| dc.contributor.author | Morgül, Ömer | en_US |
| dc.coverage.spatial | Honolulu, HI, USA | en_US |
| dc.date.accessioned | 2016-02-08T12:02:28Z | |
| dc.date.available | 2016-02-08T12:02:28Z | |
| dc.date.issued | 1990 | en_US |
| dc.identifier.issn | 0191-2216 | en_US |
| dc.identifier.uri | http://hdl.handle.net/11693/27827 | |
| dc.description | Date of Conference: 5-7 December 1990 | en_US |
| dc.description | Conference Name: 29th IEEE Conference on Decision and Control, IEEE 1990 | en_US |
| dc.description.abstract | We 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.iso | English | en_US |
| dc.source.title | Proceedings of the 29th IEEE Conference on Decision and Control, IEEE 1990 | en_US |
| dc.relation.isversionof | https://www.doi.org/10.1109/CDC.1990.203623 | en_US |
| dc.subject | Control Systems | en_US |
| dc.subject | Mechanical Variables | en_US |
| dc.subject | Equations of motion | en_US |
| dc.subject | System stability | en_US |
| dc.subject | Orientation control | en_US |
| dc.subject | Planar motion | en_US |
| dc.subject | Rigid motions | en_US |
| dc.subject | Spacecraft | en_US |
| dc.title | Orientation and control of a flexible spacecraft: planar motion | en_US |
| dc.type | Conference Paper | en_US |
| dc.department | Department of Electrical and Electronics Engineering | en_US |
| dc.citation.spage | 393 | en_US |
| dc.citation.epage | 394 | en_US |
| dc.identifier.doi | 10.1109/CDC.1990.203623 | en_US |
| dc.publisher | IEEE | en_US |
