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高超声速飞行器机体/推进一体化构型具有高性能、高升阻比等优点,但由于气动、推进与控制作用相互耦合,给飞行动力学模型研究带来新的挑战。基于高超声速飞行器空气动力学理论,研究了一体化的气动推进计算方法。该方法采用斜激波理论、普朗特迈耶公式及激波膨胀波理论计算了高超声速飞行器气动力及推力,通过与CFD的计算结果比较,验证了方法的准确性与可靠性。最后对飞行器的纵向气动特性进行了分析与讨论。
Hypersonic aircraft fuselage / propulsion integrated configuration has the advantages of high performance, high lift-drag ratio, etc. However, due to the interaction of aerodynamics, propulsion and control, it brings new challenges to the research of flight dynamics model. Based on the hypersonic aircraft aerodynamics theory, the integrated aerodynamic propulsion method is studied. In this method, the aerodynamic forces and thrusts of hypersonic vehicle are calculated by using oblique shock theory, Prandtl Meyer formula and shock wave expansion wave theory. The accuracy and reliability of the method are verified by comparison with the CFD results. Finally, the longitudinal aerodynamic characteristics of the aircraft were analyzed and discussed.