Prototype thermal bus for manned Space Station compartmentsA summary is presented of NASA efforts, to February 1986, on development of an advanced thermal bus for manned spacecraft. Design details are described for a prototype to be tested in 1987 that includes a contact heat exchanger, an air cooling heat exchanger for manned cabin conditions, and an interface heat exchanger for transferring compartment heat loads to the Space Station Central Thermal Bus. The design and performance criteria defined for the thermal bus are outlined and results are reported from comparisons of the capabilities and operational costs of pumped water and two-phase evaporating/condensing heat transport concepts. The operating temperature, launch weight/thermal performance ratios, and power requirements of each concept are discussed, along with the critical technologies identified for use of a water/titanium two-phase thermal bus.
Document ID
19870045394
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Zentner, Ronald C. (Boeing Aerospace Co. Seattle, WA, United States)
Owen, James W. (NASA Marshall Space Flight Center Huntsville, AL, United States)