NASA Logo

NTRS

NTRS - NASA Technical Reports Server

Back to Results
Development of a carbon cloth heat post module for thermal vacuum testing of a spinning spacecraftDevelopment of a high temperature, high power density, isothermal, rapid transient, infrared thermal module is described. The investigation of various alternative approaches is discussed, as well as the rationale leading to the choice of a carbon cloth concept. Evolution of module design configurations and a summary of the development test results are included, along with a detailed description of the final design, which incorporated a black plate emitter radiantly heated by the carbon cloth. The final module configuration met design criteria during a 200-hour thermal vacuum performance test at 1000 F operating temperature without contaminating a solar cell array.
Document ID
19720014636
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Levine, M. B.
(Hughes Aircraft Co. El Segundo, CA, United States)
Nelson, L. A.
(Hughes Aircraft Co. El Segundo, CA, United States)
Date Acquired
August 6, 2013
Publication Date
January 1, 1972
Publication Information
Publication: NASA. Goddard Space Flight Center Space Simulation
Subject Category
Facilities, Research, And Support
Accession Number
72N22286
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
Document Inquiry

Available Downloads

There are no available downloads for this record.
No Preview Available