This content is not included in your SAE MOBILUS subscription, or you are not logged in.
A Two-Phase Thermal Management System for Large Spacecraft
ISSN: 0148-7191, e-ISSN: 2688-3627
Published July 01, 1985 by SAE International in United States
Annotation ability available
Spacecraft have previously used passive cooling or pumped liquid loops to maintain proper thermal environments. Future large spacecraft, such as the Space Station, will have higher power levels and longer heat transport distances. To better meet these requirements, a two-phase thermal bus concept has evolved which includes a thermal transport loop with controlled temperature and pressure. A two-phase cooling system has the advantages over a single-phase system of lower mass flows, lower pumping power requirements, and operation at nearly isothermal conditions, since heat is transferred by evaporation and condensation.
The system employs an electrically-driven pitot pump to supply a controlled flow of nearly saturated liquid to any arrangement of series or parallel evaporators. The rotary fluid management device (RFMD) provides the evaporator flow, centrifugally separates the two-phase flow returning from the evaporator, recirculates flow to the condenser, resaturates subcooled liquid, and separates and collects noncondensible gases. Constant saturation conditions within the RFMD are maintained by a simple backpressure regulator. An external accumulator communicating with the RFMD maintains constant liquid level in the RFMD during system turndown.
Test results presented have been obtained with an RFMD, control regulator and accumulator, which are functionally identical to a flight system. Flight prototypic designs for the RFMD and backpressure regulating valve (BPRV) have been generated and are described.
|Ground Vehicle Standard
|Test Method for Measuring Performance of Engine Cooling Fans
|A Two-Phase Fluid Pump for Use in Microgravity Environments
|Energy Efficient Actuation Using Variable Displacement Hydraulic Control
CitationBland, T., Downing, R., and Rogers, D., "A Two-Phase Thermal Management System for Large Spacecraft," SAE Technical Paper 851351, 1985, https://doi.org/10.4271/851351.
- Bland, T.J. Downing, R.S. Rogers, D.P. “A Two-Phase Thermal Management System for Large Space Platforms.” AIAA-84-1758
- Bland, T.J. Rogers, D.P. “A Two-Phase Thermal Management System for the Space Station.” SAE 841525
- Niggemann, R.E. Greenlee, W.J. Hill, D.G. Ellis, W. Marshall, P. “A Swirl Flow Evaporative Cold Plate.” AIAA-85-0920