巡飞弹航迹导引方法研究

Guidance Approach Study for Scout Missile Flight Track

针对巡飞弹等高、常速巡飞等特点,将整条航迹分为直线段和转弯段,利用假设条件,提出一种导引方法:在直线段进行位置和偏差角控制,转弯段采用转弯控制,进而完成整个航迹导引并确保巡飞弹在飞行过程中偏离航线的误差较小。通过仿真可以看出,此方法使得巡飞弹在整个飞行过程中偏离航线的误差极小。

Scout missile has the characteristic of constant height and constant velocity cruise-flying, so the whole flight track can be divided into beeline-stage and wheeling stage. Under the reasonable hypothesis, a guidance approach can be brought forward： using position control method and deviation angle control method in the beeline-stage and using the swerve control method in the wheeling-stage in order to complete the guidance of whole track and insure that in the flying of scout missile the error of deviating fromflight track is relatively small.