| Project/Area Number |
62550048
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| Research Category |
Grant-in-Aid for General Scientific Research (C)
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| Allocation Type | Single-year Grants |
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| Research Field |
Aerospace engineering
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| Research Institution | Tokyo Metropolitan Institute of Technology |
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Principal Investigator |
FUJII Hironori Tokyo Metropolitan Institute of Technology, Department of Aerospace Engineering, Professor., 工学部, 教授 (30070650)
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| Co-Investigator(Kenkyū-buntansha) |
ISHIJIMA Shintaro Tokyo Metropolitan Institute of Technology, Department of Electronic Engineering, 工学部, 教授 (20105208)
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| Project Period (FY) |
1987 – 1989
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| Project Status |
Completed (Fiscal Year 1989)
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| Budget Amount *help |
¥1,900,000 (Direct Cost: ¥1,900,000)
Fiscal Year 1989: ¥200,000 (Direct Cost: ¥200,000)
Fiscal Year 1988: ¥400,000 (Direct Cost: ¥400,000)
Fiscal Year 1987: ¥1,300,000 (Direct Cost: ¥1,300,000)
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| Keywords | Large Space Structures(LSS) / Slew Maneuver / Vibration Suppression / Deployment / Retrieval of Subsatellite / Mission-Function Control / 大型宇宙構造物(LS滓) / スルー・マヌーバ |
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| Research Abstract |
A control algorithm, the Mission-Function Control, is introduced in order to deal successfully with the Problem inherent in dynamics and control of the large flexible space structures(LFSS). Dynamics of the LFSS is most precisely described by the distributed parameter system combined with the concentrated sensors/actuators. Often noted are such difficulty for implementation of control algorithms on LFSS as spillover effect since of too sophisticated application of the existing control algorithms to the LFSS model described by the usual modal expansion method. The Mission-Function Control algorithm is the Liapunov method and derived through inspection of such dynamical feature of the LFSS as the nonlinear and distributed parameter system. The algorithm is successfully applied to 1) control of deployment and retrieval of a subsatellite connected to a main body through a tether, and 2) slew maneuver to slew a space structure for a large angle of attitude with least suppression on the flexural vibration of the flexible structures. The Mission-Function algorithm is also experimentally demonstrated and verified its validity on a slew maneuver of a flexible space structure model. Results of the numerical and experimental analysis confirm preferable features of the Mission-Function control algorithm applied to control of the LFSS and assure the excellent performance of the Mission-Function control.
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