由于采用了一种新的剩余时间算法，在空间拦截弹的弹体纵轴方向无轨道控制发动机的情况下，也可以实现这种最优导引规律。
For a new time-to-go algorithm, the optimal guidance law can be realized without a trajectory control engine along the lengthwise axis of the missile.
研究了标称飞行轨道最优交会点选取，交会时间与发射时间计算等问题。
The ideal rendezvous time, launch time and rendezvous point in space were studied.
首先，利用庞特里亚金极大值原理将时间最短打击轨道的最优控制问题转化为两点边值问题。
Firstly the optimal control problem of minimum-time strike trajectory was translated into two-point-boundary-value problem by using Pontryagin maximum principle.
应用推荐