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A vest or belt is integrally formed with tubular, pet receiving passageways which extend around the wearer's body and terminate in pocket-like chambers for feeding and retrieval.
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| Number | Title | Issue Date |
| 8152109 | Method and system for controlling fluid flow in relation to a foil and harnessing energy therefrom A method and system 10 for controlling fluid flow 12 in relation to a body or foil 14. The system 10 has one or more channels 16, at least some of which having an inlet port 18 and an outlet port 20 defined in the foi... | 04/10/2012 |
| 8136767 | Method and system for flow control with arrays of dual bimorph synthetic jet fluidic actuators A system and method for control of a fluid flow. The system includes an array of interdependent fluidic actuators, each including a chamber, a flow control port, and opposite side walls configured to expand apart and contract together to flow a control fluid through... | 03/20/2012 |
| 8128036 | Vernier active flow control effector 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 boun... | 03/06/2012 |
| 8128037 | Apparatus and method for passive purging of micro-perforated aerodynamic surfaces A purging system for a laminar flow control system comprises an air scoop and a diffuser fluidly connected thereto. The air scoop is disposable into an external flow of an external atmosphere. The diffuser is configured to fluidly connect the air scoop to a suction ... | 03/06/2012 |
| 8033510 | Lift augmentation system and associated method A system and method for generating lift provided by a multi-element aircraft wing are provided. The system includes a main wing element, a slat interconnected to the main wing element, and a flap interconnected to the main wing element. The system also includes at l... | 10/11/2011 |
| 7922126 | Aircraft component exposed to streaming surrounding air An aircraft component, such as a wing, has perforations through an outer wall for boundary layer suction. In the space between the outer wall and inner wall partition walls form pressure channels and suction channels that are adjacent to each other and alternate, wh... | 04/12/2011 |
| 7766280 | Integral suction device with acoustic panel An inlet flow control system disposed within a nacelle includes a panel on an inner surface of that nacelle. The panel includes a noise attenuation layer that dissipates noise energy. A vacuum source generates a pressure differential across the noise attenuation lay... | 08/03/2010 |
| 7748664 | High performance synthetic valve/pulsator A system and method for actively manipulating fluid flow over a surface using synthetic pulsators. Synthetic pulsators produce pulsed jet operable to manipulate the primary fluid flow proximate to the synthetic pulsator. The synthetic pulsator includes a dual diaphr... | 07/06/2010 |
| 7367532 | High lift longitudinal axis control system A bipartite, full span airplane flap system having an inboard flap portion and an outboard flap portion, wherein the outboard flap portion includes an integrated aileron mounted on its substantially equivalent spanwise length. ... | 05/06/2008 |
| 7364118 | Propulsion arrangement In order to achieve greater operational efficiency a propulsive arrangement is provided in which a relatively large number of small propulsive assemblies 9; 31, 32, 33 are provided in aircraft structures in particular the wing 7; 30. The assemblies ... | 04/29/2008 |
| 7331752 | Method of conversion of continuous medium flow energy and device for conversion of continuous medium flow energy A device and method for conversion of the energy of medium flows are provided. The proposed device and method ensure suppression of the vortex streams in the flow on the leg of its motion along the radially converging trajectories and concentration of the flow energ... | 02/19/2008 |
| 7316539 | Vane assembly with metal trailing edge segment Embodiments of the invention relate to a vane assembly formed by a forward airfoil segment and an aft airfoil segment. The aft segment is made of metal and can define the trailing edge of the vane assembly. The forward segment can be made of ceramic, CMC or metal. T... | 01/08/2008 |
| 7290738 | Dual jet emerging lift augmentation system for airfoils and hydrofoils Separate upper and lower plenums within an aircraft airfoil or a sea hydrofoil conduct fluid under different pressures to nozzle slots from which jets emerge to augment lift in accordance with different travel conditions. Lift is induced by nozzle slot emergence of ... | 11/06/2007 |
| 7255309 | Vernier active flow control effector 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 modifyi... | 08/14/2007 |
| 7252140 | Apparatus and method for enhanced heat transfer One embodiment of the cooling module is implemented as a device having a heat sink and an integrated synthetic jet actuator. The heat sink is configured to have a channel and a jet distribution system associated with the synthetic jet actuator directs fluid flow int... | 08/07/2007 |
| 7226015 | Aircraft and missile forebody flow control device and method of controlling flow The present invention relates to a forebody flow control system and more particularly to aircraft or missile flow control system for enhanced maneuverability and stabilization at high angles of attack. The present invention further relates to a method of operating t... | 06/05/2007 |
| 7222819 | Aircraft ram air inlet with multi-member closure flap A ram air inlet includes a channel with an intake in a wing leading edge, front and rear flaps arranged in the channel for selectively closing or opening the channel, and an actuator connected to the flaps. A front end of the front flap is pivotably connected by a f... | 05/29/2007 |
| 7159383 | Apparatus, method and system for gas turbine engine noise reduction An apparatus for reducing gas turbine engine noise, such as noise generated by an aircraft gas turbine engine, comprises at least one and preferably a plurality of gas injectors for injecting gas such as high pressure engine bleed air, diverted core air, air obtaine... | 01/09/2007 |
| 7150432 | Horizontal augmented thrust system and method for creating augmented thrust A horizontal augmented thrust system includes at least one wing. The wing includes a wing outer envelope, a trailing edge and a flap. At least one pulse jet engine is positioned entirely within the wing outer envelope. The pulse jet engine produces a pulsating thrus... | 12/19/2006 |
| 7143983 | Passive jet spoiler for yaw control of an aircraft A wing for an aircraft has a passive jet spoiler for providing yaw control by increasing drag on the wing. The spoiler comprises an inlet located near the leading edge of a lower surface of the wing and at least one outlet formed on the lower surface or on an upper ... | 12/05/2006 |
| 7104143 | Oscillating vane actuator apparatus and method for active flow control An oscillating vane actuator for active control of fluid flow over a surface includes a pivoted vane surrounded by a wedge-shaped chamber, and first and second conduits with openings adjacent the surface. The actuator also includes a rotating shaft with a connecting... | 09/12/2006 |
| 7055329 | Method and apparatus for noise attenuation for gas turbine engines using at least one synthetic jet actuator for injecting air A method enables a gas turbine engine to be operated. The method comprises channeling exhaust gases from a core engine through an exhaust assembly and past at least one flow boundary surface, and selectively operating a noise suppression system extending from the at... | 06/06/2006 |
| 7048230 | Laminar flow nacelle for an aircraft engine A laminar flow nacelle for an aircraft engine (10) has an outer member (26) defining an aerodynamic shape. The nacelle (24) has an inner member (28) defining a chamber (30) with the outer member (26) of the nacelle (24 | 05/23/2006 |
| 6935592 | Aircraft lift device for low sonic boom An aircraft lift device comprises a strake capable of coupling to an aircraft fuselage and extending to a leading edge of a wing. The strake has a leading edge. The life device further comprises a leading-edge flap coupled to the strake leading edge. ... | 08/30/2005 |
| 6932012 | Multi-hull surface vessel with drag reduction on lateral hulls A marine surface vessel having a main hull and at least two lateral hulls disposed respectively on opposite sides of the main hull. The vessel includes an engine disposed in the main hull producing exhaust gas and cooling air, microbubble injectors disposed in subsu... | 08/23/2005 |
| 6899302 | Method and device for altering the separation characteristics of flow over an aerodynamic surface via hybrid intermittent blowing and suction 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 open... | 05/31/2005 |
| 6869049 | Method and apparatus for modulating flow separation An apparatus comprising: an aerodynamic surface adapted for producing an adverse pressure gradient in a fluid flow; and a first pulse detonation actuator disposed adjacent the aerodynamic surface and adapted for impulsively detonating a fuel/air mixture to produce a... | 03/22/2005 |
| 6866234 | Method and device for altering the separation characteristics of air-flow over an aerodynamic surface via intermittent suction 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 eliminatin... | 03/15/2005 |
| 6821090 | Gust alleviation/flutter suppression device 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 s... | 11/23/2004 |
| 6796533 | Method and apparatus for boundary layer reattachment using piezoelectric synthetic jet actuators A method and apparatus for active boundary layer control on an aerodynamic surface. One or more piezoelectric synthetic jet actuators operate as a boundary layer pump to ingest fluid along the surface of an aerodynamic object and discharge fluid tangentially to the ... | 09/28/2004 |
| 6752358 | Laminar flow control system and suction panel for use therewith A laminar flow control system for incorporation in, for example, an aircraft flying surface includes a suction panel comprising a perforated skin (20, 40) mounted on a base member (60), a plenum chamber (30) being in communication with a plurali... | 06/22/2004 |
| 6668638 | Active vortex control with moveable jet In a method of controlling vortex breakdown on an aerodynamic surface, a vortex generated by the aerodynamic surface is continually monitored to identify a non-linear region where vortex breakdown occurs. A fluid jet is blown into the non-linear region to... | 12/30/2003 |
| 6644598 | Modification of fluid flow about bodies and surfaces through virtual aero-shaping of airfoils with synthetic jet actuators The present invention involves a system for altering the aerodynamic shape and/or fluid flow about a solid body. The preferred embodiment comprises an obstruction disposed on the solid body and extending outwardly from the solid body into the fluid flowin... | 11/11/2003 |
| 6612524 | Forebody vortex alleviation device A forebody 10 for an aeronautical vehicle 12 is provided. The forebody 10 includes an exterior wall 14 having a first half 16 and a second half 18. The first half 16 has a first porous section 20 and the second half 18 has a second porous section 24. The ... | 09/02/2003 |
| 6543719 | Oscillating air jets for implementing blade variable twist, enhancing engine and blade efficiency, and reducing drag, vibration, download and ir signature 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... | 04/08/2003 |
| 6488238 | Boundary layer control of aerodynamic airfoils Boundary layer control of a structural element in a fluid stream is achieved by the following operations: providing in such structural element at least one region equipped with micro porous structure by an electroforming technique; having a fluid stream flow t... | 12/03/2002 |
| 6412732 | Apparatus and method for enhancement of aerodynamic performance by using pulse excitation control One aspect of the apparatus disclosed herein is a system for modifying an aerodynamic property of an aerodynamic surface in a fluid flow. The fluid flow could comprise a free stream fluid flow, or an internal fluid flow, such as in a nozzle, diffuser, or ... | 07/02/2002 |
| 6390418 | Tangentially directed acoustic jet controlling boundary layer The nozzle of an acoustic jet directs high momentum flux gas particles essentially tangentially into the boundary layer of the flow in a diffuser, an engine air inlet, a jet engine gas flow path or on the suction surface of an airfoil, the gas particles i... | 05/21/2002 |
| 6302360 | Vortex generation for control of the air flow along the surface of an airfoil Apparatus for generating vortices to control the flow of air across a airfoil of an aircraft includes a series of pressure active regions arranged along the leading edge of the airfoil. The pressure active regions include spaced apart valves connected to ... | 10/16/2001 |
| 6267331 | Airfoil with dynamic stall control by oscillatory forcing A method for inhibiting dynamic stall of an airfoil by causing a fluid to flow out of at least one location on the airfoil. This location may be anywhere on the airfoil; but if the location is within one-quarter of the airfoil chord from the leading edge ... | 07/31/2001 |
