1
Dan Miller
Daniel N Miller, Philip P Truax, Patrick J Yagle: System and method to control flowfield vortices with micro-jet arrays. Lockheed Martin Corporation, Bracewell & Giuliani, March 31, 2009: US07510149 (11 worldwide citation)

The present invention provides a system and method for actively manipulating and controlling aerodynamic or hydrodynamic flow field vortices within a fluid flow over a surface using micro-jet arrays. The system and method for actively manipulating and controlling the inception point, size and trajec ...


2
Dan Miller
Daniel N Miller, Philip P Truax, Patrick J Yagle: System and method to control flowfield vortices with micro-jet arrays. Lockheed Martin Corporation, Bracewell & Giuliani, October 18, 2011: US08038102 (6 worldwide citation)

The present invention provides a system and method for actively manipulating and controlling aerodynamic or hydrodynamic flow field vortices within a fluid flow over a surface using micro-jet arrays. The system and method for actively manipulating and controlling the inception point, size and trajec ...


3
Dan Miller
Daniel N Miller, Brent N McCallum, Stewart A Jenkins, David M Wells: Method and system for global flow field management using distributed, surface-embedded, nano-scale boundary layer actuation. Bracewell & Giuliani, August 14, 2012: US08240616 (3 worldwide citation)

Systems and methods to provide distributed flow control actuation to manage the behavior of a global flow field, are provided. An example of a system can include an aerodynamic structure having an outer surface, and an array of a plurality of effectors connected to the outer surface of the aerodynam ...


4
Dan Miller
Daniel N Miller, Brent N McCallum: Method and system for fully fixed vehicle control surfaces. Lockheed Martin Corporation, Bracewell & Giuliani, January 25, 2011: US07874525 (2 worldwide citation)

A fully fixed, non-articulating geometry vehicle that includes a number of virtual control surfaces operable to replicate a mechanical control surface's functionality. These virtual control surfaces further include a number of flow control devices on the non-articulating vehicle surface. The plurali ...


5
Dan Miller
Daniel N Miller, David D Young: Conformal aero-adaptive nozzle/aftbody. Lockheed Martin Corporation, Bracewell & Giuliani, March 30, 2010: US07686256 (1 worldwide citation)

The present invention provides flow field control techniques that adapt the aft body region flow field to eliminate or mitigate the development of massive separated flow field zones and associated unsteady vortical flow field structures. Embodiments of the present invention use one or more distribut ...


6
Dan Miller
Daniel N Miller, Brent N McCallum, Stewart A Jenkins, David M Wells: System for global flow field management using distributed, surface-embedded, nano-scale boundary layer actuation. Lockheed Martin Corporation, Bracewell & Giuliani, January 15, 2013: US08353482 (1 worldwide citation)

Systems to provide distributed flow control actuation to manage the behavior of a global flow field, are provided. An example of a system can include an aerodynamic structure having an outer surface, and an array of a plurality of nano-scale effectors connected to the outer surface of the aerodynami ...


7
Dan Miller
Philip P Truax, Daniel N Miller, Edward C Ma: Flow control redistribution to mitigate high cycle fatigue. Lockheed Martin Corporation, Bracewell & Giuliani, March 26, 2013: US08402738 (1 worldwide citation)

A method operable to improve pressure recovery and/or distortion within engine inlet is disclosed. A first fluid flow is provided to primary jet vortex generator(s) operable to inject fluid at a first injection rate into a boundary layer of a primary fluid flow within the inlet. A secondary fluid fl ...


8
Dan Miller
Neal D Domel, Dan J Baruzzini, Daniel N Miller: Passive robust flow control micro device. Lockheed Martin Corporation, Bracewell & Giuliani, March 26, 2013: US08403271

A tapered micro-plow, or a series of tapered micro-plows, are submerged in a boundary layer just upstream of a reflection point of an oblique shock. Each micro-plow develops a beneficial pair of vortices which redistribute high energy flow within the boundary layer such that flow separation is preve ...


9
Dan Miller
Daniel N Miller, Dan J Baruzzini: Prismatic-shaped vortex generators. Lockheed Martin Corporation, Bracewell & Giuliani, July 3, 2012: US08210482

A prismatic vortex generator for attenuating flow separation which occurs during supersonic flow of air over structure such as an aircraft airfoil, its fuselage, surfaces forming a part of a jet engine inlet, or similar surfaces subjected to supersonic airflow. A series of prismatic vortex generator ...


10
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 ...



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