TY  - CHAP
A1  - McInnes, Colin R.
A1  - Bothmer, Volker
A1  - Dachwald, Bernd
A1  - Geppert, Ulrich R. M. E.
A1  - Heiligers, Jeannette
A1  - Hilgers, Alan
A1  - Johnson, Les
A1  - Macdonald, Malcolm
A1  - Reinhard, Ruedeger
A1  - Seboldt, Wolfgang
A1  - Spietz, Peter
T1  - Gossamer roadmap technology reference study for a Sub-L1 Space Weather Mission
T2  - Advances in solar sailing
N2  - A technology reference study for a displaced Lagrange point space weather mission is presented. The mission builds on previous concepts, but adopts a strong micro-spacecraft philosophy to deliver a low mass platform and payload which can be accommodated on the DLR/ESA Gossamer-3 technology demonstration mission. A direct escape from Geostationary Transfer Orbit is assumed with the sail deployed after the escape burn. The use of a miniaturized, low mass platform and payload then allows the Gossamer-3 solar sail to potentially double the warning time of space weather events. The mission profile and mass budgets will be presented to achieve these ambitious goals.
Y1  - 2014
SN  - 978-3-642-34906-5 (Print) ; 978-3-642-34907-2 (E-Book)
SP  - 227
EP  - 242
PB  - Springer
CY  - Berlin [u.a.]
ER  - 
TY  - CHAP
A1  - Macdonald, Malcolm
A1  - McGrath, C.
A1  - Appourchaux, T.
A1  - Dachwald, Bernd
A1  - Finsterle, W.
A1  - Gizon, L.
A1  - Liewer, P. C.
A1  - McInnes, Colin R.
A1  - Mengali, G.
A1  - Seboldt, W.
A1  - Sekii, T.
A1  - Solanki, S. K.
A1  - Velli, M.
A1  - Wimmer-Schweingruber, R. F.
A1  - Spietz, Peter
A1  - Reinhard, Ruedeger
ED  - Macdonald, Malcolm
T1  - Gossamer roadmap technology reference study for a solar polar mission
T2  - Advances in solar sailing
N2  - A technology reference study for a solar polar mission is presented. The study uses novel analytical methods to quantify the mission design space including the required sail performance to achieve a given solar polar observation angle within a given timeframe and thus to derive mass allocations for the remaining spacecraft sub-systems, that is excluding the solar sail sub-system. A parametric, bottom-up, system mass budget analysis is then used to establish the required sail technology to deliver a range of science payloads, and to establish where such payloads can be delivered to within a given timeframe. It is found that a solar polar mission requires a solar sail of side-length 100–125 m to deliver a ‘sufficient value’ minimum science payload, and that a 2.5 μm sail film substrate is typically required, however the design is much less sensitive to the boom specific mass.
Y1  - 2014
SN  - 978-3-642-34906-5
U6  - http://dx.doi.org/10.1007/978-3-642-34907-2_17
SP  - 243
EP  - 257
PB  - Springer
CY  - Berlin, Heidelberg
ER  -