Relative Dynamics and Control for Satellite Formation: Accommodating Perturbation
Publication: Journal of Aerospace Engineering
Volume 29, Issue 4
Abstract
The effect is the dominating perturbation for satellite formation flying missions. In this paper, a linearized satellite relative motion model considering perturbation and eccentricity was derived first. Then, a real-time fuel-optimal continuous low-thrust control approach was proposed for satellite formation control in eccentric orbits on the basis of the developed linear dynamic model. This optimal control problem was converted into a mathematical programming problem by the application of the Legendre pseudospectral method, which makes real-time optimal control feasible. Finally, comprehensive simulation results validated the proposed linearized model and formation control approach.
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Acknowledgments
This work was funded by National Natural Science Foundation of China (61503093, 61074159, 91438202), Open Fund of National Defense Key Discipline Laboratory of Micro-Spacecraft Technology (Grant Number HIT.KLOF.MST.201502), and Harbin Institute of Technology under project agreement, No. AUGA5710053114.
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Published In
Journal of Aerospace Engineering
Volume 29 • Issue 4 • July 2016
Copyright
© 2016 American Society of Civil Engineers.
History
Received: Sep 19, 2014
Accepted: Nov 6, 2015
Published online: Jan 21, 2016
Discussion open until: Jun 21, 2016
Published in print: Jul 1, 2016
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