Thermal Control of the Mars Science Laboratory Spacecraft Propellant Lines -- Design Architecture and Analytical Modeling

Abstract

In 2012, NASA’s Mars Science Laboratory spacecraft will use two separate propulsion systems to safely land a roving, robotic laboratory on the surface of Mars. During deep space transit, a Cruise Stage propulsion system will be used to orient the spacecraft and perform trajectory correction maneuvers. Prior to Mars entry, descent, and landing, a Descent Stage propulsion system will be used to position the spacecraft for ballistic entry, provide thrust for closed-loop guidance maneuvers, and decelerate the entry body for soft landing of the payload. The thermal design of the propellant transfer lines on the spacecraft is complicated by both the exposure of the lines to extreme and highly variable thermal environments and a limitation on available electrical power for survival heating. This paper presents an overview of the thermal design architecture and analytical thermal modeling employed in the design of the Mars Science Laboratory propellant line thermal control.