A three-pulse algorithm for minimum-fuel rotational maneuvers

dc.contributor.advisorGhorbel, Fathi H.en_US
dc.creatorLowry, Nathanen_US
dc.date.accessioned2009-06-04T06:45:43Zen_US
dc.date.available2009-06-04T06:45:43Zen_US
dc.date.issued2004en_US
dc.description.abstractSpacecraft equipped with a Reaction Control System (RCS) for attitude control typically utilize a "bang-off-bang" control algorithm for rotational maneuvers. This type of algorithm, which commands two distinct control periods to initiate and terminate a maneuver, can be fuel-suboptimal for maneuvers in which neither the initial nor the final state is at rest. This work introduces a rotational control algorithm for inertially axisymmetric spacecraft that uses three distinct control periods in order to minimize propellant consumption for large-angle maneuvers with non-trivial initial and final angular rates.en_US
dc.format.extent113 p.en_US
dc.format.mimetypeapplication/pdfen_US
dc.identifier.callnoTHESIS M.E. 2004 LOWRYen_US
dc.identifier.citationLowry, Nathan. "A three-pulse algorithm for minimum-fuel rotational maneuvers." (2004) Master’s Thesis, Rice University. <a href="https://hdl.handle.net/1911/17702">https://hdl.handle.net/1911/17702</a>.en_US
dc.identifier.urihttps://hdl.handle.net/1911/17702en_US
dc.language.isoengen_US
dc.rightsCopyright is held by the author, unless otherwise indicated. Permission to reuse, publish, or reproduce the work beyond the bounds of fair use or other exemptions to copyright law must be obtained from the copyright holder.en_US
dc.subjectAerospace engineeringen_US
dc.subjectMechanical engineeringen_US
dc.titleA three-pulse algorithm for minimum-fuel rotational maneuversen_US
dc.typeThesisen_US
dc.type.materialTexten_US
thesis.degree.departmentMechanical Engineeringen_US
thesis.degree.disciplineEngineeringen_US
thesis.degree.grantorRice Universityen_US
thesis.degree.levelMastersen_US
thesis.degree.nameMaster of Scienceen_US
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