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。
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。
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。
Considering coupled control inputs, an integrated coupling relative position and attitude dynamic model of the on-orbit servicing spacecraft is built with respect to the target spacecraft.
考虑控制输入耦合，建立服务航天器对目标航天器的相对位置和姿态一体化耦合动力学模型。
On the other hand, the precision gravity model is important guarantees for obtaining high precision orbiting results using the dynamic or reduced-dynamic orbit determination method.
低轨重力卫星轨道的精确确定是获得精密地球重力场模型的前提，而精密重力场模型又是获得高精度定轨结果的保证。
The precision of hanging dynamic model based on CW equation was analyzed in detail, and a low earth orbit satellite octahedron configuration was simulated for validation.
对基于C-W方程的悬停动力学模型进行了精度分析，最后以低轨道航天器的八面体编队构型为例进行了数学仿真验证。
The precision of hanging dynamic model based on CW equation was analyzed in detail, and a low earth orbit satellite octahedron configuration was simulated for validation.
对基于C-W方程的悬停动力学模型进行了精度分析，最后以低轨道航天器的八面体编队构型为例进行了数学仿真验证。
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