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A micro Newton impulse-bit hydrazine thruster - design, test and mission applications

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dc.contributor.author Parker, J. Morgan
dc.contributor.author Lewis, James R.
dc.date.accessioned 2019-05-15T22:33:31Z
dc.date.available 2019-05-15T22:33:31Z
dc.date.issued 2016-05-16
dc.identifier.citation 63rd JANNAF Propulsion Meeting, Newport News, Virginia, May 16-20, 2016 en_US
dc.identifier.clearanceno 16-1662
dc.identifier.uri http://hdl.handle.net/2014/46092
dc.description.abstract Recent and numerous failures of reaction wheels have cut short and/or limited the mission functions of several spacecraft including DAWN, Mars Odyssey, and Kepler among others. A micro Newton impulse-bit hydrazine thruster has the potential to backup or even replace reaction wheels on most missions, thereby extending mission life. This paper will discuss the development and test of a plug-and-play hydrazine thruster with 30 – 130 milliNewton thrust levels, and impulse bits < 50 microNewton-sec. In addition, this paper will address mission applications that include backup for, or even replacement of reaction wheels, delta-V thrust for CubeSats, and primary attitude control for the 20 – 50 kg class of spacecraft. en_US
dc.description.sponsorship NASA/JPL en_US
dc.language.iso en_US en_US
dc.publisher Pasadena, CA: Jet Propulsion Laboratory, National Aeronautics and Space Administration, 2016 en_US
dc.title A micro Newton impulse-bit hydrazine thruster - design, test and mission applications en_US
dc.type Preprint en_US


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