Abstract
| Original language | English |
|---|---|
| Pages (from-to) | 517-525 |
| Number of pages | 9 |
| Journal | Journal of Spacecraft and Rockets |
| Early online date | 20 Jan 2015 |
| DOIs | |
| Publication status | Published - Mar 2015 |
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Keywords
- end-of-life disposal
- gossamer spacecraft
- space debris removel missions
- concept-of-operation
- analysis
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Concept-of-operations disposal analysis of spacecraft by gossamer structure. / Macdonald, Malcolm; McInnes, Colin; Bewick, Charlotte; Visagie, Lourens; Lappas, Vaios; Erb, Sven.
In: Journal of Spacecraft and Rockets, 03.2015, p. 517-525.Research output: Contribution to journal › Article
TY - JOUR
T1 - Concept-of-operations disposal analysis of spacecraft by gossamer structure
AU - Macdonald, Malcolm
AU - McInnes, Colin
AU - Bewick, Charlotte
AU - Visagie, Lourens
AU - Lappas, Vaios
AU - Erb, Sven
N1 - Copyright © 2014 by Malcolm Macdonald. Published by the American Institute of Aeronautics and Astronautics, Inc., with permission.
PY - 2015/3
Y1 - 2015/3
N2 - A gossamer structure for end-of-life disposal of spacecraft to mitigate space debris is considered in comparison with other end-of-life disposal concepts to determine when it would be preferable. A needs analysis, potential use cases, and concept-of-operations are developed. A survey of disposal strategies is presented for comparison prior to a down-selection of viable competing techniques; solar sailing, high and low-thrust propulsion, and electrodynamic tethers. A parametric comparison of the down-selection competing techniques is presented. Exploiting solar radiation pressure on the structure is of limited value. Atmospheric drag augmentation was found to be of most benefit for end-of-life disposal when an entirely passive means is required, allowing the gossamer device to act as a ‘fail-safe’. This is applicable to only low and medium mass spacecraft, or spacecraft that are unlikely to survive atmospheric re-entry, hence minimizing risk to human life. It does not significantly alter the operating ceiling altitude but does the maximum allowable end-of-life mass. Peak mass benefit occurs in the altitude range 550 – 650 km and is largely independent of de-orbit time.
AB - A gossamer structure for end-of-life disposal of spacecraft to mitigate space debris is considered in comparison with other end-of-life disposal concepts to determine when it would be preferable. A needs analysis, potential use cases, and concept-of-operations are developed. A survey of disposal strategies is presented for comparison prior to a down-selection of viable competing techniques; solar sailing, high and low-thrust propulsion, and electrodynamic tethers. A parametric comparison of the down-selection competing techniques is presented. Exploiting solar radiation pressure on the structure is of limited value. Atmospheric drag augmentation was found to be of most benefit for end-of-life disposal when an entirely passive means is required, allowing the gossamer device to act as a ‘fail-safe’. This is applicable to only low and medium mass spacecraft, or spacecraft that are unlikely to survive atmospheric re-entry, hence minimizing risk to human life. It does not significantly alter the operating ceiling altitude but does the maximum allowable end-of-life mass. Peak mass benefit occurs in the altitude range 550 – 650 km and is largely independent of de-orbit time.
KW - end-of-life disposal
KW - gossamer spacecraft
KW - space debris removel missions
KW - concept-of-operation
KW - analysis
UR - http://arc.aiaa.org/doi/abs/10.2514/1.A32919
U2 - 10.2514/1.A32919
DO - 10.2514/1.A32919
M3 - Article
SP - 517
EP - 525
JO - Journal of Spacecraft and Rockets
JF - Journal of Spacecraft and Rockets
SN - 0022-4650
ER -