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Microthrust propulsion of the LISA mission

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dc.contributor.author Ziemer, John K.
dc.contributor.author Merkowitz, Stephen M.
dc.date.accessioned 2006-11-28T19:45:18Z
dc.date.available 2006-11-28T19:45:18Z
dc.date.issued 2004-07-12
dc.identifier.citation 40th AIAA Joint Propulsion Conference, Fort Lauderdale, Florida, July 12-14, 2004 en
dc.identifier.clearanceno 04-2221
dc.identifier.uri http://hdl.handle.net/2014/40025
dc.description.abstract We present the most recent propulsion requirements for the Laser Interferometer Space Antenna (LISA) Mission and describe potential microthruster technology that can meet these requirements. LISA consists of three spacecraft in heliocentric orbits, forming a triangle with 5x10(to the 6th power) km sides that are the arms of three Michelson-type interferometers. Reflective proof masses provide the reference surfaces at the end of the interferometer arms as part of the Gravitational Reference Sensor (GRS) designed to detect gravitational waves. The microthrust propulsion system will be part of the Disturbance Reduction System (DRS), which is responsible for maintaining each spacecraft position within approximately 10 nm around the proof masses. en
dc.description.sponsorship NASA/JPL en
dc.format.extent 3850122 bytes
dc.format.mimetype application/pdf
dc.language.iso en_US en
dc.publisher Pasadena, CA : Jet Propulsion Laboratory, National Aeronautics and Space Administration, 2004. en
dc.subject electric propulsion en
dc.subject colloid thrusters en
dc.subject Field Emission Electric Propulsion (FEEP) en
dc.subject Laser Interferometer Space Antenna (LISA) en
dc.subject Space Technology 7 Disturbance Reduction System (ST7-DRS) en
dc.subject formation flying
dc.subject precision cold-gas microthrusters
dc.title Microthrust propulsion of the LISA mission en
dc.type Preprint en


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