能量省、精度高的初制导优化算法是空间拦截制导的基础。
Space interception needs optimization initial guidance method which USES few propulsion and has high precision.
该初制导方法能补偿制导方法误差和轨道摄动对拦截脱靶量的影响。
The miss distance caused by guidance method error and the effects of perturbation are compensated in this initial guidance law.
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.
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