Pulsed electrothermal thruster

Details Pulsed electrothermal thruster Pulsed electrothermal thruster

1987-12-07

1989-04-18

Stout, Donald E.

Power plants

Reaction motor

Electric, nuclear, or radiated energy fluid heating means

60204, F03H 100

Patent

active

048215090

ABSTRACT:
A plasma electrothermal thruster includes a capillary passage in which a plasma discharge is formed and directed out of an open end of the passage into a supersonic nozzle. Liquid supplied to the capillary passage becomes partially atomized to cool a confining surface of the passage. The plasma discharge is formed as the atomized liquid flows out of the open end into a supersonic equilibrium nozzle. The discharge can have a duration greater than the two way travel time of acoustic energy in the capillary to cause the plasma to flow continuously through the nozzle during the time of the discharge pulse.

REFERENCES:
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patent: 3221212 (1965-11-01), Gorowitz et al.
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patent: 3239130 (1966-03-01), Naundorf, Jr.
patent: 3353061 (1967-11-01), Davis
patent: 3360682 (1967-12-01), Moore
patent: 3545208 (1970-12-01), Stark et al.
patent: 3603089 (1971-09-01), Esker
patent: 4577461 (1986-03-01), Cann
Barrere et al., Rocket Propulsion, Elsevier Pub., Co., 3/1960, p. 462.

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