Thruster for spacecraft

Details Thruster for spacecraft Thruster for spacecraft

1992-07-01

1994-06-14

Power plants

Reaction motor

Electric, nuclear, or radiated energy fluid heating means

F03H 100, F03H 500, F02K 1100

Patent

active

053199260

ABSTRACT:
A thruster is described which is utilized, especially among other applications, for the tracking or orbital correction of a spacecraft, which comprises a housing configured as an anode, an expansion nozzle and a rod-shaped electrically insulated cathode centrally retained therein. The cathode is disposed in a combustion chamber into which propellant or propulsive gases are injected. The tip of the cathode is spaced so as to form a small air gap from the constricted cross-section of the nozzle neck. An electric arc is ignited between the anode and the cathode during the gas flow, from which arc the propellant gases receive additional thermal energy.

REFERENCES:
patent: 3359734 (1967-12-01), Ferrie et al.
patent: 3425223 (1969-02-01), Browning
patent: 4577461 (1986-03-01), Cann
patent: 4926632 (1990-05-01), Smith et al.
patent: 5027596 (1991-07-01), Steenborg

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