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.
我们将寻求最优控制和奇摄动非线性状态调节器问题的相应轨道。
We shall seek the optimal control and corresponding trajectories of the singularly perturbed nonlinear state regulator problem.
以目标轨道面倾角最大为优化性能指标，获得了升力和滚转角的最优控制规律。
The optimization performance index is to maximize the orbital plane change, and the optimal lift and bank control law are obtained.
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