Gabriel F Benavides

US Patent:

7926257, Apr 19, 2011

Filed:

Jul 22, 2008

Appl. No.:

12/177217

Inventors:

Rodney L. Burton - Champaign IL, US
Gabriel F. Benavides - Champaign IL, US
Julia K. Laystrom - Champaign IL, US

Assignee:

CU Aerospace, LLC - Champaign IL

International Classification:

F03H 1/00
H05H 1/00

US Classification:

60202, 31511121

Abstract:

A pulsed plasma thruster provides for an advanced lightweight design with solid propellant and predominately electromagnetic thrust in a coaxial geometry. Electromagnetic forces are generated in a plasma by current flowing from a small central electrode to an electrically conducting diverging nozzle electrode. The thruster employs a series of electric current pulses of limited duration and varying frequency between the pair of electrodes creating a series of electric arcs. The electric arcs pass over a propellant surface located between the electrodes, forming a plasma, which is then exhausted from the device to produce thrust. The thruster maintains a low plasma resistance and cavity pressure, which in turn yields strong electromagnetic body forces, resulting in a high efficiency and consistent pulse-to-pulse performance.

US Patent:

7926258, Apr 19, 2011

Filed:

Jul 22, 2008

Appl. No.:

12/177244

Inventors:

Rodney L. Burton - Champaign IL, US
Gabriel F. Benavides - Champaign IL, US
Julia K. Laystrom - Champaign IL, US

Assignee:

CU Aerospace, LLC - Champaign IL

International Classification:

F03H 1/00
H05H 1/00

US Classification:

60202, 31511121

Abstract:

A pulsed plasma thruster provides for an advanced lightweight design with solid propellant and predominately electromagnetic thrust in a coaxial geometry. Electromagnetic forces are generated in a plasma by current flowing from a small central electrode to an electrically conducting diverging nozzle electrode. The thruster employs a series of electric current pulses of limited duration and varying frequency between the pair of electrodes creating a series of electric arcs. The electric arcs pass over a propellant surface located between the electrodes, forming a plasma, which is then exhausted from the device to produce thrust. The thruster maintains a low plasma resistance and cavity pressure, which in turn yields strong electromagnetic body forces, resulting in a high efficiency and consistent pulse-to-pulse performance.

US Patent:

7530219, May 12, 2009

Filed:

Jul 25, 2005

Appl. No.:

11/188536

Inventors:

Rodney Burton - Champaign IL, US
Gabriel Benavides - Champaign IL, US
Julia Laystrom - Champaign IL, US

Assignee:

Cu Aerospace, LLC - Champaign IL

International Classification:

F03H 1/00

US Classification:

602031, 60202

Abstract:

A pulsed plasma thruster provides for an advanced lightweight design with solid propellant and predominately electromagnetic thrust in a coaxial geometry. Electromagnetic forces are generated in a plasma by current flowing from a small central electrode to an electrically conducting diverging nozzle electrode. The thruster employs a series of electric current pulses of limited duration and varying frequency between the pair of electrodes creating a series of electric arcs. The electric arcs pass over a propellant surface located between the electrodes, forming a plasma, which is then exhausted from the device to produce thrust. The thruster maintains a low plasma resistance and cavity pressure, which in turn yields strong electromagnetic body forces, resulting in a high efficiency and consistent pulse-to-pulse performance.