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Thermal-environmental testing of a 30-cm engineering model thrusterAn experimental test program was carried out to document all 30-cm electron bombardment Hg ion bombardment thruster functions and characteristics over the thermal environment of several proposed missions. An engineering model thruster was placed in a thermal test facility equipped with -196 C walls and solar simulation. The thruster was cold soaked and exposed to simulated eclipses lasting in duration from 17 to 72 minutes. The thruster was operated at quarter, to full beam power in various thermal configurations which simulated multiple thruster operation, and was also exposed to 1 and 2 suns solar simulation. Thruster control characteristics and constraints; performance, including thrust magnitude and direction; and structural integrity were evaluated over the range of thermal environments tested.
Document ID
Document Type
Conference Paper
Mirtich, M. J.
(NASA Lewis Research Center Cleveland, Ohio, United States)
Date Acquired
August 9, 2013
Publication Date
November 1, 1976
Subject Category
Spacecraft Propulsion And Power
Report/Patent Number
AIAA PAPER 76-1034
Meeting Information
Meeting: International Electric Propulsion Conference
Location: Key Biscayne, FL
Start Date: November 14, 1976
End Date: November 17, 1976
Sponsors: American Institute of Aeronautics and Astronautics
Accession Number
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