This content is not included in your SAE MOBILUS subscription, or you are not logged in.
High Temperature Mechanically Pumped Fluid Loop for Space Applications –Working Fluid Selection
ISSN: 0148-7191, e-ISSN: 2688-3627
Published July 19, 2004 by SAE International in United States
Annotation ability available
Mechanically pumped single-phase fluid loops are well suited for transporting and rejecting large amounts of waste heat from spacecraft electronics and power supplies. While past implementations of such loops on spacecraft have used moderate operating temperatures (less than 60ºC), higher operating temperatures would allow equivalent heat loads to be rejected by smaller and less massive radiators. A high temperature (100 to 150ºC) mechanically pumped fluid loop is currently being investigated at the Jet Propulsion Laboratory (JPL) for use on future Mars missions. This paper details the trade study used to select the high temperature working fluid for the system and the initial development testing of loop components.
CitationParis, A., Bhandari, P., and Birur, G., "High Temperature Mechanically Pumped Fluid Loop for Space Applications –Working Fluid Selection," SAE Technical Paper 2004-01-2415, 2004, https://doi.org/10.4271/2004-01-2415.
- Lam, L. Birur, G. Bhandari, P. “Pumped Fluid Loops,” Satellite Thermal Control Handbook 2nd edition Gilmore D. Aerospace Corporation El Segundo, California 2002
- Huether, U. Connolly J. M. Christensen P. A. “Apollo Telescope Mount/Thermal Systems Unit: Correlation of Predicted Data and Test Results” Fundamentals of Spacecraft Thermal Design. Progress in Astronautics and Aeronautics Series Cambridge 1971
- “NASA NSTS 1988 News Reference Manual,” http://www.spaceref.com/shuttle/newsref/stsref-toc.html
- Plough, A.H. Pavarani, A.A. “ Overview of the International Space Station Multi-Purpose Logistics Module Active Thermal Control Subsystem Water Pump Package,” SAE 1999-01-2002 , 29th International Conference on Environmental Systems 12–15 July 1999
- Trichilo, M. Gilardi, C. De Palo. S. “The Columbus Orbital Facility Water Loop Qualification,” SAE 1999-01-2001 , 29th International Conference on Environmental Systems 12–15 July 1999
- 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 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 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
- “Mars Science Laboratory Mission 2009 Landed Science Payload, Proposal Information Package,” November 21 2003 http://centauri.larc.nasa.gov/msl/MSLlib.html
- Becker, R.A. “Case Studies in Engineering—Temperature Control of the Galileo Spacecraft,” 18 Feb 1987 Jet Propulsion Laboratory Internal Document Pasadena, CA
- Stultz, J. “Radioisotope Thermoelectric Generator Waste Heat System for the Cassini Propulsion Module” SAE No. 941269 , 24th International Conference on Environmental Systems June 20–23 1994
- “ASHRAE Handbook, Fundamentals,” American Society of Heating, Refrigeration and Airconditioning Engineeers Atlanta 1985
- “Ethylene Glycol Product Information Bulletin,” Union Carbide Corp 1987
- “Therminol®59 Product Information Bulletin,” Solutia, Inc. 2002
- “Syltherm®XLT Product Information Bulletin,” Dow Chemical Co. 2001