高超声速飞行器气动布局总体性能优化设计研究

Research on aerodynamic configuration optimization of integral performance for hypersonic cruise vehicle

总体设计是吸气式高超声速巡航飞行器的关键技术之一。为提高高超声速飞行器的设计水平,获得一个总体性能较优的布局构型,对乘波布局的高超声速飞行器进行了总体优化设计研究。采用多目标遗传算法,以飞行器外形参数作为设计变量,考虑了巡航状态下的气动力、热、雷达散射截面、机体/推进一体化、机身容积、配平特性、静稳定性和机动性等指标。优化设计得到了Pareto最优前沿面,获得了很多总体性能优于基本构型的最优个体。根据设计指标,给出了一个推荐方案作为进一步研究的参考构型,并对它的气动特性进行了风洞实验验证,证明了本文优化设计方法的可行性。

Integral design is the most important key technique of Air-breathing Hypersonic Cruise Vehicle （HCV）. To improve the design level and get better integral performances of HCV, this paper researches the integral optimization design method of waverider hypersonic cruise vehicle. In the optimization design, MultiObjective Genetic Algorithms （MOGA） is selected as the optimization algorithm, and the shape parameters of aircraft are as design variables. Some performances, such as aerodynamics, aeroheating, radar cross seetion （RCS）, airframe/scramjet integration, and volume of airframe, trimmed characteristic, static stability and maneuverability at cruise stage are selected as the objectives. When the optimization process finishes, the Pareto front side is got, in which many Pareto solutions whose integral performances are more excellent than basic configuration are found. According to the design idea, we choose a Pareto solution from the Pareto front side as the recommended shape configuration for further research. To validate the aerodynamics of recommended HCV, wind tunnel test is done. And the comparison results show that the optimization design is successful.