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Supersonic Retropropulsion on Robotic Mars Landers: Selected Design Trades

Show simple item record Wolf, Aron A. Noyes, Connor Strauss, William Benito, Joel Lobbia, Marcus McCann, John Nakazono, Barry Putnam, Zachary R. Lorenz, Christopher G. 2020-05-26T15:57:28Z 2020-05-26T15:57:28Z 2018-08-19
dc.identifier.citation AAS/AIAA Astrodynamics Specialist Conference, Snowbird, Utah, August 19 - 23, 2018 en_US
dc.identifier.clearanceno 18-4380
dc.description.abstract Many concepts for future robotic Mars lander missions require landing heavier payloads than those landed to date. Mars lander architectures to date have relied on a parachute to help slow the lander; however the effectiveness of a parachute in the thin Martian atmosphere is diminished with heavier payloads unless the diameter of the parachute is increased or it is deployed at a higher Mach number, both of which are significant technical challenges. In addition the parachute can be successfully deployed only within a specific Mach number and dynamic pressure range. Targeting the entry trajectory to hit this “Mach-Q box” imposes constraints on the entry ballistic coefficient, limiting it to ~ 150-200 kg/m^2. Eliminating the parachute from the design requires descent engine ignition at supersonic speeds (Supersonic Retropropulsion, or SRP). SRP increases the propellant requirement, but also allows entry ballistic coefficients of ~600 kg/m^2 or more, with the consequence of significantly increased entry mass and landed payload mass. 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 Supersonic Retropropulsion on Robotic Mars Landers: Selected Design Trades en_US
dc.type Preprint en_US

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