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Composite materials provide design flexibility in that fiber placement and orientation can be specified and a variety of material forms and manufacturing processes are available. It is possible, therefore, to “tailor” the structure to a high degree in order to meet specific design requirements in an optimum manner. The present project has been devoted to creating modeling and design analysis methodology for use in the tailoring process of aircraft structures. Emphasis has been given to creating bend-twist elastic coupling in high aspect ratio wings or other lifting surfaces. Analysis to design elastically tailored wings with bend-twist coupling one cross section at a time. This work appears in Appendix I. Tapered wings may be analyzed with the use of item (1) to discrete spanwise wing stations and with the loads known. All of our work has been devoted to preliminary design analysis. The objective is to give the designer guidance in establishing the structural configuration. Once a viable configuration is identified, “fine tuning” to save weight and cost can proceed with the aid of large scale numerical simulation and perhaps, in addition, optimization. Flow diagram for design analysis methodology for APR, How diagram for design analysis methodology for LR. Aeroelastic tailoring is the embodiment of directional stifiess into an aircrafi structural design to control aeroelastic deformation, static or dynamic, in such a fashion as to aflect the aerodynamic and structural pegormance of the aircrafi in a beneficial way.
Tags : high aspect ratio, analysis methodology, fiber placement, design flexibility, optimum manner, numerical simulation, aircraft structure, aircraft structures, present project, flow diagram, preliminary design, structural design, composite materials, manufacturing processes, embodiment
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