卫星在输入方向约束下的次优编队重构

中文摘要 AI 辅助

卫星的近距离操作，如编队飞行和在轨服务，提供了比单颗卫星任务更先进的任务。在编队飞行的实际情况下，用于保持和控制相对轨道的推力方向受到限制，例如，为了天文观测和避免羽流撞击。本文旨在提供一种在惯性系和领导者固定系下均考虑输入方向约束的编队重构节能控制方法。所提出的控制器由两部分组成：1）基于能量最优控制器保证编队重构到期望队形；2）通过叠加额外输入来满足输入方向约束。控制输入的解析形式表明，当满足特定边界条件时，输入方向在领导者固定系中形成椭圆，该椭圆被用作考虑输入方向约束的标称控制器。由于标称控制器的奇异规避，额外输入可以解析获得。通过设置虚拟目标轨道来补偿额外输入对跟随者轨迹的影响，因此成功的编队重构仍然得到保证。一些数值仿真结果验证了所提出方法的有效性并比较了能量效率。

英文摘要

Proximity operations of satellites such as formation flying and on-orbit servicing offer more advanced missions than missions achieved by a single satellite. In a practical situation of formation flying, thrust directions for keeping and controlling a relative orbit is limited, e.g., for astronomical observation and plume impingement avoidance. The aim of this paper is to provide an energy efficient control method for a formation reconfiguration under input directional constraints with respect to both an inertial and a leader-fixed frames. The proposed controller is designed consisting of two parts: 1) guaranteeing a formation reconfiguration to a desirable formation on the basis of an energy optimal controller and 2) satisfying the input directional constraints by superimposing additional inputs. The analytical form of the control input shows that the input direction forms an ellipse in the leader-fixed frame when a particular boundary condition is satisfied, which is exploited as a nominal controller to take into account the input directional constraints. Due to the singular avoidance of the nominal controller, the additional inputs can be analytically obtained. The effect on the follower trajectory due to the additional inputs is compensated by setting a virtual target orbit, and thus the successful formation reconfiguration is still guaranteed. Some numerical simulation results verify the effectiveness of the proposed method and compare the energy efficiency.

发表机构

• Tokyo Metropolitan University（东京都立大学）

机构由 AI 辅助整理，请以论文原文为准。

补充信息

备注

Accepted for publication in Advances in Space Research