Abstract
Periodic or quasi-periodic satellite formations can minimize the active control of long-term satellite formation flying. In this paper, a design of quasi-periodic satellite formation is proposed. The quasi-periodic constrains and mean relative motion of the member satellite under J2 perturbation are used. The reference orbit must be at the critical inclination with a small eccentricity. The quasi-periodic constrains can release more DOFS to design the geometry formation than strict J2 invariant trajectory conditions. The osculating orbital elements are used in numerical simulation, the design is proved to be correct through the simulation.
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© 2011 Springer-Verlag Berlin Heidelberg
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Xu, G., Wang, H., Zhang, M. (2011). Design of Quasi-periodic Satellite Formation at Critical Inclination. In: Yang, D. (eds) Informatics in Control, Automation and Robotics. Lecture Notes in Electrical Engineering, vol 133. Springer, Berlin, Heidelberg. https://doi.org/10.1007/978-3-642-25992-0_9
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DOI: https://doi.org/10.1007/978-3-642-25992-0_9
Publisher Name: Springer, Berlin, Heidelberg
Print ISBN: 978-3-642-25991-3
Online ISBN: 978-3-642-25992-0
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