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Solar dynamic heat receiver technologyA full-size, solar dynamic heat receiver was designed to meet the requirements specified for electrical power modules on the U.S. Space Station, Freedom. The heat receiver supplies thermal energy to power a heat engine in a closed Brayton cycle using a mixture of helium-xenon gas as the working fluid. The electrical power output of the engine, 25 kW, requires a 100 kW thermal input throughout a 90 minute orbit, including when the spacecraft is eclipsed for up to 36 minutes from the sun. The heat receiver employs an integral thermal energy storage system utilizing the latent heat available through the phase change of a high-temperature salt mixture. A near eutectic mixture of lithium fluoride and calcium difluoride is used as the phase change material. The salt is contained within a felt metal matrix which enhances heat transfer and controls the salt void distribution during solidification. Fabrication of the receiver is complete and it was delivered to NASA for verification testing in a simulated low-Earth-orbit environment. This document reviews the receiver design and describes its fabrication history. The major elements required to operate the receiver during testing are also described.
Document ID
19910005984
Acquisition Source
Legacy CDMS
Document Type
Contractor Report (CR)
Authors
Sedgwick, Leigh M.
(Boeing Aerospace Co. Seattle, WA, United States)
Date Acquired
September 6, 2013
Publication Date
January 1, 1991
Subject Category
Spacecraft Design, Testing And Performance
Report/Patent Number
NAS 1.26:187040
D180-32598-1
NASA-CR-187040
Accession Number
91N15297
Funding Number(s)
CONTRACT_GRANT: NAS3-24669
PROJECT: RTOP 474-52-10
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
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