Options for Small Satellite Deorbit from LEO
- Paper number
IAC-06-B5.5.04
- Author
Mr. Angelo Grubisic, University of Southampton, United Kingdom
- Coauthor
Mr. D. Gibbon, Surrey Space Centre, University of Surrey, United Kingdom
- Coauthor
Mr. Sanjay Mistry, Surrey Satellite Technology Ltd., United Kingdom
- Coauthor
Prof. Martin Sweeting, Surrey Satellite Technology Ltd., United Kingdom
- Year
2006
- Abstract
There has been discussion on spacecraft debris mitigation by deorbit in recent years by various means. Recommendations of the Inter-Agency Space Debris Coordination Committee (IADC) will soon make this issue a design consideration for spacecraft manufacturers. Where as GEO and MEO missions do not require large fractions of fuel to move them into graveyard orbits, the delta V required to deorbit LEO spacecraft is generally much larger than the total mission delta V. This study therefore presents an analysis of deorbit options available specifically to small satellites in LEO and the ways in which these systems impact on small satellite architectures. The study is made to enable more accurate selection criteria for deorbit systems. In addition the advantages and disadvantages of integrated (dual-use) or dedicated deorbit systems are discussed.
- Abstract document