An optimal trajectory design for debris deorbiting

Gaoxiang Ouyang; Xin Dong; Xin Li; Yang Zhang

doi:10.1117/12.2230909

26 January 2016 An optimal trajectory design for debris deorbiting

Gaoxiang Ouyang, Xin Dong, Xin Li, Yang Zhang

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.

Citation Download Citation

Gaoxiang Ouyang, Xin Dong, Xin Li, and 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); https://doi.org/10.1117/12.2230909

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