基于参数空间的伪攻角姿态驾驶仪设计

Design of Attitude Autopilots with Pseudo Angle of Attack Based on Parameter Space Method

文中给出了一种基于参数空间的姿态驾驶仪设计方法。首先,提出了伪攻角姿态驾驶仪,并对驾驶仪的特性进行分析,研究了驾驶仪参数对新弹体的阻尼和静稳定度的影响,然后通过分析系统开环传函的截止频率和相位裕度,综合舵机频带等给出了驾驶仪闭环极点的选择原则,并在极点配置法的基础上,采用参数空间法进行了驾驶仪设计。最后进行了数字仿真验证。结果表明伪攻角姿态驾驶仪可稳定静不稳弹体,且对系统的不确定性具有很好的鲁棒性。

A design method based on parameter space is applied in attitude autopilots. Firstly, the attitude autopilots with pseudo angle of attack feedback is proposed and the improving of the damping and the stability by changing the parameter of the autopilots is studied. Sec- ondly, considering the open-loop crossover frequency, phase margin and the bandwidth of actuator, the selection principle of the pole is proposed. On the basis of the pole assignment, the attitude autopilots is been designed by parameter space method. The results of simula- tion indicate that the attitude autopilots with pseudo angle of attack feedback can control the unstable missile, and be robust to model uncer- tainties.