前向偏移导引律及其实现方案研究

THE PROPORTIONAL-NAVIGATION GUIDANCE LAW LEADING OF IMPACT POINT AND METHOD OF REALIZATION

红外寻制导的导弹只能探测跟踪目标（飞机）的热辐射中心，即发动机尾喷流中心。为了提高作战效能，必须使命中点前移至目标要害部位。为此，本文导出了空间飞行时实现前向偏移的相对运动方程和导引律，并提出了简化方案，探讨了控制系统实现的方法。

A proportional-navigation guidance law for leading of impact point in infrared homing guidance is studied. It is a corrected proportional-navigation guidance law,which makes correction for guidance-ratio. Infrared homing guidance only can follow heatseeking center of tail fireworks. The distance from tail fireworks to mass center of targetis h. In order to effectively hit the center of target and increase killing probability. The desired means that the point of impact must be moved h forwards.The precise formulas of plane and space proportional-navigation guidance law for leadingof tracking point are estabilished.The reduced formulas are calculated and compared with the precise one. The result showsthat the proportional-navigation guidance law for leading of impact point surely noved impact point forwards.