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Space Station Heat Rejection Subsystem Radiator Assembly Design and Development
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English
Abstract
The Heat Rejection Subsystem is designed to provide the waste heat rejection for the Active Thermal Control System of the International Space Station Alpha. The design consists of six deployed radiator arrays, each identical, interchangeable and orbital replaceable, which provide the 70 kW heat rejection needs of the two Active Thermal Control System liquid anhydrous ammonia heat transport loops. The radiators are unlatched and deployed remotely without EVA after their carrier structural segment is assembled to the space station in orbit. The radiators are designed to meet the near earth orbit space environments for a 10 year period. These environments include micrometeoroid, space debris and solar energy radiation which degrade materials' and extreme thermal environmental temperatures which can be low enough to freeze the ammonia working fluid. The radiator is designed to be stowed for launch on the Space Shuttle while attached to the mating Space Station segments. These design aspects of the Heat Rejection Subsystem are discussed. The development and qualification testing accomplished to date plus those planned are also discussed.
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Citation
Oren, J. and Howell, H., "Space Station Heat Rejection Subsystem Radiator Assembly Design and Development," SAE Technical Paper 951651, 1995, https://doi.org/10.4271/951651.Also In
References
- Raetz, John Dominick, Jeff “Space Station External Thermal Control System Design and Operational Overview” SAE Paper No. 921106 22nd International Conference on Environmental Systems July 13-16 1992
- Broeren, Robert Duschatko, John “International Space Station Alpha Design-to-Freeze Radiators” SAE Paper No. 951652 25th International Conference on Environmental Systems July 10-13 1995