空天飞行器再入姿态控制研究

Research on Reentry Attitude Control of Aerospace Vehicle

为满足空天飞行器在再入过程中各种约束条件,对其再入段的姿态控制进行研究。以HORUS-2B飞行器为研究对象,根据飞行器的舵面偏转特点,建立纵向非线性模型,通过对再入过程的约束条件分析,选定合适的初始攻角,对切换控制律进行设计,通过经典控制与模糊控制相结合的方式来整定控制参数,并进行仿真验证。仿真结果表明:控制系统能够很好地对攻角和过载进行控制,并具有很好的鲁棒性,能抑制不确定性的影响。

In order to satisfy various constraints in the reentry process of the aerospace vehicle,the attitude control of the reentry phase is studied.Taking HORUS-2B aircraft as the research object,a longitudinal nonlinear model is established according to the rudder deflection characteristics of the aircraft,by analyzing the constraints of the reentry process and choosing the appropriate initial angle of attack,the switching control law is designed,through combination of classical control and fuzzy control,the control parameters are tuned and verified by simulation.The simulation results show that the control system can control angle of attack and overload well,and has good robustness to restrain the influence of uncertainty.