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In-flight propulsion system characterization for both Mars Exploration Rover Spacecraft

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dc.contributor.author Barber, Todd J.
dc.contributor.author Picha, Frank Q.
dc.date.accessioned 2006-04-12T18:31:08Z
dc.date.available 2006-04-12T18:31:08Z
dc.date.issued 2004-07-11
dc.identifier Joint Propulsion Conference and Exhibit, Fort Lauderdale, Florida, July 11-14, 2004.
dc.identifier.citation Joint Propulsion Conference and Exhibit, Fort Lauderdale, Florida, July 11-14, 2004. en
dc.identifier.clearanceno 04-1511
dc.identifier.uri http://hdl.handle.net/2014/39129
dc.description.abstract Two Mars Exploration Rover spacecraft were dispensed to red planet in 2003, culminating in a phenomenally successful prime science mission. Twin cruise stage propulsion systems were developed in record time, largely through heritage with Mars Pathfinder. As expected, consumable usage was minimal during the short seven-month cruise for both spacecraft. Propellant usage models based on pressure and temperature agreed with throughput models with in a few percent. Trajectory correction maneuver performance was nominal, allowing the cancellation of near-Mars maneuvers. Spin thruster delivered impulse was 10-12% high vs. ground based models for the intial spin-down maneuvers, while turn performance was XX-XX% high/low vs. expectations. No clear indications for pressure transducer drift were noted during the brief MER missions. en
dc.description.sponsorship NASA/JPL en
dc.format.extent 1250188 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 Cassini Project en
dc.subject mission operations en
dc.subject performances en
dc.subject monopropellants en
dc.subject cruise stage en
dc.subject schematic en
dc.subject maneuvers en
dc.title In-flight propulsion system characterization for both Mars Exploration Rover Spacecraft en
dc.type Preprint en


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