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.
最后，采用轨道根数作为状态变量，以航天器发动机产生的推力加速度作为控制变量建立空间拦截模型。
Finally, the orbital elements are introduced as state variables and the accelerations are produced by equation as control variables, the space interception model is established.
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.
本文通过建立航天器在空间作战的拦截模型，根据运动学的理论来设计航天器空间作战最优拦截轨道。
In this paper, the intercept model of the spacecraft in space warfare was built and the optimization orbit was designed based on the theories of kinematics.
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。
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.
几何上证明了这种拦截的特征速度与最省燃料轨道的特征速度相同，并且给出了该方法的解的存在性条件。
It was proved that ?v of this interception coincide with that of minimum fuel transfer in geometry. The existence of solutions was studied.
本文分析了低轨星载拦截器进行轨道机动拦截高轨卫星的能力。
The paper analyzes the capability of satellite-board interceptor on low orbits to intercept the satellites on high orbits by orbit maneuvering.
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。
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.
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。
Based on orbit dynamic theory, the close interception model was set up.
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.
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.
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