高超声速飞行器结构热气动弹性优化设计

基于高超声速飞行器X-43外形尺寸,构建含有隔热层的全机结构有限元模型。根据分层求解思路,考虑了气动热载荷作用下结构温度的稳态特性,忽略气动热对气动力和结构弹性力的弱耦合效应。使用三阶活塞理论对其进行频域内气动力计算,采用参考焓法求得模型表面的热流密度,进而计算出经过隔热层作用后,蒙皮表面的温度分布以及相应的热应力;在对结构的刚度矩阵进行修正后,采用p-k法迭代求解其临界颤振速度。以复合材料铺层角度和铺层顺序为设计变量,在全机结构、重量保持不变的情况下,对其进行以临界颤振速度为优化目标的气动弹性优化设计,使结构的颤振特性有了较大的改善。

Aerothermal-Aeroelastic Optimization Design on Hypersonic Vehicle

On the base of the shape of the unpiloted hypersonic vehicle X-43,hypersonic full-aircraft model was built with aerodynamic heating effect. Hierarchical solution process was used to dealing with aerothermal aeroelastic coupling problem neglecting the weak coupling effect between aeroelasticity heat load and aerodynamic load or elastic load. Compute hypersonic aerodynamic heating and the steady temperature field. The stress stiffness matrix under this temperature field was developed and the flutter equations were solved by p-k method finally. This paper realizes the aerothermal-aeroelastic optimization design of the hypersonic vehicle without changing the weight of the structure weight. The skin layer angle is the design variable and the flutter velocity are the optimization objective. The result shows that the composite laminate angle has a great impact on the nonlinear speed.