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  • 1
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    Low concentration ratio solar array structural configuration (1984)
    In:  CASI
    Details
    Publication Date: 2006-04-03
    Description: The design and structural properties of a low concentration ratio solar array are discussed. The assembled module consists of six interconnected containers which are compactly stowed in a volume of 3.24 m(3) for delivery to orbit by the shuttle. The containers deploy in accordian fashion into a rectangular area of 19.4 x 68 meters and can be attached to the user spacecraft along the longitudinal centerline of the end container housing. Five rotary incremental actuators requiring about 8 watts each will execute the 180-degree rotation at each joint. Deployable masts (three per side) are used to extend endcaps from the housing in both directions. Each direction is extended by three masts requiring about 780 watts for about 27 minutes. Concentrator elements are extended by the endcaps and are supported by cable systems that are connected between the housings and endcaps. These power generating elements contain reflector panels which concentrate light onto the solar panels consisting of an aluminum radiator with solar cells positioned within the element base formed by the reflectors. A flat wire harness collects the power output of individual elements for transfer to the module container housing harnesses.
    Keywords: ENERGY PRODUCTION AND CONVERSION
    Type: NASA. Langley Research Center STEP Expt. Requirements; p 185-198
    Format: text
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    NASA TECHNICAL REPORTS
  • 2
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    Low concentration ratio solar array for low Earth orbit multi-100kW application. Volume 2: Drawings (1982)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A preliminary design effort directed toward a low concentration ratio photovoltaic array system based on 1984 technology and capable of delivering multi-hundred kilowatts (300 kW to 100 kW range) in low Earth orbit. The array system consists of two or more array modules each capable of delivering between 113 kW to 175 kW using silicon solar cells or gallium arsenide solar cells, respectively. The array module deployed area is 1320 square meters and consists of 4356 pyramidal concentrator elements. The module, when stowed in the Space Shuttle's payload bay, has a stowage volume of a cube with 3.24 meters on a side. The concentrator elements are sized for a geometric concentration ratio (GCR) of six with an aperture area of 0.5 meters x 0.5 meters. Drawings for the preliminary design configuration and for the test hardware that was fabricated for design evaluation and test are provided.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-CR-170870 , NAS 1.26:170870 , SSD-83-0075-2
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    Design of large, low-concentration-ratio solar arrays for low earth orbit applications (1982)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: IECEC ''82; Seventeenth Intersociety Energy Conversion Engineering Conference; Aug 08, 1982 - Aug 12, 1982; Los Angeles, CA
    Format: text
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    NASA TECHNICAL REPORTS
  • 4
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    Low concentration ratio solar array for low Earth orbit multi-100 kW application (1982)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: An ongoing preliminary design effort directed toward a low-concentration-ratio photovoltaic array system based on 1984 technology and capable of delivering multi-hundred kilowatts (300 kW to 1000 kW range) in low earth orbit is described. The array system consists of two or more array modules each capable of delivering between 80 kW to 172 kW using silicon solar cells or gallium arsenide solar cells respectively. The array module deployed area is 1320 square meters and consists of 4356 pryamidal concentrator elements. The module, when stowed in the Space Shuttle's payload bay, has a stowage volume of a cube with 3.24 meters on a side. The concentrator elements are sized for a geometric concentration ratio (GCR) of six with an aperture area of 0.5 meters x 0.5 meters. The structural analysis and design trades leading to the baseline design are discussed. The configuration, as well as optical, thermal and electrical performance analyses that support the design and overall performance estimates for the array are described.
    Keywords: ENERGY PRODUCTION AND CONVERSION
    Type: NASA-CR-170729 , NAS 1.26:170729 , SSD82-0172
    Format: application/pdf
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    NASA TECHNICAL REPORTS
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