BTT导弹H_∞鲁棒自动驾驶仪的6DOF数学仿真

6DOF Mathematical Simulation for BTT Missile with H ∞ Robust Autopilot

该文Ｈ∞对控制方法设计的ＢＴＴ导弹自动驾驶仪进行六自由度（６ＤＯＦ）数学仿真。与传统的逐段切换自动驾驶仪增益以控制导弹沿全弹道飞行方法相比，本仿真仅用对标准弹道上某特征点设计的一个Ｈ∞鲁棒自动驾驶仪控制导弹的全弹道飞行。仿真结果表明：设计的Ｈ∞鲁棒自动驾驶仪能控制导弹在较大空域内稳定、准确地飞行，在满足一定的性能指标要求的前提下系统有很强的鲁棒稳定性。

In this paper the 6DOF mathematical simulation for a BTT missile is given with a H ∞ Robust Autopilot. Compared with gain schedules of traditional autopilot design method of BTT missiles, the fixed H ∞ Robust Autopilot with the structure of inner-outer loop is proposed to control BTT missile flying along a trajectory or multi-trajectories. The result of 6DOF mathematical simulation declares that H ∞ Robust Autopilot can control the BTT missile flying in a large airspace stably and accurately.