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Temperature Oscillation in a Loop Heat Pipe with Gravity AssistATLAS Laser Thermal Control System (LTCS) thermal vacuum testing where the condenser-radiator was placed in a vertical position, it was found that the loop heat pipe (LHP) reservoir required much more control heater power than the analytical model had predicted. The required control heater power was also higher than the liquid subcooling entering the reservoir using the measured temperatures and the calculated mass flow rate based on steady state LHP operation. This presentation describes the investigation of the LHP behaviors under a gravity assist mode with a very cold radiator sink temperature and a large thermal mass attached to the evaporator. It is concluded that gravity caused the cold liquid to drop from the condenser-radiator to the reservoir, resulting in a rapid decrease of the reservoir temperature. When the reservoir temperature was increasing, a reverse flow occurred in the liquid line, carrying warm liquid to the condenser-radiator. Both events consumed the reservoir control heater power. The fall and rise of the reservoir temperature also caused the net heat input to the evaporator to vary due to the release and storage of the sensible heat of the thermal mass. The combination of these effects led to a persistent reservoir temperature oscillation and a repeated influx of cold liquid from the condenser. This was the root cause of the extraordinary high control heater power requirement in the LTCS TV test. Without gravity assist, such a persistent temperature oscillation will not be present.
Document ID
20140005700
Acquisition Source
Goddard Space Flight Center
Document Type
Presentation
Authors
Ku, Jentung
(NASA Goddard Space Flight Center Greenbelt, MD United States)
Garrison, Matt
(NASA Goddard Space Flight Center Greenbelt, MD United States)
Patel, Deepak
(NASA Goddard Space Flight Center Greenbelt, MD United States)
Ottenstein, Laura
(NASA Goddard Space Flight Center Greenbelt, MD United States)
Robinson, Frank
(NASA Goddard Space Flight Center Greenbelt, MD United States)
Date Acquired
May 13, 2014
Publication Date
March 25, 2014
Subject Category
Fluid Mechanics And Thermodynamics
Report/Patent Number
GSFC-E-DAA-TN13402
Report Number: GSFC-E-DAA-TN13402
Meeting Information
Meeting: 2014 Spacecraft Thermal Control Workshop
Location: El Segundo, CA
Country: United States
Start Date: March 25, 2014
End Date: March 27, 2014
Sponsors: Aerospace Corp.
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
Keywords
000
000
Two-Phase Heat Transfer
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