Study on Practical Applicability of Underactuated Attitude Control of Satellites
| Project/Area Number |
26820372
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| Research Category |
Grant-in-Aid for Young Scientists (B)
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| Allocation Type | Multi-year Fund |
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| Research Field |
Aerospace engineering
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| Research Institution | Tokyo Metropolitan University |
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Principal Investigator |
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| Project Period (FY) |
2014-04-01 – 2017-03-31
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| Project Status |
Completed (Fiscal Year 2016)
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| Budget Amount *help |
¥3,900,000 (Direct Cost: ¥3,000,000、Indirect Cost: ¥900,000)
Fiscal Year 2016: ¥1,170,000 (Direct Cost: ¥900,000、Indirect Cost: ¥270,000)
Fiscal Year 2015: ¥1,560,000 (Direct Cost: ¥1,200,000、Indirect Cost: ¥360,000)
Fiscal Year 2014: ¥1,170,000 (Direct Cost: ¥900,000、Indirect Cost: ¥270,000)
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| Keywords | 劣駆動制御 / 磁気トルカ / スラスタ / コントロールモーメントジャイロ / 姿勢制御 / 最適化 / フォールトトレラント / フォールトトレラントシステム / 劣駆動システム |
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| Outline of Final Research Achievements |
This research has focused on 1) underactuated attitude control of satellites under input directional constraints and 2) optimal fault-tolerant configurations of actuators. Underactuated control is a possible solution to enhance fault-tolerance of satellites, which enables driving a satellite state with less number of inputs than the number of state. This research has proposed magnetic attitude control method for a spinning satellite that uses only a magnetometer data for the feedback control. Furthermore, optimal fault-tolerant configurations of control moment gyros and thrusters have been derived. The optimal configurations of the actuators maximize the controllability of satellites considering underactuated control. The effectiveness of these proposed methods are numerically verified.
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Report
(4 results)
Research Products
(7 results)
