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Proceedings Paper

An optimal trajectory design for debris deorbiting
Author(s): Gaoxiang Ouyang; Xin Dong; Xin Li; Yang Zhang
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Paper 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.

Paper Details

Date Published: 26 January 2016
PDF: 8 pages
Proc. SPIE 9796, Selected Papers of the Photoelectronic Technology Committee Conferences held November 2015, 97961B (26 January 2016); doi: 10.1117/12.2230909
Show Author Affiliations
Gaoxiang Ouyang, Academy of Opto-Electronics (China)
Xin Dong, Academy of Opto-Electronics (China)
Xin Li, Academy of Opto-Electronics (China)
Yang Zhang, Academy of Opto-Electronics (China)


Published in SPIE Proceedings Vol. 9796:
Selected Papers of the Photoelectronic Technology Committee Conferences held November 2015
Weimin Bao; Yueguang Lv, Editor(s)

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