26 January 2016 An optimal trajectory design for debris deorbiting
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Proceedings Volume 9796, Selected Papers of the Photoelectronic Technology Committee Conferences held November 2015; 97961B (2016) https://doi.org/10.1117/12.2230909
Event: Selected Proceedings of the Chinese Society for Optical Engineering Conferences held November 2015, 2015, Various, China
Abstract
The problem of deorbiting debris is studied in this paper. As a feasible measure, a disposable satellite would be launched, attach to debris, and deorbit the space debris using a technology named electrodynamic tether (EDT). In order to deorbit multiple debris as many as possible, a suboptimal but feasible and efficient trajectory set has been designed to allow a deorbiter satellite tour the LEO small bodies per one mission. Finally a simulation given by this paper showed that a 600 kg satellite is capable of deorbiting 6 debris objects in about 230 days.
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Gaoxiang Ouyang, Gaoxiang Ouyang, Xin Dong, Xin Dong, Xin Li, Xin Li, Yang Zhang, Yang Zhang, } "An optimal trajectory design for debris deorbiting", Proc. SPIE 9796, Selected Papers of the Photoelectronic Technology Committee Conferences held November 2015, 97961B (26 January 2016); doi: 10.1117/12.2230909; https://doi.org/10.1117/12.2230909
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