Abstract
The optimal design of a curved, composite fuselage frame under a static crush load is presented. The objective is to maximize the absorbed energy subject to a constraint on the maximum load, and thus improve the crashworthy response of the frame. The finite element analysis is based on a Vlasov-type curved bar theory extended to include laminated composite wall construction, and a selective and progressive ply-by-ply material degradation model for graphite-epoxy laminates. Results from the progressive failure analysis are in reasonable agreement with experimental data, A genetic algorithm is used to design the stacking sequence and cross-sectional dimensions, since the design variables are limited to discrete values and the objective function and constraint function are nonlinear, non-smooth functions of the design variables. Examples are presented which show a significant theoretical increase in energy absorption for thin-walled, I-section, graphite-epoxy frames. The combined analyses for progressive failure response and design are considered appropriate for preliminary design. Language: en
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