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dc.contributor.authorBhatt, Sagar A.
dc.date.accessioned 2018-06-18T17:58:14Z
dc.date.available 2018-06-18T17:58:14Z
dc.date.issued 2007-05
dc.identifier.citation Bhatt, Sagar A.. "Optimal Reorientation of Spacecraft Using Only Control Moment Gyroscopes." (2007) https://hdl.handle.net/1911/102073.
dc.identifier.urihttps://hdl.handle.net/1911/102073
dc.descriptionThis work was also published as a Rice University thesis/dissertation: http://hdl.handle.net/1911/20489
dc.description.abstract Spacecraft reorientation can require propellant even when using gyroscopes since these have momentum saturation limits at which control is lost until thrusters are fired to desaturate them. To eliminate this need and thereby reduce cost, this work seeks trajectories that avoid saturation altogether by taking advantage of known disturbance torques. This concept is formulated as an optimal control problem and a direct transcription method is applied to obtain numerical solutions. Unlike recent related work on attitude maneuvers and momentum desaturation using only gyroscopes, this thesis allows the full rotational state (attitude, rate, and momentum) at the start and end of the maneuver to be specified. This thesis establishes the viability of this technique, which can potentially extend the operational lifetime of any gyroscope-equipped spacecraft, by successfully demonstrating it in a flight test in which the International Space Station was rotated 90 deg without propellant.
dc.format.extent 110 pp
dc.title Optimal Reorientation of Spacecraft Using Only Control Moment Gyroscopes
dc.type Technical report
dc.date.note May 2007
dc.identifier.digital TR07-08
dc.type.dcmi Text


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