Thermal Design of the Mars Science Laboratory Powered Descent Vehicle

Paris, Anthony; Fisher, Melanie; Kelly, F. P.; Hernandez, Brenda; Dudik, Brenda; Krylo, Robert; Bhandari, Pradeep

doi:10.4271/2008-01-2001

Cited by 4 publications

(3 citation statements)

References 7 publications

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“…The MSL rover utilizes a mechanically pumped, single-phase fluid loop heat rejection system (HRS) to create the backbone for thermal control 8,9,10,11,12,13,14 . The fluid loop uses chlorofluorocarbon-11 (CFC-11) as the working fluid.…”

Section: Rover Thermal Architecturementioning

confidence: 99%

CO2 Insulation for Thermal Control of the Mars Science Laboratory

Bhandari

Karlmann

Anderson

et al. 2011

41st International Conference on Environmental Systems

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Section: Rover Thermal Architecturementioning

confidence: 99%

CO2 Insulation for Thermal Control of the Mars Science Laboratory

Bhandari

Karlmann

Anderson

et al. 2011

41st International Conference on Environmental Systems

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“…Papers about the overall thermal architecture of the entire spacecraft (including the Cruise Stage, Descent Stage and Rover) have been previously published. [1][2][3][4][5] The MSL rover is designed to last an entire Martian year (669 Sols). The Rover is capable of landing in a wide range of latitudes (± 30 degrees) on Mars.…”

Section: A Msl Rovermentioning

confidence: 99%

Mars Science Laboratory Rover Actuator Thermal Design

Novak

Liu

Lee

et al. 2010

40th International Conference on Environmental Systems

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NASA will launch a 950 kg rover, part of the Mars Science Laboratory (MSL) mission, to Mars in October of 2011. The MSL rover is scheduled to land on Mars in August of 2012. The rover employs 31 electric-motor driven rotary actuators to perform a variety of engineering and science functions including: mobility, camera pointing, telecommunications antenna steering, soil and rock sample acquisition and sample processing. This paper describes the MSL rover actuator thermal design. The actuators have stainless steel housings and planetary gearboxes that are lubricated with a "wet" lubricant. The lubricant viscosity increases with decreasing temperature. Warm-up heaters are required to bring the actuators up to temperature (above-55ºC) prior to use in the cold wintertime environment of Mars (when ambient atmosphere temperatures are as cold as-113ºC). Analytical thermal models of all 31 MSL actuators have been developed. The actuators have been analyzed and warm-up heaters have been designed to improve actuator performance in cold environments. Thermal hardware for the actuators has been specified, procured and installed. This paper presents actuator thermal analysis predicts, and describes the actuator thermal hardware and its operation. In addition, warm-up heater testing and thermal model correlation efforts for the Remote Sensing Mast (RSM) elevation actuator are discussed.

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“…Cruise HRS Routing.An integrated pump assembly is located on the Cruise Stage and produces a flow rate of up to 1.5 liters per minute within the loop. The cooled fluid exiting the last radiator is routed to a series of heat exchanger plates on the Cruise Stage, Descent Stage, and Rover to remove waste heat from components that are powered during the cruise phase of the mission14 .…”

mentioning

confidence: 99%

Mars Science Laboratory Launch Pad Thermal Control

Bhandari

Dudik

Birur

et al. 2011

41st International Conference on Environmental Systems

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NASA is planning to send a large (>850 kg) rover as part of the Mars Science Laboratory (MSL) mission to Mars in 2011. The rover is powered by a Multi-mission Radioisotope Thermoelectric Generator (MMRTG), which generates about 2000 W of heat that is converted to about 110 W of electrical power for use by the rover electronics and science payload. The presence of the high thermal power MMRTG in the descent stage leads to difficult and interesting thermal problems in terms of maintaining the temperatures of the sensitive rover electronics, payload and the descent stage propulsion components within their allowable flight limits. A mechanically pumped single phase heat rejection system (HRS) using CFC-11 as the working fluid is employed to maintain the MMRTG temperature within reasonable levels by picking up its waste heat and rejecting it to the HRS radiators in the cruise stage. These radiators are cooled by the launch vehicle fairing air conditioning (A/C) system. This paper will describe the challenges faced in accommodating the warm MMRTG during the pre-launch phases of integration, launch pad operations as well as during launch. Predictions of temperatures during these phases will be presented when all the cooling systems (HRS and A/C) are operational. In-air tests conducted on the spacecraft in December 2008 to simulate the launch conditions were very successful and showed that all components would be within their allowable limits during these phases. Results of these tests will be shared in this paper.

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Thermal Design of the Mars Science Laboratory Powered Descent Vehicle

Cited by 4 publications

References 7 publications

CO2 Insulation for Thermal Control of the Mars Science Laboratory

CO2 Insulation for Thermal Control of the Mars Science Laboratory

Mars Science Laboratory Rover Actuator Thermal Design

Mars Science Laboratory Launch Pad Thermal Control

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