基于强跟踪滤波器的再入飞行器制导律设计

Design of Entry Guidance Based on Strong Tracking Filter for Reentry Spacecraft

研究了气动模型存在误差情况下高超声速再入机动飞行器的制导律设计问题。首先用强跟踪滤波器对气动参数进行估计,然后根据估计值与标称值的偏差对攻角和倾斜角进行修正,最后对原始非线性方程沿着标称轨道线性化得到线性偏差方程,并利用线性二次型最优调节器原理设计控制律。仿真结果表明所设计的制导律可以大幅度减小由于气动模型误差而引起的落点偏差。

In the case that large aerodynamic model errors exist, a guidance law based on the strong tracking filter （STF） for the reentry maneuverable spacecraft was proposed. The aerodynamic coefficients were estimated by using STE The normal angle of attack and bank angle were corrected according to the aerodynamic coefficient errors between the estimated values and the normal ones. The linear deviation equations were formulated by linearizing the original nonlinear equations of motion about the normal trajectory, and the optimal linear regulator was used to design the state feedback control law. Simulation results show the guidance law proposed can dramatically reduce the landing point error resulting from aerodynamic model errors.