Optimal Control for Spacecraft Large Angle Maneuvers Using H infinity Linear Varying Parameter Control Techniques

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dc.contributor.advisor Larry Silverberg, Committee Member en_US
dc.contributor.advisor Fen Wu, Committee Chair en_US
dc.contributor.advisor M. K. Ramasubramanian, Committee Member en_US
dc.contributor.author Hughes, Hunter en_US
dc.date.accessioned 2010-04-02T18:02:57Z
dc.date.available 2010-04-02T18:02:57Z
dc.date.issued 2006-12-11 en_US
dc.identifier.other etd-11072006-104331 en_US
dc.identifier.uri http://www.lib.ncsu.edu/resolver/1840.16/1291
dc.description.abstract This study investigates the possibility of designing and implementing a Linear Parameter Varying controller with H infinity performance criteria integrated into the synthesis of the controller for a spacecraft undergoing a large angle maneuver about its principal axes. Towards this end, Cayley-Rodrigues parameters were used to model nonlinear spacecraft dynamics and to ensure up to 180 degerees of rotation about the principal axis without singularities in the system. Several linear parameter varying (LPV) controllers with different parameter ranges were designed and the closed-loop performances were compared with respect to the H infinity upper bound gamma. The optimal gamma value obtained is roughly 0026. Two resulting LPV controllers were then examined through a series of simulations in order to observe both fuel economy and disturbance rejection capabilities for these controllers. The two controllers demonstrated fast response times and good disturbance rejection. It was also found that the controller with the smaller performance level gamma did perform better. Both control systems seemed to show some positive signs of enhanced fuel economy. There was chatter involved with certain aspects of the controller input profiles, but the simulations showed evidence that this was not caused by external disturbance, and can be eliminated by proper selection of weighting functions in the control design process. en_US
dc.rights I hereby certify that, if appropriate, I have obtained and attached hereto a written permission statement from the owner(s) of each third party copyrighted matter to be included in my thesis, dis sertation, or project report, allowing distribution as specified below. I certify that the version I submitted is the same as that approved by my advisory committee. I hereby grant to NC State University or its agents the non-exclusive license to archive and make accessible, under the conditions specified below, my thesis, dissertation, or project report in whole or in part in all forms of media, now or hereafter known. I retain all other ownership rights to the copyright of the thesis, dissertation or project report. I also retain the right to use in future works (such as articles or books) all or part of this thesis, dissertation, or project report. en_US
dc.subject Linear Parameter Varying en_US
dc.subject disturbance rejection en_US
dc.subject Cayley-Rodrigues parameters en_US
dc.subject H_infinity optimization en_US
dc.subject nonlinear control en_US
dc.subject spacecraft controls en_US
dc.subject quaternion en_US
dc.subject modified Rodrigues parameters en_US
dc.title Optimal Control for Spacecraft Large Angle Maneuvers Using H infinity Linear Varying Parameter Control Techniques en_US
dc.degree.name MS en_US
dc.degree.level thesis en_US
dc.degree.discipline Mechanical Engineering en_US


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