The application of composite materials to aircraft manufacture is described, with reference to design and analysis tools for predicting internal loads and deflections for aeroelastic, tailored lifting surfaces. Composite materials development for aircraft applications has been designed to achieve weight savings in weight-critical regions. Toward this end, graphite/epoxy composites are being used as structural materials in the form of cross-plied fiber-reinforced laminates for conventional, monolithic wing/empennage skins and substructures or as face sheets on honeycomb-type structures. All metal components have been replaced by composite structures on such aircraft as the B-1, the F-18, and the AV-8B. Weight and cost savings have been demonstrated for the B-1 aircraft. The next-generation aircraft will incorporate composites in a significantly larger proportion of the airframe structure to exploit more fully all advantageous characteristics of advanced composite structures (strength, stiffness, tailorability, weight, and fabrication cost savings). Aeroelastic tailoring and the use of integral, advanced composite structures are detailed in terms of weight and cost savings and structural integrity improvements.

  • Availability:
  • Supplemental Notes:
    • Presented at SAE Congress and Exposition, Detroit, 26 February-2 March 1979. See also HS-029 220U.
  • Corporate Authors:

    Society of Automotive Engineers (SAE)

    400 Commonwealth Drive
    Warrendale, PA  United States  15096
  • Authors:
    • Lackman, L M
    • Price, M A
    • Matoi, T T
  • Publication Date: 1979

Media Info

Subject/Index Terms

Filing Info

  • Accession Number: 00386665
  • Record Type: Publication
  • Source Agency: National Highway Traffic Safety Administration
  • Report/Paper Numbers: SAE 790146, HS-029 221U
  • Files: HSL, USDOT
  • Created Date: Jun 28 1984 12:00AM