1
Dan Miller
Daniel N Miller, Patrick J Yagle, Kerry B Ginn, Jeffrey W Hamstra: Method and apparatus of asymmetric injection into subsonic flow of a high aspect ratio/complex geometry nozzle. Lockheed Martin Corporation, Koesnter Bertani, November 8, 2005: US06962044 (5 worldwide citation)

The present invention reveals a method and apparatus for controlling the effective area and thrust vector angle of a fluid flow. In one embodiment, the fluid flow is controlled in an advanced, high aspect ratio, complex aperture geometry nozzle using asymmetric injection into the subsonic portion of ...


2
Dan Miller
Jeffrey W Hamstra, Daniel N Miller, Kerry B Ginn: System, method, and apparatus for pulsed-jet-enhanced heat exchanger. Lockheed Martin Corporation, Bracewell & Giuilani, April 2, 2013: US08408281

A pulsed-jet active flowfield control actuation system enhances the rate of heat transfer and heat removal in a heat exchanger for better management of thermal loads. The pulsed jet actuators impart an unsteady component of velocity to the working fluid of the heat exchanger. This design increases t ...


3
Dan Miller
Rob S Burgun, Kerry B Ginn, Daniel N Miller: System, method, and apparatus for control input prediction and state verification of fluidic vectoring exhaust in high performance aircraft. Lockheed Martin Corporation, Bracewell & Giuliani, November 29, 2011: US08065868

A non-invasive system, method, and apparatus for control input prediction and state verification of an aircraft's fluidic vectoring exhaust is disclosed. The control system derives a desired vector state, then predicts and sets the fluidic injection input required to produce the desired vector state ...


4
Dan Miller
Rob S Burgun, Kerry B Ginn, Daniel N Miller: System, method, and apparatus for control input prediction and state verification of fluidic vectoring exhaust in high performance aircraft. Bracewell & Giuliani, June 26, 2008: US20080149742-A1

A non-invasive system, method, and apparatus for control input prediction and state verification of an aircraft's fluidic vectoring exhaust is disclosed. The control system derives a desired vector state, then predicts and sets the fluidic injection input required to produce the desired vector state ...


5
Dan Miller
Jeffrey W Hamstra, Daniel N Miller, Kerry B Ginn: System, method, and apparatus for pulsed-jet-enhanced heat exchanger. Lockheed Martin Corporation, Bracewell & Giuliani, April 16, 2009: US20090095446-A1

A pulsed-jet active flowfield control actuation system enhances the rate of heat transfer and heat removal in a heat exchanger for better management of thermal loads. The pulsed jet actuators impart an unsteady component of velocity to the working fluid of the heat exchanger. This design increases t ...


6
Brian R Smith, Daniel N Miller, Patrick J Yagle, Erich E Bender, Kerry B Ginn: Method and system of pulsed or unsteady ejector. Lockheed Martin Corporation, William N Hulsey III, Hughes & Luce L, October 30, 2001: US06308740 (25 worldwide citation)

The present invention reveals a method and apparatus for more efficiently injecting a primary fluid flow in a fluid ejector used to pump lower velocity fluid from a secondary source. In one embodiment, the primary fluid flow is a pulsed or unsteady fluid flow contained within an inner nozzle situate ...


7
David M Wells, Brent N McCallum, Kerry B Ginn, Stewart A Jenkins: System and apparatus for vectoring nozzle exhaust plume from a nozzle. Lockheed Martin Corporation, Bracewell & Giuliani, February 12, 2013: US08371104 (2 worldwide citation)

A vectoring nozzle with external actuation generates thrust vectoring by applying mechanical or fluidic actuation, or both, on the nozzle deck, external sidewalls, and/or air vehicle aft body to produce changes in the aft body flowfield and/or exhaust plume. An external mechanical sidewall may be in ...


8
Kerry B Ginn, Stewart A Jenkins, David M Wells, Brent N McCallum: Nozzle plasma flow control utilizing dielectric barrier discharge plasma actuators. Lockheed Martin Corporation, Bracewell & Giuliani, June 4, 2013: US08453457 (1 worldwide citation)

Dielectric barrier discharge plasma actuators are used to manipulate exhaust flow within and behind a jet engine nozzle. The dielectric barrier discharge plasma actuators may be used to direct cooling airflow near the surface of the nozzle to reduce heating of the nozzle, create thrust vectoring, an ...


9
Kerry B Ginn, Stewart A Jenkins, David M Wells, Brent N McCallum: Nozzle plasma flow control utilizing dielectric barrier discharge plasma actuators. Lockheed Martin Corporation, March 3, 2011: US20110048025-A1

Dielectric barrier discharge plasma actuators are used to manipulate exhaust flow within and behind a jet engine nozzle. The dielectric barrier discharge plasma actuators may be used to direct cooling airflow near the surface of the nozzle to reduce heating of the nozzle, create thrust vectoring, an ...


10
David M Wells, Brent N McCallum, Kerry B Ginn, Stewart A Jenkins: System, method and apparatus for vectoring nozzle exhaust plume with external actuation. Lockheed Martin Corporation, Bracewell & Giuliani, April 15, 2010: US20100089031-A1

A vectoring nozzle with external actuation generates thrust vectoring by applying mechanical or fluidic actuation, or both, on the nozzle deck, external sidewalls, and/or air vehicle aft body to produce changes in the aft body flowfield and/or exhaust plume. An external mechanical sidewall may be in ...



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