The typical hovering mission contains three stages: the orbit transfer from the original orbit to the hovering orbit; hovering in the orbit; and the orbit transfer returning to the original orbit. This paper provides an in-depth study for the hovering mission in two aspects: the trajectory optimization for orbit transfer and the orbit design for the hovering stage. Using the Gauss pseudospectral method, the trajectory optimization for the orbit transfer is transformed into the nonlinear programming problem. To solve the nonlinear programming problem, a calculation method combining interior-point method with sequence quadratic programming is proposed to guarantee convergence rate and computational efficiency. The position of the mission spacecraft is fixed relative to the target spacecraft in the spacecraft hovering stage. Aiming at the orbit design of the spacecraft hovering stage, the expression of the required control to maintain spacecraft hovering is deduced by taking advantage of the characteristic of the relatively static operation state of the mission spacecraft. The simulation results prove the validity of the Gauss pseudospectral method in trajectory optimization of the hovering mission, and provide the required control to maintain hovering for the mission spacecraft.

典型的盘旋任务包括三个阶段：从原始轨道到盘旋轨道的轨道转移；盘旋在轨道上；轨道转移回到原始轨道。本文从两个方面对悬停任务进行了深入研究：轨道转移的轨迹优化和悬停阶段的轨道设计。使用高斯伪谱方法，将轨道转移的轨迹优化转化为非线性规划问题。为了解决非线性规划问题，提出了一种将内点法与序列二次规划相结合的计算方法，以保证收敛速度和计算效率。在航天器盘旋阶段，任务航天器的位置相对于目标航天器是固定的。针对航天器盘旋阶段的轨道设计，利用任务航天器的相对静态运行状态的特点，推导了维持航天器盘旋所需的控制方式。仿真结果证明了高斯伪谱方法在飞行任务轨迹优化中的有效性，为飞行任务航天器的维持飞行提供了必要的控制。