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Title: Full-size solar dynamic heat receiver thermal-vacuum tests

Conference ·
OSTI ID:5292530

The testing of a full-size, 120 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 conduct period.

Research Organization:
National Aeronautics and Space Administration, Cleveland, OH (United States). Lewis Research Center
OSTI ID:
5292530
Report Number(s):
N-91-25184; NASA-TM-104486; E-6332; NAS-1.15:104486; CONF-910801-
Resource Relation:
Conference: 26. intersociety energy conversion engineering (IECE) conference, Boston, MA (United States), 3-9 Aug 1991; Other Information: Sponsored by the American Nuclear Society, SAE, the American Chemical Society, AIAA, ASME, IEEE, and the American Inst. of Chemical Engineers
Country of Publication:
United States
Language:
English