Coupled Attitude And Orbital Control System Using Spacecraft Simulators

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dc.contributor.authorLennox, Scott Evanen
dc.contributor.committeechairHall, Christopher D.en
dc.contributor.committeememberWoolsey, Craig A.en
dc.contributor.committeememberSchaub, Hanspeteren
dc.contributor.departmentAerospace and Ocean Engineeringen
dc.date.accessioned2011-08-06T16:02:33Zen
dc.date.adate2004-07-16en
dc.date.available2011-08-06T16:02:33Zen
dc.date.issued2004-02-25en
dc.date.rdate2004-07-16en
dc.date.sdate2004-07-13en
dc.description.abstractTranslational and rotational motion are coupled for spacecraft performing formation flying missions. This motion is coupled because orbital control is dependent on the spacecraft attitude for vectored thrust. Formation flying spacecraft have a limited mass and volume for propulsion systems. We want to maximize the efficiency of the spacecraft, which leads to minimizing the error introduced by thrusting in the wrong direction. This thrust direction error leads to the need for a coupled attitude and orbital control strategy. In this thesis a coupled control system is developed using a nonlinear Lyapunov attitude controller and a nonlinear Lyapunov-based orbital controller. A nonlinear Lyapunov attitude controller is presented for a spacecraft with three-axis momentum wheel control. The nonlinear Lyapunov-based orbital controller is combined with a mean motion control strategy to provide a globally asymptotically stable controller. The attitude and orbit control laws are verified separately using numerical simulation, and then are integrated into a coupled control strategy. The coupled system simulations verify that the coupled control strategy is able to correct for an initial relative position error between two spacecraft.en
dc.description.degreeMaster of Scienceen
dc.format.mediumETDen
dc.identifier.otheretd-07132004-161249en
dc.identifier.sourceurlhttp://scholar.lib.vt.edu/theses/available/etd-07132004-161249en
dc.identifier.urihttp://hdl.handle.net/10919/10003en
dc.publisherVirginia Techen
dc.relation.haspartSEL_thesis_etd.pdfen
dc.rightsIn Copyrighten
dc.rights.urihttp://rightsstatements.org/vocab/InC/1.0/en
dc.subjectOrbital Controlen
dc.subjectSpacecraften
dc.subjectAttitude Controlen
dc.subjectCoupled Controlen
dc.titleCoupled Attitude And Orbital Control System Using Spacecraft Simulatorsen
dc.typeThesisen
thesis.degree.disciplineAerospace and Ocean Engineeringen
thesis.degree.grantorVirginia Polytechnic Institute and State Universityen
thesis.degree.levelmastersen
thesis.degree.nameMaster of Scienceen

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