Disabled satellite removal by three coordinated electromagnetic spacecraft
- Paper number
IAC-14,A6,6,1,x20997
- Coauthor
Dr. Yuan-wen Zhang, National University of Defense Technology, China
- Coauthor
Prof. Le-ping Yang, China
- Coauthor
Dr. Yan-wei Zhu, China
- Coauthor
Dr. Huan Huang, China
- Coauthor
Dr. Hou-jun Ao, China
- Coauthor
Mr. Da-Wei Qi, College of Aerospace Science and Engineering, National University of Defense Technology, China
- Year
2014
- Abstract
With the application of inter-spacecraft electromagnetic force, disabled satellite with functional magnetorquer could be non-contacting removed without propellant expenditure and complicated docking or capture mechanism. This paper investigates the working configuration design, equilibrium condition solution and corresponding controller design of the three electromagnetic spacecraft for removing a disabled satellite. Firstly, several configurations of the three electromagnetic spacecraft are analyzed and a working configuration is selected, which mainly concentrate on the control capability of the relative position and the attitude with respect to the disabled satellite and the other spacecraft. Secondly, the equilibrium conditions of the working configuration, e.g., the analytical solutions of the magnetic moments of the three electromagnetic spacecraft, are optimal solved. Thirdly, a novel control approach which combines the Artificial Potential Function (APF) method and the Linear Quadratic Regulator (LQR) is applied to design the controller of configuration maintaining. Fourthly, several numerical simulations are implemented to validate these theoretical deduction results. Lastly, the disabled satellite removal efficiency corresponding to different number of electromagnetic spacecraft is discussed, and some considerations for future on-orbit application are given.
- Abstract document
- Manuscript document
IAC-14,A6,6,1,x20997.pdf (🔒 authorized access only).
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