Large Deformation Behavior of Long Shallow Cylindrical Composite Panels

By National Aeronautics and Space Administration

An exact solution is presented for the large deformation response of a simply supported orthotropic cylindrical panel subjected to a uniform line load along a cylinder generator. The cross section of the cylinder is circular and deformations up to the fully snapped through position are investigated. The orthotropic axes are parallel to the generator and circumferential directions. The governing equations are derived using laminated plate theory, nonlinear strain-displacement relations, and applying variational principles. The response is investigated for the case of a panel loaded exactly at midspan and for a panel with the load offset from midspan. The mathematical formulation is one dimensional in the circumferential coordinate. Solutions are obtained in closed-form. An experimental apparatus was designed to load the panels. Experimental results of displacement controlled tests performed on graphite-epoxy curved panels are compared with analytical predictions. Carper, Douglas M. and Hyer, Michael W. and Johnson, Eric R. CYLINDRICAL SHELLS; DEFORMATION; GRAPHITE-EPOXY COMPOSITES; LAMINATES; MATHEMATICAL MODELS; ORTHOTROPIC CYLINDERS; PLATES (STRUCTURAL MEMBERS); COMPOSITE STRUCTURES; CURVED PANELS; DISPLACEMENT; NONLINEARITY; ORTHOTROPIC SHELLS; PLATE THEORY; VARIATIONAL PRINCIPLES...

• Format: Paperback
• Language: English
• ISBN: 1731541384
• ISBN13: 9781731541383
• Release Date: January 1
• Publisher: Independently Published
• Length: 174 Pages
• Weight: 0.92 lbs.
• Dimensions: 0.4" x 8.5" x 11.0"