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。

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Thus, the main contents of this thesis are organized as follows: First of all, the orbit dynamic model about celestial bodies and the spacecraft is established.

由此，论文主要研究内容如下：首先，建立了天体及航天器轨道动力学模型。

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At the same time, on the request to the data refresh rate in high dynamic environment, the paper deduces the rapid extrapolation algorithm of the orbit to replace dynamic model method.

同时，由于高动态环境下对数据更新率的要求，推导出轨道快速外推公式替代动力学方法来计算卫星的在轨位置。

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