In order to insure optimal operation of sensitive electronic devices in space, it is essential to have a dependable thermal control system to regulate their operating temperature. A Miniaturized Loop Heat Pipe (mini-LHP) can provide this function without many of the restrictions of conventional thermal control measures. Traditional techniques such as thermal straps and shunts, conventional heat pipes, mechanically pumped loops, and are oftentimes not readily scalable to small satellite applications and can impose large mass penalties, complicate system integration, and limit pre-launch system-level tests. This paper describes the effort performed by Swales Aerospace to design and verify the performance of next generation miniature LHPs. This work was performed for NASA Goddard Space Flight Center and was devoted to the development of a reliable miniaturized dual-evaporator and dual-condenser LHP that is prototypical of a centralized thermal bus for a small satellite. The focus of design and development was maximization of performance parameters such as heat transport and overall conductance, while minimizing auxiliary power requirements, total system mass, and integration constraints. The design description of the mini-LHP as well as a detailed discussion of test results is included in this paper. Test results show that mini-LHP offers robust, reliable performance and stable operation throughout its entire required operational range.
|Publication status||Published - 2005|
|Event||19th Annual AIAA/USU Conference on Small Satellites: Key to the future? - Utah State University, Logan, United States|
Duration: 8 Aug 2005 → 11 Aug 2005
Conference number: 19
|Conference||19th Annual AIAA/USU Conference on Small Satellites|
|Period||8/08/05 → 11/08/05|