This content is not included in
your SAE MOBILUS subscription, or you are not logged in.
A Heat Switch for European Mars Rover
Technical Paper
2008-01-2153
ISSN: 0148-7191, e-ISSN: 2688-3627
Annotation ability available
Sector:
Language:
English
Abstract
The future Mars rover thermal design presents a unique challenge to the thermal engineers: the need arises for a thermal control system able to keep rover elements within their operational and non-operational temperature ranges in the face of extreme environmental conditions, characterized by broad day/night temperature excursions, cold biased conditions and long periods in standby modes induced by dust storms.
A thermal device is needed, which allows the removal of excess heat from dissipating units during the Martian day and to keep them above their minimum operational/survival temperature during night. Moreover the scientific goals introduce strict requirements in terms of allowable internal components temperature ranges and thermal stability, which the candidate device has to fulfill against wide-ranging power dissipation modes.
Such a device has been called Variable Thermal Conductance Device, or ‘Heat Switch’. The paper presents a heat switch demonstrator concept, which is based on a Loop Heat Pipe with a temperature-regulating valve.
Heat Switch specifications are reviewed, and the main design characteristics to meet the requirements are explained. The demonstrator has been designed, built and tested for exploring its operational envelope, both versus the Rover functioning modes and the Mars environment.
Test sequence is described in detail, focusing on the methods to characterize the key parameters of the Heat Switch.
Main findings of the demonstrator development activity are summarized, and recommendations for use in an operational mission on Mars are issued.
Authors
Topic
Citation
Molina, M., Franzoso, A., Bursi, A., Fernandez, F. et al., "A Heat Switch for European Mars Rover," SAE Technical Paper 2008-01-2153, 2008, https://doi.org/10.4271/2008-01-2153.Also In
References
- “European Martian Climate Database” http://www-mars.lmd.jussieu.fr
- Sunada E. et al. “Design and Flight Qualification of a Paraffin-Actuated Heat Switch for Mars Surface Applications” ICES 2002 SAE paper 2002-01-2275 .
- Kruzelecky R.V. et al. “Integrated Thin-Film Smart Coatings with Dynamically-Tunable Thermo-Optical Characteristics” ICES 2002 SAE paper 2002-01-2549
- Konstantin A. Goncharov “Precision Temperature Control with a Loop Heat Pipe” ICES 2005 SAE paper 2005-01-2938
- Birur G.C. et al. “Thermal Control of Mars Lander and Rover Batteries and Electronics Using Loop Heat Pipe and Phase Change Material Thermal Storage Technologies” ICES 2000 SAE PAPER 2000-01-2403 .
- Pauken Michael Lankford Kurt Sunada Eric Phillips Charles Novak Keith S. Gajanana C. Birur Design and Flight Qualification of a Paraffin-Actuated Heat Switch for Mars Surface Applications ICES 2002 SAE PAPER 2002-01-2275 .
- Pauken Michael Lankford Kurt Sunada Eric Phillips Charles Novak Keith Birur Gaj Development Testing of a Paraffin-Actuated Heat Switch for Mars Rover Applications ICES 2002 SAE PAPER 2002-01-2273 .
- Nititkin Michael N. Bienert Walter B. Birur Gajanana. C. “Thermal Performance of a Miniature Variable Conductance Loop Heat Pipe” ICES 2000
- Milanez F. H. Mantelli M. B. H. “Recent Studies of a Bi-metallic Heat Switch for Space Applications”, Satellite Thermal Control Laboratory Federal University of Santa Catarina Brazil” AIAA 2001
- Williams R.J. “Transient Shutdown Analysis of Low-Temperature Thermal Diodes” NASA technical paper March 1979
- Anderson W. T. Edwards d. K. Eninger J. E. Marcus B. D. “Variable Conductance Heat Pipes Technology” final report March 1974
- Birur G. Pauken M. Novak K. “Thermal Control of Mars Rovers and Landers using Mini Loop Heat Pipes” JPL and Caltech May 2002
- Shirron Peter J. Di Pirro Michael J. “Passive gas-gap heat switch for adiabatic demagnetization refrigerator” November 1 2005
- Sunada Eric Pauken Mike Lankford Kurt Novak Keith Birur Gajanana “Paraffin Actuated Heat Switch for Mars Surface Applications” Jet Propulsion Laboratory, California Institute of Technology, Starsys Research Corporation February 6 2002
- Sunada Eric Pauken Mike Lankford Kurt Novak Keith Birur Gajanana “Paraffin Actuated Heat Switch for Mars Surface Applications” Jet Propulsion Laboratory, California Institute of Technology, Starsys Research Corporation July 15 2002
- “Starsys Catalog” Thin Plate Heat Switch
- Dillon R. O. Le K. Ianno N. “Thermochromic VO 2 sputtered by control of a vanadium-oxygen emission ratio” University of Nebraska
- Tachikawa S. Ohnish A. Shimakawa Y. Ochi A. Okamoto A. Nakamura Y. “Development of a Variable Emittance Radiator Based on a Perovskite Manganese Oxide” Institute of Space and Astronautical Science Kanagawa NEC Corporation Tokyo NEC TOSHIBA Space System
- Ford V. Parks R. “Shape-Memory-Alloy Thermal-Conduction Switches” Caltech
- Hyman N. L. “Package-interface thermal switch” The United States of America as represented by the Secretary of the Navy July 16 1996
- Cho J. McCarter C. Jiao J. Bahr D. Richards C. Richards R. “Design & characterization of a MEMS thermal Switch” Washington State University Pullman, School of Mechanical and Materials Engineering and Portland State University
- Richards C. Bahr D. Richards B. Jiao Jun Chiang D. “Nanotube based structures for high resolution control of thermal transport” Washington State University; Portland State University; Washington State University Vancouver