双通道控制旋转导弹自动驾驶仪回路的数学变换及其耦合性分析

Transform and Coupling Analysis of Double-Channel Control Rolling Missile Autopilot Loop

根据双通道控制旋转导弹的特点,通过旋转变换,将弹体坐标系下的自动驾驶仪回路变换到准弹体坐标系下,并比较了与倾斜稳定导弹标准自动驾驶仪的区别.旋转变换后自动驾驶仪的弹体环节和舵机环节的模型均发生变化.旋转导弹自动驾驶仪回路存在运动耦合、控制耦合以及加速度计不在质心时引起的耦合.研究结果表明,在自动驾驶仪设计中需要进行解耦,以减小交连的影响.

Based on the characteristics of rolling missile with double-channel control, the autopilot loop is transferred from body coordinate system to quasi-body coordinate system after a roiling transfer. Compared with a non-rotating missile standard autopilot, the body and fin servo models of the autopilot are both changed. Couplings of motion, control and the accelerometer placed at a distance ahead of the c.g. exist in the rolling missile autopilot loop. The results show that the autopilot design needs decoupling.