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.
Claims23
A thruster for use in an extraterrestrial vehicle comprising:
- (a) an outer casing;
- (b) a cathode mounted within said outer casing and having an end;
- (c) an anode mounted within said outer casing and spaced a predetermined distance from said cathode end, said predetermined distance defining a gap in which an arc is formed;
- (d) nozzle means mounted within said outer casing, and
- (e) fuel supply means for supplying propellant fuel to said thruster comprising:
- (i) an inlet conduit extending through said outer casing;
- (ii) first passageway means connecting said inlet conduit with an area within said outer casing adjacent said gap,
- (iii) said first passageway means including a supply conduit extending through said anode and including a portion thereof located upstream of said gap;
- and
- (iv) second passageway means extending from said inlet conduit and bypassing said arc.
Dependencies are inferred from the claim text.