Abstract:

To satisfy the need of the hovering technology in the spacecraft on-orbit servicing mission, a study on spacecraft hovering formation design and control is carried out. By designing the mission spacecraft orbit, the absolute orbit relationship between the target spacecraft and the mission spacecraft is presented and the mechanism of the hovering orbit is illustrated. According to the relative trajectory of the mission spacecraft relative to the target spacecraft, and using the well-defined relative orbit elements, the configuration of the hovering orbit in the target spacecraft orbital plane and out of the target spacecraft orbital plane are described. An interval impulse control strategy for hovering formation is derived and the mission spacecraft can be remained at a specified position to the target spacecraft for a long time. Furthermore, the effect of the hovering formation on the required velocity impulse is analyzed. The proposed method and conclusions are validated by simulation through some typical examples. A process of making the mission spacecraft transfer between two hovering orbits is presented. The study improves the design and control methods of spacecraft hovering orbit, and indicates the feasibility of the designed hovering orbit. The theory of spacecraft hovering dynamics and control is improved and the results could provide some references for the designers of the engineering missions.

Key words: hovering formation, hovering orbit, relative orbit elements, formation design, on-orbit servicing