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Propulsion System Options for a Potential Sample Return Lander (SRL) for Mars

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dc.contributor.author Vaughan, David
dc.contributor.author Nakazono, Barry
dc.contributor.author Preudhomme, Michael
dc.date.accessioned 2020-05-05T21:11:03Z
dc.date.available 2020-05-05T21:11:03Z
dc.date.issued 2018-05-14
dc.identifier.citation Space Propulsion 2018, Seville, Spain, May 14 - 18, 2018 en_US
dc.identifier.clearanceno 18-2208
dc.identifier.uri http://hdl.handle.net/2014/48270
dc.description.abstract A potential Mars Sample Return (MSR) campaign would be very unique challenge and has been the focus of technology development and planning efforts at JPL for several decades. The latest mission concept study focuses on a potential Sample Return Lander (SRL). The potential SRL examined several propulsion system approaches using monopropellant and bi-propellants for the terminal descent phase. A ranking was developed based on a mathematical optimization program. This paper focuses on the evaluations conducted for these system options. Historically, monopropellant and bi-propellant propulsion systems are usually considered for this application; this study took a fresh look at both conventional State of the Art (SOA) pressure fed monopropellant and bi-propellant propulsion system and augmenting the system using small Electrically Driven Pumps (EDP) for both these propulsion systems. 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, 2018 en_US
dc.title Propulsion System Options for a Potential Sample Return Lander (SRL) for Mars en_US
dc.type Preprint en_US


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