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  • 1980-1984  (5)
  • 1
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    Unknown
    Study of utilization of advanced composites in fuselage structures of large transports (1984)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The effort required by the transport aircraft manufacturers to support the introduction of advanced composite materials into the fuselage structure of future commercial and military transport aircraft is investigated. Technology issues, potential benefits to military life cycle costs and commercial operating costs, and development plans are examined. The most urgent technology issues defined are impact dynamics, acoustic transmission, pressure containment and damage tolerance, post-buckling, cutouts, and joints and splices. A technology demonstration program is defined and a rough cost and schedule identified. The fabrication and test of a full-scale fuselage barrel section is presented. Commercial and military benefits are identified. Fuselage structure weight savings from use of advanced composites are 16.4 percent for the commercial and 21.8 percent for the military. For the all-composite airplanes the savings are 26 percent and 29 percent, respectively. Commercial/operating costs are reduced by 5 percent for the all-composite airplane and military life cycle costs by 10 percent.
    Keywords: COMPOSITE MATERIALS
    Type: NASA-CR-172404 , NAS 1.26:172404 , LR-30786
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 2
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    Advanced composite vertical fin for L-1011 aircraft (1984)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The structural box of the L-1011 vertical fin was redesigned using advanced composite materials. The box was fabricated and ground tested to verify the structural integrity. This report summarizes the complete program starting with the design and analysis and proceeds through the process development ancillary test program production readiness verification testing, fabrication of the full-scale fin boxes and the full-scale ground testing. The program showed that advanced composites can economically and effectively be used in the design and fabrication of medium primary structures for commercial aircraft. Static-strength variability was demonstrated to be comparable to metal structures and the long term durability of advanced composite components was demonstrated.
    Keywords: COMPOSITE MATERIALS
    Type: NASA-CR-3816 , NAS 1.26:3816
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    Advanced manufacturing development of a composite empennage component for L-1011 aircraft. Phase 2: Design and analysis (1981)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The composite fin design consists of two one-piece cocured covers, two one-piece cocured spars and eleven ribs. The lower ribs are truss ribs with graphite/epoxy caps and aluminum truss members. The upper three ribs are a sandwich design with graphite/epoxy face sheets and a syntactic epoxy core. The design achieves a 27% weight saving compared to the metal box. The fastener count has been reduced from over 40,000 to less than 7000. The structural integrity of the composite fin was verified by analysis and test. The static, fail-safe and flutter analyses were completed. An extensive test program has established the material behavior under a range of conditions and critical subcomponents were tested to verify the structural concepts.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-CR-165634 , NAS 1.26:165634 , LR-29723
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    Advanced manufacturing development of a composite empennage component for L-1011 aircraft. Phase 4: Full scale ground test (1982)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The ground tests conducted on the advanced composite vertical fin (ACVF) program are described. The design and fabrication of the test fixture and the transition structure, static test of Ground Test Article (GTA) No. 1, rework of GTA No. 2, and static, damage tolerance, fail-safe and residual strength tests of GTA No. 2 are described.
    Keywords: COMPOSITE MATERIALS
    Type: NASA-CR-166015 , NAS 1.26:166015 , LR-30357
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 5
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    Structurally-continuous composite corners (1980)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: Flat composite materials are cut at certain angles to form boxes with corners as thick as walls. Patterns produce uniform corners, and cuts are structured so that shear loads are transferred from ply to ply instead of across one surface.
    Keywords: FABRICATION TECHNOLOGY
    Type: LAR-11942 , NASA Tech Briefs (ISSN 0145-319X); 4; 4; P. 578
    Format: text
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    NASA TECHNICAL REPORTS
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