PANDA2: Program for Minimum Weight Design of Stiffened, Composite, Locally Buckled Panels
Abstract
PANDA2 Program finds minimum weight designs of laminated composite flat or curved cylindrical panels or cylindrical shells with stiffeners in one or two orthogonal directions. The panels or shells can be loaded by as many as five combinations of in plane loads and normal pressure. The axial load can vary across the panel. The presence of overall (bowing) imperfections as well as local imperfections in the form of the local buckling mode are included. Constraints on the design include crippling, local and general buckling, maximum tensile or compressive stress along the fibers and normal to the fibers in each lamina, and maximum in place shear stress in each lamina. Local and general buckling loads are calculated with use of either closed-form expressions or with use of discretized models of panel cross sections. An analysis branch exists in which local post buckling of the panel skin is accounted for.
Document Details
- Document Type
- Technical Report
- Publication Date
- Sep 01, 1986
- Accession Number
- ADA182109
Entities
People
- David Bushnell
Organizations
- Lockheed Martin Missiles and Space