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Temperature Control with Two Parallel Small Loop Heat Pipes for GLM Program
NTRS Full-Text: Click to View  [PDF Size: 1.10 MB]
External Online Source: doi:10.5098/fhp.5.9
Author and Affiliation:
Khrustalev, Dmitry(ATK Space Systems and Services, Beltsville, MD, United States);
Stouffer, Chuck(ATK Space Systems and Services, Beltsville, MD, United States);
Ku, Jentung(NASA Goddard Space Flight Center, Greenbelt, MD, United States);
Hamilton, Jon(Lockheed Martin Space Systems Co., Palo Alto, CA, United States);
Anderson, Mark(Lockheed Martin Space Systems Co., Palo Alto, CA, United States)
Abstract: The concept of temperature control of an electronic component using a single Loop Heat Pipe (LHP) is well established for Aerospace applications. Using two LHPs is often desirable for redundancy/reliability reasons or for increasing the overall heat source-sink thermal conductance. This effort elaborates on temperature controlling operation of a thermal system that includes two small ammonia LHPs thermally coupled together at the evaporator end as well as at the condenser end and operating "in parallel". A transient model of the LHP system was developed on the Thermal Desktop (TradeMark) platform to understand some fundamental details of such parallel operation of the two LHPs. Extensive thermal-vacuum testing was conducted with two thermally coupled LHPs operating simultaneously as well as with only one LHP operating at a time. This paper outlines the temperature control procedures for two LHPs operating simultaneously with widely varying sink temperatures. The test data obtained during the thermal-vacuum testing, with both LHPs running simultaneously in comparison with only one LHP operating at a time, are presented with detailed explanations.
Publication Date: Jan 01, 2014
Document ID:
20150001430
(Acquired Feb 26, 2015)
Subject Category: FLUID MECHANICS AND THERMODYNAMICS
Report/Patent Number: GSFC-E-DAA-TN19620
Document Type: Journal Article
Publication Information: Frontiers in Heat Pipes (FHP) ; Volume 5; No. 9; 013009
Publisher Information: Global Digital Central
Financial Sponsor: NASA Goddard Space Flight Center; Greenbelt, MD United States
National Oceanic and Atmospheric Administration; Highlands, NJ, United States
Organization Source: NASA Goddard Space Flight Center; Greenbelt, MD United States
Description: 10p; In English
Distribution Limits: Unclassified; Publicly available; Unlimited
Rights: Copyright; Distribution as joint owner in the copyright
NASA Terms: TEMPERATURE CONTROL; EVAPORATORS; HEAT PIPES; LOADS (FORCES); HEAT SOURCES; AEROSPACE ENGINEERING; THERMAL ENERGY; VACUUM TESTS; HEAT SINKS; LOOPS; AMMONIA; ACTIVE CONTROL; REDUNDANCY; RELIABILITY
Other Descriptors: TWO-PHASE HEAT TRANSFER; 0000; 0000
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