A three-pulse algorithm for minimum-fuel rotational maneuvers

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dc.contributor.advisorGhorbel, Fathi H.
dc.creatorLowry, Nathan
dc.date.accessioned2009-06-04T06:45:43Z
dc.date.available2009-06-04T06:45:43Z
dc.date.issued2004
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.
dc.format.extent113 p.en_US
dc.format.mimetypeapplication/pdf
dc.identifier.callnoTHESIS M.E. 2004 LOWRY
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>.
dc.identifier.urihttps://hdl.handle.net/1911/17702
dc.language.isoeng
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.
dc.subjectAerospace engineering
dc.subjectMechanical engineering
dc.titleA three-pulse algorithm for minimum-fuel rotational maneuvers
dc.typeThesis
dc.type.materialText
thesis.degree.departmentMechanical Engineering
thesis.degree.disciplineEngineering
thesis.degree.grantorRice University
thesis.degree.levelMasters
thesis.degree.nameMaster of Science
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