Enhanced Performance Evaporative Heat Sinks for Space Applications

Paper #:
  • 981779

Published:
  • 1998-07-13
Citation:
Calayag, B., Buchmann, O., Pickup, H., Rose, S. et al., "Enhanced Performance Evaporative Heat Sinks for Space Applications," SAE Technical Paper 981779, 1998, https://doi.org/10.4271/981779.
Pages:
7
Abstract:
An evaporative heat sink has been designed and built by AlliedSignal for NASA's Johnson Space Center. The unit is a demonstrator of a primary heat exchanger for NASA's prototype Crew Return Vehicle (CRV), designated the X-38. The primary heat exchanger is responsible for rejecting the heat produced by both the flight crew and the avionics. Spacecraft evaporative heat sinks utilize space vacuum as a resource to control the vapor pressure of a liquid. For the X-38, water has been chosen as the heat transport fluid. A portion of this coolant flow is bled off for use as the evaporant. At sufficiently low pressures, the water can be made to boil at temperatures approaching its freezing point. Heat transferred to liquid water in this state will cause the liquid to evaporate, thus creating a heat sink for the spacecraft's coolant loop. The CRV mission requires the heat exchanger to be compact and low in mass. The unit must operate over as much as a 9 hour mission duration with a 3 year docked lifetime. These design specifications led to the selection of a plate-fin, parallel flow heat exchanger as a prototype. This paper summarizes the pertinent design considerations for this type of heat exchanger and discusses the test results obtained to date.
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