In this paper, the precise initial guidance law based on velocity gain guidance and the state transition matrix for orbit interception were proposed.
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。
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.
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。
Whether the interception mission successfully completed is depended on the amount of fuel consumption in the interception process, thus orbit optimization and control is of great significance.
拦截过程燃料消耗的多少很大程度上决定了拦截任务是否能够圆满完成，因此拦截轨道的优化和控制具有重要的意义。
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