空地导弹对应不同驾驶仪下的中制导高度控制回路设计

Design of Altitude Control Loops Relating to Different Autopilots for Air-to-ground Missiles’ Midcourse Guidance

使用频率法和根轨迹法设计了姿态驾驶仪内回路对应的高度控制回路;对内回路姿态驾驶仪结构和过载驾驶仪结构分别对应的高度控制回路进行了对比分析。结果表明,两种内回路驾驶仪结构对应的高度控制回路性能基本一样,都是可行的。并在此基础上分析了内回路驾驶仪结构切换对中末制导交班切换的影响。结果表明,驾驶仪结构切换对中末制导交班切换的影响很小,可以考虑将中末制导交班切换时的两个切换同时进行。

An altitude control loop based on the attitude autopilot inner loop was designed by using frequency method and root locus method. Also a comparing study was made between the altitude control system combined with attitude autopilot and the altitude control system combined with acceleration autopilot. The results indicate that the performance of these two altitude control systems is the same in essence. Then the effect of switching the autopilot inner loops on the transition from midcourse guidance to terminal guidance was analyzed. It is found that the effect is little, so it is feasible to switch the inner autopilots and the guidance loops simultaneously.