Accession Number:

ADA305549

Title:

Minimum-Mass Design of Filamentary Composite Panels under Combined Loads: Design Procedure Based on Simplified Buckling Equations.

Descriptive Note:

Technical note,

Corporate Author:

NATIONAL AERONAUTICS AND SPACE ADMINISTRATION HAMPTON VA LANGLEY RESEARCH CEN TER

Personal Author(s):

Report Date:

1976-10-01

Pagination or Media Count:

54.0

Abstract:

An analytical procedure is presented for designing hat-stiffened and corrugated panels made of composite material and subjected to longitudinal in the direction of the stiffeners compression and shear loadings. The procedure is based on nonlinear mathematical programing techniques and a simplified set of buckling equations. Design requirements considered are buckling, strength, and extensional and shear stiffness. Studies show the effects of specified thickness, variation of cross-section dimensions, stiffness requirements, local-buckling boundary conditions, and the effect of combined compression and shear loadings. AN

Subject Categories:

  • Laminates and Composite Materials
  • Mechanics

Distribution Statement:

APPROVED FOR PUBLIC RELEASE