Update on Technology Development Plan for a Low Temperature Hybrid Mars Ascent Vehicle Concept

Karp, Ashley C.; Nakazono, Barry; Vaughan, David; Story, George; Oglesby, Britt; Prince, Andrew

dc.contributor.author	Karp, Ashley C.
dc.contributor.author	Nakazono, Barry
dc.contributor.author	Vaughan, David
dc.contributor.author	Story, George
dc.contributor.author	Oglesby, Britt
dc.contributor.author	Prince, Andrew
dc.date.accessioned	2020-05-13T23:17:21Z
dc.date.available	2020-05-13T23:17:21Z
dc.date.issued	2018-07-09
dc.identifier.citation	2018 AIAA Propulsion and Energy Forum, Cincinnati, Ohio, July 9 - 11, 2018	en_US
dc.identifier.clearanceno	18-3089
dc.identifier.uri	http://hdl.handle.net/2014/48432
dc.description.abstract	Technology development to mature a hybrid rocket option for a potential Mars Ascent Vehicle has been underway at the Jet Propulsion Laboratory and Marshall Space Flight Center. A conceptual design was completed in 2016 and has been used to determine the motor size for risk reduction development. The task plan for the FY17 testing, actually completed in mid FY18, is discussed. The major achievement of this effort was successful full scale hotfire testing with a representative ambient Earth storable propellant combination: SP7/MON3. A near term plan, through July 2019 is briefly discussed.	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	Update on Technology Development Plan for a Low Temperature Hybrid Mars Ascent Vehicle Concept	en_US
dc.type	Preprint	en_US