面向总体性能的高速飞行器布局优化

Hypersonic vehicle shape optimal design based on overall performance

飞行器气动布局的选型和优化技术在总体设计中处于关键地位,在临近空间飞行的飞行器对升阻比和操控性能都提出了更高的要求。翼身组合的升力体外形由于兼顾内部装填以及升阻特性成为了目前高速飞行器主要的设计方向。以一类具有普适性的面对称升力体外形为基础,采用相关性分析手段提取出飞行器的关键几何参数,挖掘出几何参数对所关心的总体性能指标的影响度大小,并建立起基于CFD方法的气动布局优化平台,以总体性能指标为约束,优化出高升阻比外形,通过风洞试验验证了优化设计方法的有效性,为高速飞行器的气动布局工程化设计提供了有效的技术手段。

Aerodynamic configuration design and optimization are vital to overall design of aircraft. High- er requirements of lift-drag ratio and control performance are put forward for near space vehicles. The lifting- body shape of the wing-body combination has become the main design direction of the hypersonic vehicle due to its internal loading and lift-drag characteristics. According to a class of universal symmetry lifting-body con- figuration, the key geometry parameters of vehicle were extracted using interrelation analysis method. The effect of geometry parameters on concerned overall performance was dug out. Aerodynamic shape optimization platform was established based on CFD method. With several key overall performance constraints, high lift- drag ratio shape was designed and optimized. The effectiveness of optimal design has been verified by wind tunnel test, which will provide an effective technical means for rapid engineering aerodynamic shape design of hypersonic vehicle.