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Low cost Mercury orbiter and sample return missions using solar sail propulsion

Published online by Cambridge University Press:  04 July 2016

C. R. McInnes ,
G. Hughes  and
M. McDonald
C. R. McInnes
Affiliation:
Department of Aerospace Engineering, University of Glasgow, Glasgow, UK
G. Hughes
Affiliation:
Department of Aerospace Engineering, University of Glasgow, Glasgow, UK
M. McDonald
Affiliation:
Department of Aerospace Engineering, University of Glasgow, Glasgow, UK
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Abstract

The use of solar sail propulsion is investigated for both Mercury orbiter (MO) and Mercury sample return missions (MeSR). It will be demonstrated that solar sail propulsion can significantly reduce launch mass and enhance payload mass fractions for MO missions, while MeSR missions are enabled, again with a relatively low launch mass. Previous investigations of MeSR type missions using solar electric propulsion have identified a requirement for an Ariane V launcher to deliver a lander and sample return vehicle. The analysis presented in this paper demonstrates that, in principle, a MeSR mission can be enabled using a single Soyuz-Fregat launch vehicle, leading to significant reductions in launch mass and mission costs. Similarly, it will be demonstrated that the full payload of the ESA Bepi Colombo orbiter mission can be delivered to Mercury using a Soyuz-Fregat launch vehicle, rather than Ariane V, again leading to a reduction in mission costs.

Type
Research Article
Information
The Aeronautical Journal , Volume 107 , Issue 1074: University of Glasgow 50th year anniversary special , August 2003 , pp. 469 - 478
Copyright
Copyright © Royal Aeronautical Society 2003 

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References

1. McInnes, C.R. Solar Sailing: Technology, Dynamics and Mission Applications, 1999, Springer-Verlag, London.Google Scholar
2. McInnes, C.R., Solar sail mission applications for non-Keplerian orbits, Acta Astronautica, 1999, 45, (5-9), pp 567–575.Google Scholar
3. McInnes, C.R., MacDonald, M., Angelopolous, V. and Alexander, D., Geosail: Exploring the geomagnetic tail using a small solar sail, J Spacecraft and Rockets, 2001, 38, (4), pp 622–629.Google Scholar
4. Garner, C. and Leipold, M. Developments and activities in solar sail propulsion, 2000, AIAA paper 2000-3858, 36th AIAA/ASME/SAE/ASEE Joint Propulsion Conference, Huntsville, July 2000.Google Scholar
5. McAdams, J., Farquhar, R. and Yen, C. Improvements in trajectorry optimization for Messenger: the first Mercury orbiter mission, 2001, AAS paper 01-458, AAS/AIAA Astrodynamics Specialist Conference, Quebec City, October 2001.Google Scholar
6. McInnes, C.R. Solar sail missions and technology requirements, 2000, Final Report, ESA contract 13848/99/NL/MV, November 2000.Google Scholar
7. Leipold, M. and Wagner, O., Mercury sun-synchronous polar orbits using solar sail propulsion, J Guidance, Control and Dynamics, 1996, 19, (6), pp 137–141.Google Scholar
8. Hughes, G. and McInnes, C.R. Solar sail hybrid trajectory optimisation, 2001, Paper AAS 01-470, AAS/AIAA Astrodynamics Specialist Conference, Quebec, 30 July – 2 August 2001.Google Scholar
9. McDonald, M., and McInnes, C.R. Analytic control laws for near-optimal geocentric solar sail transfers, 2001 Paper AAS 01-472, AAS/AIAA Astrodynamics Specialist Conference, Quebec, 30 July – 2 August, 2001.Google Scholar