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。
Based on orbit dynamic theory, the close interception model was set up.
根据轨道动力学理论，建立了近距离空间拦截轨道的数学模型。
Although it is complicated in technology, space-based interception, which can intercept a target in any low, middle and high orbit, has more strategic value than ground-based interception.
天基拦截尽管技术复杂，但是可以拦截低、中、高轨道目标，比地基拦截更具有战略价值。
Based on the great orbit-transfering velocity increment and less intercepting time of kinetic weapon in space, this dissertation brings a new method of determining a predictive interception point.
针对天基动能武器速度增量大、拦截时间小的特性，提出了一种新的确定预测拦截点的方法。
Based on the great orbit-transfering velocity increment and less intercepting time of kinetic weapon in space, this dissertation brings a new method of determining a predictive interception point.
针对天基动能武器速度增量大、拦截时间小的特性，提出了一种新的确定预测拦截点的方法。
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