Accession Number:

ADA200850

Title:

Design of a kW, DC Magnetically Contained Electrothermal Thruster

Descriptive Note:

Final technical rept. Jul 1986-Jul 1987

Corporate Author:

SEITEC INC CLEVELAND OH

Personal Author(s):

Report Date:

1988-07-01

Pagination or Media Count:

108.0

Abstract:

This effort included 1 the engineering design of a kW thruster, 2 the design andor identification of all the equipment required to test the thruster, and 3 the fabrication of partial shear and containment coils of the thruster to demonstrate the suitability of their design. The resulting nominal 5 kW, completely magnetically contained thruster design has the potential for long operating life and an overall thrust efficiency between 60 and 80 in the specific impulse range of 2000-3000 seconds, i.e., 50-100 higher efficiency than any existing plasma thruster. This novel thruster concept produces thrust by the expansion of hot plasma in a pair of magnetic nozzles. Upstream containment of the plasma is achieved by a stable, stellarator like, magnetic containment system. Plasma heating is accomplished by a DC discharge between the two anodes located inside the magnetic nozzle coils and a downstream hollow cathode which is located on a magnetic field line that passes near the center lines of the anodes. Almost all of the xenon propellant is injected into the discharge through the anodes. The resulting thruster should, based upon the predicted performance, be very attractive for future orbital Air Force electric propulsion applications. Keywords Electric propulsion Plasma, Electrothermal Magnetoplasmadynamic thrusters.

Subject Categories:

  • Electric and Ion Propulsion

Distribution Statement:

APPROVED FOR PUBLIC RELEASE