乘波体是高超声速飞行器的主流构型,若将其设计成可变体,能有效拓展飞行包线,确保全局的稳定性能.针对可变形乘波体综合设计方法进行研究,首先基于给定的基准乘波体外形,依据高超声速空气动力学理论和瑞利流公式估算出气动力和推力值,建立飞行器模型,然后给出飞行器可变前体多级压缩的约束条件,探讨可变形乘波体气动、推进与翼面控制之间的协调变化关系,最后通过仿真得到可变形乘波体的设计参数,验证综合设计方法的可行性.%Waverider is considered as the main configuration for hypersonic vehicle. If it is designed as a morphing body, the flight envelope can be effectively expanded, and the global stability performance can be ensured. Hence, the integrated design of deformable waverider is researched. Firstly, based on the given referenced waverider shape, the aerodynamics force and thrust are calculated according to the hypersonic aerodynamic theory and the Rayleigh flow formula, and the vehicle model is established. Then the constraint condition of multistage compression is given for the deformable forebody of the vehicle. Furthermore, the coordinated changing relationships among aerodynamic, propulsion and actuator control are discussed. Finally, by simulation,design parameters are obtained for the deformable waverider, and the feasibility of the integrated design is validated.
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