高超声速飞行器气动/隐身优化设计方法

针对高超声速飞行器气动布局设计中气动设计与隐身设计矛盾的问题，采用高精度气动和隐身计算方法，建立了基于直接全局优化算法、二次曲线参数化方法和Kriging代理模型的多学科优化设计平台，并对典型高超声速布局升力体外形开展气动/隐身一体化优化设计研究。结果表明：升力体布局典型状态下升阻比由3.13提高到3.69，考虑垂直极化和水平极化状态，俯仰±30°的雷达散热截面（RCS）均值下降60%以上，表明该平台具有良好的寻优能力，风洞试验结果验证了优化算法的可行性；高超声速飞行器的机身和翼/舵等部件具有显著的绕射特性，物理光学法等高频算法不能准确捕捉前后缘绕射，应当采用矩量法计算其RCS特性；高超声速飞行器的垂直极化和水平极化的RCS特性差异巨大，在设计中应当予以考虑。

Aerodynamic and Stealthy Optimization Design Method of Hypersonic Vehicle

To deal with the diametrically different requirements between the aerodynamic and stealth design of hypersonic vehicle, high fidelity methods are used to evaluate the aerodynamic performance and stealth characteristics of hypersonic vehicle, and a multi-objective optimization platform is established based on the deterministic global optimization algorithm, the conic curve parameterized method and Kriging surrogate model. The aerodynamic and stealthy performance of typical lift body configuration is optimized. The results show that the lift to drag ratio increases from 3.13 to 3.69 in the typical condition, radar cross section(RCS) decreases more than 60% in the key azimuth (ranging from -30° to 30° in pitch) considering the horizontal polarization and vertical polarization. The tunnel test verified the feasibility of the optimization algorithm. The fuselage and wing/rudder of hypersonic vehicle have strong diffraction effect, the high-frequency method such as physical optics couldn′t compute the diffraction characteristics, which should be computed in method of moment. The horizontal polarization characteristics differ greatly from the vertical polarization characteristics，which should be paid special attention in the design.