TY - JOUR
T1 - Index
T2 - Piggy-back satelite for aurora observation and technology demonstration
AU - Saito, H.
AU - Masumoto, Y.
AU - Mizuno, T.
AU - Miura, A.
AU - Hashimoto, M.
AU - Ogawa, H.
AU - Tachikawa, S.
AU - Oshima, T.
AU - Choki, A.
AU - Fukuda, H.
AU - Hirahara, M.
AU - Okano, Shouichi
PY - 2001/3/1
Y1 - 2001/3/1
N2 - This paper describes outline of the piggy-back satellite "INDEX" for demonstration of advanced satellite technologies as well as for observation of fine structure of aurora. Aurora observation will be carried out by three cameras(MAC) with a monochromatic UV filter. Electron and ion spectrum analyzer (ESA/ISA) will measure the particle phenomena together with the aurora hanging. INDEX satellite will be launched in 2002 by Japanese H2-A. The satellite is mainly controlled by the high-speed, fault-tolerant on-board RICS processor (three-voting system of SH-3). The attitude control is a compact system of three-axis stabilization. Although the size of INDEX is small (50Kg class), several newly-developed technologies are applied to the satellite system, including silicon-on-insulator devices, variable emittance radiator, solar-concentrated paddles, lithium-ion battery, and GPS receiver with all-sky antenna-coverage.
AB - This paper describes outline of the piggy-back satellite "INDEX" for demonstration of advanced satellite technologies as well as for observation of fine structure of aurora. Aurora observation will be carried out by three cameras(MAC) with a monochromatic UV filter. Electron and ion spectrum analyzer (ESA/ISA) will measure the particle phenomena together with the aurora hanging. INDEX satellite will be launched in 2002 by Japanese H2-A. The satellite is mainly controlled by the high-speed, fault-tolerant on-board RICS processor (three-voting system of SH-3). The attitude control is a compact system of three-axis stabilization. Although the size of INDEX is small (50Kg class), several newly-developed technologies are applied to the satellite system, including silicon-on-insulator devices, variable emittance radiator, solar-concentrated paddles, lithium-ion battery, and GPS receiver with all-sky antenna-coverage.
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U2 - 10.1016/S0094-5765(01)00079-0
DO - 10.1016/S0094-5765(01)00079-0
M3 - Article
AN - SCOPUS:0035264806
SN - 0094-5765
VL - 48
SP - 723
EP - 735
JO - Acta Astronautica
JF - Acta Astronautica
IS - 5-12
ER -
