Advanced filamentary composite materials are playing an increasing role in the aerospace industry. Before curing, their form as flexible tape or wide goods provides manufacturing advantages over metals resulting in cost savings in many cases. In addition, the physical characteristics of stiff fibers in a soft matrix can provide superior fracture and fatigue properties when combined with proper detail design techniques. Several methods of laminate optimization for strength and stiffness requirements have been developed. Some of these have been extended to include plate stability and, in some cases, sandwich and stiffened plate construction. Computer programs have also been developed for the design of more complex composite structures such as stiffened cylinders, wing box sections, and lifting surfaces including aeroelastic requirements. These procedures are discussed along with their limitations and utility considering current design philosophy.

  • Supplemental Notes:
    • Presented at the ASME AMD Meeting, Nov. 17-21, 1974 held in New York, N.Y.
  • Corporate Authors:

    American Society of Mechanical Engineers

    Two Park Avenue
    New York, NY  United States  10016-5990
  • Authors:
    • McCullers, L A
  • Publication Date: 1974

Media Info

  • Features: References;
  • Pagination: p. 119-133
  • Serial:
    • Volume: 7

Subject/Index Terms

Filing Info

  • Accession Number: 00072789
  • Record Type: Publication
  • Source Agency: Engineering Index
  • Files: TRIS
  • Created Date: Jan 16 1976 12:00AM