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高超声速飞行器所采用的超燃冲压发动机工作时,进气道和尾喷口的流场扰动将造成气动参数变化,控制系统应在这个变化条件下保证飞行器的姿态精度。为了考虑发动机工作流场的影响,有针对性地设计控制系统,研究分析了在发动机不同工作状态下升力体构型高超声速飞行器气动特性的变化,以及操纵舵面偏转对其气动特性的影响。着眼于保证飞行器飞行姿态的控制系统设计,对超燃冲压发动机不同工作状态下的高超声速飞行器的气动特性给出了解析描述,为控制算法的设计提供了重要参考。
When the scramjet used in the hypersonic vehicle is working, the disturbance of the flow field of the inlet and the tail nozzle will cause the change of the aerodynamic parameters. The control system should ensure the attitude accuracy of the aircraft under the changing conditions. In order to consider the influence of the engine working flow field, the control system is designed in detail. The changes of the aerodynamic characteristics of the lift structure hypersonic vehicle under different working conditions of the engine and the influence of the deflection of the control surface on the aerodynamic characteristics are studied and analyzed. Focusing on the design of the control system to ensure the flight attitude of the aircraft, the aerodynamic characteristics of the hypersonic vehicle under different working conditions of the scramjet are analyzed and described, which provides an important reference for the design of the control algorithm.