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Full-size solar dynamic heat receiver thermal-vacuum testsThe testing of a full-size, 102 kW, solar dynamic heat receiver utilizing high-temperature thermal energy storage is described. The purpose of the test program was to quantify receiver thermodynamic performance, operating temperatures, and thermal response to changes in environmental and power module interface boundary conditions. The heat receiver was tested in a vacuum chamber with liquid nitrogen cold shrouds and an aperture cold plate to partly simulate a low-Earth-orbit environment. The cavity of the receiver was heated by an infrared quartz lamp heater with 30 independently controllable zones to allow axially and circumferentially varied flux distributions. A closed-Brayton cycle engine simulator conditioned a helium-xenon gas mixture to specific interface conditions to simulate the various operational modes of the solar dynamic power module on the Space Station Freedom. Inlet gas temperature, pressure, and flow rate were independently varied. A total of 58 simulated orbital cycles, each 94 minutes in duration, was completed during the test period.
Document ID
Document Type
Conference Paper
Sedgwick, L. M.
(NASA Lewis Research Center Cleveland, OH, United States)
Kaufmann, K. J.
(Boeing Aerospace and Electronics Seattle, WA, United States)
Mclallin, K. L.
(NASA Lewis Research Center Cleveland, OH, United States)
Kerslake, T. W.
(NASA Lewis Research Center Cleveland OH, United States)
Date Acquired
August 15, 2013
Publication Date
January 1, 1991
Subject Category
Spacecraft Propulsion And Power
Meeting Information
Meeting: IECEC ''91: Intersociety Energy Conversion Engineering Conference
Location: Boston, MA
Country: United States
Start Date: August 4, 1991
End Date: August 9, 1991
Accession Number
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