A spacecraft module, to be integrated with the FLTSATCOM spacecraft, was tested in a simulated orbit environment separate from the host spacecraft. Thermal vacuum testing of the module was accomplished using internal IR heating rather than conventional external heat sources. For this configuration, the technique produced boundary conditions expected for flight to enable verification of system performance and thermal design details.
Thermal testing by internal IR heating of the FEP module
1986-01-01
Aufsatz (Konferenz)
Keine Angabe
Englisch
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