Astronomy:HIBARI (satellite)
| Operator | Tokyo Institute of Technology |
|---|---|
| COSPAR ID | 2021-102F |
| Spacecraft properties | |
| Manufacturer | Tokyo Institute of Technology |
| Launch mass | 55 kg (121 lb) |
| Dimensions | 50 × 50 × 50 cm (20 × 20 × 20 in) |
| Start of mission | |
| Launch date | 9 November 2021, 00:55 UTC |
| Rocket | Epsilon (No. 5) |
| Launch site | Uchinoura Space Center |
| Contractor | JAXA |
| Orbital parameters | |
| Reference system | Geocentric orbit (planned) |
| Regime | Sun-synchronous orbit |
| Perigee altitude | 560 km (350 mi) |
| Apogee altitude | 560 km (350 mi) |
| Inclination | 97.6° |
| Instruments | |
| Ultraviolet telescope | |
HIBARI is a space mission by Japan for a microsatellite that would test a new attitude control (orientation) method to achieve high accuracy pointing for its small telescope, and was launched on 9 November 2021 by an Epsilon launch vehicle as part of the Innovative Satellite Technology Demonstration Program-2 mission.[1] The key technology to be tested on HIBARI is called "Variable Shape Attitude Control" (VSAC), and it is based on reaction torque by rotating its four solar array paddles.
Conceptual design
HIBARI is a space mission by the Japanese scientists from the Tokyo Institute of Technology to develop high pointing stability and agile maneuvering of a small satellite by using reaction torque of the satellite's structure.[2][3] This technology, first presented in 2016,[4] is hoped to substitute the use of reaction wheels and control moment gyroscopes (CMG), which arguably have difficulty achieving both agility and stability simultaneously.[2] This capability would be useful for a very fast response to observe in the direction of gravitational waves or other transient astrophysical phenomena.[3]
The spacecraft is a 55 kg (121 lb) microsatellite configured in a 50 cm (20 in) cube,[3] where half of it would carry a small ultraviolet telescope to verify the pointing stability (< 10 𝑎𝑟𝑐𝑠𝑒𝑐2) and accuracy of the VSAC system. The orientation high accuracy would be achieved by rotating the arms of its four solar arrays in an orthogonal axis.[2] Solar cells would be mounted on both sides of each of four solar array paddles.[3]
References
- ↑ "Error: no
|title=specified when using {{Cite web}}" (in ja). JAXA. 9 November 2021. https://www.jaxa.jp/press/2021/11/20211109-1_j.html. - ↑ 2.0 2.1 2.2 Variable Shape Attitude Control Demonstration with Microsat "HIBARI" Kenichi Sasaki, Yuhei Kikuya, Sho Koizumi, Yuto Masuda, Yusuke Shintani, Tsubasa Tsunemitsu, Takashi Furuya, Yohei Iwasaki, Yuichiro Takeuchi, Kei Watanabe, Saburo Matunaga Tokyo Institute of Technology 32nd Annual AIAA/USU Conference on Small Satellites 2018
- ↑ 3.0 3.1 3.2 3.3 Variable Shape Attitude Control Demonstration with Microsat "HIBARI" (Slide presentation) Kenichi Sasaki, Yuhei Kikuya, ShoKoizumi, YutoMasuda, ToshikiOzawa, Yusuke Shintani, Tsubasa Tsunemitsu, Yuichiro Takeuchi, Yoichi Yatsu, Saburo Matunaga Tokyo Institute of Technology 4 August 2018
- ↑ A Study of Rest-to-Rest Three-Axis Attitude Maneuver with Shape Variable Function Watanabe Fuuta Tokyo Institute of Technology January 2016 doi:10.1299/jsmesec.2016.25.2B1
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| Hibernating (Mission completed) | |
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