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dc.contributor.authorKim, J.J.
dc.contributor.authorAgrawal, B.N.
dc.dateJuly 6-11, 2008
dc.date.accessioned2013-07-18T19:18:25Z
dc.date.available2013-07-18T19:18:25Z
dc.date.issued2008
dc.identifier.citation17th IFAC World Congress, July 6-11, Seoul, Korea, 2008.
dc.identifier.urihttp://hdl.handle.net/10945/34522
dc.descriptionThe article of record as published may be found at http://dx.doi.org/10.3182/20080706-5-KR-1001.02040en_US
dc.description.abstractThis paper presents a slew maneuver control design of three-axis rotational flexible spacecraft. The focus of the work is to investigate the nonlinear effect of the three axis maneuver for a flexible spacecraft when a vibration suppression technique for linear systems such as input shaping is used in the control design. A simple method of slewing three-axis rotational spacecraft using input shaping is proposed and the proposed technique is implemented on an experimental three-axis spacecraft simulator. This paper presents a slew maneuver control design of three-axis rotational flexible spacecraft. The focus of the work is to investigate the nonlinear effect of the three axis maneuver for a flexible spacecraft when a vibration suppression technique for linear systems such as input shaping is used in the control design. A simple method of slewing three-axis rotational spacecraft using input shaping is proposed and the proposed technique is implemented on an experimental three-axis spacecraft simulator. This paper presents a slew maneuver control design of three-axis rotational flexible spacecraft. The focus of the work is to investigate the nonlinear effect of the three axis maneuver for a flexible spacecraft when a vibration suppression technique for linear systems such as input shaping is used in the control design. A simple method of slewing three-axis rotational spacecraft using input shaping is proposed and the proposed technique is implemented on an experimental three-axis spacecraft simulator. This paper presents a slew maneuver control design of three-axis rotational flexible spacecraft. The focus of the work is to investigate the nonlinear effect of the three axis maneuver for a flexible spacecraft when a vibration suppression technique for linear systems such as input shaping is used in the control design. A simple method of slewing three-axis rotational spacecraft using input shaping is proposed and the proposed technique is implemented on an experimental three-axis spacecraft simulator.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.titleRest-to-Rest Slew Maneuver of Three-Axis Rotational Flexible Spacecraften_US
dc.contributor.departmentDepartment of Mechanical and Aerospace Engineering


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