NDLI: Relative Orbit Design for Maintaining Constant Distance in Satellite Formation Flying

Content Provider	IEEE Xplore Digital Library
Author	Rucai Che Honghua Zhang
Copyright Year	2006
Description	Author affiliation: Beijing Inst. of Control Eng. (Rucai Che; Honghua Zhang)
Abstract	The concept of satellite formation flying has been known for some times. Areas of satellite formation flying application include stereographic viewing, interferometry and synthetic aperture synthesization for radar and other applications. The formation with a constant separation between adjacent satellites in an elliptical orbit is required. In this paper, a novel relative orbit design strategy for maintaining constant separation between satellites in formation flying is proposed. The relative dynamics of formation flying with elliptical reference orbits is studied in the true anomaly domain. Using the homogenous solutions to these equations, it is demonstrated that there exists an initial state that will keep almost constant separation between satellites in an elliptical orbit. The separation distance error between adjacent satellites is proportional to the eccentricity of the leader satellite. Simulation results have verified the effectiveness of the proposed method
Starting Page	675
Ending Page	679
File Size	2727008
Page Count	5
File Format	PDF
ISBN	7302139229
DOI	10.1109/CESA.2006.4281738
Language	English
Publisher	Institute of Electrical and Electronics Engineers, Inc. (IEEE)
Publisher Date	2006-10-04
Publisher Place	China
Access Restriction	Subscribed
Rights Holder	IMACS
Subject Keyword	Nonlinear equations relative motion Spaceborne radar Instruments Maintenance engineering Radar applications Space vehicles Satellites orbit design formation flying Space technology Synthetic aperture radar Interferometry
Content Type	Text
Resource Type	Article

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