Due to the dragging force, trajectories of spacecraft circling planetoid can departure from the standard taper curve orbit which is obtained by the two-body hypothesis.
绕小行星运行的航天器由于受到摄动力的影响，运行轨迹会偏离二体假设下的圆锥曲线轨道。
Introduce the reference frame and time system used in orbit design particularly. Analyzed the orbit characteristic of two-body problem and launch window.
详细介绍了用于轨道设计的坐标系统和时间系统，分析了二体轨道特性和发射窗口的基本特性。
Finally, the two level differential corrections method was proposed to transform the orbit designed under the circular restricted three-body problem model into the perturbed three-body problem model.
最后使用两层微分修正方法将圆型限制性三体问题模型下设计的轨道转换到受摄三体问题模型下。
Finally, the two level differential corrections method was proposed to transform the orbit designed under the circular restricted three-body problem model into the perturbed three-body problem model.
最后使用两层微分修正方法将圆型限制性三体问题模型下设计的轨道转换到受摄三体问题模型下。
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