A series of small scientific satellite with flexible standard bus
Japan Aerospace Exploration Agency has a plan to develop the small satellite standard bus for various scientific missions and disaster monitoring missions. The satellite bus is a class of 250–400 kg mass with three-axis control capability of 0 . 02 ∘ accuracy. The science missions include X-ray astr...
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| Published in: | Acta astronautica Vol. 65; no. 9; pp. 1345 - 1359 |
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| Main Authors: | , , , , |
| Format: | Journal Article |
| Language: | English |
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Elsevier Ltd
01-11-2009
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| Abstract | Japan Aerospace Exploration Agency has a plan to develop the small satellite standard bus for various scientific missions and disaster monitoring missions. The satellite bus is a class of 250–400
kg mass with three-axis control capability of
0
.
02
∘
accuracy. The science missions include X-ray astronomy missions, planetary telescope missions, and magnetosphere atmosphere missions. In order to adapt the wide range of mission requirements, the satellite bus has to be provided with flexibility. The concepts of modularization, reusability, and product line are applied to the standard bus system. This paper describes the characteristics of the small satellite standard bus which will be firstly launched in 2011. |
|---|---|
| AbstractList | Japan Aerospace Exploration Agency has a plan to develop the small satellite standard bus for various scientific missions and disaster monitoring missions. The satellite bus is a class of 250–400
kg mass with three-axis control capability of
0
.
02
∘
accuracy. The science missions include X-ray astronomy missions, planetary telescope missions, and magnetosphere atmosphere missions. In order to adapt the wide range of mission requirements, the satellite bus has to be provided with flexibility. The concepts of modularization, reusability, and product line are applied to the standard bus system. This paper describes the characteristics of the small satellite standard bus which will be firstly launched in 2011. Japan Aerospace Exploration Agency has a plan to develop the small satellite standard bus for various scientific missions and disaster monitoring missions. The satellite bus is a class of 250-400kg mass with three-axis control capability of 0.02(?) accuracy. The science missions include X-ray astronomy missions, planetary telescope missions, and magnetosphere atmosphere missions. In order to adapt the wide range of mission requirements, the satellite bus has to be provided with flexibility. The concepts of modularization, reusability, and product line are applied to the standard bus system. This paper describes the characteristics of the small satellite standard bus which will be firstly launched in 2011. |
| Author | Saito, Hirobumi Sawai, Syujiro Fukuda, Seisuke Kitade, Kenji Sakai, Shin-ichiro |
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| References | T. Yamada, A table-driven messaging protocol for controlling spacecraft and instruments, in: 2nd ESA Workshop on Tracking, Telemetry and Command Systems for Space Applications, October 2001. T. Takahashi, et al., Space cube 2—an onboard computer based on space cube architecture, in: International SpaceWire Conference 2007, September 2007. H. Saito, et al., An Overview and Lessons-learned of Small Scientific Satellite “INDEX” (REIMEI), IAC-07-B4.4.05, September 2007. Gonzalez-Zugasti (bib5) 2000; 2 T. Yamada, Generic Software for Spacecraft Testing and Operations Based on a Spacecraft Model, Space Ops 2006, AIAA-2006-5529, June 2006. 10.1016/j.actaastro.2009.03.065_bib3 Gonzalez-Zugasti (10.1016/j.actaastro.2009.03.065_bib5) 2000; 2 10.1016/j.actaastro.2009.03.065_bib4 10.1016/j.actaastro.2009.03.065_bib1 10.1016/j.actaastro.2009.03.065_bib2 |
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| Title | A series of small scientific satellite with flexible standard bus |
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