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Conceptual Design of the Space Station Polar Platform Thermal Control Subsystem
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Abstract
NASA's Space Station Freedom Program encompasses unmanned polar-orbiting platforms (POPs) in low-earth orbit (LEO) designed to support a variety of scientific and earth-observation missions. The platforms are modular in design, permitting in-orbit maintenance and replacement of limited-life subsystem and payload components. Such in-orbit servicing can extend the platform's useful life to 15 years or more, far exceeding that of a typical LEO spacecraft. The long life and modular design has forced a new approach to thermal control subsystem (TCS) design. The platform's TCS must be readily adaptable to, and compatible with, the physical reconfiguration and resultant heat load changes. NASA has, in fact, identified thermal management as a critical factor in the overall platform design.
A dual approach was used for the current polar platform TCS design. Platform thermal control is maintained using a distributed network of heat pipe panels, while payload thermal control is maintained via a centralized system of two-phase capillary pumped loops. This paper describes this baseline platform thermal design and the analytical tools used to validate the design concepts.
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Bond, H., Benko, D., Chalmers, D., and Pergament, S., "Conceptual Design of the Space Station Polar Platform Thermal Control Subsystem," SAE Technical Paper 891461, 1989, https://doi.org/10.4271/891461.Also In
References
- “Trade Study of Two-Phase Heat Transport Technologies,” 1986 NASA Space Station WP-03 Advanced Development Program, Task 3 For Advanced Thermal Management Systems
- Braun C. E. et al. “Thermal Design of the Space Station Free-Flying Platforms,” AIAA-88-2698
- Ku J. et al. “Functional and Performance Test of Two Capiliary Pumped Loop Engineering Models,” A1AA-86-1248
- Ku J. et al. “A Hybrid Capillary Pumped Loop,” SAE- 88-1083
- Ku J. et al. “Capillary Pumped Loop GAS and Hitchhiker Flight Experiments,” AIAA-86-1249
- Chalmers D. et al. “Design of a Two-Phase Capillary Pumped Flight Experiment,” SAE- 88-1086
- Chalmers D. et al. “Capillary Pumped Loop Systems Concepts for Application on Space Platforms,” Fourth International Heat Pipe Conference 1987
- Fredley J. et al “A Low Pressure Drop Heat Exchanger With Integral Heat Pipe,” ASME National Heat Transfer Conference 1988
- Thermal Radiation Analyzer System (TRASYS) User's Manual, Version P22 Lockheed Engineering and Management Service Company April 1988
- Cullimore B. et al. SINDA’85/FLUINT Systems Improved Numerical Differencing Analyzer and Fluid Integrator User's Manual Martin Marietta Corporation November 1987