对于轨道拦截问题，给出了一种基于速度增益制导和状态转移矩阵的精确初制导方法。
In this paper, the precise initial guidance law based on velocity gain guidance and the state transition matrix for orbit interception were proposed.
仿真结果表明，所提出的精确初制导方法合理、有效，能在增加较小燃料消耗的情况下，大大提高轨道拦截的制导精度。
The simulation results show that the precise initial guidance method is rational and efficient, and it can greatly improve the accuracy of orbit interception with an extra little fuel consuming.
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.
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