DESIGN-OPTIMIZATION OF A CURVED LAYERED COMPOSITE PANEL USING EFFICIENT LAMINATE PARAMETERIZATION

摘要

Layered composites have proven essential for the successful design of high-performance spacernstructures. The aviation industry are increasingly using more and more layered compositesrnwithin commercial aircraft, replacing traditional aluminum designs, to achieve weight savings.rnWhen optimizing layered composite structures it is desirable to find design solutions that satisfyrnglobal requirements early in the design phases. Particularly because of the number of designrnvariables associated with composite layups once models become more detailed are complex:rnmaterial selection, layer orientation and thickness for each ply for example.rnIn this paper, part of an aircraft door surround model is optimized with respect to the objectivesrnand constraints typical for this type of component. Related load-response calculations, failurernand buckling reserve factor analyses are made. The design process is built around optimizationrnfeatures offered by HyperStudy [1] - a solver-neutral design optimization and stochastic studyrnsoftware - along with ESAComp [2] – a software for design and analysis of composites -rnapplying an efficient laminate layup parameterization approach based on sub-laminates tornsupport manufacturing-oriented design.rnDifferent parameterization concepts are evaluated. Both numerical results and the performancernof the optimized structures are reported and compared with an aluminum baseline design.