Show simple item record

dc.contributor.authorMorgül, Ömeren_US
dc.coverage.spatialHonolulu, HI, USAen_US
dc.date.accessioned2016-02-08T12:02:28Z
dc.date.available2016-02-08T12:02:28Z
dc.date.issued1990en_US
dc.identifier.issn0191-2216en_US
dc.identifier.urihttp://hdl.handle.net/11693/27827
dc.descriptionDate of Conference: 5-7 December 1990en_US
dc.descriptionConference Name: 29th IEEE Conference on Decision and Control, IEEE 1990en_US
dc.description.abstractWe consider a flexible spacecraft modeled as a rigid body which rotates in an inertial frame; a light flexible beam is clamped to the rigid body at one end and free at the other end. We assume that the flexible spacecraft performs only planar motions. We pose two control problems; namely, the orientation and the stabilization of the system. It is shown that suitable boundary controls applied to the free end of the beam and suitable control torques applied to the rigid body solve the problems posed above.en_US
dc.language.isoEnglishen_US
dc.source.titleProceedings of the 29th IEEE Conference on Decision and Control, IEEE 1990en_US
dc.relation.isversionofhttps://www.doi.org/10.1109/CDC.1990.203623en_US
dc.subjectControl Systemsen_US
dc.subjectMechanical Variablesen_US
dc.subjectEquations of motionen_US
dc.subjectSystem stabilityen_US
dc.subjectOrientation controlen_US
dc.subjectPlanar motionen_US
dc.subjectRigid motionsen_US
dc.subjectSpacecraften_US
dc.titleOrientation and control of a flexible spacecraft: planar motionen_US
dc.typeConference Paperen_US
dc.departmentDepartment of Electrical and Electronics Engineeringen_US
dc.citation.spage393en_US
dc.citation.epage394en_US
dc.identifier.doi10.1109/CDC.1990.203623en_US
dc.publisherIEEEen_US


Files in this item

Thumbnail

This item appears in the following Collection(s)

Show simple item record