On the design and test of a liquid injection electric thrusterThe design of the thruster described incorporates a coaxial four-segment trigger assembly to discharge a high-energy capacitor. The discharge ablates a waxy perfluorocarbon from the surface of porous annular metal ring, and the resulting plasma is electromagnetically accelerated to ambient producing thrust. Tests revealed a thruster performance well in excess of the major design goals.
Document ID
19740029484
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Youmans, E. H.
Kenney, J. T. (General Electric Co. Philadelphia, Pa., United States)
Dahlgren, J. B. (California Institute of Technology, Jet Propulsion Laboratory, Pasadena Calif., United States)
Date Acquired
August 7, 2013
Publication Date
October 1, 1973
Subject Category
Propulsion Systems
Report/Patent Number
AIAA PAPER 73-1069
Meeting Information
Meeting: Electric Propulsion Conference
Location: Lake Tahoe, NV
Start Date: October 31, 1973
End Date: November 2, 1973
Sponsors: American Institute of Aeronautics and Astronautics