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  • 1
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    Vacuum jacketed composite propulsion feedlines for cryogenic launch and space vehicles. Volume 2: Appendixes (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: For abstract, see N74-18505.
    Keywords: SPACE VEHICLES
    Type: NASA-CR-134554
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 2
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    Lightweight thermally efficient composite feedlines for the space tug cryogenic propulsion system (1975)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Six liquid hydrogen feedline design concepts were developed for the cryogenic space tug. The feedlines include composite and all-metal vacuum jacketed and nonvacuum jacketed concepts, and incorporate the latest technological developments in the areas of thermally efficient vacuum jacket end closures and standoffs, radiation shields in the vacuum annulus, thermal coatings, and lightweight dissimilar metal flanged joints. The feedline design concepts are evaluated on the basis of thermal performance, weight, cost, reliability, and reusability. Design concepts were proved in a subscale test program. Detail design was completed on the most promising composite feedline concept and an all-metal feedline. Three full scale curved composite feedlines and one all-metal feedline assembly were fabricated and subjected to a test program representative of flight hardware qualification. The test results show that composite feedline technology is fully developed. Composite feedlines are ready for space vehicle application and offer significant reduction in weights over the conventional all-metal feedlines presently used.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-CR-134870 , REPT-04236
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    Vacuum jacketed composite propulsion feedlines for cryogenic launch and space vehicles, volume 1 (1974)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Thin metallic liners that provide leak-free service in cryogenic propulsion systems are overwrapped with a glass-fiber composite that provides strength and protection from handling damage. The resultant tube is lightweight, strong, and has a low thermal flux. The inside commodity flow line and the outside vacuum jacket were fabricated using this method. Several types of vacuum jackets were fabricated and tested at operating temperatures from 294 to 21 K (+70 to minus 423 F) and operating pressure up to 69 N/cm2 (100 psi). The primary objective of the program was to develop vacuum jacket concepts, using previously developed concepts for the inner line. All major program objectives were met resulting in a design concept that is adaptable to a wide range of aerospace vehicle requirements. Major items of development included convolution of thin metallic sections up to 46 cm (18 in.) in diameter, design and fabrication of an extremely lightweight tension membrane concept for the vacuum jacket, and analytical tools that predict the failure mode and levels.
    Keywords: SPACE VEHICLES
    Type: NASA-CR-134550
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    Low thermal flux glass-fiber tubing for cryogenic service (1977)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: This paper describes analytical techniques, fabrication development, and test results for composite tubing that has many applications in aerospace and commercial cryogenic installations. Metal liner fabrication is discussed in detail with attention given to resistance-welded liners, fusion-welded liners, chem-milled tubing liners, joining tube liners and end fittings, heat treatment and leak checks. Composite overwrapping, a second method of tubing fabrication, is also discussed. Test programs and analytical correlation are considered along with composite tubing advantages such as minimum weight, thermal efficiency and safety and reliability.
    Keywords: COMPOSITE MATERIALS
    Type: International Cryogenic Materials Conference; Jul 22, 1975 - Jul 25, 1975; Kingston, Ontario; Canada
    Format: text
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    NASA TECHNICAL REPORTS
  • 5
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    Lightweight thermally efficient composite feedlines, preliminary design and evaluation (1974)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Six liquid hydrogen feedline design concepts were developed for the cryogenic space tug. The feedlines include composite and all-metal vacuum jacketed and non-vacuum jacketed concepts, and incorporate the latest technology developments in the areas of thermally efficient vacuum jacket end closures and standoffs, radiation shields in the vacuum annulus, thermal coatings, and lightweight dissimilar metal flanged joints. The feedline design concepts were evaluated on the basis of thermal performance, weight, cost, reliability, and reusability. It is shown that composite tubing provides improved thermal performance and reduced weight for each design concept considered. Approximately 12 kg (26 lb.) can be saved by the use of composite tubing for the LH2 feedline and the other propulsion lines in the space tug.
    Keywords: SPACE VEHICLES
    Type: NASA-CR-134631
    Format: application/pdf
    Location Call Number Expected Availability
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    NASA TECHNICAL REPORTS
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