Hovering Method at Any Selected Position over Space Target on Elliptical Orbit

Abstract

Abstract: By implementing a continuous control acceleration, the relative position of a mission satellite to a target satellite can keep fixed during the mission. So the hovering flying at any selected position over a satellite on elliptical orbit is carried out. The relative motion was studied and the gravitation between the two satellites was researched. The formulae for radial, tangential and normal control acceleration required during the hovering flying mission were put forward. The numerical simulation for typical mission was conducted, and the energy requirements of the hovering spacecraft for different tasks were compared and analyzed. The results show that it is feasible to hover over a special target satellite within a period of time.

Key words: Elliptical orbit, Hovering control, Energy requirement, Satellite

ZHU Ya-Wen, YAN Ye. Hovering Method at Any Selected Position over Space Target on Elliptical Orbit[J]. , 2010, 30(6): 17-23.

References

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