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dc.contributor.authorH. Chen
dc.contributor.authorAgrawal, B.N.
dc.dateAugust 5-8, 2002
dc.date.accessioned2013-07-18T19:18:20Z
dc.date.available2013-07-18T19:18:20Z
dc.date.issued2002
dc.identifier.citationAIAA Guidance, Navigation, and Control Conference and Exhibition, Monterey, California, August 5-8, 2002.
dc.identifier.urihttp://hdl.handle.net/10945/34487
dc.descriptionThe article of record as published may be found at http://dx.doi.org/10.2514/6.2002-4656en_US
dc.description.abstractThe low-frequency flexible modes of solar arrays on spacecraft are excited by the minimum-time bang-bang control during a slew maneuver. These flexible modes limit the control bandwidth and degrade the pointing error at the end of slew maneuver, resulting in a longer settling time. The objective of this investigation is to develop and verify methods to shape the torque profile of reaction wheels for the slew maneuver such that, at the end of slew, vibration are minimized and the settling time is reduced. Effectiveness of the smooth versine input profiles, torque feedforward, and input shaping are accessed. Both numerical simulation results and ground simulated experimental results are presented in this paper.en_US
dc.rightsThis publication is a work of the U.S. Government as defined
in Title 17, United States Code, Section 101. As such, it is in the
public domain, and under the provisions of Title 17, United States
Code, Section 105, is not copyrighted in the U.S.en_US
dc.titleMethod of Slewing the Spacecraft to Minimize Settling Timeen_US
dc.contributor.departmentDepartment of Mechanical and Aerospace Engineering


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