Abstract
| Language | English |
|---|---|
| Pages | 784-796 |
| Number of pages | 13 |
| Journal | Journal of Spacecraft and Rockets |
| Volume | 44 |
| Issue number | 4 |
| DOIs | |
| Publication status | Published - Jul 2007 |
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Keywords
- space craft
- space flight
- rockets
- astrodynamics
- propulsion systems
- solar sails
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GeoSail : an elegant solar sail demonstration mission. / Macdonald, Malcolm ; Hughes, Gareth W.; McInnes, Colin; Lyngvi, Aleksander; Falkner, Peter; Atzei, Alessandro.
In: Journal of Spacecraft and Rockets, Vol. 44, No. 4, 07.2007, p. 784-796.Research output: Contribution to journal › Article
TY - JOUR
T1 - GeoSail
T2 - Journal of Spacecraft and Rockets
AU - Macdonald, Malcolm
AU - Hughes, Gareth W.
AU - McInnes, Colin
AU - Lyngvi, Aleksander
AU - Falkner, Peter
AU - Atzei, Alessandro
PY - 2007/7
Y1 - 2007/7
N2 - In this paper a solar sail magnetotail mission concept was examined. The 43-m square solar sail is used to providethe required propulsion for continuous sun-synchronous apse-line precession. The main driver in this mission was found to be the reduction of launch mass and mission cost while enabling a nominal duration of 2 years within the framework of a demonstration mission. It was found that the mission concept provided an excellent solar sail technology demonstration option. The baseline science objectives and engineering goals were addressed, and mission analysis for solar sail, electric, and chemical propulsion performed. Detailed subsystems were defined for each propulsion system and it was found that the optimum propulsion system is solar sailing. A detailed tradeoff as to the effect of spacecraft and sail technology levels, and requirements, on sail size is presented for the first time. The effect of, for example, data acquisition rate and RF output power on sail size is presented, in which it is found that neither have a significant effect. The key sail technology requirements have been identified through a parametric analysis.
AB - In this paper a solar sail magnetotail mission concept was examined. The 43-m square solar sail is used to providethe required propulsion for continuous sun-synchronous apse-line precession. The main driver in this mission was found to be the reduction of launch mass and mission cost while enabling a nominal duration of 2 years within the framework of a demonstration mission. It was found that the mission concept provided an excellent solar sail technology demonstration option. The baseline science objectives and engineering goals were addressed, and mission analysis for solar sail, electric, and chemical propulsion performed. Detailed subsystems were defined for each propulsion system and it was found that the optimum propulsion system is solar sailing. A detailed tradeoff as to the effect of spacecraft and sail technology levels, and requirements, on sail size is presented for the first time. The effect of, for example, data acquisition rate and RF output power on sail size is presented, in which it is found that neither have a significant effect. The key sail technology requirements have been identified through a parametric analysis.
KW - space craft
KW - space flight
KW - rockets
KW - astrodynamics
KW - propulsion systems
KW - solar sails
U2 - 10.2514/1.22867
DO - 10.2514/1.22867
M3 - Article
VL - 44
SP - 784
EP - 796
JO - Journal of Spacecraft and Rockets
JF - Journal of Spacecraft and Rockets
SN - 0022-4650
IS - 4
ER -