摘要
针对高超声速飞行器的再入非线性动力学模型,利用SDRE(state dependent Riccati equation)设计姿态控制器。基于奇异摄动理论,把姿态动力学分解成姿态角和姿态角速度跟踪内、外环回路,同时把非线性动力学伪线性化。每个跟踪回路用SDRE获得控制律,考虑到SDRE局部渐近稳定的特点,可以保证系统闭环稳定。最后设计高超声速飞行器飞行控制系统,并在高超声速条件下进行仿真,验证了该方案的有效性。
A controller is designed using the state dependent Riccati equation theory for nonlinear reentry attitude dynamics of a hypersonic vehicle. The dynamics is separated into fast and slow loops as attitude angular and attitude angular velocity based on the singular perturbation theory, simultaneously, the nonlinear attitude dynamic equations are pseudolinearied based on the state dependent coefficient. Each loop gets the dynamic control law by solving optimal SDRE. The characteristics of SDRE theory guarantee closed-loop systems to be stable. Finally, the flight control system of re-entry vehicle under hypersonic re-entry is designed by the proposed method. Simulation results demonstrate effectiveness of the method.
出处
《空间控制技术与应用》
2008年第4期51-54,共4页
Aerospace Control and Application
