fourth semiannual report to congress

8/7/2019 Fourth Semiannual Report to Congress

1/290

uhcslnlstration

S H I N G T 0 N 2 5 , D C

iiii!iiiiiiiiiiiiiiii!iii_iiiiiiiiiii!!_ii!!iii_iiiiii!i!iiiiiii!!!_i!_!!ii_i!i!ii!_:i_i_!_ii!i_!i_i_ii_!_!i_i_iiii!_iiii!!ii!ii_ii_!!i_i!_iii!_ii_iii!_ii_ii_!_iiiiii!_iii_ii!ii!ii:_i_i_ili ;_i_i!ili!i!iiii!i!_i_i_iililillii!i!;!iiii!iiiiiiiiiiiii_iiiiiii!iiilil_!i!!!_!ilili;i:i iil;i_ili iii!ii!i:i,lil:iii_ii!ili!!ii!i!!ii!iii!ilill!!i iiiiiiii!:i!i!i__ i_ i_i !! _ i i _?_;_ _ i_ i_ i_ ii !_ i! ii _i __ _ i___i_!_i//i;:i_ _;_ __:_:_!i!_i_,ii_ii_i_ _/_ i_:_!_:i_i;!?/

!!'_i!i'_ii_i_i!!i!!!!i!_ii_i!i!!_!!ii!!i!i!_!i_i!_!i_!!i!i_!_i_!!_i!!ii!!!!_!i!_!!_!i_!!!!_!i_,_ii!_!_!!i!!!i!!_i!!:ii!!_i'_!_i_'i_!_:!!_!!!_i_:_!__!_i!_!i!!!_ii_!i_i!i!!_i_ii!!_iii_i_i_i_!!,,_!!_i!i_ii!!!_i_!i,_,i_!i!!_!i!_i!!_ii!_ii!'_'__i)_i_!_i_!i_ii_i_i_i_!ii_i_i_!!!_!_!i!i_!_ii_i_i!!_i_:_ii_i_i_i_!_!_ii_i_!__i_/_!_i_!_,_iii_i!(i!i_ili!_i:_i!_:_,ili_!_i_i//i_i_i_i_ii!_ i_!_ _ !!_!_ii?i_i!i_iiii!_i_iiiiiii_il/_?_i_!_ii!_iiii_i_!_ii!_!!i!ii!_ii!iii_i!ii_i_i_ii_ii_!ii_! _i _ ii i i li i __ i _ _... _ _)_ii_i_! _IW=_:! _==_ _ _.......

FOURTHS[MiANNUAL[PORiTO

i!ll_;i!_i!;i:i!:i!ili_!]_!=!i ; i_ _ii!iiii!ii!ii!_i_ii!!i:!_!i!_!]i/iiii)

Jill IB HI il i IIII

RIL 1, 1960 THROUGHM BER 30, 1960


2/290

National Aeronauticsand Space Administration

WA S H I N 6 T 0 N 2 5, D C.

FOURTH$[MIANNIIAIR[PORITOCONGI

APRIL 1_1_--T H R O U (3 HSEPTEMBER :30, 1960


3/290

TO THE CONGRESS OF THE UNITED STATES:

Pursuant to the p r o v is ion s of the Nation_!

Aeronautics and Space Act of 1958, I transmit h e r e-

with for the information of the Congress the Four th

Semiannual Keport of the National Aeronautics and

Space Administration, covering the p e r i o d April 1,

1960 through September 30, 1960.

DWIGHT D. EISENHOWER

THE WHITE HOUSE,JANUARY 18, 1961


4/290

N A T ! O N A LAERONAUTICSA N D S P A C EADMINISTRATION

IN REPLY REFER TO

OFFICE OF THE ADMINISTRATOR1520 H STREET NORTHWESTWAS H I N GTON 25, D.C.TE1.EPHON: EXECUTIVE 3-3260 TWX: WA 755

IZ January 1_'"2OA

The PresidentThe White House

Dear Mr. President:

This Fourth Semiannual Report of the National Aeronautics andSpace Administration, covering the period April 1 through September30, 1960, is submitted to you for transmittal to the Congress in ac-cordance with the National Aeronautics and Space Act of 1958, SectionZ06(a).

Progress in NASA's aeronautics and space programs is sum-marized in the introduction. The agency's major activities are reportedin detail in the chapters that follow.

During the twoyears since NASA's inception (October i, 1958),the staff has simultaneously had to plan, o r g an iz e, an d conduct re-s e a r ch and development and operational programs -- programs boldand imaginative and at the same time realistic enough to be carried outwith reasonable prospects of success. During this formative period,the agency has drawn together into a vigorous organization numerousGovernment scientific and technical units possessing substantial spaceresearch capabilities. NASA also has been taking increasing advan-tage of the resources of private research and educational groups.Moreover, despite its own growth, NASA is pursuing a policy wherebyprivate industry is utilized for an ever- larger share of the agency'sprogram.

The Nation can well be proud of NASA's operational a c h i e v e-rnents. As of early December 1960, the agency had launched 29 earthsatellites, of which 15 were still in orbit. Ten of the 15were stilltransmitting data. Two U.S. spacecraft were in solar orbit.

Several attempts to send payloads t o th e vicinity of the moon,however, have ended in failure. 0nly Pioneer IV, which passed within


5/290

The President 12 January 1961

37, 300 miles of the moon in March 1959, achieved some of its objec-tives. Despite the setbacks to be expected in any research and devel-opment program in such a new, fast-b re aking field, the informationtransmitted by these satellites and spacecraft has already proven offar-reaching scientific significance.

From the mile-upon-mile of telemetered data, we are learningmore about the ocean of air in which we live, and about the limitlessspace beyond. We are also learning much about the earth itself -- itstrue shape and the composition of its interior.

NASA has now moved out of its formative stage. Within theframework of a Long-Range Plan for space exploration, which theagency prepared and set in motion in 1960, NASA is pursuing a pro-gram with three principal objectives:

1) early application of earth satellites to practical uses;

2) study of the space environment and celestial bodies to gainscientific knowledge;

3) determination of man's capacity to function usefully in thespace environment, in order to open the way to manned exploration ofspace, of the moon, and of planets in our solar system.

History may wellviewour space effort as the first major revo-lution in the affairs of mankind conceived, and in large measure guidedby, scientists. It is clear that the present de c ade will witness rapidexpansion of the frontiers of knowledge with resultant benefits to peoplesof all nations.

Sincerely,

T. Keith GlennanAdministrator


6/290

CONTENTS

CHAPTER i - INTRODUCTION AND HIGHLIGHTS .............CHAPTER 2 - SATELLITE APPLICATIONS ................

PAGE19

Weather and Communications Satellites ProveFeasible ...................... 9

Commnnications Satellites .............. 9World Conmmnications Systems Becoming inadequate.. 9Project Echo .................... lO

Vertical Flight Test Successful ......... lOFirst Experiment Unsuccessful .......... lO

Echo I Achieves Planned Objectives ......... 10Injected into Nearly Circular Orbit ....... lOPresident's VoiceRelayed Via Sphere ....... llMany Experiments Conducted with Echo ....... llOrbital Computations ............... llFirst Intercontinental Radar Signal Relayed . . . llTrans-Atlantic Radio Transmission ........ 13Wirephotos Bounced from Satellite ........ 13Echo Enters Earth,s Shadow ............ 13Sunlight Shifts Orbit .............. 13Radio Beacons Operating Only in Sunlight ..... 15Loses Roundness But Still Bounces Radio Waves . . 15Internal Pressure Loss .............. 15Perforations from Micrometeoroids ........ 15Radar Tracking Still Possible .......... 16Cooperation with Voice of America ........ 16

Echo Program Management .............. 16Participation in Project .............. 16Rigidization Techniques for Later Commnnications

Satellites .................... 17Contract Awaited ................. 17Results Show Promise ............... 17

Meteorological Satellites .............. 17TIROS I ...................... 17

Data Analysis .................. 18Interrogation Halted ............... 18Final Spin Rockets Activated .......... 18Second TIROS Planned ................ 18

Foreign Participation Invited ........... 19TIROS Project Management and Participation ..... 19Nimbus Sat ellit e Development ............ 20Nimbus Project Management ............. 20

-i-


7/290

CHAPTER - MANNEDPACEFLIGHT.................PAGE2323Project Mercury Is Springboard For Apollo ......

Project Mercury Progress ............... 23Suborbital Flight Nears .............. 23Twenty-Four Capsules Involved ........... 23Suborbital and Orbital Flight Plans ........ 2_Progress During Report Period ........... 2_First Test of Mercury Production Capsule ...... 2_Second Production Capsule Test ........... 26Capsule Modifications Continue ........... 26Astronaut Training Moves Ahead ........... 27

Mercury Tracking And Communications System IsReadied ...................... 30Network Stresses Reliability and Speed ....... 30

Mercury Medical Team Organized ............ 32Recovery Support ................... 32Chimpanzees Readied for Flight ............ 33Space Task Group Manages Project Mercury ....... 33

CHAPTER _ - SCIENTIFIC SATELLITES AND SOUNDING ROCKETS ...... 35Program Description ................. 35Geophysical Sounding Rocket Experiments ....... 35

Aerobee Probes Atmosphere Composition andPressure ...................... 35

Nike-Asp Investigates Winds in Upper Atmosphere 36Nike-Cajun Grenade Experiment ........... 36Aerobee Cloud-Cover Experiments .... o...... 36Aerobee Ionosphere Investigations ......... 37SHE Launchings ................... 37NERV Experiment s Begin ............... 37

NERV Payload Description ............. 38Argo D-8 ..................... 38Mold Spore Experiment .............. 38Two Aspects of Radiation Study .......... 38Prime Contractors ................ _0

Aerobee Measures Upper Atmosphere Neutrons ..... AONike-Asp Delays .................. _0

Astronomical Sounding Rocket Experiments ....... _lAerobee Ultraviolet Experiments .......... _lProgress On Scheduled Satellites ........... _2

Geophysical Satellites ................ _2Atmospheric Structure Satellite .......... _2Micromet eoroid Satellite .............. _3Air Density-Drag Measurements Satellite ......Ionosphere Direct Measurements Satellite ...... _J,Ionosphere Beacon Satellite ............ _5Swept-Frequency Topside Sounder .......... A6

- ii -


8/290

Fixed-Frequency Topside Sounder ..........Electron Density Profile Probe.... ....International Ionosphere Satellite (U.K.'No.'I) [ .International ProgramSatellite (No. 2) ......Energetic Particles Satellite ...........Recoverable Nuclear Emulsions Probe ........Orbiting Geophysical Observatory ..........Principal Astronomical Projects ...........GamnaRayAstronomySatellite ...........Orbiting Astronomical Observatory .........Orbiting Solar Observatory .............Recent Progress in Scientific SatelliteInvestigations ...................Explorers VI and VII and Vanguard III .......Scientific Data from Echo I ............CHAPTER - LUNAR,PLANETARY,NDINTERPLANETARYROGRAF_...

Progress In Planning.................Lunar Spacecraft Being Developed..........More AdvancedSpacecraft Being Designed ......Lunar Program ....................Data Sought on Origin of Earth-Moon and PlanetarySystems .....................Atlas-Able V....................Ranger.......................First Ranger Missions ..............Objectives of Last Three Rangers.........Major Experiments ................Surveyor Soft-Landing Spacecraft ..........Lunar Orbiters Basedon Surveyor .........Prospector ......................Planetary Missions ..................Long-TermObjectives ................Pioneer V Orbital Elements..............Commnnications..................Scientific Results .................MagnetometerProbe.................._riner Fly-by Series ................VenusMission Objectives ..............._rs Nission Objectives ...............Voyager Orbiter Series ................

CHAPTER - TRACKINGNDDATAACQUISITION...........Keeps Pace_fith SpaceExploration .........._nitrack Network ..................

Cc_n_%.-m_ir.+.'__nn,_. , , , , , , , , _ , , , , , = , = , ,

PAGE4747484S484949515152525/+5455

575757585858585859595959616Z616162626]6364646666

67676767

- iii -


9/290

Control Center Moved...............Standardization of Telemetry Systems........Automatic Data Read-Out System...........Photoelectric Optical Tracking Equipment......Conversion of Tracking Frequencies .........DeepSpaceNetwork..................CanProvide Continuous Communicationwith Inter-planetary Craft .................Construction ....................Studies of Larger Antennas Begin..........Optical Tracking ...................Supporting Activities ................Jodrell Bank Telescope Contract Extended......Navy To Support TIROS...............Plans for Centaur Support .............

CHAPTER - LAUNCHEHICLEPROGRAMNDLAUNCHOPERATIONS....Standardized Vehicles ................Vanguardand Jupiter C Programs Completed .....Scout . . .... Thor-AgenaB and Atlas-Agena B...........Atlas-Centaur ...................Saturn Is Largest Vehicle .............Study Saturn Successor...............Nova. ..... .... Nuclear and Electric Propulsion ..........Scout Flight-Test ed ................Scout X .....................First Complete Scout Launched on July 1 ......First Delta Test ..................Delta No. 2 Attains Objectives ...........Nine Agena B Stages Under Contract .........Thor-Agenas To Use P_ ..............Atlas-Agena B Will Launch Ranger Capsules ...._rshall Has Technical Direction ..........NASAExpandsCentaur Development Period ......Propulsion SystemsTests Begin..........Marshall Develops Saturn First Stage........Engines UseLOXand RP-1.............Complete First Static Test Series ........Stage Designated SA-T ..............Three ProblemAreas ...............Will Simulate LaunchModel............ComponentFabrication Progresses.........C-1 Third Stage Contract To Be Let ........Contract for AdvancedSecond-StageEngineSigned.....................

PAGE6969696970707o7O7O7171717171737373737374747474757575757777797979797980818181818182828282

- iV -


10/290

DynamicTest Stand Being Constructed .......NewData Processing System Installed .......LaunchFacilities Progress............Complex3_....................Complex37....................Saturn First Stage Transportation ........Personnel Transfer on July 1...........Test F-1 EngineTs Thrust Chamber.........Launch Operations Directorate Established ......Launch Vehicle Facility Status ...........ProgramFacility Status ..............Scout . . . . . . . . . . ............Delta . . . ........ . . ...... . .Thor-Agena B...................

CHAPTER - PROPULSIONNDNUCLEARNERGYPPLICATIONSORSPACE......................Energy - Key To Space Exploration ..........Liquid-Propellant Rocket Engines ...........

H-1 Hydrocarbon-Oxygen Engine ...........Tests of Clustered Engines ............Strength and Reliability Requirements ......

XLR-115 Hydrogen-0xygen Engine ...........Turbopump Drive Unconventional ..........Program Generally on Schedule ..........Summary of Recent Accomplishments ........

XLR-119 Hydrogen-0xygen Engine ...........Pratt & Whitney Chosen ..............

J-2 Hydrogen-Oxygen Engine .............F-1 1.5-_llion-Pound Thrust Hydrogen-Oxygen

Engine ......................Static Tests of Uncooled Thrust Chambers .....New Test Stand Damaged ..............Tests of Gas Generator ..............Turbopump Assembly Completed . Thrust Chamber Fabrication Tech_ques ......

Advanced Technology - T_quid Rocket Engines ....Plug Nozzle ...................Storage of Propellants in Space Environment . . .Studies of Combustion Instability ........Tests of Turbopumped Rocket Engine ........

Solid-propellant Rockets ...............Scout Vehicle Development .............

Algol ......................Castor. . ...... ............Antares ...............

PAGE83_38383_384

_48585_58586s6

_7_787878888888889898990909O9O919191919292929293939_9A9A9_

-- V --


11/290

PAGEAltair ...................... 95

Sounding Rocket Develo_nent ............ 95Arcon ...................... 95Iris ....................... 96Eleven Types Employed or Planned. ....... 96Nike-Asp Flights Suspended ............ 97

High-Performance Rocket Engines .......... 97Upper-Stage Rockets ............... 97'_ozzleless" Rocket ............... 99Experimental Rocket Engine With Layered

Construction .................. 99End-Burning Propellant Charges in Low-Weight

Upper Stages .................. 99Nozzle Cooled by Liquid Metal ......... 99Sounding Rocket Combining Several Advanced

Design Features ............... lO0Very Large Solid-Propellant First-StageEngines ..................... lO0

Three Contractors Selected ............ lO0Steering and Velocity Control Studies ....... lO1

"Steering Package" Concept ............ lO1Thrust Modulation ................ lO1

High Temperature Nozzle Materials and _nu-facturing Techniques ............... 1G2

Segmented and Tapered Rocket Construction ..... 102Electric Propulsion ................. 102

Electric Arc-Jet Engines .............. 1021-KW Arc-Jet Engine ........ ....... 10330-KW Arc-Jet Engine ............... 103Ion Engines .................... 103Experimental Engine Contract Awarded ....... lO_

Applied Research and Development .......... lO_Nuclear Energy Applications For Space ........ 105

Nuclear Heat Transfer Rockets ........... 105NASA-AE C Responsibilities ............ 105Joint AEC-NASA Nuclear Propulsion OfficeEstablished .................. 106Applied Research ................. 106

AEC Test Fires Kiwi-A-Prime Reactor ........ 106Early Step in Project Rover ........... 106

Nuclear Rocket Test Study ............. 107Two Companies Selected for Contract ....... 107To Be "Paper" Study Only ............. 107Three or More Approaches To Be Considered .... 108

Nuclear Electric Power Generating Systems ..... 108SNAP-8 Development ................ 108High-Power Reactor Turbogenerator Systems .... 109

Radioisotope Thermoelectric Generator for LunarLanding Missions ................. 109

-vi-


12/290

PACECompact Auxiliary Power Unit Required ...... 10915-Watt Unit Being Considered .......... llO

CHAPTER 9 - INTERNATIONAL PROGRAmmeS............... iiiTracking Network Negotiations ............ iiiSatellite Applications ................ lll

International Participation in Echo i ....... lllInternational Cooperation in Second TIROS

_-_o_ _o_+ 112Research In Space Sciences .............. ll2

Argentina ..................... ll2Australia ..................... ll2Canada ....................... ll2Chile ....................... ll3Italy ....................... ll3Japan ....................... ll3United Kingdom ................... 113

Dissemination of Technical Information ........ ll4Explorer VII Calibrations ............. ll4Exhibits, Motion Pictures, and Publications .... ll4

Fellowships And Exchange Programs .......... ll4International Organizations ............. ll5

CHAPTER i0 - RESEARCH PRI_r_RILY SUPPORTING AERONAUTICSACTIVITIES ..................... ll7

Stability And Control Of Aircraft ........... 117Research on VTOL/STOL Aircraft ........... 117

Tests %@ith Flight Simulator ........... ll7The Lifting Fan Engine .............. ll7Jet-Powered Turbofan VTOL Airplane ........ ll9

Aeronautical Propulsion Systems ........... ll9Inlets of Jet Engines ............... ll9

Design Criteria Established ........... 121V_ind Tunnel Studies ............... 121Other Studies to Improve Jet Engine

Performanc e .................. 122Aeroelasticity And Dynamic Load Problems ....... 124

Variety of Studies In Progress ........... 124Blast Loading Studies .............. 124Rotary Wing D}mamics ............... 125Studies of Flutter in X-15 Fairing Panels .... 125Measurements of Severe Storm Turbulence ..... 125High-Altitude Atmospheric Measurements ...... 126

Aeronautical Structures ............... 126High-Temperature Structures ............ 126

Studies of Heat Transfer Through SandwichPanels ..................... 126

-vii -


13/290

PAGECompressiveStrength of Sandwich Panels ..... 127

CHAPTERi - RESEARCHRI_L_RILYSUPPORTINGPACEACTIVITIES 129Astronautics Research ................ 129Control and Guidance of Space Vehicles ....... 129Precise Attitude Control for Satellites ..... 129Stability and Control of Entry Vehicles ...... 129Studies of Lateral Movementsof EntryVehicles .................... 129Use of Drag Control During AtmosphereEntry . . . 130Aerodynamic Heating Problems............ 130Heating on Lifting Entry Vehicles ........ 130Aerodynamic Heating of Returning Spacecraft . . . 132Theoretical Predictions of Heat Transfer andPressure .................... 132Thermal Radiation Protection ........... 133Chemical Rocket Propulsion ............. 133Sea-Level and High-Altitude Simulators ...... 134CombustionResearch ............... 134Hypergolic and "Storable', Propellants ...... 135Fuel Sloshing in Rocket Tanks .......... 135Nuclear Propulsion ................. 136Heat Transfer Research.............. 136GaseousReactor ................. 136Neutron Probe .................. 137NewNuclear Systems Division at Lewis ...... 139Electric Propulsion ................ 139Ion Rockets ................... 1A2PlasmaRockets.................. 143Electric Thermal Rockets............. 1A3Materials for SpaceStructure ........... l_High Temperature Materials ............ l_Studies of High-Temperature Coating _terials . . 1AAStudies of Surface Emissivities of Materials... 145Fatigue Characteristics of Metals . . . ..... 146Materials for Powerplants ............. 146Experimental Study of the Growth of Voids inSilver ........... , ......... 146Materials for Cryogenic Propellant Tanks..... 146Tungsten and Tungsten Alloys in Tension at VeryHigh Temperatures ............... 147Boiling SodiumCorrosion Research withRefractory Metals ..... - - -- - - -- - 147Alloy Systems for High Temperature'(1,8OO-2,100F. ) ................... 148Effects of F_crometeoroid Impacts on SpaceStructures ................... 148

- viii -


14/290

PAGENozzle Materials for Solid PropellantRockets i_8 @ 4

Structures of _nn_ Space Cabins ......... 1_9Erectable Structures ............... 1_9Rigid Space Cabins ................. 150

Studies of Pressure Vessels ............ 150Landing Impact Structures ............. 151Fluctuating Loads on Multi-Stage Rockets ...... 151Inflated Sphere Landing Vehicle .......... 152

Direct Conversion Electrical Power Systems ...... 152No Rotating Parts Required ............. 152Analysis of Direct Conversion and Conventional

Systems ..................... 153Thermionic and Plasma Diodes ............ 153Photoelectric Cells ................ 153

CHAPTER 12 - SPECIAL RESEARCH PROJECTS .............. 155Research Projects Convert Theory To Reality ..... 155The X-15 Research Airplane .............. 155

Two Records Set .................. 155Four-Year Speed Record Broken .......... 155Altitude Flight Record Broken .......... 156

Executes Space Functions .............. 156Heat Barrier and Handling Tests ......... 156Estimated 500 Degrees Air Friction Heating .... 156Other Pilots Test X-15 .............. 157

XLR-99 Engine Being Installed in X-15 No. 2 .... 157Tests With New Engine Expected Soon ....... 157

X-15 No. 3 Being Rebuilt .............. 157Repairs Required After Test Stand Explosion . . . 157

Status of _jor Program Objectives ......... 158Flight Control at Very High Altitude ....... 158Atmospheric Exit and Entry Techniques ...... 158Terminal Guidance ................ 159Aeromedical Tests ................ 159Landing Gear Research ............. 159

NASA Support of the Dyna-Soar Program ........ 160The Dyna-Soar-I Program .............. 160Program Has Two Phases .............. 160

Role of NASA ................... 160Glider Requirements ............... 160Studies in Progress ............... 161Low Speed Dynamic Characteristics ........ 161Investigations at Transonic Speeds ........ 161Tests at Hypersonic Speeds ............ 162

Flight Research Center Participation in the Dyna-Soar Program ................... 162

- ix -


15/290

PAGEAir VehiclB Systems Support ........ 163Flight Test Operation .............. 163Investigation of Landing Problems ......... 163Air Vehicle SystemsDevelopment .......... 16_

CHAPTER3 - RESEARCHENTERDIRECTSUPPORT........... 165AdvancedResearch Applies To ManyPrograms..... 165Project Scout ................... 165Vehicle Is Langley Concept............ 165Design Data Obtained............... 165Project Centaur .......... i ....... 166Propellant Tank Insulation Studies ....... 166Uninsulated Tank Experiments ........... 166Studies of Propellants During Weightlessness... 166GroundOperations Problems............ 167Fluctuating Pressure Tests ............ 167Studies of Base Heating ............. 167Multiple Studies at Langley ........... 168Project Echo.................... 169Sphere Is Langley Development .......... 169Rigidization Study................ 169Project Nimbus................... 169Stabilization and Control Development ...... 169Project Mercury .................. 169Wind Tunnel Tests ................ 169High Altitude Simulation Tests .......... 169Capsule Preparation ............. 170Tracking and Ground Instrumentation ....... 170Other Assistance ........... . ...... 170Orbiting Astronomical Observatory ......... 170Preliminary Work in Progress........... 170Project Trailblazer ................ 171Cooperative Project ............... 171Trailblazer I .................. 171Trailblazer II .................. 171Micrometeoroid Satellite .............. 171Langley Develops Payload............. 171

CHAPTERA - CONSTRUCTIONNDEQUIPmenT............. 173AmesResearch Center, Mountain View, Calif ...... 1733.5-Foot Hypersonic Wind Tunnel .......... 17312-Inch Helium Wind Tunnel............. 173Flight Research Laboratory ............. 173H_qoervelocity Research Laboratory ......... 175_ss Transfer Cooling and Aerodynamics Facility . . 175Centrifuge Facility Modifications ......... 175Data Reduction Center ............... 175

-- X --


16/290

PAGEFlight Research Center, Edwards, Calif ........ 176

X-15 Research Airplane Program Facilities ..... 176Test Stands for F-1 Engine Development ....... 176

Goddard Space Flight Center, Greenbelt, Md ...... 176Jet Propulsion laboratory, Pasadena, Calif ...... 177Laboratory and Engineering Facilities ....... 177

Addition to Guidance Laboratory 161 ....... 177Plant Services Engineering and Shop Building... 177Vehicle Assembly Building and Environmental

Testir_ T_b_+ _y ............... 177Solid-Propellant Facilities ........... 177Liquid-Propellant Facilities ........... 177

Support Facilities ................. 178Administrative Services Building ......... 178Reports and Periodicals Building ......... 178Utilities .................... 178

langley Research Center, Hampton, Va ......... 17820-Inch Variable _ch Blowdown Tunnels ....... 178Eight-Foot Transonic Pressure Tunnel ........ 17826-Inch Transonic Pressure Tunnel ......... 17919-Foot Pressure Tunnel .............. 179Structures Research Laboratory ........... 179Other Projects ................... 179

Lewis Research Center, Cleveland, Ohio ........ 179Nuclear Propulsion Facilities ........... 179Propulsion Systems Laboratory ........... 180Rocket Systems Research Facility .......... 180Supersonic Wind Tunnel ............... 180Hypersonic Rocket Propulsion Facility ....... 180_terials Research Laboratory ........... 180Rocket Engine Research Facility .......... 181Cleveland .................... 181

Plum Brook .................... 181Ion and Plasma Jet Facility ............ 181Contemplated Construction ............. 181

Marshall Space Flight Center, Huntsville, Ala .... 182Dynamic Test Stand ................. 182Static Test Stand ................. 182Pressure Test Cell.. . . 182Extension to Assembly _ll&ngs 705"-'A706 : 182Transportation Facilities ............. 182Other Projects ................... 183

Wallops Station, Va ................. 183Launching Facilities ....... 183DOVAP (Doppler Velocity and Positioni and

Ionosphere Facility ............... 183Communications ................... 183Other Projects ................... 183

-xi-


17/290

PAGEAtlantic Missile Range, CapeCanaveral, Fla ..... 18_Saturn Launch Facilities .............. 18_Saturn Transportation Facilities .......... 18_Centaur Launch Facilities ............. 185

CHAPTER5 - LIFE SCIENCESPROGRAMS............... 187Organization Progress ................ 187Flight Medicine and Biology: Biotechnology .... 187>light Medicine and Biology: BiomedicalFlight Experiments................ 188SpaceMedical and Behavioral Sciences ....... 188Space Biology ................... 189Three Life Sciences CommitteesAppointed ...... 189NASA-Departmentof Defense Coordination ...... 189Foreign Scientists to Participate ......... 190Biosciences Conferences .............. 190Spacecraft Decontamination Techniques ...... 190Radiation Problems in _nned Space Flight .... 190Biomedical Experiments inExtraterrestrial Environments ......... 190

CHAPTER6 - ORGANIZATIONALEVELOPMENTS............ 193_rshall Transfer Completed ............. 193Largest NASAFacility ............... 193President Dedicates Center............. 193Expansion of Functions ................ 193NewLaunch Organization Activated .......... 193Office of Technical Information And EducationalProgramsEstablished ................ 194Administration Of Research Grants And ContractsReorganized .................... 19ANuclear Propulsion Coordination Office Established.. 195NASAAnd DODOrganize Coordinating Board....... 195

CHAPTER7 - PROCUREmeNT,ONTRACTS,NDGRANTS......... 199Bulk Of NASABudget Spent With Industry ....... 199Procurement Placement ............... 199Method of Placement - Awards to Business ...... 199Procurement Fromor Through Other GovernmentAgencies..................... 200Major Contract Awards ............... 201Research Grants and Contracts ........... 202Eighty-Three Awards _de ............. 202Procurement _nagement ............... 202Revised Procedure for Source Evaluation andSelection ................... 202

- xii -


18/290

PAGEProcurement Plan................. 202Source Evaluation Board ............. 202Reliability Program ............... 202Preparation of ProcurementRegulations ....... 203

Small Business.................... 203Summaryof Awards ................. 203ProgramManagement................ 203CHAPTER8 - PERSONNEL ...................... 205

The NASA Staff .................... 205Recruiting Scientific Personnel ........... 206Youth Program .................... 208Dr. Dryden Honored .................. 208Executive Personnel Changes ............. 208Research Center Wins Safety Award .......... 209

CHAPTER 19 - FINANCIAL _@aNAGEI_[ENT................ 211CHAPTER 20 - OTHER ACTIVITIES ................... 215

Scope Of Chapter ................... 215NASA Patent Program ................. 215

Reporting of Inventions by NASA .......... 215Protection of NASA Inventions ........... 216U.S. Settles Goddard Patent Claim ......... 216

Guggenheim Foundation Receives $1 Million .... 216Armed Services and NASA To Share Payment ..... 216Settlement Covers Two Patents .......... 216

Other Patent Infringement Claims .......... 216Review of Patent Applications ........... 217

Inventions And Contributions ............. 217Purpose and Authority ............... 217Third Waiver Petition Granted ........... 217Contributions Awards ................ 217

Long Range Studies .................. 218Information And Education .............. 219

Technical Information ............... 219International Exchange Program .......... 219Technical Publications Release .......... 219Domestic Information Exchange and

Coordination .................. 219Technical Dictionary ............... 219

Publications .................... 219Motion Pictures .................. 220Exhibits ...................... 221

- xiii -


19/290

ILLUSTRATIONS

Delta Launch Vehicle on Pad Prior to Launching Echo I . . .Aluminized Plastic Shell of Echo I Is Inspected ......

Schematic Portrayal of Transcontinental Communications ViaEcho I..........................Nimbus Meteorological Satellite ..............Mercury Capsule Being Prepared For _y 9 Beach Abort Test .Mercury Capsule Being Lowered in Altitude Chamber for

Testing .........................Mercury Control Central Facility at Cape Canaveral, Fla...

Nuclear Emulsion Recovery Vehicle (NERV) ..........Orbiting Astronomical Observatory (OAO) ..........Ranger and _ariner Spacecraft ...............Minitllack T_acking and Data Acquisition Network -- Station

Locations ........................

Baker-Nunn Satellite-Tracking Camera and Baker-Nunn StationLayout ...................... _ . . .

Scout Launch Vehicle Rises from Wallops Station, Va., onJuly i ..........................Schematic Portrayal of Separation Sequence in Delta Launch.Iris Sounding Rocket Is Launched from Wallops Station . . .X-l& Aircraft in Hovering Flight ..............Large-Scale Model of V/STOL Research Aircraft .......Aerodynamic Flow Patterns .................Model of Entry Vehicle in 12-Inch Shock Tube ........Cutaway View of Gaseous Reactor ..............Neutron Probe, Front and Side Views ............Power Response Curve for Solid State Neutron Probe .....

PAGE

Frontispiece12

142125

2831395365

68

72

767898

118120123131138l_Olgl

- xiv -


20/290

AmesFive- Degree-of-Freedom Simulator ...........Organizational Chart of NASA................MapShowing Locations of NASA Installations .........

PAGE17_197207

le

e

o

5.6.

TABLES

NASA Satellite and Probe Launchings, April 1 -September 30, 1960 ..................

Method of Placement of Direct Contract Awards toBusiness ..... . . . . . . . . . ...... . . .

Distribution of NASA Personnel .............NASA Fiscal Year 1960 Program Effort (Financial Report).NASA Budget Estimates, Fiscal Year 1961 .........Fiscal Year 1961 Financial Status as oi"September 30,

1960 .........................

2OO2O6211212

213

--_V --


21/290

AppendicesAPPENDIX A - Memberships of Congressional Committees on

Aeronautics and Space ...........

APPENDIX B - Membership of the National Aeronautics andSpace Council ...............APPENDIX C - Membership of the NASA-DOD Aeronautics and

Astronautics Coordinating Board ......APPENDIX D - Membership of the Civilian-Military LiaisonCommittee .................APPENDIX E - Membership of NASA Committee on Long RangeStudies ..................

APPENDIX F - Membership of NASA Inventions andContributions Board ............APPENDIX G - Membership of NASA Advisory Committee on

Space Medical and Behavioral Sciences . . .APPENDIX H - Membership of NASA Advisory Committee on

Space Biology ...............APPENDIX I - Membership of NASA Advisory Committee on

Flight Medicine and Biology .......

APPENDIX J - Memberships of NASA Space Sciences SteeringCommittee and Subcommittees ........APPENDIX K - Research Grants and Contracts ........APPENDIX L - R&D Contracts or Amendments Thereto of

$100,000 and Over Shown By Program .....

PAGE

223

225

22?

229

231

233

235

237

239

263

-xvi-


22/290

A f lood- l i t De l ta launch veh ic le i s poised on i t s l a unch pa d p r io r to p la c ingthe Ec ho I comm unica t ions s a te l l i te in to o rb i t .


23/290

SECTION

PROGRESSN NASAAERONAUTICSAND SPACEPROGRAMS


24/290

Introduction and HighlightsChapter 1

SUMMARY OF PROGRESSNASA pursued aeronautical research and space research

and development across a broad front during the April 1 -September 3u, iWou period covered by its Fourth SemiannualReport. Initial experiments with the Echo I communicationssatellite and the TIROS I weather satellite yielded encour-aging results, indicating the feasibility of operationalsystems. Other activities ranged from work on VTOL(Vertical _Take-Off and Landing) aircraft to planning forspacecraft missions to the moon and beyond.

The X-15 rocket-powered airplane set world speed(2,196 mph) and altitude (136,500 feet) records with anengine several times less powerful than the final versionon which its design performance is based.

Saturn, the giant launch vehicle which shares toppriority with Project Mercury, completed in satisfactoryfashion its first series of static tests one month ahead ofschedule. Meanwhile, other members of NASA's new fleet ofstandardized launch vehicles began moving on line to replacethe older vehicles which owed their parentage to componentsdeveloped in either the Department of Defense missile pro-gram or Project Vanguard.

The Delta vehicle completed its first successful launchwhen it propelled the Echo I inflatable sphere into orbit.Scout was being readied for its second full-scale flighttest after one partly successful launch.

The production model of the Project Mercury flightcapsule entered the shakedown, or qualification stage. Thecapsule passed a flight test of its rocket-equipped escapetower, with the combination showing good aerodynamic sta-bility. An entry test to qualify the capsule structure andheat protection system ended when a malfunction occurredabout one minute after lift-off, resulting in destructionof the Atlas launch vehicle.

The seven Mercury astronauts continued intensifiedtraining preparatory to the first manned Redstone ballisticflight and the first manned orbital flight in 1961.

-1-


25/290

The worldwide Mercury Tracking and Ground Instrumenta-tion Network progressed on schedule toward completion earlyin 1961. Formal agreements for all NASA tracking stationsabroad had either been signed or were in final stages ofnegotiation by the end of September.Other international developments included: i) discus-sions with Australia, Great Britain, France, and Spain con-cerning use of their air-sea rescue units in Project Mercury;2) participation by many foreign scientists in the Echo Iexperiment; 3) discussions and/or agreements with Australia,Canada, Chile, Italy, Japan, and the United Kingdom, amongothers, concerning cooperative space projects.The Launch Operations Directorate (LOD) was createdwithin the Office of Launch Vehicle Programs to facilitatestandardization of launch operations and facilities. LODwill launch most NASA vehciles and support the launch oper-

ations of the remainder.The NASA Long Range Plan continued to serve as theguide to advanced missions including those of Ranger,Surveyor, Prospector, and Mariner spacecraft. Ranger willland the first survivable payloads on the moon; Surveyorand Prospector will make controlled landings on the moon;and Mariner will carry out deep penetrations of interplane-tary space, including missions to Venus and Mars.NASA's Committee on Long Range Studies has set inmotion, through contracts to private research organizations,

a series of studies concerning the wide-ranging implicationsof space exploration, including practical applications andlegal aspects.NASA's personnel increased from 9,755 to 15,603, therise for the most part reflecting the transfer to NASA ofthe Army Ballistic Missile Agency's Development OperationsDivision (Marhsall Space Flight Center), Huntsville, Ala.Highlights of NASA aeronautical and space activitiesduring the report period follow:

...April 1 -- TIROS I (_elevision Infra-Red ObservationSatellitei, a 270-pound experiment_l wea_her-satellite,_as launched by a Thor-Able from AF_, attaining a near-circular orbit with a perigee of 428.7 miles, an apogee of465.9 miles. TIROS I made meteorological history betweenApril 1 and June 29 when its two television cameras trans-mitted 22,952 photographs of cloud cover and other phenom-ena of value to weathermen.

-2-


26/290

...April 29 -- Interim or formal agreements for all overseasMercury tracking stations were concluded and constructionhad started on the sites by June 30....May 6 -- Maj. Robert M. White, USAF, flew X-15 No. i toan altitude of 60,800 feet and a Mach number 2.2. ..May 9 -- The first production model of the ProjectMercury capsule was test flown in a simulated "pad abort"at Wallops Station to check the escape system, landingsystem, and post-landing equipment....May 12 -- NASA pilot Joseph Walker flew X-15 No. I to78,000 feet and a speed of Mach 3.2....May 13 -- The first attempt to orbit a lOO-foot diameterProject Echo passive communications satellite ended whenthe attitude control jets in the second stage of the Deltavehicle apparently malfunctioned....June 8 -- While undergoing ground tests by the contrac-tor, North American Aviation, Inc., the fuel and hydrogenperoxide tanks of X-15 No. 3 exploded on the stand. Con-tractor pilot Scott Crossfield was uninjured....June 15 -- The first series of Saturn static tests wascompleted with a 122-second firing of the complete proto-type eight-engine first stage at the Marshall Space FlightCenter....June 26 -- The last communication with the Pioneer Vspace probe, a six-minute message, was received at JodrellBank. At that point, the probe was an estimated 22,462,740miles from earth. Pioneer V was launched on March ll.

...July 1 -- The Development Operations Division of ArmyBallistic Missile Agency, Huntsville, Ala., was transferredofficially to NASA and became the George C. Marshall SpaceFlight Center. ..July 1 -- The first complete four-stage Scout was launchedfrom Wallops Station. The first three stages performed satifactorily but fourth stage ignition was prevented by commandsignal from Wallops when faulty radar indicated wrongly thatthe vehicle was deviating from its course....July 29 -- An Atlas launch vehicle exploded during anattempted entry test that was to have qualified the struc-ture and the heat protection system of the Mercury produc-tion capsule.

-3-


27/290

-..August 4 -- X-15 No. 1 set a new world speed record of2, 196 mph -- more than three times the speed of sound (Mach3.31). NASA pilot Walke_ was at the controls....August 12 -- With Maj. _ White piloting, X-15 No. 1reached a world altitude record of 136,500 feet, surpassingthe previous record of 126,200 feet set in 1956 by the X-2....August 12 -- Echo i, the first passive communicationssatellite, was launched by a Thor-Delta from AMR. The lO0-foot-diameter inflatable sphere was used to relay voice mes-sages, facsimile photographs, teletype signals, and two-way telephone conversations. Transcontinental and trans-Atlantic signal relays were completed, and experiments wereconducted to learn more about the effects of the ionosphereon radio signals....September 19 -- The first of a series of NERV (NuclearEmulsion Recovery Vehicle) experiments to provide detailedanalysis of the lower portion of the Great Radiation Regionwas launched from Point Arguello, Calif. The NERV capsulereached an altitude of 1,260 miles. It was recovered inthe Pacific, 1,300 miles from the landing point....September 30 -- Formal agreements for all NASA trackingstations, planned at present, were either concluded or nearconclusion.

-A-


28/290

g

ig

f..,.1,-1.,,


29/290

o

i

E-,

o'=

A

0

o=

o

uc,

,.-I

c_ E_

,-I

E-,_

o w., o

i

oo_

b._o

o _ .._ _: o_= _ I_ "__. _. _ _._.o_ _ o._._o__ii _0.o:o0_12_,o

-6-


30/290

o

o= o

_oo. .J(1) .,-I"cJ

0 0

de0 _

o_

Z _

OF PO0_ QUALITY


164/290


165/290

For space flight within the solar system, specific im-pulses of about i,O00 seconds are desired. This should beadequate for such missions as raising earth satellites fromlow to high-altitude orbits. For deep space and other ad-vanced missions, higher specific impulses will be required.

Experiments and investigations in progress at Lewiscenter on very small electric rocket engines that can betested in glass bell jars and with other bench-scale appa-ratus. Four stainless steel vacuum tanks (diameters of 3and 5 feet) in which pressures below one billionth of atmos-pheric pressure can be obtained, are used to investigatelarger ion rockets. Tanks with diameters of 15 feet and25 feet are being fabricated. In these, it will be possibleto investigate larger electric rockets and to evaluate inter-actions of smaller rockets in clusters.

Ion Rockets -- Ion rockets are particularly suited tooperation at very high specific impulse; the higher the im-pulse, the higher the power efficiency of the ion rocket.A year ago, NASA scientists had achieved ion rocket powerefficiencies of 58 percent, with specific impulses of about20,000 seconds. Since then, ion rocket efficiency has beenimproved for lower specific impulse. One type of ion rocketthat has been developed and tested uses cesium propellantwhich is passed through an ion emitter of porous tungsten.This engine achieved a power efficiency of slightly morethan 50 percent, at 12,O00 seconds specific impulse. How-ever, the porous tungsten emitters are difficult to fabri-cate and to join to surrounding engine parts. Satisfactorymethods have yet to be devised. Research on these problemsis continuing both at Lewis and in private industry.

An alternate approach -- known as the "reverse feed"system -- is also under study. Solid, rather than porous,tungsten is employed as the emitter. Cesium is fed ontothe ionizing surface from propellant injectors located"downstream" of the emitter. The arrangement eliminatesfabrication problems associated with porous tungsten, butintroduces new difficulties: as neutral cesium propellantatoms are injected onto the emitter, some encounter high-velocity ions coming from the emitter, and charge-exchangetakes place. In the process, low-energy ions are formed,some of which are intercepted on the accelerating electrodeand cause erosion.

Recent theoretical studies indicate that proper designcan reduce the charge-exchange enough for the reverse-feedengine to compare with engines employing porous emitters.The theoretical potential of this engine, however, has notbeen achieved in practice.

- 142 -


166/290

These and other serious problems with cesium propel-lant have dictated development of mercury as an ion source.Ions are generated by bombarding mercury vapor with mag-netically constrained electrons. Power efficiencies wellabove 60 percent have been measured at a specific impulseas low as 5,500 seconds. Propellant utilization of about80.percent has been demonstrated.

How to neutralize the ion beam as it leaves the rocketIn theory, introducing electrons which carry negativecharges into the beam of positively charged ions shouldneutralize it. Recent experiments to test the theory indi-cate that this technique reduces beam spreading to a markeddegree, indicating that the ion beam has been at leastpartially neutralized. Further experiments are requiredto learn whether this method can completely neutralize theion beam. Apparatus and instrumentation have been fabri-cated, and experiments will soon be under way. Tests invacuum tanks may leave doubt about neutralizing the ionbeam in space. Ultimately, a flight experiment may be re-quired.

Plasma Rockets --Work on a number of plasma accelera-tion methods (described in Chapter ll of NASA's Third Semi-annual Report to Congress) has been narrowed to two devicesshowing good potential over-all power and propellant utili-zation efficiencies. One is a traveling-wave plasma accel-erator which employs a radio-frequency power supply. A40-kw power supply has been purchased and initial experimentsare in progress. The other method employs two coxially-mounted (one inside the other) tubes between which an arcforms, each arc producing a "pulse" acceleration in theplasma. Apparatus for studying this acceleration schemewas being designed as the report period closed.

A number of techniques for generating plasma efficientlyare being investigated at Lewis Research Center. Plasmasources under study include radio-frequency induction heat-ing of a gaseous propellant, three different configurationsof electric arcs, and an oscillating-electron device. Anyof these generators could be combined with any of the accel-erators into a plasma rocket system.

Electric Thermal Rockets -- For missions requiring aspecific impulse of 1,200 seconds or lower, such as satel-lite orientation and orbit adjustment, electric-thermal

- IA3 -


167/290


168/290


169/290

Fati6ue Characteristics of Metals -- An importantmethod of judging the resistance of structural materialsto fatigue is the rate at which cracks occur and propagate.Practically all information on this subject deals withcracking under repeated, steady pressures or stresses.Recent tests at Langley of aluminum-alloy sheet specimenshave shown that an appreciable delay in crack propagationis encountered, and is followed by a resumption at a lowerrate when the stress amplitude is reduced. Photographs ofsurface of fractures are also being studied in the hope ofdeducing the kinds of loads or stresses that caused thefractures. Results of these studies should contribute tounderstanding of fatigue and to better methods for assessingit in the design stages. The work is being continued onhigh-strength steels of the types used in launch vehicletanks and in the structures of advanced vehicles.

Materials for PowerplantsThe search for better materials for space propulsion

systems and a better understanding of why materials behaveas they do under the unique conditions encountered in spaceand in high performance powerplants continues at the Langley,Ames, and Lewis Research Centers. These basic investiga-tions promise better understanding of how and why materialsfail. Studies have included the effects of heat treatmenton the mechanical behavior of ceramic materials, and measure-ment of the way materials bend or deform for single crystalssubjected to both chemical treatment and thermal treatment;these treatments affect their purity, surface structure, andinternal structure in known ways.

Experimental Study of the Growth of Voids in Silver --Voids or cracks that form in metals when they are deformedconstitute one of the principal processes leading to break-down or failure. The growth rate of these voids has beenmeasured in silver at several temperatures. It was shownthat minute defects produced during deformation migrate tograin boundaries where they collect to form voids. Therate of void growth increases with increasing temperature.When several small voids are close together, they attracteach other and have a tendency to join; this occurrenceappears to be of major importance in the formation of voids.Further studies are being conducted to confirm the inter-pretations of these experiments.

Materials for Cryo6enic Propellant Tanks -- Thisproject was undertaken to permit rocket fuel tanks to bemade lighter without losing strength. Sheets of titaniumalloys were subjected to conventional strength tests; some

- l&6 -


170/290

were stronger (in ratio of density to strength) and tougherat room temperatures than any of the best heat-treated steelsnow available. They also stood up well at very low (cryogenictemperatures.Several alloys each of aluminum, austenitic stainless

steel,_ and titanium have been tested at cryogenic temper-atures. It is possible to state tentatively which are thebetter alloys of each metal but not which metal is mostpromising for minimum weight application. This is becausethe strongest alloys are also the hardest to work and aremost affected by we_u_, _u_, and _-_-- fittings. Equipmenthas been designed and tests have started on small-scalepropellant tanks to determine their strength at temperaturesdown to -423F.Tungsten and Tunssten Alloys in Tension at Very High

Temperatures -- Lewis Research Center is working to-developtungsten and tungsten alloys that can be fabricated orshaped. Melting and casting of tungsten results in coarsegrain structure that is difficult to work. Hot extrusionof tungsten alloys does not fully refine the grain structure.Addition of small amounts of molybdenum improves the internalstructure of the tungsten, and should make it easier to workand fabricate. NASA scientists are continuing to assess themechanical properties of these and other tungsten alloys attemperatures as high as 4,500F.

Boilin_ Sodium Corrosion Research with RefractoryMetals -- Auxiliary nuclear and solar power systems for spacevehicles will use liquid metals as a working fluid to drivethe electrical generator in much the same way as steam isused in conventional power plants. The efficiencies of thesesystems will be much improved if they can operate at temper-atures of about 2,000F. Materials such as steel have littlestrength at these temperatures. Consequently, high strength-high temperature refractory metals -- niobium, tantalum,molybdenum, and tungsten -- must be used. A project to de-termine the corrosive effect of the "working fluid" (sodium,potassium, or rubidium in the form of liguid and vapor metal)on these metals at temperatures of 2,000F and higher is nowunder way at Lewis Research Center. Experimental apparatushas been fabricated. In this project, doughnut-shaped metalloops, partially filled with liquid sodium or potassium, are

A type of heat-treated carbon steel characterized byhigh strength, ductility, and toughness.

- 147 -


171/290

heated so that the liquid metal in the bottom section boils.The metal vapor rises to the top of the loop where it cools,condenses to a liquid, and flows back down the walls of theloop to the bottom where it is brought to a boil again.Thus, on a small scale, the effects of corrosion of liquidmetal fluids on refractory metals can be evaluated o_erlong periods of time and under varying temperatures.Alloy Systems for High Temperature (l_800-2,100F.)Use -- Temperature, atmosphere, and imposea stresses alla--_ect the behavior of materials. Alloys that, under highstresses, can withstand corrosive atmospheres in the 1,800 to 2,10OOF temperature range have much potential in manyspace applications. Exploratory studies of nickel- andcobalt-base alloys at Lewis have been narrowed to a singlenickel-base alloy series. Several of these alloys have beendeveloped. Each has demonstrated substantial improvementin physical properties over its predecessors. The alloyswere evaluated by means of conventional tension tests (stress-rupture and creep tests). The latest alloy has strengthproperties well over those of commercially available nickel-base alloys. It can support a load of 15,000 pounds persquare inch (psi) for 200 hours at a temperature of 1,900F.It appears that this alloy will also be ductile and easy toshape.

Effects of Micrometeoroid Impacts on Space Structures --Also under study are some of the effects of meteoroid impacton the strength of materials. These will be investigatedby: l) a satellite experiment on a Scout rocket (scheduledfor launching in early 1961) in which penetrations on twothicknesses of stainless steel will be counted, and 2) im-pact studies (which approximately simulate micrometeoroids)on stressed sheet material to determine how much stressspace structures can stand, with or without penetrations.

Three micrometeoroid impact detectors are being pre-pared for the Scout experiment. The first has been sent toLangley for environmental testing. Fabrication of theother packages is on schedule.

Nozzle Materials for Solid Propellant Rockets -- Duringthe report period, studies of material for solid-propellantrockets continued at Lewis. The test installation, con-sisting of a small-scale rocket motor that simulates theexhaust gas composition and temperatures encountered in full-scale solid-propellant rocket engines, was thoroughly checkedout. Tests on tungsten, high density graphite, molybdenum,and certain ablating materials were initiated with non-aluminized

- 14S -


172/290


173/290


174/290

the load without breaking. Studies at Langley have shownthat the more filaments are broken, the higher the stress isconcentrated in the adjacent filaments. However, the ratiobetween the dynamic and static stress concentration isvirtually independent of the number of broken filaments, themaximum dynamic stress being about 20 percent higher thanthe static stress.

Landing Impact Structures m_ ......... ___._ ....-- i_i_ _UIAV_I_ULA_ Way toabsorb impact energy on landing is to use hydraulic shock-_h_orber struts. For spacecraft, the impact will often bequite severe, and the deleterious effects of the space andentry environment on lubricants and shock-absorber fluidsmay make conventional shock absorbers impractical. "One-Shot"landing gears with replaceable yielding metal elements, forexample, is a promising approach that is being investigatedat Langley. Another involves the use of skids of variouskinds. In one phase of this investigation the properties ofsuitable yielding elements and skids are being studied ex-perimentally and theoretically. In another phase, modelsof typical winged spacecraft, such as Dyna-Soar (see Chapter12, Special Research Projects, pp. 160-16A ), are testedwith appropriate landing gear to determine impact accelera-tions and dynamic behavior.

The studies indicate that satisfactory characteristicscan be obtained from simplified landing gears. Special dif-ficulties arise when one of the main skids touches downbefore the other, but proper location of the skids willreduce the demands on piloting techniques that this produces.The yielding elements can be designed to absorb energy bystretching, bending, or crushing.

Fluctuatin 6 Loads on Multi-Stage Rockets -- After alarge rocket-powered vehicle is launched, it acceleratesgradually and passes through the transonic speed rangewhile it is still within the earth's atmosphere. In thisspeed range (popularly, though not entirely accurately,known as the "sound barrier"), fluctuating pressures acton the surface of the vehicle as shock waves build up.These unsteady pressures, in combination with the steadypressures to which the vehicle is subjected during atmos-pheric flight, sometimes become so severe that they maycause portions of the structure to fail.

Fluctuating pressures are being investigated in the14-foot transonic wind tunnel at Ames Research Center. Ad-ditional tests and analyses -- taking into account theeffects of various vehicle shapes -- are in progress. A

- 151 -


175/290

method of estimating fluctuating pressures on the basis ofthe more easily measured steady pressures is also beingsought.Inflated Sphere Landin5 Vehicle -- Various means are

being studied for landing instrument packages safely on themoon or planets. One simple and promising device is the in-flated sphere landing vehicle. The instrument package to belanded will be suspended in the center of a sphere by cordsextending from all sides and attached to the sphere's skin.No guidance, control, or attitude stabilization would berequired, and payloads that can tolerate several thousandg's acceleration (a very reasonable requirement for certaintypes of electronic instruments) can be cushioned to with-stand impact velocities up to 1,000 feet per second (fps).

Studies of this type of landing vehicle are in progressat Ames Research Center. It has been found that the cordssupporting the payload package in the center of the sphereneed weigh only half as much as the payload they support inorder to withstand impact velocities up to 500 fps. Therequired sphere diameter will be only 12 feet if the ac-celeration is 2,000 earth g's. Landing performance has beencalculated for various payload weights and landing speeds.

In a related study, the effects of tapering the payloadsuspension cords are being analyzed. In some cases, a sig-nificant increase in the size of the payload can be handledwhen the cords are properly tapered. Finally, skin stressesof the sphere were analyzed during impact, to establishdesign requirements based on the strengths of the materialsused.

Direct Conversion Electrical Power SystemsAs spacecraft grow more and more complex, so do mission

requirements. For projected landings on celestial bodies,probing deep space, and orbiting man around the earth, theneeds for electrical power increase enormously. Heretoforethe approach has been to develop highly specialized electri-cal power systems to meet specific requirements of a particu-lar space mission. Steps are now being taken to organizeresearch so that it will yield information that can be usedin a number of systems. Fortunately, the various means ofgenerating electrical power for space missions have much incommon.

No Rotatin_ Parts Required -- Direct conversion systemsutilize solar, nuclear, or chemical energy to excite the

- 152 -


176/290

positive and negative electrical charges that exist in allmatter. A barrier is then imposed between the energeticcharges to separate them and provide useable electricity.The term "direct conversion" is used because electricity isgenerated directly without the need for first producingheat energy to boil a working fluid as is the case in aconventional generating system.

Some of the direct energy converters being studied atthe Lewis Research Center are thermionic diodes, plasmadiodes, plasma thermocouples, semiconductor thermocouples,and photovoltaic solar cells. All are similar in principlebut differ in the nature of the barrier that separates thecharge.With the exception of photovoltaic solar cells, all theabove direct energy converters are "heat engines," having

similar thermodynamic cycles and operating conditions. Forpractical applications, each must be able to develop hightemperature in order to generate needed power in proportionto weight.Analysis of Direct Conversion and Conventional SystemsIn connection with this problem, a systems analysis was

recently completed at Lewis. A turboelectric power genera-tion system and a thermionic system were compared in somedetail. Results indicated that the efficiencies, radiatorrequirements and the ratio of power to weight were quitesimilar.

Thermionic and Plasma Diodes -- Studies of thermionicand plasma diodes are again concentrated in the high tempera-ture region; the problem is to handle the electrical powerefficiently, and to reduce losses from radiation. The pro-portion of electrical power can be increased by increasingthe current flow and radiation losses can be reduced byshielding. Experimental work is progressing in both areas.Plasma effects are being studied to increase power density,and radiation shields of various kinds are being tried outwith plasmas.

The plasmas under study are gaseous forms of the alka-line metals (for example, cesium). The work is closelyrelated to that being carried on in ion jets and nuclearturboelectric research (see Chapter 8, Propulsion and NuclearEner_ Applications for Space, pp. 103-108) _

Photoelectric Cells -- Unlike "thermal" energy con-verters, which depend upon high temperature for improvedefficiency, photovoltaic cell converters can be improved

- 153 -


177/290

primarily through improved fabrication techniques. Theconversion efficiency of the sun's rays by photovoltaicaction of silicon is very close to the expected theoreticalvalue. To achieve gains in power to weight, it will benecessary to produce thin, flexible crystalline films ofsilicon, rather than the bulky "sliced" cells in use today.Experimental films of silicon have been produced and areundergoing preliminary testing.

- 15A -


178/290

SpecialResearchProjectsChapter 12

RESEARCH PROJECTS CONVERT THEORY TO REALITY_ _ _ __ __m _ _ _ _lm__'_,_ __ __ _,_ _,e ro_ powered

X-15 experimental airplane and the Dyna-Soar manned orbitalglider -- in which NASA and the Department. of Defense arecooperating -- take theory learned in the laboratory and, byincorporating it into flying aircraft, convert abstract dataInto reality. Experimental, ultra-hlgh, ultra-swift aircraftsuch as these and their predecessors are important for tworeasons: they test validity Of theory and furnish practicaland realistic means of finding out if theoretical studieshave overlooked important factors.

The X-15 is the latest of a long series of researchairplanes, the first of which -- the X-1 -- brought aboutthe long-awalted breakthrough to supersonic flight. TheX-15 will be the first to penetrate to the fringes of space.After the X-15 will come the Dyna-Soar, which will be car-ried into space by a launch vehicle and return to earthafter undergoing the terrific aerodynamic heating that re-sults when a body enters the earth's atmosphere.

The X-15 is a Joint Air Force - Navy - NASA program;the Dyna-Soar is a Joint Air Force - NASA program. Thischapter details over-all progress and NASA participationin both projects during the report period.

THE X-15 RESEARCH AIRPLANETwo Records Set

Four-Year Speed Record Broken -- On August 4, at theFlight Research Center, Edwards AFB, Calif., the rocket-powered X-15 research airplane No. 1 extabllshed a newworld's speed record of 2,196 mph -- more than three timesthe speed of sound (Mach 3.31). NASA test pilot Joseph A.Walker was at the controls. The flight started at 8:58 a.m.PDT, after the airplane had been released from its mothership at an altitude of 45,000 feet. Walker opened the tworocket engines to full thrust. In four minutes of poweredflight before the fuel burned out at 66,000 feet, the X-15

- 155 -


179/290


180/290

In making these measurements, structural-temperatureand aerodynamic-heat-transfer data are obtained from thermo-couple and surface-pressure measuring devices. In addition,special paints that indicate temperature are used for quali-tative information in support of the measured data. Thepaints have been valuable in indicating particular areassubjected to greater heat than the rest of the airplane. Asexpected, no critical or flight-llmitinT temperatures were

Other Pilots Test X-15 -- Test pilots Walker and Whitetook the X-15 through additional tests early in SeptemberAt the same time, four new X-15 test pilots also beganflights. The first was made during the week of September 13by Navy Lt. Cmdr. Forrest S. Petersen. The other three newpilots are Air Force Capt. Robert R. Rushworth, and NASApilots Nell A. Armstrong and John B. McKay. Each will maketwo flights to familiarize himself with X-15 No.l.

XLR-99 Engine Being Installed in X-15 No.2Tests With New Engine -- X-15 No. 2 was being fitted wi

the final, much more powerful (57,000-pound-thrust) XLR-99engine. Test flights with the new unit by pilots White andWalker were delayed when the engine was removed to replace acorroded hydrogen peroxide tank. Initial powered flightswill use only about half the engine's rated potential

X-15 No. 3 Being RebuiltRepairs Required After Test Stand Explosion -- By early

June development of the final design engine, the 57,000-pound-thrust unit had progressed almost to the flight stage.However, on June 8, while undergoing final ground tests bythe contractor, North American Aviation, Inc., the fuel andhydrogen-peroxide tanks in X-15 No. 3 (the airplane in whichthe XLR-99 engine had been installed), exploded on the stand.Pilot Scott Crossfield was seated in the cockpit of the air-plane, but was uninjured when the blast hurled the forwardsection 20 feet away. The aft section, containing the engineremained secured to the stand and was almost completely de-stroyed.

The XLR -99 engine had been tested many times before, badditional ground tests were required after the engine wasmated to the aircraft, to determine a variety of factors sucas vibration levels, the ability of the pilot to stop and

- 157 -


181/290

restart the engine, and the rocket's automatic shutdown sys-tem (the engine is equipped with detectors, or sensors, thatcut off the power in case of excessive heat or vibration).The accident has caused some serious delays in the pro-gram: l) the first flight with the XLR-99 engine was delayed

by two months; 2) delivery of an airplane in the final con-figuration to the Government was also delayed at least threemonths;.3) the availability of the X-15 No. 3 for use in theflight test program has been set back about 16 months; and4) the Government program now under way with X-15 No. 1 wasdelayed about two months.Final Air Force approval for reconstructing X-15 No. 3was granted about September l, and the contractor has startedwork, which will take an estimated ll months and cost about$4 million. After reconstruction is completed, a slx-weeksperiod of ground testing will be required before the airplane

can be delivered to the Government about October l, 1961.Status of Major Program Objectives

In addition to the aspects of the X-15 program previouslydiscussed, the following major objectives are of interest:flight control at very high altitude; atmospheric exit andentry techniques; terminal guidance; aeromedical aspects; andlanding load research. A brief summary of each major objec-tive and related areas of interest is given below:

Flight Control at Very High Altitude -- As yet, therehas been no evaluation of the reaction controls of the X-15at high altitude. The Government flight program is beingconducted without using this system. However, in the record-altitude flight to 136,500 feet, good control was achieved(minimum dynamic pressure of about l0 pounds per square footwas attained) and there were no significant piloting problems,despite the absence of reaction controls.

Valuable information on reaction controls is being ob-tained on a supporting project -- tests have been made of areaction control system on an F-104A airplane. Results sofar cannot be applied directly to the X-15 program, butparticipating pilots agree that the experience they haveobtained in this first high-altltude use of reaction controlsis quite valuable.

Atmospheric Exit and Entry TechniQues -- The techniquesemployed in completing the record hlgh-altitude flight were,of course, quite simple in comparison with those that willbe required for exit and entry on later missions to 250,000

- 158 -


182/290

feet and higher. However, an evaluation of the flight tech-niques used, augmented by wind-tunnel and theoretical studies,indicate no severe problems are to be expected. The controlcharacteristics of the X-15 with the "damper system" (auto-matic equipment that prevents excessive oscillations or over-response to control) have generally been rated very good bythe test pilots. Wind-tunnel and theoretical predictionshave in general been substantiated by the flight tests. Aflxed-base simulator, programmed on the basis of wind tunneldata, has proved an invaluable tool for planning flights andtraining pilots.

Terminal Guidance -- The fixed base simulator has givenexcellent training and preparation to the test pilots thusfar, in making flights over distances of as much as lO0 milesfrom the landing site. On the basis of landing experience todate, a composite landing pattern is used that combines thebest features of a conventional circular approach and thestraight-in pattern proposed by the Ames Research Center. Thepattern begins with a circular approach at about 500 mph (in-dicated air speed), with the rate of descent planned so thatthe pilot will have maximum permissible altitude in the finalstraight-ln leg. This is followed by predetermined "flarecontrol" procedures -- that is, the airplane descends in asmooth curve, making a transition from a steep descent to adirection of flight substantially parallel to the landingsurface. In recent flights, the X-15 has been brought downin this phase at a speed of between two and four feet persecond, and touchdown has generally been within 1,000 feet ofthe desired point.

To prepare the pilots for the low lift-drag character-istics of the X-15, practice approaches were made in an F-IO4Aairplane with somewhat similar handling qualities. The useof this airplane has enabled the pilots to maintain theirproficiency even when long periods occur between X-15 flights.

Aeromedical Aspects -- To date, physiological measure-ments made on the test pilot during flight have been of arelatively limited nature. In the near future, more completemeasurements will be made. Additional equipment for detec-ting various kinds of radiation, cosmic rays, etc., will becarried inside and outside the X-15 on later flights.

Landin_ Gear Research -- Research on the stresses andstrains encountered by the X-15's landing gear (described inChapter 13 of NASA's Second Semiannual Report to Congress)has continued. During the period data were obtained on 17landings, at various rates of descent of up to 9.5 feet persecond at touchdown, and at ground speeds from 167 to 274

- 159 -


183/290

miles per hour. The results indicate that the highest forcesand strains on the main gear (skids located well back on theairplane, behind its center of gravity) occur when the nose-_ear touches down. It was also found that the strain on thelanding gear is affected more by the airplane's attitude orangle than by the sinking speed or rate of descent at thetime of touchdown. The high drag of the main-gear skids hasbeen found to give more than adequate directional stability.

NASA SUPPORT OF THE DYNA-SOAR PROGRAM

The Dyna-Soar-I ProgramA projected manned orbital glider under development as

a joint program between the Air Force and NASA -- has reachedthe stage at which many design and hardware features havebeen specified, and operational techniques are being developed.Molybdenum has been chosen as the material to be used for mostof the glider structure. Areas that will be subjected to highaerodynamic heating will be coated with ablation material.

A winged glider, the Dyna-Soar, will be carried intoorbit by a modified Titan launch vehicle. Unlike the Mercurycapsule (see Chapter 3, Manned Space Flight, pp. 23-2A ). Dyna-Soar will not make sea landings, but will come down at con-ventional landin[ fields. Boeing Airplane Co., Seattle, Wash.,under contract will build II vehicles for ground tests, un-manned test flights, and piloted flights.

Program Has Two Phases -- The program will begin withair drops of the glider from a mother craft (in much the sameway that the X-15 research airplane is dropped), followed bylong-range suborbital launchings by a modified Titan-J launchvehicle.

Role of NASA -- NASA research in support of the Dyna-Soaris directed toward providinT the Air Force with technical as-sistance in all aspects of the Dyna-Soar project.

Glider Requirements -- Briefly stated, the requirementsfor the glider configuration are: I] it must be aerodynamicallystable and controllable throughout the range from orbitalspeeds to subsonic landing speeds] 2) it must be built to with-stand the intense heat generated by air friction during atmos-pheric entry] and 3) it must be structurally sound, to with-stand the strains and pressures imposed upon it during launch-ing and all phases of flight. In combination with the launchvehicle, the over-all unit must be aerodynamically compatible,stable, and controllable.

- 160 -


184/290

Studies in Progress -- To aid in selecting a final con-figuration that will meet these requirements, NASA is carry-ing out extensive investigations over the anticipated speedrange. Studies are in progress on the effects of changes ingeometry on stability and control and aerodynamic heating --for example, the diameter of the leading edge of wings, theamount of sweep (angling back of the wing in relation to thebody), the dihedral angle (a tilting upward or downward ofand the vertical tall shape, to mention a few. Some of theNASA investigations are specifically requested by the AirForce; others are more general research projects that havedirect application to the Dyna-Soar program.

Low Speed Dynamic Characteristics -- The dynamic charac-teristics of the glider at the relatively low speeds at whichit comes in for a landing will be determined at the LangleyResearch Center. Using the full-scale wind tunnel, dynamicstability and control characteristics will be determined witha flying (remotely controlled free-flight) model operatingunder its own power. Also at Langley, the Radio Control TestUnit will be employed, using a I/5-scale model (nonpowered,radlo-controlled) ballasted to simulate dynamic characteris-tics of the full-size unit. The model will be dropped froma helicopter at an altitude of about 3,000 feet, to studydynamic stability characteristics through the entire flightrange, with emphasis on "high angle of attack" performance.At NASA's Ames Research Center, the 12-foot Pressure Tunnelis being employed to measure the effects of many changes inthe shape of configuration of the glider at Mach numbersfrom .25 to .50. Tests are also under way at this facilityto find out how ground winds affect the launch vehicle glidercombination while it is on the launching pad.

Investigations at Transonic Speeds -- At the speedrange approximately that of sound (Mach I), an investigationwas conducted in the Langley 8-foot wind tunnel to determinethe static ("at rest") aerodynamic characteristics of thegilder-launch vehicle combination, using several differentfin configurations on the launch vehicle. Information wasobtained on the best sizes and shapes of fins on the vehicleto give good stability, both longitudinal and lateral. Simi-lar tests are under way at the Langley 16-foot Transonic Tun-nel to learn more about stability and control of the glideralone. The effects of changes in size and shape of the

- 161 -


185/290

vertical fin, the body, wing camber*, and elevon** geometrywill be investigated. Over the speed range from Mach .6 toMach 3.5 (high subsonic to supersonic speeds), the stabilityand control characteristics of the launch vehicle glidercombination and the glider alone are being investigated atthe Ames Unitary Plan wind tunnels. Tests in this facilityare under way.

Tests at Hypersonic Speeds -- In the hypersonic speedrange (more than five times the speed of sound), an investi-gation is in progress at Langley on the problems of instabil-ity at low angles of attack tO to 15), and the effect onstability of various nose and canopy shapes. Tests are beingcarried out in the Langley ll-inch hypersonic wind tunnel, ata Mach number of 9.6. The effects of vertical fin size andthe angle of the fins to the airstream are also being inves-tigated. Other factors under study include the size and shapeof lower win__ surfaces, fins, etc., and the manner in whichthey affect aerodynamic heating characteristics. The mostpromising configurations will be studied at a Mach number of18 at a later date. A program of atmospheric entry studiesat speeds up to Mach 21 (about 20,000 feet per second) isbeing pursued at Langley. The program will also have appli-cation to the Dyna-Soar project.

Flight Research Center Participation in the Dyna-Soar ProgramParticipation of NASA's Flight Research Center (FRC),

Edwards, Calif., in the Dyna-Soar program consists of engi-neering, research, developmental, and planning effort in twogeneral categories: I) air vehicle systems development; and2) flight-test operations. The Center is conducting specificand general research in development programs; it is providingresearch, development, and planning efforts for specific Dyna-Soar systems, and keeping in close touch with the requirementsfor the systems. FRC cooperates closely with the Air ForceDyna-Soar Weapons Systems Project Office. Engineering person-nel have been assigned as members of Joint Government-Contrac-tor Technical Groups, to the Dyna-Soar Systems DevelopmentTest Force and to the Instrumentation Development Team.

* The curvature of an airfoil or wing from front to back(leading edge to trailing edge) in comparison with astraight line (chord) joining the two edges.

** A control surface that functions both as an elevator andan aileron (flap).

- 162 -


186/290

Air Vehicle Systems Support -- FRC effort in the areaof air vehicle systems development has consisted of moni-toring and evaluating the launch vehicle, glider, and sub-systems designs. The Center expresses concurrence with con-tractor concepts and proposals, or recommends alternateapproaches to the Dyna-Soar Weapons Systems Project Office,which is charged with technical direction of the program.FRC has devoted considerable effort to establishing flight-test and flight research data requirements and to specify-ing and developing concepts for the necessary specializedinstrumentation and data system for the glider.

Flight Test Operation -- Major FRC efforts to date havebeen to establish Dyna-Soar Step I flight testing objectives,to develop a flight-test concept for a hypervelocity glidercarried by a modified Titan vehicle, and to establish thedetailed flight-test techniques that must be used. Theselatter studies are being conducted in close cooperation withAir Force and Contractor personnel. The supporting flighttest program currently consists of such activities as reac-tion control, infrared sensing, and low lift-to-drag ratiolanding program on the F-10g airplane, and practically allfacets of the X-15 program.

Investisation of Landing ProblemsThere are three principal requirements for the Dyna-

Soar landing gear system: l) the skid material must be ableto withstand the high aerodynamic heating encountered duringentry; 2) the skids must be designed so that the vehiclemaintains its stability during all phases of the landing; *and 3) the glider must be able to stop within the limits im-posed by the landing fields down range from Cape Canaveral_thus the skid materials must have a high enough friction co-efficient to slow and stop the vehicle within a distance of8,000 feet. (Available runways are lO,O00 feet long, allow-ing a 1,O00-foot over-run at each end.) These problems arebeing investigated at the Langley Research Center's LandingLoads Track. On the basis of tests of numerous materials andshapes, wire brush material has been selected for the mainskids, and a cermet (mixture of ceramic and metal) for thenose skid. With this arrangement, a full-size model of theDyna-Soar system will be investigated. Aerodynamic loadswill be programmed into the simulation during landing tests,so that landing loads and stability can be determined usingfull-scale hardware.

To accomplish this, the nose skid must slide more easily(have a lower friction coefficient) than the two main rearskids.

- 163 -


187/290

Air Vehicle Systems DevelopmentDuring the next two years, FRC will devote an increasing

effort to assure the design and procurement of a usable anduseful Dyna-Soar vehicle. In parallel with this effort,vehicle flight characteristics and flight environment will bepredicted and assessed. Specific research and developmentflighfi tests in direct support of the development of the Dyn_Soar glider systems will be conducted both independently of,and as part of, joint NASA-USAF-contractor test programs.

- 16_ -


188/290

ResearchCenterDirect SupportChapter 13

ADVANCED RESEARCH APPLIES TO MANY PROGRAMS

progress in specific aeronautical and space programs.Facilitating this progress, however, has been much broadlybased research -- some of it quite general, some of itapplied -- in direct support of these programs, under thedirection of NASA's Office of Advanced Research Programs,which includes the Ames, Lewis, Langley, and Flight ResearchCenters originally established by the National AdvisoryCommittee for Aeronautics (NACA), NASA's predecessor agency.

The Office of Advanced Research Programs works closelywith the Offices of Launch Vehicle Programs and Space FlightPrograms to provide research and technical assistance essen-tial to their projects. It also furnishes research assist-ance to the military services, other Government agencies,and to industry. This research, which under NACA wasdirected almost entirely to the technical requirements ofcivilian and military aircraft, is now directed to the needsof space activities as well.

Typical examples of direct support of research follow.

Project ScoutVehicle Is Langley Concept -- The concept of the Scout

was originated in 1958 by scientists and engineers atLangley Research Center. Langley is systems manager for theprogram, with responsibility for the airframe, guidance andcontrol systems, and rocket engine contracts. The centeralso designed, developed, constructed, and installed Scouttelemetry systems.

Design Data Obtained -- At various stages in Scoutdevelopment, design data on aerodynamics, flutter, aerody-namic heating, response to controls, and structural behaviorwere obtained by analytical and experimental investigation.During the past six months, the first test vehicle wasdelivered to Wallops Station, assembled, put through athorough laboratory check, and launched successfully (seeChapter 7, Launch Vehicles and Launch Operations, pp. 75-77).A second test vehicle is being assembled and checked out;

- 165 -


189/290


190/290

During the "over the top" portion of the curve, there areshort periods of weightlessness. The experiments shouldhelp clarify areas of uncertainty and aid in obtaininggreater vehicle reliability.

Ground Operations Problems -- Another area of Lewisresearch is the investigation of problems associated withground operations for liquid hydrogen-fueled vehicles suchas Centaur. Methods of loading and "topping" (adding fuel(Clearing tanks and lines after unloading), are being studied,using an insulated, flight-weight tank. Techniques androutines have been established that appear adequate to sat-isfy the requirements/of Centaur launch operations. Duringthese experiments, it was found that the cork insulation --mentioned earlier

fourth semiannual report to congress

Documents