Our proposed innovation is a simple two-phase thermal transport system that's used for temperature control of large, crewed space vehicles. It's innovation lies in the resolution of many anomalies that have plagued previous designs. Based on mixed twophase flow, our system incorporates many innovative features that result in: efficient thermal management with minimal electrical power consumption and minimization of cost by using existing NASA developed hardware. Specifically these innovations include: a simple low power positive displacement pump that provides increased pressure for flow stabilization; a simple, more reliable two-phase accumulator; and, use of already developed evaporator and condenser hardware. This innovation is directly applicable to NASA's subtopic 09.02 for advanced heat transport systems to support human space missions operating at higher loads and more severe environments. It provides the needed stable temperature control, high efficiency and reliable operation that is being sought by NASA.Commercial applications would be government programs that utilize large space platforms requiring very stable thermal interface temperatures for attached payloads. Such opportunities would exist on the space station, EOS programs, as well as any current potential users of capillary pumped loop technology. The latter could be as a subsystem/component supplier to large Aerospace contractors developing advanced platforms for DOD missions. Commercialization activities also involve using the simplified two phase system as a substitute for pumped liquid run-around loops. These run-around loops are typically used in process industries to transfer heat between widely dispersed heat exchangers.
Keywords: Phase_I, NASA, Abstract, FY94
