采用正交试验设计方法生成初始数据库,建立二次多项式响应面近似模型,以最大巡航距离为设计目标,机体/推进一体化外形参数和巡航弹道参数为设计变量,对高超声速飞行器进行了多约束多学科的并行子空间优化设计.优化设计获得了多学科融合条件下的最优化外形和弹道参数,可作为飞行器进一步详细设计的参考方案. Orthogonal experimental design method was used to generate the initial database, the quadratic polynomial response surface approximate model was established, the maximum cruise distance was taken as the design target, the body / propulsion integrated shape parameter and the cruise trajectory parameter were the design variables, and the hypersonic vehicle was multi-constrained Multidisciplinary parallel subspace optimization design Optimized design obtains the optimal shape and ballistic parameters under multidisciplinary integration conditions and can be used as a reference scheme for further detailed design of the aircraft.