This content is not included in
your SAE MOBILUS subscription, or you are not logged in.
Two-Phase Survivable Thermal Management - Heat Acquisition and Transport Components
Annotation ability available
Sector:
Language:
English
Abstract
This paper describes advanced heat acquisition and transport components developed and tested as part of the Two-Phase Survivable Thermal Management (TSTM) Program. The components are: a pumped heat pipe coldplate capable of removing very high-flux waste heat loads with a minimum temperature drop; and a thermal transport system designed to transport large quantities of waste heat over large distances with a long life and low power consumption. These components are intended for use in an advanced thermal control system which removes waste heat from high-power spacecraft.
For the heat acquisition component, a successful design development phase was completed, resulting in a producible design which met program goals. This design was subjected to extensive tests to demonstrate performance under a wide variety of conditions. The component was found to perform in a predictable manner. Measured overall component thermal conductance was 4.0 W/cm2/°C for fluxes up to 60 W/cm2. The device was operated at steady-state heat fluxes up to 100 W/cm2, and was subjected to brief pulse loads up to 200 W/cm2.
For the heat transport component, existing pump and valve designs were substantially modified and a life test using ammonia working fluid was initiated. Design modifications were based on reliability requirements and prior ammonia loop experience. An ammonia life test flow loop was designed and constructed for the life tests. The ongoing tests have uncovered two design deficiencies in the centrifugal pump, which resulted in bearing degradation and failure. Design modifications were implemented, tests were resumed and the modified pump has been continuously operated for over 7500 hours without problems. The regulating valve has been continuously exposed to ammonia for over eighteen months and operated for over 7500 hours without any failures.
Recommended Content
Aerospace Material Specification | Heat Treatment of Wrought Aluminum Alloy Parts |
Technical Paper | Space Station Freedom Carbon Dioxide Removal Assembly Two-Stage Rotary Sliding Vane Pump |
Technical Paper | Closed-Loop CDRA Operation Using a 2-Stage Rotary Sliding Vane Pump: Performance Analysis and Optimization |
Authors
Topic
Citation
Ambrose, J., Tung, J., Feild, A., and Holmes, H., "Two-Phase Survivable Thermal Management - Heat Acquisition and Transport Components," SAE Technical Paper 921035, 1992, https://doi.org/10.4271/921035.Also In
References
- Benner, K. et al. “Two-Phase Survivable Thermal Management” April 1989 September 1990
- Holmes, H.R. Hewitt H.W. Goepp J.W. “Development of the Lockheed Pumped Two-Phase Thermal Bus,” AIAA Paper No. 87-1626 June 1987
- Edelstein, F. Brown R. “Initial Testing of a Two-Phase Thermal Loop,” AIAA Paper No. 86-1296 1986
- Tuckerman, D.B. Pease, R.F.W. “High Performance Heat Sinking for VLSI,” IEEE Electron Device Letters EDL-2 5 May 1981
- Holman, J.P. Ghodbane, M. “Experimental Study of Droplet Heat Transfer Suitable for Cooling of Electronic Equipment,” May 1989
- Tilton, D.E. Pais, M.R. Chow, L.C. “High Power Density Spray Cooling,” July 1989
- Jacobson, D.L. et al. “Analysis and Testing of a Heat Pipe Mirror for Lasers,” AIAA Paper No. 75-719 1975
- Ku, J. Kroliczek E.J. Taylor W.J. McIntosh R. “Functional and Performance Tests of Two Capillary Pumped Loop Engineering Models,” AIAA Paper No. 86-1248 1986
- Fleischman, G. Basiulis A. Gottschlich J. “Advanced Heat Pipe Components for High Power Spacecraft Thermal Management,” AIAA Paper No. 90-0058 1990
- Myron, D.L. Parish R.C. “Development of a Prototype Two-Phase Thermal Bus System for Space Station,” AIAA Paper No. 87-1628
- Department of the Air Force “Standard General Requirements for Safe Design and Operation of Pressurized Missile and Space Systems,” May 1984
- Rome Air Development Center “Nonelectronic Parts Reliability Data” NPRD 3 1985
- Lockheed Missiles & Space Co., Inc. “Nonelectronic (Mechanical) Parts Failure Rates” 1985
- IEEE “IEEE Guide to the Collection of Electrical, Electronic, Sensing Components and Mechanical Equipment Reliability Data for Nuclear Power Generating Stations” IEEE Standard 500-1984 1984
- Brady, T. “Summary of Results from the Testing of Three Prototype Thermal Bus Systems for Space Station Freedom,” AIAA Paper No. 90-1740 1990