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Microgravity heat pump for space station thermal management.

R E Domitrovic1, F C Chen, V C Mei

  • 1Systems Development Institute, University of Tennessee, Knoxville, TN, USA.

Habitation (Elmsford, N.Y.)
|November 25, 2003
PubMed
Summary
This summary is machine-generated.

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A new heat pump design for spacecraft, like the International Space Station, was developed to reduce radiator size. This gravity-independent system demonstrated high efficiency and temperature lift, crucial for space applications.

Area of Science:

  • Spacecraft thermal management
  • Vapor compression heat pumps

Background:

  • Spacecraft require efficient thermal management systems, often relying on large radiative heat rejection panels.
  • Reducing the size of these panels is critical for mission design and mass savings.

Purpose of the Study:

  • To develop and test a gravity-independent vapor compression heat pump for spacecraft.
  • To maximize temperature lift and operational efficiency for reduced radiator size.

Main Methods:

  • Two heat pump iterations (LBU-I and LBU-II) were designed and tested using commercially available components.
  • Experiments simulated microgravity by being orientation-independent, varying parameters like inlet temperatures and compressor speed.
  • Evaluated functionality, efficiency (Coefficient of Performance - COP), and temperature lift.

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Main Results:

  • The LBU-II system, featuring a direct-drive compressor and plate heat exchangers, outperformed the LBU-I system.
  • Achieved a COP of 4.5 +/- 10% and a temperature lift of 55°F (30.6°C) +/- 10%.
  • Maximum temperature lift significantly reduces potential radiator area, with efficiency playing a secondary role.

Conclusions:

  • The developed heat pump technology is suitable for spacecraft thermal management.
  • High temperature lift and efficiency are key to significantly reducing radiative heat rejection panel size.
  • The LBU-II design shows promise for future space missions, optimizing thermal control and reducing mass.