建立了基于流固耦合的高超声速飞行器舵面结构在激光辐照下静气动弹性模型, 流体控制方程为三维雷诺平均N-S方程, 分别采用了中心格式和AUSM+up格式对粘性项和对流项进行空间离散, 时间推进采用了高斯-塞德尔隐式推进方法, 湍流粘性系数求解使用Menter SST模型。利用冯·卡门研究所高超风洞实验结果对模型进行了校核, 预估了激光辐照对高超舵面的热力影响。结果表明, 气动力/热计算模型与实验数据符合较好, 能够准确模拟高超飞行器的热力参数, 根据模型外推结果, 激光在较低功率下加热高超飞行器舵面可能导致舵面材料弹性模量大大降低, 继而发生弯曲发散而折断, 高超飞行器可能因此发生气动失稳而坠毁。

A static aero elastic model of hypersonic aircraft under laser irradiation was built based on computational fluid dynamics (CFD) and computational structural dynamics coupling numerical computational methodology. The flow was governed by 3-D Reynolds averaged Navier-Stokes equations. To split the viscosity flux and the convective flux of the NS equations, the second order central scheme and the AUSM+up scheme were adopted respectively. With the implicit Gauss-Seidel scheme, the code was advanced in time. The Menter SST turbulence model was used for turbulence simulations. The model was proofread with the experiment data from von Karman Institute hypersonic wind tunnel. Hypersonic aircraft wing under laser irradiation was simulated with this model. The results indicated that the energy addition could reduce the Young’s modulus of hypersonic rudder. Hypersonic aircraft may prang due to the destroy of the rudder.