Space Station Heat Rejection Subsystem Radiator Assembly Design and Development

Paper #:
  • 951651

Published:
  • 1995-07-01
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.
Pages:
12
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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