Accession Number:

ADA301714

Title:

Minimum-Mass Design of Filamentary Composite Panels Under Combined Loads: Design Procedure Based on a Rigorous Buckling Analysis.

Descriptive Note:

Technical note,

Corporate Author:

NATIONAL AERONAUTICS AND SPACE ADMINISTRATION HAMPTON VA LANGLEY RESEARCH CEN TER

Report Date:

1977-07-01

Pagination or Media Count:

42.0

Abstract:

A procedure is presented for designing uniaxially stiffened panels made of composite material and subjected to combined inplane loads. The procedure uses a rigorous buckling analysis and nonlinear mathematical programing techniques. Design studies carried out with the procedure consider hat-stiffened and corrugated panels made of graphite-epoxy material. Combined longitudinal compression and shear and combined longitudinal and transverse compression are the loadings used in the studies. The capability to tailor the buckling response of a panel i.e., design a panel so that it will have specified buckling loads at various buckling wavelengths is also explored. Finally, the adequacy of another, simpler, analysis-design procedure is examined. The report demonstrates that a panel design procedure with a high-quality buckling analysis and with complete generality of constraints is practical. Such a procedure can be used to avoid failure from complex buckling modes and to determine mass and proportions of panels for multiple design load conditions and constraints. MM

Subject Categories:

  • Laminates and Composite Materials
  • Mechanics

Distribution Statement:

APPROVED FOR PUBLIC RELEASE