This content is not included in
your SAE MOBILUS subscription, or you are not logged in.
Thermal Design of the Mars Science Laboratory Powered Descent Vehicle
Technical Paper
2008-01-2001
ISSN: 0148-7191, e-ISSN: 2688-3627
Annotation ability available
Sector:
Language:
English
Abstract
NASA's Mars Science Laboratory mission will use a Powered Descent Vehicle to accurately and safely land a roving, robotic laboratory on the surface of Mars. The precision landing systems employed on this vehicle are exposed to a wide range of mission environments from deep space cruise to atmospheric descent and require a robust and adaptable thermal design. This paper discusses the overall thermal design philosophy of the MSL Powered Descent Vehicle and presents analysis of the active and passive elements comprising the Cruise, Entry, Descent, and Landing thermal control systems.
Authors
- Anthony D. Paris - Jet Propulsion Laboratory, California Institute of Technology
- Melanie L. Fisher - Jet Propulsion Laboratory, California Institute of Technology
- Frank P. Kelly - Jet Propulsion Laboratory, California Institute of Technology
- Brenda J. Hernandez - Jet Propulsion Laboratory, California Institute of Technology
- Brenda A. Dudik - Jet Propulsion Laboratory, California Institute of Technology
- Robert J. Krylo - Jet Propulsion Laboratory, California Institute of Technology
- Pradeep Bhandari - Jet Propulsion Laboratory, California Institute of Technology
Citation
Paris, A., Fisher, M., Kelly, F., Hernandez, B. et al., "Thermal Design of the Mars Science Laboratory Powered Descent Vehicle," SAE Technical Paper 2008-01-2001, 2008, https://doi.org/10.4271/2008-01-2001.Also In
References
- Prakash R. et al. “Mars Science Laboratory Entry, Descent, and Landing System Overview” IEEE Aerospace Conference Big Sky, MT March 1-8, 2008
- Edquist K.T. et al. “Mars Science Laboratory Entry Capsule Aerothermodynamics and Thermal Protection System,” Aerospace Conference, 2007 IEEE Big Sky, MT 1 13 March 3-10, 2007
- Tracey T.R. Morey T.F. “Thermal Design of the Viking Lander Capsule,” AIAA 12th Aerospace Sciences Meeting Washington D.C. January 30-February 1, 1974
- Bhandari P. Birur G.C. Gram M.B. “Mechanical Pumped Cooling Loop for Spacecraft Thermal Control,” SAE Technical Paper No. 961488 26th International Conference on Environmental Systems Monterey, California July 8-11, 1996
- Ganapathi G.B et al. “Active Heat Rejection System on Mars Exploration Rover – Design Changes from Mars Pathfinder” Space Technology Applications International Forum 2003 Albuquerque, NM February 2-5, 2003
- Tsuyuki G. et al. “The Hardware Challenges for the Mars Exploration Rover Heat Rejection System,” AIP Conference Proceedings 699 1 59 70 February 4, 2004
- Bhandari P. Birur G. Prina M. Ramirez B. Paris A.D. Novak K. Pauken M. “Pumped Fluid Loop Heat Rejection & Recovery Systems for Thermal Control of the Mars Science Laboratory,” 17th Spacecraft Thermal Control Workshop El Segundo, CA March 16, 2006
- Bhandari P. Birur G. Pauken M. Paris A.D. Novak K. Prina M. Ramirez B. Bame D. “Mars Science Laboratory Thermal Control Architecture,” Proc. of 35th International Conference on Environmental Systems (ICES) Rome, Italy July 11-15, 2005
- Incropera F.P. DeWitt D.P. “Introduction to Heat Transfer,” 2nd John Wiley & Sons New York 1990
- Bennington J. et al. “Phoenix Flight System Thermal Control,” Critical Design Review Document Lockheed Martin Aerospace November 29 2005