Analysis and simulation of dynamics of spacecraft power systems

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dc.contributor.authorLee, Jae Ryongen
dc.contributor.committeecochairCho, Bo H.en
dc.contributor.committeecochairLee, Freden
dc.contributor.committeememberRahman, Saifuren
dc.contributor.committeememberTam, Kwa Suren
dc.contributor.committeememberJohnson, Lee W.en
dc.contributor.departmentElectrical Engineeringen
dc.date.accessioned2015-06-24T13:35:13Zen
dc.date.available2015-06-24T13:35:13Zen
dc.date.issued1988en
dc.description.abstractComprehensive analyses, including dc, small-signal and large-signal analyses, of the dynamics of various spacecraft power systems are performed. Systems' dynamics are analyzed for various operating modes, such as the shunt, battery-charge and battery-discharge modes, as well as the transition mode. Computer models using the EASY5 program are developed for the Direct Energy Transfer (DET) system, solar array switching system and partial shunt system to facilitate design, analysis and performance verification. Large-signal analyses are performed to identify stability conditions and to predict large-signal dynamic behavior for each mode of operation. The equivalent source and load characteristics of a solar array power system with a constant-power load, shunt regulator, battery charger and discharger, are identified to predict large-signal dynamic behavior. Employing the equivalent source and load, the state trajectories of shunt failure, battery discharger failure and solar array/battery lockup are predicted and verified through time-domain simulations. Small-signal analyses of the DET system are performed for the three modes of operation. The system loop gain is defined. Design guidelines for the feedback control loop of the shunt regulator, battery charger and discharger are developed to shape the system loop gain for the optimum bus dynamic performance and stability of the system. Designed subsystems are simulated both in frequency-domain and time-domain to verify the design concept. Various spacecraft power systems, such as solar array switching systems, a partial shunt system, a peak power tracking system and the COBE (Cosmic Background Explorer) power system are analyzed and simulated. Design guidelines of the power conditioning equipment for each system are provided.en
dc.description.degreePh. D.en
dc.format.extentvi, 212 leavesen
dc.format.mimetypeapplication/pdfen
dc.identifier.urihttp://hdl.handle.net/10919/53568en
dc.language.isoen_USen
dc.publisherVirginia Polytechnic Institute and State Universityen
dc.relation.isformatofOCLC# 19258028en
dc.rightsIn Copyrighten
dc.rights.urihttp://rightsstatements.org/vocab/InC/1.0/en
dc.subject.lccLD5655.V856 1988.L4435en
dc.subject.lcshElectric power systems -- Testingen
dc.subject.lcshSpace vehicles -- Electric equipmenten
dc.titleAnalysis and simulation of dynamics of spacecraft power systemsen
dc.typeDissertationen
dc.type.dcmitypeTexten
thesis.degree.disciplineElectrical Engineeringen
thesis.degree.grantorVirginia Polytechnic Institute and State Universityen
thesis.degree.leveldoctoralen
thesis.degree.namePh. D.en

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