Design of a three-axis stabilized ORION satellite using an all-thruster attitude control system
dc.contributor.advisor | Titus, Harold A. | |
dc.contributor.author | Dee, Suzanne M. | |
dc.date | December 1988 | |
dc.date.accessioned | 2012-11-27T18:17:10Z | |
dc.date.available | 2012-11-27T18:17:10Z | |
dc.date.issued | 1988 | |
dc.identifier.uri | https://hdl.handle.net/10945/23169 | |
dc.description.abstract | An all-thruster three-axis stabilized attitude control system has been designed for the Naval Postgraduate School (NPS) satellite bus, ORION. The satellite is a cylinder, 19 inches in diameter, 35 inches in length, 250 pounds maximum mass with 32 pounds for payloads. ORION will be ejected from an extended Get-Away-Special (GAS) canister. Launch from any GAS can configure expendable booster or the space shuttle is assumed. The minimization techniques of Pontryagin have been used to derive control laws that support fuel efficient operation. A minimum time cost function is applied in the acquisition phase to reduce rates to acceptable levels. A weighted minimum fuel-time cost function is used during the on-station phase. Bang-Off-Bang control with two switching curves is employed outside of a boundary region. Inside the boundary region, four pulse limit cycle control with time constants on the order of 100 seconds is applied | en_US |
dc.description.uri | http://archive.org/details/designofthreeaxi1094523169 | |
dc.format.extent | 107 p.: 28 cm. | en_US |
dc.language.iso | en_US | |
dc.rights | This publication is a work of the U.S. Government as defined in Title 17, United States Code, Section 101. Copyright protection is not available for this work in the United States. | en_US |
dc.title | Design of a three-axis stabilized ORION satellite using an all-thruster attitude control system | en_US |
dc.type | Thesis | en_US |
dc.contributor.secondreader | Burl, Jeffrey | |
dc.contributor.department | Department of Electrical and Computer Engineering | |
dc.subject.author | Satellite | en_US |
dc.subject.author | Lightsat | en_US |
dc.subject.author | Orion | en_US |
dc.subject.author | Naval Postgraduate School | en_US |
dc.subject.author | Three axis stabilization | en_US |
dc.subject.author | All- thruster attitude control | en_US |
dc.subject.author | Get away special | en_US |
dc.description.service | Lieutenant, United States Navy | en_US |
etd.thesisdegree.name | M.S. in Electrical Engineering | en_US |
etd.thesisdegree.level | Masters | en_US |
etd.thesisdegree.discipline | Electrical Engineering | en_US |
etd.thesisdegree.grantor | Naval Postgraduate School | en_US |
dc.description.distributionstatement | Approved for public release; distribution is unlimited. |
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