Full report

Original page 1

General Disclaimer One or more of the Following Statements may affect this Document This document has been reproduced from the best copy furnished by the organizational source. It is being released in the interest of making available as much information as possible. This document may contain data, which exceeds the sheet parameters. It was furnished in this condition by the organizational source and is the best copy available. This document may contain tone-on-tone or color graphs, charts and/or pictures, which have been reproduced in black and white. This document is paginated as submitted by the original source. Portions of this document are not fully legible due to the historical nature of some of the material. However, it is the best reproduction available from the original submission. Produced by the NASA Center for Aerospace Information (CASI)

Original page 2

NASA TECIINICAL MEMORANDUM NASA T"4 X-73398 ( NA SA-TM-X-7339 y ) SOLAR F.NFRGY BTdLIOGPAPHY N78-13554 (NASA) 32 N HC A0 J/!",F A01 CSCL 10A unclds G 3/44 55445 SOLAR ENERGY BIBLIOGRAPHY Compiled by Stephen Crargus Management Services Office !I I July 1977 NASA Geoff, C. Marshall Space Flight Center Marshall Space Flight Center Al MtiFC - Form 3190 ( Rev June 1971) ti DEC 1917 ,yrD !N Sri FicafTy r F1 6

Original page 3

r TPf-&A If-Ai RFOART CTANT)ART) TITI F P ► r.F 1. RFPONT N0, 2. GOVa:RNMENT ACCESSION N0, 3. NASA T:VI X- 734)m 4, TITLE AND SUDTITLE -Solar F,nergy Bihliography 7. AUTHOR(S) hen Compiled by Step Cr, rgus 9 PERFORMING ORGANIZATION NAME AND ADDRESS RECIPIENT'S CATALOG N0. 5 REPORT DATE Jul y 14)77 6 PERFORMING ORGANIZATION C(Clg,PERFORMING ORGANIZATION REPnR' u 10 WORK UNIT NO. George C. 'Marshall Space Flight Center 11. CONTRACT OR GRANT NO. Marshall Space Flight Center, Alabama 35812 12. S P ONSORING AGENCY NAME AND ADDRESS 13 TYPE OF REPORT 9 PERIOD COVERED National Aeronautics and Space Administration Technical Memorandum !"ashington, D. C. 20546 15. SUP P LEMENTARY NOTES 16, ABSTRACT 1.1 SPONSORING AGENCY CODE. This document consists of listings of technical briefs, reports, and papers pertaining to research being performed by NISFC personnel and contractor in the field of solar enera. 17. KEY WORDS f I r 18, DISTRIBUTION STATEMENT Unclassifed-Unlimited 19, SECURITY CLASSIF, (of thin repart) 20. SECURITY CLASSIF, (of this pap) 21 NO. OF PA(,FS 22. PRICE Unclassified Unclassified 31 A®FC - Form 3797 (naay 1960) y National Technical Information Service, Springfield. Virginia 22161

Original page 4

PREFACE The source from which the document is available is quoted in each citation. The addresses for these sources are listed below. National Technical Information Service 5285 Port Royal Road Springfield. Virginia 22161 Energy Research and Development Administration Technical Information Center P.U. Box 62 Oak Ridge, 'fennessee 37830 NASA Technology Utilization Office Attn: AT01 Marshall Space Flight Center, Alabama 35812 Commissioner of Patents U.S. Patent Office Washington, U.C. 20231 ii

Original page 5

TABLE OF CONTENTS Page ONGOING RLSLAK" , H . . . . . . . . . . . . . . . . . . I TECH IIRIf:FS . . . . . . . . . . . . . . . . . . . . . 4 PAPERS AND Pl.RI'JDICALS . . . . . . . . . . . . . . . 8 TECHNICAL REPORTS AND PATENTS . . . . . . . . . . 10 SUBJECT INDEX . . . . . . . . . . . . . . . . . . . . 26

Original page 6

74K 1 1 130 NAS8-31 100 Air Conditioning/Air Conditioning Thermal Energy Storage Development Equipment/Cooling/Cooling Systems/Energy Study. Lockheed Missiles ant; Space Co., Conservation/Energy Technology /Solar Huntsville, AL. Collectors/Solar Energy Conversi oil /Thermudynamic Efficiency/'T hermudynarnic Proper- Chemical Reactions/Energy Storage/ ties/Thennodynamics. I feat /Ifeat Storage/Phase Transformations/ Solar Energy/Thermal Control Coatings/ 75K I U 225 NAS8-31 189 Thermal Energy/Thermal Protection/Transi- Optimization of Absorption Air tion Temperature. see N76-13592 Conditioning Systems for Solar Energy Applications. Memphis State University, 75K 10164 NAS8-3101 6 TN. Interconnect and Bonding Technologies for Large Flexible Solar Arrays. Air Conditioning/Air Conditioning Lockheed Missiles and Space Co., Equipment/Convective Heat Transfer/Cool- Sunnyvale, CA. ing/Economic Factors/Energy Absorption/ Energy Conversion/Energy Conversion Effi- Adhesive Bonding/Arrays; Bonding/Degra- eiency/Heat Transfer/Optimization/Refrigeratdation/Electrical Properties/Environmental ing/Solar Co'lectors/Solar Energy/Solar Energy 'tests/Flexibility/Flexible Bodies/1oi.iing/Life Conversion/Temperature Control/Thermal Ab- (Durability)/Mechanical Properties/Mounting/ sornt ion /Thermal Energy. Solar Arrays/Solar Cells/Solar Collectors/Solar see N77-17560 Energy Absorbers. see N76-32653 75K 10551 NAS8-31326 75K10193 NAS8-3075 8 Design, Fabrication, Testing, and Development of a Solar Powered Resi- Delivery of a Solar Collector. Chamberdential Air Conditioner. AiResearch Mfg. lain Corp., Waterloo, IA. Co., Torrance, CA. Design/Design Analysis/Energy/Energy Air Conditioning/Air Conditioning Absorption Films/Energy Conversion/Fabrica- Equipment/Cooling/Energy/Heat Exchangers/ tion/Product Development/Solar Collectors/ Residential Areas/Solar Collectors/Solar Solar Energy/Solar Energy Conversion/Solar Energy/Thermal Energy. see N76-30000 Generators. see N76-22671 N76-30659 N76-30656 75K 10554 NAS8-31309 N76-30655 Design, Fabrication, Installation, and N76-30653 Checkout of a Prototype Sunrall M,.mitur N76-2U632 System. International Business Machines 75K 10205 NAS8-307"6 Corp., HUlltsville, AL. Development of a Solar Powered Resi- Data Processing/Digital Data/Environdential Air Conditioner. Chrysler Corp., mental Control/Radiation Measuring Instru- Cape Canaveral FL. ments/Sensors/Skv Brightness/Sky Radiation/ ORIGINAL PAt;I; la OF POUR QUALnT,

Original page 7

r Solar Collectors/ Solar Energy/Solar Instru- 75K 1 1454 NAS8-31670 ments/Solar Radiation/Solar Sensors/Sunlight/ Solar Cell Selection and Characterization Trackiag (Position). see N76-10444 for Solar Electric Propulsion (SEP). Boeing Aerospace Co., Seattle, WA. 75KI0612 NAS8 -31327 Design, Fabrication, Testing and Delivery Aerospace Environments/Energy Conof a Solar Lnergy Collector Systent for version/Encrgy C;unversion Efficiency/Environ- Residential Heating and Cooling lfoney- mental Test s/Plane I ary Atniospheres/Silicon/ well, Inc., Minneapolis, MN. Solar Cells/Solar Electric Propulsion/Solar Energy Conversion. Cooling Syste ins /Solar Collectors/Solar Lnergy/Solar Iteating. see N77-10638 7oK 10736 NAS8-31662 Design, Fabrication, Assembly, Testing 75KI0650 NAS8-3138 and Delivery of an Earth Based Solar Design, Fabrication, Testing and Delivery Power. Wyle Labs., Inc.. Huntsville, AL. of a Solar Collector. PPG Industries, Inc., Pittsburgh, PA. Electric Power Plants/Energy Conversion/Incentives/Marketing/Solar Collectors/ Cooling Systems/Energy Absorption Solar Energy/Solar Energy Conv- Films/Energy Conversion/Solar Collectors/ ersion/Technology Utilization. Solar Energy/Solar Energy Absorbers/Solar Energy Conversion/Solar Heating, 70K 11070 NAS8-31293 Solar If-.ating and Cooling Technical 75K 109'_5 NAS8-3143 7 Data and Systems Analysis. University Development of a Solar Powered Resi- of Alabama., Huntsville, AL. dential Air Conditioner (Generator Optimization). Chrysler Corp., Cape Cooling/Cooling Systems/Solar Energy/ Canaveral, FL. Solar I-leating/Systems Analysis. see N77-17987 Air Conditioning/Air Conditioning N77-12507 1:yuipment/Electric Generators/Energy Con- N76-32650 version/Solar Collectors/Solar Energy/Solar N76-15588 Lnergy Conversion/Solar Generators. I6-15587 see N76-24702 76K 11313 NCA8-103 75K 1 1328 NAS8-31564 An Investigation of Fresnel Lens Utilization of Solar Energy for Residen- Utilization in Collecting Solar Energy for tial Heating and Cooling Application. Power Generation. Ball State. Univ., Tennessee Technological Univ., Cooke- Muncie, l „ ville, TN. Electric Generators/Lenses/Solar Collec- Air Conditioning/ Energy Conversion/ tors/Solar Energy/Solar Energy Conversion/ Energy Conversion Efficiency/Flow Velocity/ Solar Generators/Sun. Fluid Flow/Puntps/Solar Energy/ Solar Energy Conversion/Solar Heating/System Effective- 70K 1 1314 NCA8-101 ness. 2 Investigation of Fresnel Lens Utilization in Collecting Solar Energy for Power Generation. Ball State Univ., Muncie, IN,

Original page 8

Electric Generators/Lenses/Solar Collec- Electrical Resistivity/Fatigue Life/lrraditors/Solar Energy/Solar Energy Conversion/ ation/Kapton (trademark)/Life (Durability)/ Solar Generators/Sun. Materials Tests/Microwaves/Nondestructive Tests/Optical Measurement/Quartz/Radiation 76K 11336 I SG-8G25 Dosage/Radiation Effects/Silicon/Solar Inhibitor Analysis for a Solar Beating Arrays/Solar Cells/Solar Electric Propulsion/ and Cooling System. Southern Univ., Teflon (trader.ark). Baton Rouge, LA. Cooling Systems/Solar Heating. see N77-57516 76K 11493 NAS8-31 189 Optimization of Absorption. Air Conditioning Systems f.:- Solar Energy Applications. Memphis State Univ., TN. Absorbers (Equipment)/Air Conditioning Equi Pill Cnt/Cooling Syste ms/Dry inf/Solar Energy. see N77-175oO 76K11922 • NSG-8041 Parametric Study of Rock Pile Thermal Storage for Solar Heating. Alabama A&M Univ., Normal, HURtSVilIC, AL. Buildings/Energy Storagc/lieat Storage/ Heating/Residential Areas/Rucks/Solar Collectors/Solar Energy/Solar Heating. 76K 12132 NAS8-32161 A Feasibility Study of the Satellite Power System Concept. Rockwell International Corp., Downey, CA. Alulrlr .lUtll /Atltetlnas/Ecollorlllc Analysis/ Electricity/Feasibility Analysis/Gallium Arsenides/Ground Stations/Microwave Antennas/ Microwave Transmission/Radio Antennas/Satellite ('on figurations/Sate Ili te Orbits/Satellite Solar Energy Conversion/Satellite Solar Power Stations/Solar Cells/Solar Energy. 77K 10207 NAS8-32398 Measurements of Materials Properties for Solar Cells: Nondestructive Tesi.ing by Microwave Means. Marshall Space Flight Center, Huntsville, AL. 3

Original page 9

M-FS-14706 TECH BRIEFS 6/71 Solar powered hcating and cooling sys- IMPROVED THERMAL PAINT FOR- tem with possible application to residences is MULATION. Gates, U.W.: Roger, F.O.; described. Operating principles of system are Zerlaut, G.A. Marshall Space Flight defined and illustration of typical energy Center, Huntsville, AL. NAS8-5379. stora ,^ and exchange system isis provided. AVAIL: Marshall Space Flight Center. (patent) ATO 1. 671-10180 M-FS-22562 3/74 PotaSSlLlrll silicate-treated zinc oxide SELECTIVE COACI ► ' FOR COLLECTpains stabilizes pigment against ultraviolet- ING SOLAR ENEku ON ALUMINUM. induced, bleachable degradation in infrared Lowery, J.R. Marshall Space Flight ('enter, region, and permits use of ZnO as pigment in Huntsville, AL. AVAIL: Marshall Space ultraviolet-stable coatings based ui,un poly- Flight Center, AT0L methyl siloxane elastomers and resins. Material has low absorption /enrittance ratio. 673-10527 see N72-175321 Presently used coatings, %hich were I ITR 1-U6002-94 originally developed for brass, copper, and M-1=S-21628 steel sunstrales, yield relatively low absorp- 3/74 tance/emittance ratios when applied to SOLAR-ENERGY CONVERSION SYS- aluminum. Efficient, black-nickel plating TLM PROVIDES ELECTRICAL POWER applied to aluminum substrate cnlianccs solar AND THERMAL CONTROL FOR Lll : l:- absorptance to 93 percent and reduces SUPPORT SYSTEMS. Davis, B.K. Mar- emittance to 6 percent. (patent) shal Space Flight Center, Huntsville, AL. AVAIL: Marshall Space Flight Cent;.-r, M-FS-22563 5/75 AT01 B73-10524 HEATING AND COOLING SYSTEM. A PRACTICAL SOLAR ENERGY System utilizes freon cycle and includes Oneill, M.J.; McDanal, A.J.; Sims, W.H, boiler turbogenerator with heat exchanger, Lockheed Missiles and Space Co., regenerator and thermal-control heat Huntsville, AL. AVAIL: Marshall Space exchangers, low-pressur: and boiler-feed Flight Center, AT01. Inimps, and condenser. Exchanger may be of B73-10156 interest to engineers and scientists investigat- Recent study has concluded that ing new energy sources. see N75-32581 solar-powered residential heating and cooling (patent) system is nontechnically and economically M-FS-21927 feasible. Proposed systern provides space 10;'. 2 heating, air conditioning, and hot water. SOLAR POWERED ABSORPTION Installation costs will be greater than for CYCLE HEAT PUMP USING PHASE conventional heating systems, but this differ- CHANGE MATERIALS FOR ENERGY ence will eventually be defrayed by very low STORAGE. Middleton, R.L. Marshall operating costs. see M-TU-75-3 Space Flight Center, Huntsville, AL. M-TU-74-3 AVAIL: Marshall Space Flight Center, LMSC-HREC-D306275 AT01. 1372-10615 4

Original page 10

M-FS-22743 3/74 solar energy collector efficiencies for three SOLAR ENERGY ABSORBER, ACTIVE: main conversion technologies. Sec N76-10444 INF-RARED OR) 'I RAP. Brantley, L.W., IBM -74W-00001 Jr. Marshall Space Flight Center, Ifunts- Ipatent) ville, AL. AVAIL: Marshall Space Flight IMI-73W-00253, Vol. I Center, A"COI. 1173-10484 Efficiency of solar-energy absorbers may M-FS-23U57 1/75 be improved to 95 percent by actively cooling SELF-REGENERATING DESICCANT their intermediate glass plates. This approach SYSTF.M. Anthony, K.C;.. Herndon, E.P. may be of interest to manufacturers of solar Marshall Space (light Center, Huntsville. absorbers and to engineers and scientists AL. AVAIL: Marshall Space Flight Center. AT01. developing new sources of energy. See N76-2657 B74-10266 (patent) ('ompact ,ystern use, inherent diurnal cyclic airtlow in system and energy of sun as M-F S-22744 3/74 drying heat. System requires no power for SOLAR-I:NERC;Y ABSORBER, ACTIVU operation. has no moving parts to wear out, INFRARLD 010 TRAP WITHOUT requires no blowers or manifolds, and is GLASS. Brantley. L.W., Jr. Marshall relatively inexpensive to produce. Space Flight Center, Huntsville, AL. (patent application) AVAIL: Marshall Space Flight Center, ATO I . M-FS-23062 2/75 B73-10485 MF.CIIANICAL SOLAR MOTOR, A Absorber efficiency can be unproved to CONCEPT. Hein, L.A.: Myers, W.N. 90 percent by removing glass plates and using Marshall Space Flight Center, ffuntsvrlle. infrared traps. Absorber configuration may be AL. AVAIL: Marshall Space Flight of interest to manufacturers of solar absorbers Center, AT01. and to engineers and scientists developing flew B74-10292 sources of energy. sec N76-4696 Motor is proposed to convert radiation (patent) from sun directly into mechanical energy. Motor utilizes thermal expansion of liquid, M-FS-22943 9/74 heated by sun. as driving force. Unlike most REMOTE SUNFALL MONI fOR. A thermally powered systems it does not require CONCEPT. Lollar, R.B.: Mandt, R.R. that liquid be converted into vapor. International Business Machines Corp., see N77-12402 Huntsville, AL (Federal Systems Div.). (paten tI AVAIL: Marshall Space Flight Center, AT01. NAS8-1400. tit-F S-23128 3/76 B74-1 U 149 PRINTI-.U-('IKCUII SOLAR-('I LL Monitor is proposed as spectral monitor ARRAY. Currier, R F.: Palmer, W.L. system design to record digital data simultane- Lockheed Missiles and Space Co., ously from two types of sensors, mounted on Sunnyvale, CA. AVAII.: Marshall Space. both stationary assembly and tracking Flight Center, ATOI . assembly. Both Direct and total V;dues of solar 117o-10007 radiation are recorded. System may measure ORIGINAL PAGE IS OF POOR QUALITy

Original page 11

W Flexible solar-cell array is made thinner M-FS-23200 8/75 and lighter by placing array on substrate SOLAR RESIDENTIAL. HEATING AND which is a lamination of two sheets of plastic COOLING SYSTEM. Meltun, D. E., film with etched electrical connector for cells Humphries, W.R. Marshall Space Flight between films. M-FS-23138 Center, Huntsville, AL. AVAIL: Marshall Space Flight Center, ATOI. B75-10165 PRINTED-CIRCUIT SOLAR-CELL System has been placed in operation to ARRAY. Currier, R.F.: Palmer, W.L. verify technical feasibility of using solar Lockheed Missiles and Space Co., energy to provide residential heating and Sunnyvale. CA. AVAIL: Marshall Space coulimg. Complete system analysis was per- Flight Center, ATOI. fonncd to provide design information. see N75-22903 A flexible solar-cell arra, has been made N75-24107 thinner and lighter than previous solar arrays. SI IC-500 I The array is placed un a substrate, which is a lamination of two sheets of plastic Will with NI-FS-23272 12/75 an etched electrical connector for the cells LOW-COST HOT-AIR SOLAR COLLECbetween the filins. Thus, the substrate TOR. Herndon, E,P.; Anthony, K.G. mechanically supports the cells and inter- Marshall Space Flight Center, Huntsville, connects them electrically. AL. AVAIL: Marshall Space Flight Center, ATO1. M-FS-23167 6/75 B75-10301 LARGE-SCALE SOLAR I fit 'RMAL System has only three components Ixr COLLECTOR CONCEPTS. Brantley, L. cell. Cell harts are fabricated from readily W. Marshall Space Flight Center, Hunts- available materials and, following; a construcville, AL. AVAIL: Marshall Space Flight tion procedure which requires use of only Center, ATO1. B75-10098 one person. simple handtools, can be mounted in place by Thermal collector could be used ulti- ( patent application) inately to power steamplant to produce electricity. Collector would consist of two M-FS-23349 8!76 major subsystems (1) Series of segmented HORIZONTALLY-MOUNTED SOLAR tracking mirrors with two major subsystems COLLECTOR. Black, D.H. Marshall (2) Absorber mounted on centrally located Space Flight Center. Huntsville. Al_. tower. M-FS-23195 AVAIL: Marshall Space Flight ('enter, ATO 1. 8/75 B7ti-1056 ZENNI:R-REGULATED SOLAR Systems consists of three major ARRAY/BAT I'ERY POWER SYSTEM. components: vertical deflector assembly, Eliason, J.T. Sperry Rand Corp., Hunts- stationary reflector, and motor driven trackville. AL. AVAIL: Marshall Space Flight ing mechanism. Deflector assembly directs Center, ATOL NAS8-21812. 875-1016: tion. using series of' horizontally mounted incident incoming; energy to a vertical direc- Zenner-diode limits solar cell voltage vanes. Energy is then redirected via reflector used to charge battery. System improves life to fixed collector. and reliability of solar cells. (patent application) 6

Original page 12

M-FS-23403 8/76 Study descrifxs technique developed for PkOPOSED LOW-TFMPERATUR1, comparison of de v ii:vs to determine it conven- SOLAR LNGINE. Peoples, J.A.; Kearns. tional energy resources mat be saved. G.B. Marshall Space Flight ('enter. see N 76-14600 Huntsville, AL. AVAIL: Marshall Space Flight Center, ATOI. 876-1054 UNIVERSAL SOLAR-CELL TERMI- M-FS-23505 Engine, proposed for conversion of sun's NAL Bashin, S.; Kelley. F.G. TRW Inc., heat to motion without need for Itcat pun111s AVAIL: Marshall Space Flight Center, .end associated equipment, uses cxp.msiun ;end ATO I . contraction of aluminum rod to drive two out-of-phase windlasses. Linear displacement The universal solar-cell terminals use the of 0.076 cm m rod will exert sufficient force dissimilar material bonding properties (ntrtalto drive pumps. generators, and compressors. all to-glass andlor ceramics) of allo> in conjunction with standard M-1-S-23420 8/76 termination. Loop receptacles replace the COA TIN( , I uR SOLAR PANELS. conventional connector posts. Guntbs. K.W. R. Gumbs Assoc., Newark, N1, AVAIL: Marshall Space Flight Centcr, ATOI. NAS8-31626. B76-10!,i Inexpensive composition with k-,a energy-absorptivity and low emissivity requires no primers for adhesion to aluminum, copper, and stainless steel and uses commercially available materials. M-FS-23428 8/76 SOLAR CONCENTRATOR/ABSORBER. vor. Tiesenhausen, C.F. Marshall Space Flight Center, Huntsville, AL. AVAIL: Marshall Space Flight Center, ATOI. B7h-10253 C:olicctor/energy converter, consisting of dual-slope optical concentrator and counterflow thermal energy absorber, is attached to multiaxis support structure. Efficient over wide range of illumination levels, device tray be used to generate high temperature steam, .serve as solar powered dryer, or power absorption cycle cooler. .M-FS-23432 8/76 SOLAR HEATING AND COOLING PERFORMANCE. Littles, J.W.; Cody, J.C. Marshall Space f = light Center, Huntsville, AL. AVAIL.,: Marshall Space Flight Center. ATOI. B76-10235 7 411IGTNAL PAGF IS PooR (QUALITY OF

Original page 13

PAPERS AND PERIODICALS 10/76 was assembled to provide operational A77-10913 PHOTOVOLTAIC AND THERMAL experience in the utilization of solar energy ENERGY CONVERSION FOR SOLAR for heating and cooling buildings. The major POWERED SATELLfrLS. von Ticscn- subsystems are the solar collector, the energy li.uscn. G.F. Marshall Space Flight storage tank, the simulated living space, the Center, Huntsville, AL. air conditioning and heating subsystems, and the controls. These subsystems are descrbed International Astronautical Federation, with emphasis placed on major results and International Astronautical Congress, conclusions. A cursory CValuati0 of the 27th, Anaheim, CA, Oct. 10-16. 1976, system for cooling is given from energy and 11 p. power consul-10ion viewpoints. This data evaluation indicates the current system is summary is provided concerning the capable of supply SO percent of the thermal most important aspects of present investiga- energy required to drive the a'- conditioner. tions related to a use of solar power satellites A preliminary evaluation of winter data (SPS) as a future source of terrestrial energy, indicates that more than 90 percent of the General SPS characteristics are briefly con- heating re(luired can be provided by the solar sidered, early work is reviewed, and descrip- system. tion of current unvcstigatnons is presented. System options presently under study include A75-4194 1974 a photovoltaic array, a thermionic system, CUP.RLNT TECHNOLOGY FOR and a closed Brayton cycle. Attention is given UF.VLLOPMENT OF Lt)W SOLAR to system reference options, basic buildit;g ABSO RPTANCE/HI(di LMITTANO] blocks, questions of system analysis and COATINI,S SPACECRAFT THLR engineering. photovolatic conversion, :and the MAL CONTROL SURFACE MATERIutility interface. It is concluded that an SPS ALS. Gilligan,J.E.; Ilarada, Y.; Gates. may be cost effective compared to terrestrial U.W. 111 Research Institute, Chicago, 1L. systems by 1995. Marshall Space Flight Center, Huntsville, AL. A76-31378 1975 STATUS OF MARSHALL SPACE In: Evaluation of the effect of the space FLIGHT CENTER SOLAR HOUSE. environment on materials; International Humphries, W.K. Marshall Space Flight Conference, Toulouse. I rance. June. Center, Huntsville, AL 17-21, ;974. Proceedings. (A75-24100 09-18 ► Paris, Centra National U'Etudes In: Aoplication of solar energy; Proceed- Spatiales. 1974, p. 567-589. NASAings of the First Southeastern Confer- suoported research. ence, Huntsville, AL, March 24-26, 1975. (A76-31376 14-44) Huntsville, AL, UAH A com prehensive program to develop Press, 1975, p. 15-30. low solar absorptance/high emittance coatings, to be successful, must coordinate basic The Marshall Space Flight Center materials preparation, coatings technology, (MSFC) solar facility is described herein, and environmental simulation, production, and test result, obtained from late May 1974 to flight-test evaluation. The prime criteria for September 1974 are discussed. Phis facility "white" thermal-control coatings are low !.olar 8

Original page 14

I absorptance and, most importantly, solarabsorptance stability. Many variablesaffc;ct the solar absorptance and its stability. These effects must be discerned arid evaluated. The factors involved, however, ate nt ,t entirely independent. accordingly, the present paper emphasizes the mayor variables, the relationships amot.- them, and how important they are in improving the properties and performance of the coatings. 1)/74 A75-14012 SOLAR LNERGY RECORDER FOR COP.VLRn.R SITL SLLECTION. NAS8-14000. Lollar, R.B.; Mandt. R.R. IBM Corp.. Huntsville. AL. Solar Energy, Vol. 16, Oct. 1974, p. 73-80. A serious obstacle to the large-scale terrestrial application of solar energy lies in the scarcity of ' • - data ort the amount of solar eneq!y a: dll"lddte converter sites. This paper describes a system designed to monitor ,:rid ► ecord, automatically, the values o! - the direct and total (sun and sky) solar radiLdOn which would be seen by e:'hcr tracking or fixed-type so!ar converters. A lurtlier pressing need addressed by the system is the means for efficiency testing and evaluation of solar cells, solar collectors and solar concentrator ',stems, under outdoor exposure to nati al sunlight and weather conditions for extenued periods. The design was accomplished in support of the Marshall Space Flight Center, NASA. where design concepts and materials for large-scale terrestrial solar energy converters are currently being evaluated. 9

Original page 15

TECHNICAL REPORTS AND :'ATENTS NASA-CASE-MPS-21628-1 9/9/75 NASA-CASL-MFS•22458-1 10/5/76 SOLAR ENERGY POWLR SYSTEM - PHOTOVOLTAIC CELL ARRAY. USING FREON. Davis. B.K. Marshall Lhason, J. T. Sperry Rand Corp., Space blight Center, Huntsville, Al.. Huntsville, AL, AVAIL: U.S. Patent AVAIL. U.S. Patent Office. N75-32581 Office. N77-10635 A solar energy vapor (freon) powered A photovoltaic cell array consisting of system for generating electrical energv is parallel columns of silicon filaments is described in which a portion of ti , c heat described. Each fiber is doped to pr, duce an absorbed from the sun in daylight is stored inner region of one polarity type and an for use during uarkness by a thermal outer region of an opposite polarity type to capacitor. A mass of pyrone, having a high thereby form a continuous radial semiconducthermal capacity, liquifies wh-, heat is tor junction. Spaced rows of electrical applied to it and goes through a solidification contacts alternately connect to the inner and process to provide a heat output. A highly outer regions to provide a plurality of efficient solar boiler is constructed utilizing electrical outr,uts which may be combined in an anodized titanium surface and a particular parallel or in series. +:oiuu.; nation of sliapcd boiler tubes and complementary reflectors. 'file overall effi- NASA-CASE-MFS-22562-1 11/18/75 ciency of the system is further improved by a PANEL FOR SELECTIVELY ABSORBunique arrangement of heat recovery devices. ING SOLAR THERMAL ENLRGY AND THE METHOD OF PRODUCING SA!!r NASA-CASE-MFS-21628-2 5/18/76 PANEL. Lowery, J.R. Marshall Space SOLAR ENERGY POW1:R SYSTEM. Flight Center, Huntsville, AL. AVAIL: Davis, B.K. Marshall Space Flight Center, U.S. Patent Office. N76-14595 Huntsville, AL. A 3AIL: U.S. Patent Office. N76-23675 A panel is described for selectively absorbing solar thermal energy comprised of a A solar energy vapor (freon) powered metallic substrate, a layer of bright metallic -ystem is described for generating electrical material carried oil substrate, and a solar energy in which a portion of the heat thermal energy absorbing coating carried on absorbed from the sun in daylight is stored the bright metallic material. A layer ( f zinc is for use during darkness by a thermal interposed between the metal substrate and capacitor in which a mass of pyrone, having a the layer of bright material or the metallic high thermal capacity, liquifies when heat is substrate can be anodized for receiving thr, applied to it and goes through a solidification layer of bright metallic material. Also disprocess to provide a heat output. A highly closed is the method for producing the efficient solar boiler is constructed utilizing coating which selectively absorbs solar an anodized titanium surface and a particular thermal energy. combination of shaped boiler tubes and complementary reflectors. The overall effi- NASA-CASE-MFS-22743-1 4/20/76 tll- roved by a SOLAR ENERGY ABSORBER. ciency of the system is further i ► unique arrangement of heat recovery devices. Brantley, L.W., Jr. Marshall Space Flight ORIGINAL PAGE I5 10 OF POOR DUALITY

Original page 16

Center. Huntsville, AL. AVAIL: U.S. An improved rotatable mass adapted to Patent Office, N76-22657 be used as a flywheel in energy stor..ge devices is reported. The flywheel is character- A solar energy ab-:)rber is described, ized by a plurality of coaxially aliened, which includes a tubu'.ar absorber surface contiguous disks mounted on i spin shaft. through which a fluid passes for transferring Each disk is formed of a plurality of woven thermal energy from the absorber to other fibers disposed in a plane transversely related devices. Positioned above the tubular absorber to an axis of rotation with the fibers of surface are spaced glass layers. Positioned alternate disks being continuous throughout between an upper layer and the next layer is their length. The midportion of the fibers of a vacuum, or air for minimizing thermal the remaining disks is removed for defining energy, losses through convection. A clear annular voids concentrically related to the liquid passes between two intermediate layers spin shaft. of glass for transferring the thermal energy absorbed by either the initial passage of the NASA-CASL-MFS-23062-1 10/26/76 visible spectrum of electromagnetic rays or by MECHANICAL THERMAL MOTOR. infrare d radiation from art absorber posi*.ioned Hein. L.A.; Myt-rs. W.N. Marshall Space below. Flight Center, Huntsville, AL. AVAIL: U.S. Patent Office. N77-12402 NASA-CASE-MFS-22744-1 5/25/76 SOLAR ENERGY TRAP. Brantley, An apparatus is described for converting L.W., Jr. Marshall Space Flight Center, thermal energy such as solar energy into Huntsville, AL. AVAIL: U.S. Patent mt-chanical motion for driving fluid pumps Office. N76-24696 and similar equipment. The thenna; motor comprises an inner concentric cylinder carried An apparatus is described for trapp :Ag by a stationary core member. The core solar energy for heating a fluid that could be member has a cylindrical disc plate fixed subsequently used in turbines and similar adjacent to a lower portion and extending devices. The apparatus includes an elongated radially from it. An outer concentric Cylinder vertical light pipe having an open end through rotatably carried on the disc plate defining a which the visible spectrum of electromagnetic space between the inner and outer concentric radiation from the su,r passes to strike a cylinders. A spiral tubular nnm:ier encircles tubular absorber. The L,,.it i.:pc has a coated the inner concentric cylinders and is coninterior surface of a low absorptivity and a tained within the space between the inner anti high reflectivity at the visible wavelengths and outer cylinders. One portion is connected to a high absorptivity/ernissivity ratio at infrared the inner concentric cylinder and a second :wavelengths. The tubular absorber has a portion connected to the outer concentric: coating on the surface for absorbing visible cylinder. A heated Iluid is conveyed through wavelengths to feat the fluid passing through. the tubular member and is periodically cooled Infrared wavelengths are radiated from the causing the tubular member to expand and tubular absorber back into the light pipe for contract. This causes the outer concentric heating fluid. cylinder to reciprocally rotate on the base plate accordingly. The reciprocating motion NASA-CASE-MFS-23051-1 11/14/75 of the outer concentric cylinder is then AN IMPROVED ROTATABLE MASS !rtilized to drive a pump member in a pump FOR A FLYWHEEL. Weyler, G.M., Jr. chamber. Marshall Space Flight ('enter. Huntsville, AL. AVAIL: NTIS.

Original page 17

1 , NASA-CASE-MFS-23167-1 8/31/76 The assessment procedure includes THERMAL ENERGY STORAGE SYS- input/output analysis to bridge the flows TEM OPERATING ON SUPERHEAT- between the sectors, and net economics and ING OF LIQUIDS. Brantley, L.W., Jr. net energetics as performance criteria for the Marshall Space Flight Center, Huntsville, conservation actions. Targets of opportunity for large act energy savings and the applica- AL. AVAIL: U.S. Patent Office N76-31667 tion of technology to achieve these savings are discussed. A thermal energy storage system is described for converting a fluid such as %vater NASA-CR- 129012 9/73 into a superheated vapor for driving a turbine TERRASTAR: TERRESTRIAL APPLIand it also includes an energy storage device CATION OF SOLAR TECHNOLOGY fur storing thermal energy from the vapor to AND RESEARCH, FINAL REPOR 1. be u t ilizzd should the pressure of the vapor Auburn Univ., Auburn, AL. (School of' fall below a predetermined value. 'rite energy Engineering). NGT-01-003-044. .AVAIL: storage device Includes a storage tank 1 ►aving a NTIS. N74-12674 plurality of stacked vertical compartments containing metallic spheres filled with inetal The application of solar energy to the alloy for storing the thermal energy t1wrein energy crisis of the 70's and beyond is and a fluid reservoir below the stacked discussed in the context of energy co ►tsumtpcompartments. Diagrams of the system are tion in the U.S., energy resources in the U.S., and tl ► e state-of-the-art of solar energy shown. applications. Solar energy application NAS-CR-120668 9/75 concepts, such as solar farms (a term used to ECASTAR: ENERGY CONSERVA- describe vast fields of concentrato rs collecting TION; AN ASSESSMENT OF SYS- solar energy for the generation oi' steam to AND drive power turbines), an orbiting r,olar power TEMS, TECHNOLOGIES REQUIREMENTS, FINAL REPORT. station, and the conversion of solar energy Auburn Univ., Auburn, AL. into solar power for hating .;id cooling of NjT-01-003-344. AVAIL: NTIS. individual buildii:gs on the Earth, are dis- N76-21686 cussed. The report emphasizes the application of solar energy to the ;creating and cooling of A method ,)Iogy for a systems approach buildings since this application seems to be display and assessment of the potential for more promising in the near term as far as energy conservation actions •g ad the impacts researtl. and development are concerned. The of those actions waE presented. The U.S. importance of initiating research and developeconomy is divided into four sectors: energy ment on all solar application concepts is industry, industry, residential/commercial and stressed as an important step in pursuing the transportation. Each sector is assessed with use of solar energy. li- ► nndiate steps leading respect to energy conservation actions and to the application of solar energy to heating impacts. The four sectors are combined and and cooling of buildings are outlined to insure three strategies for energy conservation appreciable energy displacement through the actions for the combined sectors are assessed. use of solar energy by the year 2020. The three strategies (nationa; energy conservation, electrification and diver.; ; fication) repre- NASA-CR-142728 4/4/75 sent energy conservation actions for the near THE DEVELOPMENT OF A SOLAR term (nor to 1985), the mid term (1985 to RESIDEi:TIAL HEATING AND COOL- 2090) and the far term (1.000 and beyond). ING SYSTEM. Marshall Space Flight Center, AL. AVAIL: NTIS. M-TU-75-3 N75-24107 12

Original page 18

The MSFC solar heating and cooling Grodzka, P.G. Lockheed Missiles and facility was assembled to demonstrate the Space Co., Iuntsville, AL, ( Research and engineering feasibility of utilizing solar energy Engineering Center). NAS8-31100. for heating and cooling buildings, to provide AVAIL: NTIS. LMS(`-HRI:C'-TRan engineering evaluation of the total system U4966U0 N76-13592 and the key subsystems, and to investigate areas of possible improvement in design and The principles involved in thermal energy efficiency. The basic solar heating and cowling storage by sensible licit. chemical potential system utilizes a flat plate solar energy energy, and latent heat of fusion are collector, a large water tank for thermal examined for the purpose of evolving selectenergy storage, heat excirangers for space ion criteria for material candidates in the low heating, and an absorption cycle air condi- (0 C) and high (100 C) temperature ranges. tioner for space cooling. A complete descrip- The examination identifies some unresolved tion of all systems is given. Development theoretical considerations and permits a preactivities for this test system included liminary formulation of an energy storage assembly, checkout, operation, modification, theory. A number of candidates in the low and data analysis, all of which are discussed. and high temperature ranges are presented Selected data analyses fo.- the first fifteen along with a rating of candidates or potential weeks of testing are inrluled, findings candidates. A few interesting candidates in associated with energy storage a id the energy the U to 1000 region are also included. It is storage systeni are outlined. and conclusions concluded that storage by means of reactions resulting front test findings are provided. An whose reversibility can be controlled either by evaluation of the data for sunimer operation product removal or by catalytic_ means appear indicates that the current systeni is capable of to offer appreciable advantages over storage supplying an average of fifty percent of the with reactions whose reversability cannot be thernial energy required to drive the air controlled. Among such advantages are listed conditioner. Preliminary evaluation of data higher heat storage capacities and more collected for operation in the heating niode favorable options regarding temperatures of during the winter indicated that neat l} one collection, storage, and delivery. Among the hundred percent of the thermal energy disadvantages are lower storage efficiencies. required for heating can be supplied by the system. NASA-CR-1441 10 9/75 SOLAR HEATING AND COOLING NA:,A-CR-144006 4/30/75 TLCIINICAL DATA AND SYSTEMS SUNFALL MONITOR CALIBRATION ANALYSIS PROGRESS REPORT, OCT. PLAN. Lollar, R. B. International 1974 - AUG. 1975. Christensen, U.L. Business Machines Corp., Huntsville, AL. University of Alabama, Huntsville, AL. NAS8-31309. AVAIL: NTIS. IBM-75W- (Center for Environmental and Energy 00061 N76-10444 Studies). NAS8-31 293. AVAIL. N iS. N76-15587 The initial on-site, and subsequent periodic calibration and adjustments are The solar energy research is reported described for the pyroheliometer, pyranonie- including climatic data, architectural data, ter, equatorial mount, and the data manage- heating and cooling equipment. thermal loads, ment system. and economic data. Lists of data sources presented include selected d-rta sources for NASA-CR-144081 11/75 solar energy heating and cooling: bibliography THERMAL ENERGY STORAGE BY of solar energy, and other energy sources: MEANS OF CHEMICAL RLACTIONS. sources for manufacturing and sales, solar ORIGINAL. PAGE 18 13 OF POOR (QUALITY

Original page 19

energy collector., and solar energy healing which is low in cost and aesthetically appealing is described. Phase one work and cooling projects. reviewed the current collector design and NASA-CR-14 .11 11 NAS8-31293 developed a low-cost design based on specific SOLAR III:ATING AND COOLING; design/performance/cost requirements. TECHNICAL DATA AND SYSTEMS Throughout this phase selected collector ANALYSIS. PRESENTATION CHARTS component installation. maintainability and (BRIEFING TO NASA 17 SEPTHMBI R durability. The resultant colle-:tor design was 1975). University of Alabama, lEuntsville, composed of an absorber plate, insulation, AL, (Center for Environmental and fran;e, cover, de%%icant and sealant. In phase Energy Studies). NAS8-31293. AVAIL: two, three collector prototypes were fabricat- NTIS. N76-15588 ed and evaluated for both nontherntal and thermal characteristics. 'tests included static An interim status briefing concerning the load tests of covers, burst pressure tests of solar energy research is presented. Systems absorber plates, and tests for optical characplanning, methodology and procedures. which teristics of selective absorber plate coatings. might be applied to trte current program are The three prototype collectors were shipped included. to Marshall Space Flight Center for use in their solar heating and cooling test facility. NASA-CR-144234 1 1,/28/75 DEVELOPMENT OF A SOLAR. NASA-CR-144312 7/26/76 POWERED RESIDENTIAL AIR CON- INfERCONNECT AND BONDING DITIONLR FINAL SUMMARY TLC'IINOLOGIES FOR LARGE FLEX- REPORT. AiResearch Mfg. Co., Torrance, IBLE SOLAR ARRAYS FINAL CA. NAS8-30758. AVAIL. NTIS. REPORT. Lockheed Missiles and Space N76-20631" Co., Sunnyvale, CA. ( Space Systems Div.). NAS8-31016. AVAIL: NTIS The initial objective of the program was LMSC-D492654 N76-32653 the optimization (in terms of cost and performance) of a rankine cycle mecha7ical l hennocompression bonding and conrefrigeration system which utilizes thermal ductive adhesive bonding are developed and energy, from a flat solar collector for aric evaluated as alternate methods of joining solar conditioning residential buildings. however, cells to their interconnect ass ,:mblies. Bonding feasibility investigations of the adsorption materials and process controls applicable to process revealed that a dessicant-type air fabrication of large, flexible Substrate solar conditioner offers many significant advan- cell arrays are studied, The primary potential tages. As a result, limited efforts were use of the techniques developed is on the expended toward the optimization of such a solar array developed by NASA/MSFC and system. LMSC for solar electric propulsion (SEP) and shuttle payload a p plications. This array is NASA-C R-144265 1/76 made up of flexible panels approximately 0.7 DESIGN, FABRICATION, TESTING by 3.4 meters. It is required to operate in AND DLI.IVL:RY OF A SOLAR space between 0.3 and 6 AU for five years COLLECTOR. FINAL REPORT. Sims, ,:Jth limited degradation. Materials selected W.H.; Ballheim, R.W.: Bartley. S.M., trust be capablt. of enduring this space Smith, G.W. Chamberlain Corp., Water- environment, including outgassing and radialoo, IA. NAS8-31326. AVAIL: NTIS. tion. C8092-PR-012 N76-22671 A two phase program encompassing the redesign and fabrication of a solar collector 14 t

Original page 20

NASA-CR-144314 3/76 Lin, J.H. Honeywell, Inc., Minneapolis, DEVELOPMENT OF A SOLAR MN (Systems and Research Center). POWERLD RESIDENTIAL AIR CON- NAS8-31545. AVAIL: NTIS. DITIONER (GENERAL OPTIMIZA- N76-28404 TION) FINAL REPORT. Lowen, U.J. Chrysler Corp., Cape Canaveral, FL. Selectively absorbing black nickel coat- NAS8-31437. AVAIL: NTIS. ings are among the most optically efficient N76-24702 low cost coatings for use on flat plate solar collectors. However, a current fJi-?-n-S-O A commercially available three ton coating in use is quite susceptible to a humid residential lithium bromide (Liar) absorption environment, degrading badly in less than ten air conditioner was modified for use with days at 38°C (100°F) at 95 percent relative lower temperature solar heated water. The humidity. Therefore, a black nickel formula modification included removal of components was d•:velopcd which can withstand such such as the generator, concentration control exposures with no loss of optics,' efficiency. chamber, liquid trap, and separator; and the solar absorption of 0.92 and an infrared addition of a Chrysler designed generator, an emittance (at 100°C) of 1.00 were still off-the-shelf LiBr-solution pump. The design present after 14 days of humidity exposure. goal of the modified unit was to Lp" rate wit;i This compares to a solar absorptance of only water as the hea l.-transfer fluid at a target 0.72 for the previous formula after a similar temperature of 85C (185F). 29AC (85F) time period. The electroplating bath and cooling water inlet, producing 10.5 kw (3 conditions were changed to obtain the more tons) of cooling, Tests were performed on the stable coating configuration. The effects of system before and after modification to Lath composition, tet.iperature, pli, and provide comparative data. At elevated tem- plating current density and time on the peratures (96C, 205F), the test results show coating composition, spectral optical properthat lithium bromide was carried into thy tieS and durability were investigated systenicondenser due to the extremely violent atically. boiling and degraded the evaporator per- NASA-CR-149971 I 1 122/74 formance. DEVELOPMENT 01 A SOLAR- NASA-CR-149785 2/29/76 POWERED RESIDLNTIAL AIR CON- INEIII31TOR ANALYSIS FOR A SOLAR DITIONER, DESIGN REQUIREMENTS HEATING AND COOLING SYSTEM, AND TRADE-OFF PARAMETERS. FINAL REPORT. Tabony, J.H. Southern AiResearch Mfg. Co., Los Angeles, CA. Univ., Baton Rouge, LA. (Dept. of NAS8-30758. AVAIL: NTIS. Mechanical Engineering). NSG-8025, AIRESLARCH-74-10996(2) N76-30654 AVAIL: NTIS. N77-75716 Data basic to the design, characteriza- Cooling Systems/Corrosion Prevention/ tion, comparison, and evaluation of solar- Inhibitors/Solar Heating/Aluminum/Copper/ -powc-,ed residential air conditioner concepts Electrochemical Corrosion/Pitting/Steels. are presented. 6/76 NASA-CR-149972 1/13/75 NASA-CR-149928 IMPROVEMENT OF BLACK NICKEL DEVELOPMENT OF A SOLAR- COATINGS PRODUCT DEVELOP- POWERED RESIDENTIAL AIR CON- MENT FOR USE IN SOLAR COLLEC- DITIONER. AiResearch Mfg. Co., Los TORS FINAL REPORT. Peterson. R.E.; ORIGINAL PAGE IU 15 OF POOR QUALITY

Original page 21

r Angeles. CA. NAS8-30758. AVAIL: concerned with the generation of parametric NTIS. iURESEARCH-74-10996(3) design data for different condenser N76-30656 approaches; i.e., (1) an an)hient air condenser, (2) a humidified ambient air condenser, (3) An extensive review of 1"ic literature was an evaporating condenser, and (4) a water conducted which was concem cd with the condenser (with a cooling tower). All systems characterisation of systems and equipment tiature a high performance turbocompressor that could be applicable to (lie development and a single refrigerant (R-ll) for the power of solar-powered air conditioners based oil and refrigeration loops. Data were • obtained Rankine cycle approach, and the establish- by compute rized methods developed to pernient of baseline data defining the perform- mit system characterization over a broad ance, physical characteristics, and cult of range of operating and design conditions. The systems using t i-iBr/H20 absorption cycle. criteria used for comparison of the candidate NASA-CR-144973 DEVELOPMENT OF A system approaches were (1) overall system 4/8/75 cop (refrigeration effect/solar heat input), ('- ) SOLAR- auxiliary electric power for fans and punq)s, POWERED RI:SIDI.NTIAL AIR CON- DITIONLR. PROGRAM and (3) system installed cost or cost to the RLVIL•W. user. AiResearch Mfg. Co., Los Angeles, CA. NAS8-30758. AVAIL: NTIS. NASA-CR-149975 1 1;'7/75 AIRESEARCH-74-10996(5) N76-30665 DEVELOPMENT OF A SOLAR- POWERED RESIDENTIAL AIR CON- Progress in the effort to develop a DITIONER. SYSTEM 01-TIMIZATION residential solar-powered air conditioning PRELIMINARY SPEC.'IIICATION. system is reported. The topics covered include Rousseau, J.; Hwang, K.C. AiResearch the objectives, scope and status of the Mfg. Co., Los Angeles, CA. NAS8-30758. program. The results of state-of-art, design, AVAIL: NTIS. 11RESEAR('II-74and economic studies and component and 10996(8) N76-30060 system data are also presented. NASA-CR-149974 DEVELOPMENT OF A lnvesti.-ations aimed at the optimization 7/25/75 of a baseline Rankine cycle solar powered air SOLAR- conditioner and the development of a pre- POWERED RESIDENTIAL AIR CON- liminary system specification were conducted. DITIONER. SCREENING ANALYSIS. Efforts encompassed the following; (1) inves- Mfg. Co., Los Angeles, CA. tigations of' the use of' recuperators/regenera- AiResearch NAS8-30758. AVAIL: NTIS. tors to enhance the performance of the AIRESEARCII-74-10996(7) N76-30659 baseline system, (2) development of an off-design computer program for system Screening analysis armed at the defini- performance prediction, (3) optimization of tion of an optimum configuration of a the turbocompressor design to cover a broad Rankine cycle solar-powered air conditioner range of conditions and permit operation at designed for residential application were low heat source water temperatures, (4) conducted. Initial studies revealed that system generation of parametric data describing performance and cost were extremely sensi- system performance (cop and capacity), (5) tive to condensing temperature and to the development and evaluation of candidate type of condenser used in the system. system augmentation concepts and selection Consequently, the screening analyses were of the optimum approach, to) generation of 16

Original page 22

auxiliary power requirement data, (7) devel- computerized data base using the Marshall opment of a complete solar collector-thermal hitormation Retrieval and Data System storage-air conditioner computer program, (8) (MIRADS) deve!uped by NASA-MSFC is evaluation of the baseline Rankine air condi- discussed. This data base provides extensive rioner over a t7ve day period simulating the technical and socioeconomic information NASA solar house operation, and 0) evalua- related to solar energy heating and cooling on tion of the air conditioner as a heat pump. a national scale. A broadly based research :,;l proach was used to assist in the support of NASA-CR-149976 3/28/75 program management and the application of a DEVELOPMENT OF A SOLAR cost-ch'ective program for solar energy devel- -POWERLDRESIDI.NTIALAIRCON- opment :urd dennxrstration. 011IONI:R. ECONOMIC ANALYSIS. ArResearch Mfg. Co., Los Angeles, CA. NASA-CR-150032 10/76 DESIGN, FABRICATION, TLSTING, NAS8-30758. AVAIL: NTIS. AIRLSLARCIi-74-10096(4) N70-30653 AND DELIVL• RY OF A SOLAR Er4LR(;Y COLLLCTOR SYSTLM FOR The results of investigations aimed at the RESIDLNTIAL HEATING AND COOLdevelopment of cost models to be used ur ;he ING. Ilolland, T.H.: Borzoni, J.T. economic assessawnt (it' Rankine-powered air Honeywell Iric., Minneapolis, MN. conditioning systems for residential applica- (Energy Resources Center). NAS8-31327. tion are summarised, The rationale used in AVAIL: NTIS. N77-10638 the development of the cost model was to (I) collect cost data oil systems and on A low cost flat plate solar energy the major equipment used ill systems; collector was designed for [lie heating and (2) reduce these data and establish relation- coding of residential buildings. The system ships between cost and other engineering meets specified performance requirements, at parameters such as weight, size, power level, the desired system operating levels, for a etc..: and (3) derive simple correlations from useful life of 15 to 20 years. at minimum which cost-to-the-user can be calculated from cost and uses state-of-the-art materials and performance requirements. The equipment technology. The rationale for the design considered in the survey included Ite:!t method was based on identifying possibl,: exchangers, fans, motors, and turboconi- material candidates for various collector pressors. This kind of hardware represents components .end then selecting the compomore than 2!3 the total cost of conven- nents which best meet the solar collector of design requirements. The criteria used to tional air conditioners. eliminate certain materials were performance NASA-CR-150006 6/76 and durability test results, cost analysis, and SOLAR HFA r'ING AND COOLING prior solar collector fabrication experience. TLCIINICAL DATA AND SYSTEMS ANALYSIS PROGRESS REPORT, SE.P. NASA-CR- 150004 7/76 1975 JUN. 1976, Christeasen, 1). L. LISTING OF SOLAR RADIATION University of Alabama, Huntsville, AL. MLASURING EQUIPMENT AND (Center for Environmental and Energy GLOSSARY. Carter, L.A.; Greenbaum. Studies). NAS8-31293. AVAIL: NTIS. S.A.; Patel. A.M. University of Alabama. N76-32050 Huntsville, AL. (Center for Environmental and Lnergy Studies). NAS8-31293. The acquisition and processing of AVAIL: NTIS. FRDA/NASA-31 293-76/3 selected parametric data for inclusion in a N77-1507 17 ORIGINAL PAGE; IS OF POOR QUALITY,

Original page 23

An attempt is made to list and provide Princeton. NJ. NAS8-31308. AVAIL: all available information about solar radiation NTIS. F L T-76-145-2-VOL-I measuring equipment which are being manu- N77-15404 factured and are available oil market. The list is in tabular form and includes sensor The technical and economic aspects of type, response time. cost data and comments satellite solar power systems are presented for each model. A cost code is included With a focus on the current configuration which shows ranges only. 5000 MW system. The technical studies include analyses of the orbital system struc- NASA-CR-1 ~0171 5/26/76 tures, control and stationkeeputg. and the SPACI -BAS1 1) POWER CONVERSION formulation of program plans and costs for AND POWER RELAY SYSTEMS: PRI::- input to the economic anal ses. The LIMINARY ANALYSIS OF ALTER- econotrtic analvscs centered about the devel- NATE SYSTEMS. INTL:RI\f REPORT, opment and use of a risk analysis model for a 7/8/75-5/26/76. Boeing Aerospace Co., systenj cost assessment, identification of Seattle. VA. NASS-31628. AVAIL: critical issues and technologies, and to provide NTIS. N77-16447 information for programmatic decision making. A preliminary economic examination The results are presented of nine months of some utility interface issues is included. of technical study of nonphotovoltaic options Under the present state-of-knowledge, it is for the generation of electricity for terrestrial possible to formulate a program plan for the use by satellite power stations (SPS). A development of a satellite solar power system concept for thL augmentation of ground-based that call economicall y justified. The key solar power plants by orbital sunlignt retlec- area of' technological uncertainty is roan's tors was also studied. Three SPS types having ability to fabricate and assemble large struca solar energy source and which used nuclear tures in space. reactors were investigated. Data derived for each included (1) configuration definition. NASA-CR-150147 6/30/76 including mass statement: ( . 2) information for SPACE-BASED SOLAR POWL.R CON use in enviromnental impact assessment: (3) VERSION AND DELIVERY SYSTEMS energy balance (ratio of energy produced to STUDY. VOLUME 2: ENGINEERING that required to achieve operation); and (4) ANALYSIS OF ORBITAL SYSTEMS, development and other cost estimates. Cost INTERIM RI.I'OR4. Grumman Aeroestimates were dependent upon the total space Corp.. Bethpage NY. NAS8-31308. program (development, placement and opera- AVAIL: NTIS. REPT-70-145-2-VOL-2 tion of a number of satellites) which was N77-15495 Postulated. This postulation was based upon an analysis of national power capacity trends Program plans, schedules. and costs are and guidelines received from MS1=C. determined for a synchronous orbit-based power generation and relay system. Require- NASA-CR-150146 6/30/76 ments fOr the satellite WRS) are explored. SPACE-BASED SOLAR POWER CON- Engineering analysis of large solar arrays, VERSION AND DELIVERY SYSTEMS flight mechanics and control, transportation, STUDY, VOLUME I: EXECUTIVE assembly and maintenance, and microwave SUMMARY, INTERIM REPORT. transmission are included. Hazelrigg• G. A., Jr. ECON, Inc., 18

Original page 24

i NASA-C R-150 148 6/30/76 absorption cycle is investigated. Included are SPACE:-BASED SOLAR POWER CON- computer simulations of a solar-cooled house, VERSION AND Di.LIVLRY SYSTEMS analyses and incasurements of' heat transfer STUDY. VOLUME 3: EC'ONOMI( rates in absorption system components, and ANALYSIS OF SPACE-BASF,D SOLAR design and fabrication of various system POWER SYSTEMS, INTERIM REPORT. components. A survey of solar collector llazelrigg, G.A., Jr. EC'ON, Inc., convection suppression methods is presented. PRINCETON, NJ. NAS8-31308. AVAIL. NASA-CR-15U 177 11/76 NTIS. RFPT-76-145-2-VOL-3 IR-2 N77-15496 SOLAR RADIATION OBSLR% A I ION STATIONS Willi COMPLETE LIST- A variety of economic and programmatic INGS OF DATA ARCHIVED BY TEIL issues are discussed concerning the develop- NATIONAL CLIMATIC CENTER, ment and deployment of* a fleet of space- ASHE:VILLE, NORTII CAROLINA AND based solar power satellites (SSPS). The costs, INH IAL LISTING OF DATA NOT uncertainties ano risks associated with the CURRENTLY ARCIilk'ED. Carter, E.A.; currciit photovoltaic SSPS configuration. and Wells, R.E.; Williams, B B.; Christensen, with issues affecting the development of an U.L. University of Alabaina, Huntsville, economically viable SSPS development pro- AL; Energy Research and Development grain are analyzed. The desirability of a low Administration, Washington. U.C. earth orbit (LEO) demonstration satellite and (Center for Environmental and Energy a geosynchronous (GEO) pilot satellite is Studies), NAS8-31.'.93. AVAIL. NTIS. examined and critical technology .areas are N77-17987 identified. In addition, a preliminary examination of utility interface issues is reported. I he A listing is provided of organizations main of the effort reported is the taking solar radiation data, the 1 00 stations EMUS dev^-lopinent of' SSPS unit production, and where observations are made, the type of operation and maintenance cost models suit- equipment used, the form of the recorded able for incorporation into a risk assessment data, and the period of operation of each (Monte Carlo) model (RAM). It is shown that station. Included is a listing of the data from the key technology area deals with the 150 solar radiation statiuns collected over the productivity of mail space, not, as might past 25 years and stored by the National be expected, with some hardware component Climatic Center. teclulolol;y. NASA-CR-150209 3/21 /7 7 12/76 SYSTEMS UEFINITION SPACE BASED NASA-C'R-150176 OPTI.NIIZA"PION OF ABSORPTION POWER CONVERSION SYSTEMS. AIR-CONDITIONING; FOR SOLAR FINAL REPORT-EXECUTIVE SUM- ENERGY APPLICATIONS, FINAL MARY. Boeing Aerospace Co., Seattle. REPORT 9/1x74-1031/76. Perry, E.H. WA. NAS8-316213. AVAIL: NTIS. ;Memphis State Univ., TN (Dept. of' Mechanical Fngineering). NAS8-31189. AVAIL: NTIS. N77-17560 This study investigated potential spacelocated systems for the gen-_ration of elec- Improved performance of solar cooling trical power for use on Earth. These systems systems using the lithium broi-ide water were of three basic types: (1) systems 19

Original page 25

prouucing electrical power from solar energy NASA-TM-X-3509 (2,) systems producing; electrical Dower from S()LAR ABSORPTION CIIARACTEP nuclear reactors; (3) systems for augmenting TICS OF SLVLRAL COA KINGS A;., ground-based solar power plants by orbital SURFACL FINISHES I UR SOLAR ► 2 ) would LNl.R(;Y COLLLCTORS. Lowery, J R. sunlight reflectors. Systems i I and ( _ utilize a microwave beam stela to transmit Marshall Space Flight ('enter. Alabama, s^ their output to Earth. Configurations AVAIL: N'rIS 77N20567 implementing these concepts were developed through an optimization process intended to Solar absorption characteristics are yield the lowest cost for each. A complete established for several films potentially favorprogram was developed for cacti concept, able for use as receiving surfaces m solar identifying required production rates, energy collectors. Included in the investigagl:antities of launches, required facilities, etc. tions were chemically produced black films, Each program was costed in order to provide black electrode posits, and anodized coatings. the electric power cost appropriate to cacti It was found that black nickel exhibited the best combination of selective optical properconcept. ties of any of the coatings studied. A serious NASA-CR-150268 5/18/77 drawback to black nickel was its high SYSTEMS DEFINITION SPACE BASED susceptibility to degradation in the presence P(Ml R C'ONVLRSION SYSTEMS of high moisture environments. Iaectroplated (HNAL. REPORT, DLTAILLD TIiCH- black chrome generally exhibited high absorp- NI('AL KITORT). Boeing Aerospace tivities, but the emissivity varied considerably Co., Seattle, WA, NAS8-31628. AVAII. and was also relatively high under somcondltions. The black chronic had the greatest NTIS. moisture resistance of any of the coatings The purpose of this study was the tested. Black oxide coatings out copper and investigation of potential space-located sys- steel substrates showed the best combination tems for the generation of electrical power of selective optical properties of any of the for use on Earth. These systerns were of three chemical films studied. basic types: (1) sN stems producing; electrical power from solar energy; 12) systems producing electrical power from nuclear reactors; NASA-TM-X-5395 9/16/69 (3) systems for augmenting ground-based solar THL THLRMAL STRUCTURE OF TilE power plants by orbital sunlight reflectors. SUN. Schocken. K. Marshall Space Hight Systems ( I) and (2) would utilize a micro- ('enter. Alabama. AVAIL: MISIS MSFCwave beam systems to transmit their output to R - RP-INT-67 -3 70N37503 Earth. Configurations implementing; tl:.sc concepts were developed through an optimization Mathematical Models/Solar Energy/Solar process intended to yield the lowest cost for Tensperaturc/Solar Flux/Solar Protons/Solar each. A complete program was developed for Radiation/Solar SIMUlatron each concept, identifying required production rates, quantities of launches, required facili- NASA-'I'M-X-53930 9/16/69 ties, etc. Each program was costed in order to Till'. III :AT PIPE I XPERi\11:NT. provide the electric power cost appropriate Shelton, R.D. Marshall Space Flight Center., Alabama, AVAIL. NTIS. to cacti concept. MSFC-R-SSL-INN-67-10 70N37575 '0V

Original page 26

Pipes I [eat irg/Solar NASA-TM-X-649.14 9/74 (Tubes)/Radiant Heating/ Absorners Heat/Heat SOLAR RLSIDENTIAL HEATING AND (Material) Sinks/Radiant Heat Transfer NASA-TM-X-60705 COOLING SYSTEM DEVLLOPMI-NT TLST 11 i3O6 tAM IlLimphries. W.R.. 5/6/62 Melton, 1) E. Marshall space Flight DEVELOPMENT OF TE INIQUES ('enter. Huntsville, Alabinn s. AVAIL: FOR FORMING SF-G MENTS OF A NTIS. 75N22903 PARABOLIC SOLAR CONCENTRA- TOR Schucrer, P.H. Marshall Space A solar heating ano.l cooling system is Flight Center, Alabama AIL: NTIS. dewribed, which was installed in a simulated A'-I M TP-M E-62-1 68N81707 home at Marshall Space Flight ('enter. Performance data are provided for the Manufacturing/Parabolic Bodies/Produc- checkout and initial operational phase for key tion Engincerirtg/Segments /Solar Cullectors subsystems and fur the total system. Valuable NASA-TM-X-62639 information was obtained with regard to 8/5/68 operation of a solar cooling system during the PROCEEDINGS OF THE THIR') first summer of operation. Areas where SOUTHEASTERN SEMINAR ON improvcnicnts and modifications are required THI RMAL SCILNCLS. Atkins, If L.. to optinuie such a system are discussed. Vach(ni, R.I. Auburn University and Marshall Space Flight Center, Alabama. NASA-TM-X-649 40 61175 AVAIL: NTIS. MISC-SSL-69-1 ON 18680 SC)LAic ENERGY SIORAGE TANK. FLU!Ij MANIFOLD DESIGN FOR A Il Lill) phries. N'-R., Hewitt, H.C., •and Acrodyw1 inic Heating/Conferences/Fluid Griggs, E.I. Marshall Space Flight Center, Mechanics/Heat Shielding/Heat Transfer/Space Huntsville, Alabama. Tennessee Tech- Flight/Spacecraft Environments/Blunt Bodies/ r^t>li ,gical University. AVAIL: NTIS. Lnergy Conversion/Elehum,'Hydrogen/Low 75N27562 Temperature 1 1 hysics/Mass Transfer/Matheinatical Modclsil lidymer Physics/Rhcology/ A design technique for a t1uid rnanifuld Thermal Protection/'Chcrmodynaniic Proper- t'or use in a solar energy storage tank is given. ties/Therrnophysical Properties. This analytical treatment generalizes the fluid equations pertinent to manifold design, giving NASA-rM-X-64757 5/7/73 manifold pressures, velocities, and orifice TERRESTRIAL ENVIRONMENT (CLI- pressure differentials in terms of appropriate MAfE) CRITERIA GUIDELINES FOR fluid and manifold geometry parameters. USI IN AEROSPACE VEHICLE' DE-VLL- Lxperimental results used to corroborate OPMI;N'I*. Daniels, G.E. Marshall Space analytical predictions are presented. These Flight ('enter, Alabama. AVAIL: WIS. data indicate that variations in orifices can 74N 16292 cause deviations between analytical predictions and actual performance values. Guidelines are provided on probable climatic extremes and terrestrial environment NASA-TM-X-64958 2/28/75 data applicable to space vehicle and associated INTU RIM PLRFORMANCF. CRITERIA equipment design and development. Opera- FOR COMMERCIAL SOLAR HEATING tional criteria for ground support sites are AND COMBINED 11f:ATING/COOLING emphasized. ORIGINAL PAGE IS 21 OF POOR QUALITY

Original page 27

I. SYSTLMS AND FACILITIES. Marshall ADS efforts to demonstrate the engineer- Space FliLi t Center, Huntsville, mg feasibility of utilizing solar power for ► Alab:mia. AVAIL: NTIS. 751\3.555 I hose efforts were concentrated on the 9tt%t 10001 I )C- residential heating and cooling are described. analysis. design, and test of a full-sc4le Air Conditioning/Solar hnergy Conver- demonstration system which is currently sion/Heat Transfer/Solar Collectors/Solar under construction at the National Heating/Technology Assessment. Superseded Aeronautics and Space Administration, by NBSIR 76-1187 Marshall Space Flight Center, Huntsville, Alabama. The basic solar heating and cooling NASA-TM-X- 5111 /74 system under dcvelopm.nt utilizes a flat plate 64 0 09 CONSIDL RAT IONS FOR PLRE ORM- solar energy collector, a large water tank for ANC E: EVALUATION OF SOLAR thermal energy storage. heat exchangers for III:ATING AND COOLING SYSTEMS. space heating and water heating, and an Littles, 1.W,, Cody, J.C. Marshall Spar_ absorption cycle air conditioner for space Flight Center, Huntsville, Alabama. cooling. AVAIL: NTIS 76N14000 NASA-TM-X-7.' 199 11/74 One of the many factors which must be ANALYTICAL DI:SCRIP"I'lON OF THI considered in performance evaluation of solar MOM RN STI_AM AUTOMODILL-. energy is the relative merit of a given solar Peoples. J.A. Marshall Space Flight energy system when compared to a standard ('enter, Huntsville. Alabama. AVAIL: conventional system. Although initial and NTIS. M-TU-74-7 75N 14134 operational costs will be do mmant factors in the consideration in system selection, suffi- The sensitivity of operating conditions cient data are not yet available for a upon performance of the modern steam definitive treatment of these variables. It is automobile is discussed. The word modern possible, however, to formulate relationships has been used in the title to indicate that between the nonsolar energy requirements of emphasis is upon miles per gallon rather than the solar energy systems and the energy theoretical thermal efficiency. This has been requirements of a conventional system in accomplished by combining classical power terms of the primary performance parameters analysis with the ideal pressure-volume of the systems. Derivations of such relation- diagram. Several parameters are derived which ships, some parametric data for selected characterize performance capability of the ranges of the performance parameters, and modem steam car. The report illustrates that data with respect to limiting conditions are performance is 'actated by the characteristics presented. of the working niedouim, and the supply temperature. Performance is nearly independ- NASA-7 M-X-7008'_, 10/5/74 ent of pressures above 800 psis. Analysis 1IIL lWVLLOPME:NT OF A SOLAR- techniques were developed specifically for POWI.RLD RI:SIDI:NTIAL HLATING reciprocating steam engines suitable for AND COOLING SYSTF_M. Marshall automotive application. Specific performam-. Space Flight Center, Huntsville. charts have been constrw:ted on the basis of Alabama. AVAIL: NTIS. MA-U-74-3 water as a working medium. 'I he conclusion 74N?6504 and data interpretation are limited within this a 22 scope.

Original page 28

NASA-TM-X-73333 8/76 orbital transfer are investigated. Space AN ANALYTICAL AND F.XPI RI- shuttles, local space tra_tsportation, and the M FNTAL LVALUATION 01 A heavy lift launch vehicle required are also F RLSNE:L LENS SOLAR CONC'I:NTRA- discussed. TOR. Hastings. L.J.: Allunts, S.A.. Cosby, R.M. Hall State University and NASA-1- M-X-73355 9/76 Iluntsville A PERFORNIANCE EVALUATION OF Marshall Space Flight Center, 7uN33011 VARIOUS COMINGS, SUITS'I RAT1 Alabama. AVAIL: NTIS. MA'I ERIALS, AND SOLAR COLLEC- An analytical and experimental evalua- TOR SYSTIMS. Dulan, I.J. Marshall Fresnel lenses with Space Flight Center, Iluntsville, Ala, Gon of line focusing appiication potential in the 200 to 37WC AVAIL: NTIS 77N 15481) range was studied. Analytical techniques were formulated to assess the solar transmission An experimental apparatus was conand imaging properties of it grooves down structed and utilized in conjunction with both Experiment was based on a 56 cm wide, a solar simu lation and actual sunlight to test 1-, 1.0 lens. A sun tracking heliostat provided and evaluate various solar panels coatings, a nonmoving solar source. Measured data panel designs, and scaled-down collector indicated more spreading at the profile base subsystems. Data were taken by an automatic than analytically predicted, resulting in a peak digital data acquisition system and reduced concentration 18 percent lower than the and printed by a computer system. l he solar computer peak of 57. The nipasured and collector test setup, data acquisition system. computed transmittances were 85 and 87 and data rcdu,;tion and pnntout !^N stcu► a were percent, respectively. Preliminary testing with considered to have operated very satisfaca subsequent lens indicated that modified torily. Test data indicated that there is a manufacturing techniques currected the practical or useful Iimit in scaling down profile spreading problem and should enahle :xyond which scaled-down testing cannot improv.d analytical experimental correlation. produce result., comparable to results of larger scale test. lest data are presented as are NASA-TM-X-73344 6/11 schematics and pictures of test equipment antl SATELLITE: POWER SYSTEM ENGI- test hardware. NLI:RING AND LCONOMIC ANALYSIS SUMMARY. Marshall Space Flight Center. NASA-ThI-X-7339: 4/77 I luntsville, Alabama. AVAIL: NTIS. AN ANALYTICAL AND LXPF.RI- 77N 15486 MLNTAL INVESTIGATION OF A 1.8 BY 3.7 MI : TI.R FRI:SNEL 1.1 NS A system engineering and economic SOLAR CONCENTRATOR. llasti-igs, J.: analysis was conducted to establish typical Allurns. L.: and Jensen, S. Marshall reference baselines for the photovoltaic, solar Space Flight Center. Huntsville. Alathermal, and nuclear satellite power systems. bama. AVAIL. NTIS. Tentative conclusions indicate that feasibility and economic viability are characteristic of Line-focusing acrylic Fresnel lenses with the satellite power system. Anticipated tech- application potential in the 200 to 370°C nology related to manufacturing. construc- range are being analytically and experition, and maintenance operations is described. mentally evaluated. Investigations pr,•viously Fuel consumption. environmental effects, and conducted with 56 cm wide lens have been ORIGINAL PAGE IS OF POOR QUALITY 23

Original page 29

extended by the ;resent study to experi- A new motel is l,roposed for the analysis of mentation analyses with a 1.8 by 3.7 in lens. ultra , anic attenuation in lure sil;nrcon- A ntea-aired peak concentration ratio of 54 ductors with two partially decoupled energy, with 90 percent of the transmitted :nergy bands. To analyze tho.. attenuation in pure fiacused into a 5.0 cm s. idth was achieved. A superconducting NB, the existence of two peak concentration of 61 avid a 90 percent energy gaps was assumed to b•: associated target width of 4.5 ctr, was analytically with the two partially d , ;oupled energy computed. ''he exp.^rimeut::l land analytical bands. One of* the gaps was found to have the lees transmittance was b I percent and 86 normal BCS value of 4 and the oth ,: r gap percent, respectively. Thus, the analytical/ was found to have the anomalously large experim.ntal lens performance correlation is value of 10. No exnerirttental evidence was considered good. The lens also was efficiency found sugpr' sting that the seemed energy gap ranged from 42 percent at 100'C to 26 had a dilrerent transition temperature. The percent at 300°C, whereas all of 40 interpretation of the results for the NB-MO percent at 300°C was anticipated. Apparently, alloys is shown to be compl i cated by the the reflective cavity surrounding the absorber possible existence of a second supercondu^ttube did not perform as expected. Therefure, ing please with a transition temperature of' future receiver assemblies will decrease or 0.35 of the transition temperature of the first eliminate reliance of reflective surlaces, i.e., phase. The elastic constants of NB-MO alloys the energy focused directly oil absorber arc shown to be approximately independent tube surfaces will be increased. Efficiency of MO composition to nine atomic percent improvements to the 40 to 50 , crcent range MO. These results do not agree with the are anticipated. current microscopic theory of transitit-m temperature for the transition elements. 6/,2 NASA-TN-D-6828 ULThASONIC INVESTIGATIONS OF NASA-TN-D-8409 2/77 IIIE SUPERCONDUCTING PROPI:R- CORROSION INHIBITORS FOR TILS OF THE NB-MO SYSTEM. Lacy, SOLAR E,EATING AND COOLING L.L. 'Marshall Space Flight (enter, SYSTEMS. Huntphries, T,S.. DeramUS, Iluntsvillc, Alabama. AVAIL. NTIS. GJF ., j'r. Marshati Space Hight Center, 7'-N26433 Huntsville, Alabama. AVAIL: NTIS, 77N 17 198 The superconducting properties of single ell{ crystals of' NB and two alloys of NB with MO Problems dealing with corrosion and were investigated by ultrasonic techniques. corrosion protection of solar heating anti The results of measurements of the ultrasonic cooling systems are discussed. A test program attenuation and velocity as a I'unction of was conducted to find suitable and effectiv: temperature, MO composition, crysta!lo- corrosion inlubitur^ for :,ystents employing graphic direction, and ultrasonic fi,:luency either water or anti-frceze solutions for heat are reported. 7 he attenuation t ;stall transfer and storage, Alun• inum-mild:steelvelocity changes associated with the super- copper-sninless steel assemblies in electrical -onductivity of the samples are shown to be contact were used to simulate a inultimetallic oil depend..nt sample resistivity ratio systei;: which is most likely the type to be which varied from 4.3 ^r NB-9% MO to cntployed. Several inhibitors show promise for 6500 for Kure NB. The ultrasonic attenuation this application. data are analyzed in terms of the superconducting; :^nergy ga p term of the BCS theory. 24

Original page 30

t Effectiveness of corrosion un;ubiting solutions containing sodium c01111xninds for aluminum and mild steel sheets at room temperatures and elevated temperatures; variables include degree of chemical attack, corrosive characteristics, solution p11, length to first visual attack, weight loss, and trmherature effects; no figures and 6 tables incluue numeric data. 25

Original page 31

SUBJECT INDEX ADHESIVE BONDING: K75.101(4 NASACR-144312 AIR CONDITIONING: A76.31378 K75-10205 K75 . 10225 K75 . 10612 K75.10650 K75-10925 K75-11328 K76-11070 K76-11336 K76-11493 M-FS-22563 M-FS•23057 M-FS-23260 M-FS-23432 NASACR-142728 NASACR-144110 NASA-CR-1441 1 1 NASA-CR-144234 NASA-CR-144314 NAS,:-CR-149785 NASACR-149971 NASACR-149972 NASACR-149973 NASACR-149974 NASA-CR-149975 NASACR-149976 NASA CR-1 50006 NASACR-150032 NASACR -150176 ECONOMIC ANALYSIS: K75.10225 K75.12132 NASACR-149976 NASA-TM-X-73344 ELECTRICAL RESISTIVITY: K77-10207 ENERGY ABSORPTION FILMS: K75.10551 K75.10650 M-l-S-2342U ENERGY CONSERVATION: K75-10205 NASACR-120668 ENERGY CONVERSION: K75.10225 K75-10551 K75.10650 K75.10925 K75.11328 K75-11454 K70.10736 K76.11919 M•FS-21628 M-FS-22743 M-FS-22744 M-FS-23062 NI-FS-23195 M-FS-23403 NASA-TM-X-64924 NASA 4'ASE-MFS-23062-1 NASA-TM-X-64958 NASA-TM-X-62639 NASA-TM-X-64969 NASA-TM-X-72199 NASA-TM-X-70089 NASA-TN-D-8409 CALIBRATING: NASACR-144006 COATINGS: A75-24194 M-FS-14706 M-FS-22562 M-FS-23420 ENERGY POLICY: A75.14012 ENERGY REQUIREMENTS: NASACR-120668 NASACR -129012 ENERGY STORAGE: K74-11130 M-FS•22563 NASA -CASE -MFS•22562-1 M-FS-23260 NASACR-149928 NASACR-150032 NASA-TM-X-3509 NASA-TM-X-73355 DATA ACQUISITION: NASACR -130177 26 NASACASE-MFS-23051.1 ENERGY SOURCES: NASACR-129012 ENERGY TRANSFER: M-FS•21927 NASACASE-Ml-S-22743-1 ORIGMAL PAGE IS OF POOR (QUALITY

Original page 32

ENGIN!'S: M-FS-:3403 q()LAR ARRAYS K75.10164 K77.10207 FLYWIII LLS: NASA-CASE-MFS23051-1 M-FS-3138 NASA-CR-144312 FREON: NASA-CASE-MFS-21628.1 111-AT STORAGE: K74-11130 K76-11922 M-FS-23167 SOLAR CELLS: K75.10164 K75-11454 K76.12132 K77.10207 NASA-CASE•M FS-22744-1 M-FS-21328 NASA-CASE-M FS-23167.1 M-FS-23138 NASA-CR-144081 M-FS-23195 NASA-TM-X-64940 NASA-CASE-M FS-22458-1 I M AT TRANSFER: M-FS-21628 M-FS-22743 M-FS-22744 SOLAR COLLECTORS K75.10164 K75.10205 K75.10_225 NASA-TM-X-62639 K75.10551 LENSES: K76-1 1313 K76.11314 K75.10554 K75.10012 K75 . 1U650 NASA-TM-X-73333 K75-10925 NASA-TM-X-73392 K76-10736 K76-11313 MOLYBDENUM: NASA-TN-D-6828 K76-11922 MOTORS: M-FS-23062 M-I-S-21927 M-FS-22562 NASA-CASE-M FS-23062.1 M-FS-22743 PAINTS: M-FS-14706 M-FS-22744 M-FS-22943 M-FS-23057 MIOTOVOLTAIC CELLS: NASA-CASE-MFS-22458-1 M-FS-23167 RADIATION MEASURING INSTRUMENTS: K75.10554 M-i'S-23260 NI-FS-23272 M-FS-23349 NASA-CR-1440)6 M-FS-23420 NASA-C R-150064 M-FS-23428 RECORDING INSTRUMENTS: A75-14012 NASA-('R-144265 NASA-C R-149928 NASA -CR-150032 NASA-TM-X-3509 ROTATING BODIES: NASA -CASL-MFS-23051-1 NASA-TNI-X-60757 SATELLITE PO% LR TRANSMISSION TO EARTH: A77-10913 NASA-TM-X-73333 NASA-TM-X-73335 SOLAR LLL•CTRIC NASA-Cl 150146 PROPULSION: K75.11454 NASA-CR-I 50147 NASA-TM-X-73344 SOLAR ENERGY SATELLITE SOLAR ENERGY CONVERSION K76.12132 CONVERSION: K75.10205 K75-10225 K75-10551 NASA-CR-150146 K75.10650 NASA- R-150171 K75.10925 SATELLITE SOLAR POWER STATIONS: K76.12132 K75-11328 K75-11454 K76.10736 NASA-T!k1-X-73344 K76.11313 ORIGMAL PAGE 16 27 OF POOR QUALITY 1

Original page 33

SPACECRAFT 1'()WLR SOLAR LNERGY SUPPLIES: NASACASE-MFS-21628.2 CONVLRSION: M-FS-23428 (Concluded) M-FS-23432 SUN L I(_"I ll K75.10554 M-FS-23349 NASA-CASE•M FS-21628-2 K70-11313 NASACR !44110 NASA-CR-14411 I TfIERNIAL ENERGY: K74-11130 NASACR-149971 K75.10225 NASACR-149972 NASA-CASE•MFS-23167.1 NASA-CR•149973 NA SAC R-149974 N A SA C R-149975 NASA-C: R-149976 NASA-C R- 150000 NASA4- R-150147 NASA-CR-150148 NASACR.-150176 NASA-TM-X-64058 NASA-TM-X-64969 NASA-TM-X-70089 SOLAR LNERGY ABSORBLRS: K75-10164 K75-10650 M-FS-22743 M-FS-22744 M-FS-23349 WFS-23420 M-FS-23428 NASA-CASE-Ml-'S-22562-1 NASACASE-M FS-22743-1 NASACASL-MFS-22744-1 NASA-('R-15003 2 SOLAR HEATING: K75-10612 K75-10650 K75-11328 K76-11070 K76.11336 K76-1193.1 M-FS-21927 M-F S-22563 M-FS-23432 NASA-('R-144314 NASA-('R-149785 NASA-TM-X-53930 NASA-TM-X-64924 NASA-TM-X-73355 SOLAR RADIATION: K75-10554 NASA-CR-150064 NASA-('R-150177 NASA-TM-X-53925 SOLAR TEMPLRATURE: NASA-TM-X-53925 28 0 U.S. GOVERNMENT PRINTING OFFICE 1977 - 740-049/381 REGION NO. 4 •

Original page 34

APPROVAL SOLAR ENERGY BIBLIOGRAPHY Compiled by Stephen GM—gus The information in this report has been reviewed for security classification Review of any information concerning Department of' Defense or Atomic L-'nergy Commission programs has been made by the MSI-C Security Classification Officer. his report. in its entirety, has been determined to be unclassified. This document has also been reviewed and approved fur technical accuracy. C1711 I. SHI THIRD Director, Administration and Program Support