Mars Science Laboratory Descent Stage Propulsion tubing configuration and design

JPL is in the process of designing the next rover to be sent to the surface of Mars. The landing scheme for this mission requires the development of a Descent Stage (DS) in order to perform a "skycrane" maneuver. The Descent Stage carries all the fuel and flight controls for the entry, des...

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Bibliographic Details
Published in2009 IEEE Aerospace conference pp. 1 - 10
Main Authors Etters, Andy, Rober, Mark, Lee, Darlene, Guernsey, Carl, Long, Michael, Knopp, Mike
Format Conference Proceeding
LanguageEnglish
Published IEEE 01.03.2009
Subjects
Aerospace control
Assembly systems
Control systems
Fuels
Helium
Laboratories
Mars
Pressure control
Process design
Propulsion
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Summary:JPL is in the process of designing the next rover to be sent to the surface of Mars. The landing scheme for this mission requires the development of a Descent Stage (DS) in order to perform a "skycrane" maneuver. The Descent Stage carries all the fuel and flight controls for the entry, descent and landing (EDL) phase of this mission. The Descent Stage propulsion system is a pressure-fed monopropellant system that consists of two helium tanks, three propellant tanks, eight Mars Landing Engines (MLE), eight Reaction Control System (RCS) thrusters, one pressure control assembly and three propellant control assemblies. The propulsion tubing ranges in size from ¼ inch to 1-¼ inch outer diameter, consists of stainless steel and titanium tubes, and has a total length of approximately 120 feet. This paper will explore and discuss the steps taken to place the major components and tubing of the propulsion system, the required structural analysis of the system, and the testing setups to validate the analysis.
ISBN:1424426219
9781424426218
ISSN:1095-323X
2996-2358
DOI:10.1109/AERO.2009.4839587