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Two Dimensional Heat Transfer around Penetrations in Multilayer InsulationThe objective of this task was to quantify thermal losses involving integrating MLI into real life situations. Testing specifically focused on the effects of penetrations (including structural attachments, electrical conduit/feedthroughs, and fluid lines) through MLI. While there have been attempts at quantifying these losses both analytically and experimentally, none have included a thorough investigation of the methods and materials that could be used in such applications. To attempt to quantify the excess heat load coming into the system due to the integration losses, a calorimeter was designed to study two dimensional heat transfer through penetrated MLI. The test matrix was designed to take as many variables into account as was possible with the limited test duration and system size. The parameters varied were the attachment mechanism, the buffer material (for buffer attachment mechanisms only), the thickness of the buffer, and the penetration material. The work done under this task is an attempt to measure the parasitic heat loads and affected insulation areas produced by system integration, to model the parasitic loads, and from the model produce engineering equations to allow for the determination of parasitic heat loads in future applications. The methods of integration investigated were no integration, using a buffer to thermally isolate the strut from the MLI, and temperature matching the MLI on the strut. Several materials were investigated as a buffer material including aerogel blankets, aerogel bead packages, cryolite, and even an evacuated vacuum space (in essence a no buffer condition).
Document ID
20120017916
Acquisition Source
Kennedy Space Center
Document Type
Technical Publication (TP)
Authors
Johnson, Wesley L.
(NASA Kennedy Space Center Cocoa Beach, FL, United States)
Kelly, Andrew O.
(NASA Kennedy Space Center Cocoa Beach, FL, United States)
Jumper, Kevin M.
(Sierra Lobo, Inc. Kennedy Space Center, FL, United States)
Date Acquired
August 25, 2013
Publication Date
October 1, 2012
Subject Category
Fluid Mechanics And Thermodynamics
Report/Patent Number
NASA/TP-2012-216315
Distribution Limits
Public
Copyright
Public Use Permitted.
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