Harold R Kaufman, Raymond S Robinson: End-Hall ion source. Hugh H Drake, August 29, 1989: US04862032 (95 worldwide citation)

A gas, ionizable to produce a plasma, is introduced into a region defined within an ion source. An anode is disposed near one end of that region, and a cathode is located near the other. A potential is impressed between the anode and the cathode to produce electrons which flow generally in a directi ...

Todd Foret: System, method and apparatus for lean combustion with plasma from an electrical arc. Foret Plasma Labs, Daniel J Chalker, Edwin S Flores, Chalker Flores, December 13, 2011: US08074439 (79 worldwide citation)

The present invention provides a plasma arc torch that can be used for lean combustion. The plasma arc torch includes a cylindrical vessel, an electrode housing connected to the first end of the cylindrical vessel such that a first electrode is (a) aligned with a longitudinal axis of the cylindrical ...

Scott W Tilley, Tung Y Liu, John S Higham: Spacecraft attitude control and momentum unloading using gimballed and throttled thrusters. Space Systems Loral, Perman & Green, September 20, 1994: US05349532 (46 worldwide citation)

A spacecraft (201) maintains its north-south positioning by using one of two pairs of single-gimballed throttled thrusters (221-224) on a face of the spacecraft (201). The throttles (118) and gimbals (116) of the thrusters (221-224) are controlled to produce torques on the spacecraft (201) that will ...

A Dorian Challoner, Robert L Poeschel: Spacecraft with modulated thrust electrostatic ion thruster and associated method. Hughes Aircraft Company, Steven M Mitchell, Mark J Meltzer, A W Karambelas, May 2, 1989: US04825646 (46 worldwide citation)

An axial electrostatic ion thruster for use on a dual-spin stabilized spacecraft is disclosed. The thruster is mounted on the spun portion of the spacecraft and continuously fired for an integral number of spin periods to provide north-south velocity and attitude control. To achieve zero attitude pr ...

Gordon L Cann: Spacecraft optimized arc rocket. Sherman and Shalloway, March 25, 1986: US04577461 (46 worldwide citation)

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 adjacen ...

Burkhart James A: Magneto-plasma-dynamic arc thruster. The United States of America represented by the Administrator of the, May 29, 1973: US3735591 (42 worldwide citation)

Improving the performance of a magneto-plasma-dynamic arc thruster in the 600 to 2,100 seconds specific impulse range by locating its cathode in the exhaust beam downstream of the anode and main propellant injection point.

John R Beattie, John D Williams, Jesse N Matossian: Ion thruster with long-lifetime ion-optics system. Hughes Electronics Corporation, V D Duraiswamy, M W Sales, July 20, 1999: US05924277 (37 worldwide citation)

Ion erosion of grids is reduced in an ion thruster with a multiple-grid ion-optics system. The thruster has an array of aperture sets in which aperture areas change in a perimeter region of the array. In one ion-optics system embodiment, a screen aperture area is reduced and a decelerator aperture a ...

Dominique Valentian, Alexei Morozov, Antonina Bougrova: Plasma accelerator of short length with closed electron drift. Societe Europeenne de Propulsion, Weingarten Schurgin Gagnebin & Hayes, December 12, 1995: US05475354 (31 worldwide citation)

The system (31 to 33, 34 to 38) for generating a magnetic field in the main channel of the plasma accelerator are adapted to produce, in the main channel (24) an essentially radial magnetic field at the downstream end (225) of the channel (24), its induction being maximum at this point. The magnetic ...

Bernard James Renggli: Split shroud exhaust nozzle. General Electric Company, Adams Evans P A, William Scott Andes, February 13, 2007: US07174704 (30 worldwide citation)

A variable geometry convergent-divergent nozzle for a gas turbine engine includes a centerbody extending rearward along a longitudinal axis of the engine which has a throat section of increased diameter. An inner shroud surrounds the centerbody and cooperates with the centerbody to define the throat ...

Rodney L Burton, Yeshayahu S A Goldstein, Derek A Tidman, Niels K Winsor: Pulsed electrothermal thruster. GT Devices, Lowe Price Leblanc Becker & Shur, April 18, 1989: US04821509 (29 worldwide citation)

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 disc ...