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The current status of the Nano-JASMINE project

Published online by Cambridge University Press:  01 October 2007

Y. Kobayashi ,
N. Gouda ,
T. Yano ,
M. Suganuma ,
M. Yamauchi ,
Y. Yamada ,
N. Sako  and
S. Nakasuka
Y. Kobayashi
Affiliation:
National Astronomical Observatory of Japan, 2-21-1 Osawa, Mitaka, Tokyo, 181-8588Japan Department of Astronomy, The University of Tokyo, 7-3-1 Bunkyoku, Hongo, Tokyo, Japan The Graduate University for Advanced Studies 2-21-1, Osawa, Mitaka, Tokyo, Japan
N. Gouda
Affiliation:
National Astronomical Observatory of Japan, 2-21-1 Osawa, Mitaka, Tokyo, 181-8588Japan The Graduate University for Advanced Studies 2-21-1, Osawa, Mitaka, Tokyo, Japan
T. Yano
Affiliation:
National Astronomical Observatory of Japan, 2-21-1 Osawa, Mitaka, Tokyo, 181-8588Japan
M. Suganuma
Affiliation:
National Astronomical Observatory of Japan, 2-21-1 Osawa, Mitaka, Tokyo, 181-8588Japan
M. Yamauchi
Affiliation:
National Astronomical Observatory of Japan, 2-21-1 Osawa, Mitaka, Tokyo, 181-8588Japan Department of Astronomy, The University of Tokyo, 7-3-1 Bunkyoku, Hongo, Tokyo, Japan
Y. Yamada
Affiliation:
Faculty of Science, Kyoto University Kitashirakawa, Oiwakecho, Sakyoku, Kyoto, Japan
N. Sako
Affiliation:
School of Engineering, The University of Tokyo, 7-3-1 Bunkyoku, Hongo, Tokyo, Japan
S. Nakasuka
Affiliation:
School of Engineering, The University of Tokyo, 7-3-1 Bunkyoku, Hongo, Tokyo, Japan
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Abstract

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Nano-JASMINE is a nano-size astrometry satellite that will carry out astrometry measurements of nearby bright stars for more than one year. This will enable us to detect annual parallaxes of stars within 300 pc from the Sun. We expect the satellite to be launched as a piggy-back system as early as in 2009 into a Sun synchronized orbit at the altitude between 500 and 800 km. Being equipped with a beam combiner, the satellite has a capability to observe two different fields simultaneously and will be able to carry out HIPPARCOS-type observations along great circles. A 5 cm all aluminum made reflecting telescope with a aluminum beam combiner is developed. Using the on-board CCD controller, experiments with a real star have been executed. A communication band width is insufficient to transfer all imaging data, hence, we developed an onboard data processing system that extracts stellar image data from vast amount of imaging data. A newly developed 2K × 1K fully-depleted CCD will be used for the mission. It will work in the time delayed integration(TDI) mode. The bus system has been designed with special consideration of the following two points. Those are the thermal stabilization of the telescope and the accuracy of the altitude control. The former is essential to achieve high astrometric accuracies, on the order of 1 mas. Therefore relative angle of the beam combiner must be stable within 1 mas. A 3-axes control of the satellite will be realized by using fiber gyro and triaxial reaction wheel system and careful treatment of various disturbing forces.

Keywords

space vehiclesinstrumentation: detectors
Type
Contributed Papers
Information
Proceedings of the International Astronomical Union , Volume 3 , Symposium S248: A Giant Step: from Milli- to Micro-arcsecond Astrometry , October 2007 , pp. 270 - 271
Copyright
Copyright © International Astronomical Union 2008

References

Suganuma, M. et al. 2008, Proc. IAU symposium No. 248, this volume p. 284CrossRefGoogle Scholar
Yamauchi, M. et al. 2008, Proc. IAU symposium No. 248, this volume p. 294CrossRefGoogle Scholar