-axis simulator, forcontrol moment gyroscope systems, for thermal and contaminationstudies, for an ATM neutral buoyancy trainer test article, and forthe vernier pointing control system.

The full-scale ATM mockup was completed as was the ATM spartest unit. (Fig . 1-10.) The ATM structural design was released for fab-rication. Astronauts performed one-G walk-through tests for evaluationof the Lunar Module (LM) and the film was retrieved for evaluation.The ATM installation and interface requirements were established formodifying the LM to suit the LM-ATM configuration. Initial thermalstability tests of the ATM spar were performed, and preliminary resultsindicated no apparent problems concerning the spar deflection.

The Command and Service Module contractor completed preliminarystudies of the modifications that would be required to give the CSM thecapability for a space mission lasting up to 56 days. These modificationswould adapt the CSM to a two-gas system (nitrogen and oxygen), wouldenable it to carry cryogenics f o r longer fuel cell operation and sufficientoxygen f o r the astronauts, would provide more stabilization thrusterpropellant f o r the increased stabilization demands of experiments and


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26 NASA SEVENTEENTH SEMIANNUAL REPORT TO CONGRESS

Figure 1-10. Over all view, le ft side, of ATM.

long-duration flight, and would add solid retro engines to provide abackup re-entry capability.

Long-lead procurement was initiated for those items required to keepopen the option of buying additional uprated Satu rn I and Saturn Vlaunch vehicles.Experiments

By the end of the period, 62 experiments had been reviewed by theManned Space Flight Experiments Board, approved by the AssociateAdministrator for Manned Space Flight, and assigned to AAP forimplementation. Twenty-five additional experiments were identified andwere under consideration for assignment. Contracts were awarded orwere in the process of being awarded for development of approvedexperiments. Most of this experiment hardware is in either the designor the development phase. The payload integration centers (MSFC andMSC) were actively working with the principal investigators an d werein the process of integrating experiments into the spacecraft modules.This integration includes such items as he necessary suppor t provisions,electrical power, coolants, storage locations, and mounting brackets.


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MANNED SPACE FLIGHT 27Mission operations requirements were being established, including suchitems as the required crew training and in-flight time allocation.

The majority of the approved experiments were assigned to the firstfive AAP flights. Fourteen experiments were being considered for use onmission AAP-lA, including science experiments previously assigned tothe Apollo Program, earth resources experiments, and meteorology ex-periments. Payload integration and compatibility studies were beingconducted t o define the mission payload.

Representative of the experiments t o be carried is one for makingmeasurements in X-ray astronomy, and one f o r photographing selectedground sites using a variety of films and filters. These experimentswould provide early data for use in determining the feasibility andapplicability of conducting earth resource surveys from space.

The second and third AAP flights, AAP-1 and AAP-2, are being plan-ned as a dual launch mission, one manned, and one unmanned butcarrying the Orbital Workshop experiment. Thirty-five experiments arebeing considered for these flights-eight medical, ten engineering, sixDepartment of Defense, six advanced technology, and five scientificexperiments.

The medical experiments for AAP-1 and AAP-2 would be aimedprimarily at determining the effects on man of a flight of up to 28 days'duration. The significant engineering experiment, involving the orbitalworkshop, would be to evaluate crew quarters, a food managementsystem, and a waste management system. Also, the crew quarters wouldbe evaluated t o determine suitability f o r a mission duration of up t o 56days, as planned f o r the AAP-3 and AAP-4 mission, and possible suit-ability for a crew member remaining in orbit up to 90 days, as is plannedin future AAP missions.Department of Defense selected experiments would be aimed at ob-taining early information useful t o the Manned Orbital LaboratoryProgram. Other DOD experiments would obtain advanced technical dataneeded to design advanced systems.

Typical advanced technology experiments would be those to furtherdefine the micrometeorite phenomena and the associated effect on thespacecraft. Scientific experiments would be aimed at gathering addi-tional astronomy data which will be more advanced than the astronomydata from AAP-1A.

The four th and fifth flights, AAP-3 and AAP-4, were also being plan-ned as a dual launch, one manned and one unmanned, carrying theApollo Telescope Mount (ATM) . The mission would have two primeob ectives-one to conduct solar astronomy experiments, and the otherto conduct additional medical experiments.

The medical experiments would try to determine the effects on man


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28 NASA SEVENTEENTH SEMIANNUAL REPORT TO CONGRESSof up to 56 days in space, a major duration extension over the planned28-day mission of AAP-1 and AAP-2. In addition, evaluation of theorbital workshop quarters would be continued because the orbital work-shop from the AAP-1 and AAP-2 mission would be revisited andreactivated.

The ATM is expected to carry five major solar astronomy experi-ments: a white light coronograph, UV coronal spectrographs, an X-rayspectrographic telescope, UV spectrometers, and dual X-ray telescopes.These experiments are expected to obtain high resolution images of thesun and detailed views of selected portions of it, primarily i n the ultra-violet and X-ray portions of the light spectrum. This research is impor-tant t o the scientific community because the 1969-1971 period of peaksolar activity will not be duplicated for 11years.

Preliminary design was completed f o r most ATM experiment equip-ment. Preliminary design and interface reviews were conducted to verifythe experiment design and performance specifications and to define ex-periment interface requirements of the ATM supporting subsystems.Long-lead time procurement was authorized f o r the ATM experimentequipment, and the thermal-mechanical units were being fabricated.Breadboard testing t o verify the design concept of all ATM experimentswas completed. (Fig. 1-11.)

Figure 1- 1 I . ATM X-ray telescope being removed from thermallvacuum chamber.


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MANNED SPACE FLIGHT 29Program Management

Refinements continued to be made in the definition of programresponsibilities. Assignments were made to the field centers for theintegration of experiments, support systems, and experiment carriers,and responsibility interfaces were clarified among MSC, MSFC, and theprime contractor.

Coordination activities also continued. Intercenter coordinationpanels were established to identify and define technical and manage-ment problems that may arise among the three MSF field centers.Meetings were conducted with the Department of Defense to exchangeinformation on AAP plans, manned space flight experience, and MOLprogram plans and experience. To assure closer working relationshipsat Headquarters on the ATM project, personnel were assigned to AAPfrom both the Office of Space Science and Applications and the Officeof Advanced Research and Technology.

The payload integration contractor was selected. His primary taskswill be to assure compatibility between the space vehicles and the pay-loads, including experiments, experiment operational and supportequipment, and expendables ; and to make certain that experimentrequirements and plans will be compatible with mission plans.

The preparation of AAP management plans continued. The Relia-bility and Quality Assurance plan was published and distributed. Aversion of the Test Requirements Document was circulated for finalcomments from project organizations at the field centers. The AAPproject office at KSC completed plans for AAP KSC operations f o r theearly missions. These plans provided a baseline for launch facilitiesmodifications, launch operations requirements, and the joint AAP andApollo use of launch facilities.Progress was also made in scheduling and control. A formal set ofschedules with associated review procedures was started between thecenters and Headquarters. These management tools are expected toassist management in the day-to-day process of investigation, assessment,corrective action, and program adjustment.

Advanced Manned MissionsThe Advanced Manned Missions Program continued studies aimed at

identifying mission requirements, investigating modes for mission ac-complishment, determining hardware design concepts, and identifyingrequired resources and technology. Studies were also underway to de-sign integrated manned space flight programs that would accomplishmore ambitious national goals than those set for Apollo and ApolloApplications.


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30 NASA SEVENTEENTH SEMIANNUAL REPORT TO CONGRESSThe studies showed that the accumulation of systems design and

operating experience in preceding programs will make it feasible tolaunch Earth-orbiting space stations in the 1970 s. These stations couldbe designed fo r five years of continuous operation, accommodating acrew of nine to twelve men. Several space station concepts identified inthe studies could be reasonable f ollow-ons to the Earth-orbiting missionsof the Apollo Applications Program. The concepts differ in cost, sophisti-cation, and abil ity to accommodate conflicting requirements. Some con-figurations could provide artificial gravity should that be necessary o rdesirable, and all could be launched by Sa tu rn V vehicles. All of theseconcepts are to be analyzed and refined so that a realistic set of optionswill be available when the time comes to initiate space stationdevelopment.

Operating a long life-time space station requires an efficient and ver-satile logistics system for rotating the crews, replenishing expendables,delivering experimental equipment, and returning data. Systems beingstudied would meet these demands and use Gemini and Apollo hard-ware and subsystems. The logistics spacecraft would consist of a crewmodule accommodating six to nine men and a combined cargo/pro-pulsion module.

Advanced manned studies conducted to date indicate that the spacestation is the key to future exploration and exploitation of space. It ishere that Earth-oriented applications in the fields

Seventeenth Semiannual Report to Congress, 1 January - 30 June 1967

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Transcript of Seventeenth Semiannual Report to Congress, 1 January - 30 June 1967