Session
Technical Session X: Advanced Technologies 1
Abstract
This paper describes a small satellite thermal control architecture based on the multi-evaporator hybrid loop heat pipe (ME-HLHP), a two-phase loop cooling system that combines capillary pumped loop (CPL) and loop heat pipe (LHP) functionalities. The cooling system incorporates multiple heat load sharing evaporators for cooling/heating remote (or nearby) components, dual counter-flow freeze-tolerant condensers for reduced attitude dependence, and miniaturized Teflon wick evaporators for minimum control power. With concomitant functionalities like heat load sharing and thermal diode action, this system can better meet the needs of future extended eclipse/limited power small satellite missions compared to the traditional "cold-biasing plus heater power" approach. Extensive ME-HLHP ground testing has been performed to demonstrate the capabilities of the system for future small satellite missions. This paper will review the design/testing of this and five additional ground-based ME-HLHP cooling systems.
Presentation Slides
Multi-Evaporator Hybrid Two-Phase Loop Cooling System for Small Satellites
This paper describes a small satellite thermal control architecture based on the multi-evaporator hybrid loop heat pipe (ME-HLHP), a two-phase loop cooling system that combines capillary pumped loop (CPL) and loop heat pipe (LHP) functionalities. The cooling system incorporates multiple heat load sharing evaporators for cooling/heating remote (or nearby) components, dual counter-flow freeze-tolerant condensers for reduced attitude dependence, and miniaturized Teflon wick evaporators for minimum control power. With concomitant functionalities like heat load sharing and thermal diode action, this system can better meet the needs of future extended eclipse/limited power small satellite missions compared to the traditional "cold-biasing plus heater power" approach. Extensive ME-HLHP ground testing has been performed to demonstrate the capabilities of the system for future small satellite missions. This paper will review the design/testing of this and five additional ground-based ME-HLHP cooling systems.
