面向控制研究的高超声速飞行器气动力与动力一体的建模新方法

The new modeling method of aerodynamic and dynamic integration facing control study for hypersonic vehicle

高超声速飞行器采用乘波构形后,将对其模型研究带来新挑战,主要体现在建模过程中应充分考虑气动、推进与控制作用相互耦合,因此为了保证建模的准确性,有必要引入新方法来研究高超声速飞行器的模型。本文基于高超声速空气动力学理论,提出了一种高超声速飞行器纵向模型研究的新方法,该方法采用斜激波理论、普朗特-迈耶关系式及瑞利流原理来估算高超声速飞行器气动力及推力,建立飞行器纵向模态的非线性数学模型,并在不同平衡点分析飞行器纵向运动的气动特性,以掌握高超声速飞行的特点,为控制系统设计提供好的对象。仿真研究表明,应用该方法来研究高超声速飞行器纵向模型是可行的。

Waverider configurations applied to hypersonic vehicle will bring new challenges for its model study,which mainly consider mutual couplings in aerodynamic、propulsion and control effects should be considered enough in the modeling process.Therefore,it is necessary to introduce a new method to study the hypersonic vehicle model in order to ensure the accuracy of the model.Based on the theory of hypersonic aerodynamics,this paper proposes a new method for hypersonic longitudinal model,including using oblique shock wave theory、Prandtl-Meyer relation and Rayleigh flow principle to estimate aerodynamic force and thrust of hypersonic vehicle,establishing its non-linear mathematical longitudinal model,and analyzing its aerodynamic characteristics of longitudinal motion in different trim points in order to grasp the characteristics of hypersonic flight and provide good object for the design of control system.Simulation studies show this method is feasible to longitudinal model of hypersonic vehicle.