| Patent Number |
Title Of Patent |
Date Issued |
| 8128036 |
Vernier active flow control effector |
March 6, 2012 |
| Methods and apparatus for controlling the attitude of a mobile platform with a resolution suitable for vernier attitude control. In one embodiment a method includes flowing fluid through an orifice of an aerodynamic surface. The method also includes modifying a boundary layer of the |
| 8016245 |
Dynamic bumps for drag reduction at transonic-supersonic speeds |
September 13, 2011 |
| A system for reducing overall drag of a mobile platform includes a surface on which an airflow forms a boundary layer and a generally normal shockwave. The airflow is at a first velocity that is one of transonic and supersonic. An oscillating jet injects and extracts a jet flow throu |
| 7255309 |
Vernier active flow control effector |
August 14, 2007 |
| Methods and apparatus for controlling the attitude of a mobile platform with a resolution suitable for vernier attitude control. In a preferred embodiment, a method includes flowing fluid through an orifice of an aerodynamic surface. The method also includes modifying a boundary layer |
| 7195210 |
Fiber matrix for a geometric morphing wing |
March 27, 2007 |
| An airfoil member (14) includes a geometric morphing device (18). The geometric morphing device (18) has an inflatable member (30). The inflatable member (30) has an exterior wall (32) and multiple inflated states. The exterior wall (32) includes a layer with one or more fibers embed |
| 6994297 |
Method and apparatus for controlling a vehicle |
February 7, 2006 |
| A method of controlling movement of a vehicle including generating a fluid jet adjacent an aerodynamic surface of the vehicle, and changing at least one of a strength and a position of a shock wave traveling over the aerodynamic surface of the vehicle by directing the jet into a boundary |
| 6899302 |
Method and device for altering the separation characteristics of flow over an aerodynamic surfac |
May 31, 2005 |
| An active flow control device and method for improving the aerodynamic efficiency of airfoils. The device and method pertain to the application of hybrid intermittent suction or intake of low-energy boundary layer fluid into an airfoil through one or more inlet openings while also ap |
| 6866234 |
Method and device for altering the separation characteristics of air-flow over an aerodynamic su |
March 15, 2005 |
| Active flow control devices and methods are disclosed for improving the aerodynamic efficiency of airfoils. The devices and methods pertain to applying intermittent suction or intake of low-energy boundary layer fluid into airfoils in a manner delaying or eliminating boundary layer s |
| 6860770 |
Method and device for low-noise underwater propulsion and for reducing hull drag |
March 1, 2005 |
| A method and apparatus is disclosed for producing propulsion underwater with minimal acoustical emission. In basic concept, the method comprises the expulsion and sucking of liquid into and out of a liquid port of a watercraft in a manner generating compression and expansion waves adjace |
| 6851990 |
Method and device for low-noise underwater propulsion |
February 8, 2005 |
| A method and apparatus is disclosed for producing propulsion underwater with minimal acoustical emission. In basic concept, the method comprises the expulsion and sucking of liquid into and out of a liquid port of a watercraft in a manner generating compression and expansion waves adjace |
| 6821090 |
Gust alleviation/flutter suppression device |
November 23, 2004 |
| An active control device is disclosed comprising an array of actively controlled oscillating air jets disposed on an aircraft structure. In a preferred embodiment, the device senses parameters associated with incipient unsteady aerodynamic excitation, such as free stream gusts, shed |
| 6713901 |
Linear electromagnetic zero net mass jet actuator |
March 30, 2004 |
| A linear electromagnetic zero net mass jet (ZNMJ) actuator incorporating a pair of permanent magnets. The magnets are arranged such that an air gap is formed therebetween and further such that opposite poles of the magnets are arranged on opposite sides of the air gap. This concentrates |
| 6543719 |
Oscillating air jets for implementing blade variable twist, enhancing engine and blade efficienc |
April 8, 2003 |
| A porous surface on an aircraft structure driven with oscillating positive and negative pressures is used as an active control device for attenuating negative aerodynamic interactions. The porous surfaces can be driven with positive and negative pressures either continuously or when pred |
| 6478541 |
Tapered/segmented flaps for rotor blade-vortex interaction (BVI) noise and vibration reduction |
November 12, 2002 |
| An active control device for reducing blade-vortex interactions (BVI) noise generated by a rotorcraft, such as a helicopter, comprises a segmented trailing edge flap located near the tip of each of the rotorcraft's rotor blades. The various flap segments may be independently actuated acc |
| 6471477 |
Jet actuators for aerodynamic surfaces |
October 29, 2002 |
| A jet actuator positioned within a hollow space in an aerodynamic structure for controlling the flow over an aerodynamic surface thereof includes a movable member linearly displaced by a voice coil mechanism and a flexible diaphragm defining a compression chamber open to the exterior of |
| 6453669 |
Helicopter in-flight rotor tracking system, method, and smart actuator therefor |
September 24, 2002 |
| A system for quasi-statically correcting tracking of rotor blades of a helicopter rotor during operation includes a trim tab mounted on each rotor blade and deflectable relative to the rotor blade so as to change a tracking path of the rotor blade, and a rotor track and balance analyzer |
| 6322324 |
Helicopter in-flight rotor tracking system, method, and smart actuator therefor |
November 27, 2001 |
| A system for quasi-statically correcting tracking of rotor blades of a helicopter rotor during operation includes a trim tab mounted on each rotor blade and deflectable relative to the rotor blade so as to change a tracking path of the rotor blade, and a rotor track and balance analyzer |
| 6234751 |
Oscillating air jets for reducing HSI noise |
May 22, 2001 |
| Porous surfaces on an aerodynamic structure driven with positive and negative pressures are used in an active control system for attenuating shock waves responsible for high-speed impulsive (HSI) noise. The control system includes an array of apertures in the outer skin of the structure |
| 6092990 |
Oscillating air jets for helicopter rotor aerodynamic control and BVI noise reduction |
July 25, 2000 |
| An active control system for reducing blade-vortex-interaction (BVI) noise generated by a rotor blade. The active control system includes a pressure sensor assembly, a device for changing a lift generated by the rotor blade, and a controller for activating the device upon a detected chan |
| 5938404 |
Oscillating air jets on aerodynamic surfaces |
August 17, 1999 |
| An active control device for use on an aerodynamic structure is provided. The aerodynamic structure includes an outer aerodynamic skin and an interior volume, wherein the outer aerodynamic skin surrounds the interior volume. The active control device includes at least one aperture dispos |
| 5813625 |
Active blowing system for rotorcraft vortex interaction noise reduction |
September 29, 1998 |
| A pressurized porous surface near the leading edge of a rotorcraft blade, is designed to be used as an active control device which alleviates the aerodynamics of blade vortex interactions (BVI) and thus the impulsive BVI noise levels and signature. The pressurized porous surface can be a |
| 5711651 |
Blade vortex interaction noise reduction techniques for a rotorcraft |
January 27, 1998 |
| An active control device for reducing blade-vortex interactions (BVI) noise generated by a rotorcraft, such as a helicopter, comprises a trailing edge flap located near the tip of each of the rotorcraft's rotor blades. The flap may be actuated in any conventional way, and is scheduled to |
| 5588800 |
Blade vortex interaction noise reduction techniques for a rotorcraft |
December 31, 1996 |
| An active control device for reducing blade-vortex interactions (BVI) noise generated by a rotorcraft, such as a helicopter, comprises a trailing edge flap located near the tip of each of the rotorcraft's rotor blades. The flap may be actuated in any conventional way, and is scheduled to |
