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Variable Specific Impulse Magnetoplasma Rocket EngineAn engine is disclosed, including a controllable output plasma generator, a controllable heater for selectably raising a temperature of the plasma connected to an outlet of the plasma generator, and a nozzle connected to an outlet of the heater, through which heated plasma is discharged to provide thrust. In one embodiment, the source of plasma is a helicon generator. In one embodiment, the heater is an ion cyclotron resonator. In one embodiment, the nozzle is a radially diverging magnetic field disposed on a discharge side of the heater so that helically travelling particles in the beater exit the heater at high axial velocity. A particular embodiment includes control circuits for selectably directing a portion of radio frequency power from an RF generator to the helicon generator and to the cyclotron resonator so that the thrust output and the specific impulse of the engine can be selectively controlled. A method of propelling a vehicle is also disclosed. The method includes generating a plasma, heating said plasma, and discharging the heated plasma through a nozzle. In one embodiment, the nozzle is a diverging magnetic field. In this embodiment, the heating is performed by applying a radio frequency electro magnetic field to the plasma at the ion cyclotron frequency in an axially polarized DC magnetic field.
Document ID
20020038753
Acquisition Source
Johnson Space Center
Document Type
Other - Patent
External Source(s)
MSC-23041-1
Authors
Franklin R Chang-Diaz
(Johnson Space Center Houston, United States)
Date Acquired
August 20, 2013
Publication Date
January 1, 2002
Publication Information
Publisher: United States Patent and Trademark Office
Subject Category
Spacecraft Propulsion And Power
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
Patent
US-Patent-6,334,302
Patent Application
US-Patent-Appl-SN-351152
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