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结构优化设计剪裁是减轻结构质量、提高设计品质和产品竞争力的重要手段。以某无人机复合材料机翼为例,采用复合材料结构优化设计系统COMPASS进行满应力设计,给出满足结构静强度约束条件(应力、应变)的结构件总体尺寸分布;在初步设计尺寸基础上,进行以结构质量最小为目标,以复合材料铺层厚度、铺层角度为设计变量的数学规划法优化设计,最终确定满足翼尖变形、自振频率、颤振速度、操纵效率等约束条件的结构件尺寸分布。结果表明,通过复合材料结构优化设计剪裁实现了对大展弦比复合材料机翼结构的静力、动力和气动弹性综合优化设计,有效缩短研制周期,提高了结构效率。
Structural design optimization is to reduce the structure of the quality of cut, improve design quality and product competitiveness an important means. Taking a UAV composite wing as an example, the full-strength design of composite structural optimization design system (COMPASS) is used to design the overall size distribution of structural members that satisfy the structural static strength constraints (stress and strain). Based on the preliminary design dimension , The optimal design of the mathematical programming method which takes the minimum structural mass as the target, the composite ply thickness and the ply angle as the design variables is finally determined to meet the constraints of wing tip deformation, natural frequency, flutter speed and steering efficiency The structure of the size distribution. The results show that the optimal design of the composite structure with large aspect ratio can be achieved by optimizing the design of the composite structure. The optimization of the static, dynamic and aeroelasticity of the composite wing structure with large aspect ratio is achieved, which can effectively shorten the development cycle and improve the structural efficiency.