Spacecraft optimized arc rocket
OwnerGordon L. Canninventor
Life of this patent
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Abstract
This invention relates to a thruster apparatus applicable to the environment of a space vehicle or satellite and operable for positioning such vehicle or satellite in the proper orbital location. The device utilizes a unique configuration of passageways to convey the propellant to a location adjacent an electrical arc forming device. The propellant, heated thereby, then travels out a nozzle section of the thruster to thereby produce thrust. If desired, an external heater may be provided to preheat the thruster to thereby contribute to greater efficiency in the use of propellant. Further, if desired, the thruster may include an accelerator extension.
Claims4
A thruster apparatus having a longitudinal axis comprising:
- (a) an arc section comprising:
- (i) an elongated cathode;
- (ii) an annular buffer electrode at least partially surrounding said elongated cathode, said buffer electrode comprising an anode;
- (iii) said elongated cathode including a tip spaced from an end of said buffer electrode to thereby define a gap therebetween, and
- (iv) a first flow path for fuel flow including a passageway in said buffer electrode opening in a direction upstream of said gap along said axis;
- (b) an accelerator section comprising:
- (i) a substantially annular anode entirely downstream of said arc section along said axis and being separated from said buffer electrode by an insulating gap of open space, and
- (ii) a second flow path for fuel flow opening into a chamber formed within said accelerator section anode;
- (c) said thruster apparatus further including:
- (i) an accelerating magnet in substantially surrounding relation to said arc section, and
- (ii) a focusing magnet in substantially surrounding relation to said accelerator section.
Dependencies are inferred from the claim text.