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  • SPACE VEHICLES  (5)
  • PHYSICAL SCIENCES  (1)
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  • 1
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    Receiver For Solar Air Turbine (1985)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: Solar receiver heats air to temperature high enough to drive gas turbine. Receiver has thermal output of about 70 kilowatts. Pointing downward at focal position of solar reflector, proposed receiver accepts intense concentrated sunlight. Although temperatures in receiver may rise to 1,500 degrees F (816 degrees C) or more, calculations show receiver loses less than 10 percent of insolation by convection through aperture. Receiver designed for 30-year life without scheduled maintenance or replacement.
    Keywords: PHYSICAL SCIENCES
    Type: NPO-15124 , NASA Tech Briefs (ISSN 0145-319X); 8; 3; P. 343
    Format: text
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    NASA TECHNICAL REPORTS
  • 2
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    Space vehicle integrated thermal protection/structural/meteoroid protection system, volume 2 (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: For abstract, see .
    Keywords: SPACE VEHICLES
    Type: NASA-CR-121104 , D180-15172-2
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    Space vehicle integrated thermal protection/structural/meteoroid protection system, volume 1 (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A program was conducted to determine the merit of a combined structure/thermal meteoroid protection system for a cryogenic vehicle propulsion module. Structural concepts were evaluated to identify least weight designs. Thermal analyses determined optimum tank arrangements and insulation materials. Meteoroid penetration experiments provided data for design of protection systems. Preliminary designs were made and compared on the basis of payload capability. Thermal performance tests demonstrated heat transfer rates typical for the selected design. Meteoroid impact tests verified the protection characteristics. A mockup was made to demonstrate protection system installation. The best design found combined multilayer insulation with a truss structure vehicle body. The multilayer served as the thermal/meteoroid protection system.
    Keywords: SPACE VEHICLES
    Type: NASA-CR-121103 , D180-15172-1
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    Lightweight evacuated multilayer insulation systems for the space shuttle vehicle (1973)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: The elements in the evacuated multilayer insulation system were investigated, and the major weight contributors for optimization selected. Outgassing tests were conducted on candidate vacuum jacket materials and experiments were conducted to determine the vacuum and structural integrity of selected vacuum jacket configurations. A nondestructive proof test method, applicable to externally pressurized shells, was validated on this program.
    Keywords: SPACE VEHICLES
    Type: NASA-CR-121105 , D180-15171
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 5
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    Evaluation of a metal shear web selectively reinforced with filamentary composites for space shuttle application. Phase 1 summary report: Shear web design development (1972)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: An advanced composite shear web design concept was developed for the Space Shuttle orbiter main engine thrust beam structure. Various web concepts were synthesized by a computer-aided adaptive random search procedure. A practical concept is identified having a titanium-clad + or - 45 deg boron/epoxy web plate with vertical boron/epoxy reinforced aluminum stiffeners. The boron-epoxy laminate contributes to the strength and stiffness efficiency of the basic web section. The titanium-cladding functions to protect the polymeric laminate parts from damaging environments and is chem-milled to provide reinforcement in selected areas. Detailed design drawings are presented for both boron/epoxy reinforced and all-metal shear webs. The weight saving offered is 24% relative to all-metal construction at an attractive cost per pound of weight saved, based on the detailed designs. Small scale element tests substantiate the boron/epoxy reinforced design details in critical areas. The results show that the titanium-cladding reliably reinforces the web laminate in critical edge load transfer and stiffener fastener hole areas.
    Keywords: SPACE VEHICLES
    Type: NASA-CR-132320 , D180-15104
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 6
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    Evaluation of a metal shear web selectively reinforced with filamentary composites for space shuttle application. Phase 2: summary report: Shear web component fabrication (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The fabrication of two shear web test elements and three large scale shear web test components are reported. In addition, the fabrication of test fixtures for the elements and components is described. The center-loaded beam test fixtures were configured to have a test side and a dummy or permanent side. The test fixtures were fabricated from standard extruded aluminum sections and plates and were designed to be reuseable.
    Keywords: SPACE VEHICLES
    Type: NASA-CR-132321 , D180-15323
    Format: application/pdf
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    NASA TECHNICAL REPORTS
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