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A mechanical, thermal and electrical packaging design for a prototype power management and control system for the 30 cm mercury ion thrusterA prototype Electric Power Management and Thruster Control System for a 30 cm ion thruster has been built and is ready to support a first mission application. The system meets all of the requirements necessary to operate a thruster in a fully automatic mode. Power input to the system can vary over a full two to one dynamic range (200 to 400 V) for the solar array or other power source. The Power Management and Control system is designed to protect the thruster, the flight system and itself from arcs and is fully compatible with standard spacecraft electronics. The system is designed to be easily integrated into flight systems which can operate over a thermal environment ranging from 0.3 to 5 AU. The complete Power Management and Control system measures 45.7 cm x 15.2 cm x 114.8 cm and weighs 36.2 kg. At full power the overall efficiency of the system is estimated to be 87.4 percent. Three systems are currently being built and a full schedule of environmental and electrical testing is planned.
Document ID
Document Type
Conference Paper
Sharp, G. R.
(NASA Lewis Research Center Cleveland, OH, United States)
Gedeon, L.
(NASA Lewis Research Center Cleveland, OH, United States)
Oglebay, J. C.
(NASA Lewis Research Center Cleveland, OH, United States)
Shaker, F. S.
(NASA Lewis Research Center Cleveland, OH, United States)
Siegert, C. E.
(NASA Lewis Research Center Cleveland, Ohio, United States)
Date Acquired
August 9, 2013
Publication Date
April 1, 1978
Subject Category
Spacecraft Propulsion And Power
Report/Patent Number
Meeting Information
Meeting: International Electric Propulsion Conference
Location: San Diego, CA
Country: US
Start Date: April 25, 1978
End Date: April 27, 1978
Sponsors: American Institute of Aeronautics and Astronautics, Deutsche Gesellschaft fuer Luft- und Raumfahrt
Accession Number
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