高速再入飞行器的制导与控制系统设计

DESIGN OF GUIDANCE AND CONTROL SYSTEM FOR HIGH SPEED REENTRY AEROCRAFT

针对高速再入飞行器模型的快时变 ,强耦合 ,严重非线性的特点 ,采用反馈线性化方法 ,设计了自动驾驶仪 ;同时采用最优制导律设计与理想速度曲线相结合的方法 ,设计了能同时保证末端制导精度及速度方向、大小的制导律。最后 ,进行了六自由度仿真 ,结果表明 :设计的制导律及控制方案是合理、有效的 ,易于实现。

An autopilot design scheme is presented with feedback linearization technique against the fast time-varying, strong coupling and high nonlinear system of the high-speed reentry aerocraft dynamics. Furthermore, a guidance law is proposed by using a combination of optimal guidance law design with ideal velocity curve approach. The terminal guidance accuracy, the direction and amplitude of the aerocraft velocity are guaranteed by using the derivative guidance law. Finally, 6 DOF simulations are made based on a kind of reentry aerocraft. The results show that the proposed control scheme and the guidance law are rational, efficient and easy for implementation.