论文部分内容阅读
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。
The dynamic aerodynamic model of hypersonic rudder surfaces based on fluid-structure interaction under laser irradiation is established. The governing equations of fluid are three-dimensional Reynolds-averaged Navier-Stokes equations. The viscoelastic and convective terms are calculated using the central format and the AUSM + up format Spatial discretization, Gauss-Seidel implicit propulsion method is used for time propulsion, and Menter SST model is used for solving turbulent viscosity coefficient. The model was verified by using the von Karman Institute’s superb wind tunnel experiment results to predict the thermal effects of laser irradiation on the super-rudder surface. The results show that the aerodynamic / thermal calculation model is in good agreement with the experimental data and can accurately simulate the thermal parameters of the hypersonic vehicle. According to the model extrapolation results, laser heating at higher power of the aircraft surface at lower power may lead to material elastic modulus Greatly reduced, followed by bending divergence and fracture, superb aircraft may be the result of aerodynamic instability and crashed.