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穿越地球大气层的高速飞行器同时受到气动加热载荷和机械载荷的作用,其结构设计必须满足热和机械设计要求。本文采用权函数法,同时考虑了机械性能和导热性能要求,以结构质量最轻为目标函数,分别对结构型式和结构参数进行了优化设计。首先,对应不同机械载荷和温度载荷要求的权重之比,进行多目标拓扑优化,获得合理的结构型式;然后,对应拓扑优化得到的不同结构型式,进行结构参数化建模,用遗传算法进行结构参数优化,找出最优解;最后,通过加筋板的实际算例,验证了该方法的可行性和有效性。
High-speed aircraft that cross the Earth’s atmosphere are subjected to both aerodynamic heating loads and mechanical loads, and their structural design must meet thermal and mechanical design requirements. In this paper, the weight function method is adopted, taking into account the requirements of mechanical properties and thermal conductivity, the structure type and structural parameters are optimally designed with the lightest structure as the objective function. Firstly, multi-objective topology optimization is carried out according to the ratio of the weights of different mechanical loads and temperature loads, and a reasonable structure type is obtained. Then, corresponding to the different structure types obtained by the topology optimization, the structure parameterization modeling is carried out, and the genetic algorithm Parameter optimization to find the optimal solution. Finally, the practical examples of stiffened plates are used to verify the feasibility and effectiveness of the method.