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dc.contributor.advisorAgrawal, B.N.
dc.contributor.authorMcClelland, Robert S.
dc.dateMarch, 1994
dc.date.accessioned2013-04-11T21:53:32Z
dc.date.available2013-04-11T21:53:32Z
dc.date.issued1994-03
dc.identifier.urihttp://hdl.handle.net/10945/30554
dc.description.abstractMany current satellites employ on-off thrusters to accomplish attitude control tasks which may include initial acquisition, rotational maneuvers, and on-orbit stabilization. This work shows that the use of pulse- width pulse-frequency (PWPF)-modulated thrusters provides several important advantages over conventional bang- bang thruster control methods, including less thruster activity and closer-to-linear actuation. The PWPF modulator is implemented in simulations using the Matrix/System build software package. Simulations assuming a rigid spacecraft are first performed to compare the performance of the PWPF-modulated thrust controller with that of conventional bang-bang and time-optimal bang-bang controllers. The discussion is then extended to the case of a spacecraft with structural flexibility, as is encountered quite often in three-axis stabilized vehicles with large fold-out solar arrays. Simulations for comparison of the controllers are performed using the flexible spacecraft dynamics model. The control loop design in the presence of flexibility and possible interaction with the PWPF modulator nonlinearity are addressed. Using a describing function model of the modulator, stability margin with respect to the structural mode limit cycle is predicted. Simulations are then conducted to verify the predicted stability margin.en_US
dc.description.urihttp://archive.org/details/spacecraftttitud1094530554
dc.format.extent95 p.;28 cm.en_US
dc.language.isoen_US
dc.publisherMonterey, California. Naval Postgraduate Schoolen_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, may not be copyrighted.en_US
dc.titleSpacecraft attitude control system performance using pulse-width pulse-frequency modulated thrustersen_US
dc.title.alternativeNAen_US
dc.typeThesisen_US
dc.contributor.departmentMechanical Engineering
dc.subject.authorNAen_US
dc.description.funderNAen_US
dc.description.recognitionNAen_US
dc.description.serviceNaval Research Laboratory author (civilian).en_US
etd.thesisdegree.nameM.S. in Mechanical Engineeringen_US
etd.thesisdegree.levelMastersen_US
etd.thesisdegree.disciplineMechanical Engineeringen_US
etd.thesisdegree.grantorNaval Postgraduate Schoolen_US


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