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In response to the identified needs of emerging high power spacecraft applications, a multiple evaporator Hybrid Loop Heat Pipe (H-LHP) was developed and tested as part of a Dual Use Science and Technology (DUS&T) program co-sponsored by ATK and AFRL/PRP. During the course of the DUS&T program, a two-kilowatt system with three evaporators was developed and tested to identify viable system architectures and characterize system performance capabilities as a function of heat load profiles and spatial distribution of the evaporators. Following the successful development of the two-kilowatt system, a 10-kilowatt system with six evaporators was fabricated and tested. Tests were performed with the system operating in a totally passive, capillary-pumped mode, where applying a small amount of power to a sweepage evaporator provides the auxiliary flow through the primary evaporators, and as a self-regulating, capillary-controlled mechanically pumped system.

The Capillary Pumped Loop (CAPL) Flight Experiment has undergone numerous design modifications to reflect recent changes in the thermal control system baselined for Earth Observation System (EOS) spacecraft. The experiment redesign has also allowed technological advances in two-phase fluid loop components to be incorporated. The experiment's reservoir is one of the components targeted for redesign. The design and development of a new reservoir for the CAPL Flight Experiment is discussed in this paper. A prototype reservoir is described, and a hydrodynamic analysis of its wick structure is included. Testing of the prototype reservoir is also discussed.