惯导解算误差的自动驾驶仪设计方法

New Design Method of Autopilot with Inertial Navigation Error

空空导弹在应急发射时,主、子惯导未进行传递对准,会导致自动驾驶仪调参出现误差;针对这个问题,提出了一种参数空间方法与变结构控制相结合的控制方案;采用参数空间方法设计自动驾驶仪阻尼回路,实现对弹体的增稳作用;采用基于趋近律的积分型变结构控制设计自动驾驶仪过载回路,实现对过载指令的精确跟踪;对标称状态下设计的自动驾驶仪,在惯导解算误差条件下进行校核;仿真结果表明,该方法在自动驾驶仪出现调参误差的情况下,可以有效提高控制系统稳定性。

The controller parameter is inaccurate,when the air to air missile is launched without transfer alignment.An approach which is based on parameter space method and variable structure control is proposed in this paper for solving the problem.The inner loop controller is designed based on parameter space method,which ensures the stability of system.The outer loop controller is designed based on variable structure control with integral type.The simulation results showed that the autopilot designed based on this method enhance the stability of system.