 Patent Application Title |
Patent App Num. |
Date |
| Manufacturing wtg blade having a spar | 20110020131 | 20110127 |
| Within the field of wind turbine generators (WTG), to provide a consistent way of manufacturing a WT blade there is disclosed a blade mould and a blade spar fixture to support the spar in the mould so as to provide a fixed predetermined relative position, and preferably also orientation, between at least a root end, such as a bushing in the root end of the blade spar, and a root end of the mould. Overall consistency is also obtained in that hereby a blade with anticipated aerodynamic and strength characteristics is provided, among others in that at least adjacent to the root of the spar there is substantially the same distance for a cured adhesive between an innermost surface of each of blade shells and an... |
| Wind turbine and rotor blade with reduced load fluctuations | 20110018268 | 20110127 |
| A wind turbine includes a rotor having a number of rotor blades. At least one rotor blade has openings. The rotor blade has air-displacement elements which, in use, alternately force air out of and into the openings. A sensor is provided for detecting wind speed fluctuations. A control unit is provided for controlling the air-displacement elements depending on the wind speed fluctuations detected by the sensor. The rotor blade has an aerodynamic profile with a suction side and a pressure side. At least one opening is provided on the suction side. The control unit is designed for operating the air-displacement elements of the opening on the suction side if the sensor has detected a positive speed fluctuation. At least one opening is provided on the pressure... |
| Sea landing of space launch vehicles and associated systems and methods | 20110017872 | 20110127 |
| Launch vehicle systems and methods for landing and recovering a booster stage and/or other portions thereof on a platform at sea or on another body of water are disclosed. In one embodiment, a reusable space launch vehicle is launched from a coastal launch site in a trajectory over water. After booster engine cutoff and upper stage separation, the booster stage reenters the earth's atmosphere in a tail-first orientation. The booster engines are then restarted and the booster stage performs a vertical powered landing on the deck of a pre-positioned sea-going platform. In one embodiment, bidirectional aerodynamic control surfaces control the trajectory of the booster stage as it glides through the earth's atmosphere toward the sea-going platform. The sea-going platform can broadcast its real-time position to the... |
| Device for the production of a composite material piece that comprises smoothing panels with sliding junctions and process for the production of smoothing panels with sliding junctions | 20110017389 | 20110127 |
| A device for the production of a part of an aircraft made of composite material of which one surface is able to be in contact with aerodynamic flows includes a male mold, and at least two smoothing panels (12) that can exert pressure on the piece to be produced during a polymerization phase during which a contraction phenomenon appears. At least one of the two smoothing panels (12.1, 12.2) includes a smooth edge with a beveled shape against which at least one surface of the other smoothing panel can slide to compensate for the contraction phenomenon.
... |
| Mounting of drag reducing devices for stacked intermodal rail cards | 20110017093 | 20110127 |
| Disclosed is a series of stacked intermodal containers, being pulled by a locomotive of a train, with aerodynamic drag reducing devices. A first set of containers has an aerodynamic drag reducing device with a drag reducing fairing and an attachment frame attached thereto. The attachment frame includes first and second mounting devices configured to be removably mounted to connection openings of the corner fittings of the top container of the first set of containers. The first mounting device(s) may be rotatably locked within the top connection openings, while the second mounting device(s) may be hooks for latching into the bottom connection openings. A method of attaching the aerodynamic drag reducing device is also disclosed.
... |
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| Cross-sectional profile for the struts or the fairing of struts and service lines of a turbofan engine | 20110016883 | 20110127 |
| The aerodynamically shaped, symmetrical cross-sectional profile for the struts or the fairing (7) of struts and service lines in the bypass duct and the core-flow duct of a turbofan engine is defined by a course of the local thickness (T) and a position of maximum thickness (PMT) on both sides over the central chord (C) extending from the leading edge (LE) to the trailing edge (TE) of the strut or fairing (7). In order to avoid flow separations the course of the local thickness (T) between the position of maximum thickness (PMT) and a trailing-edge position (PTE), which is at 95 percent of the chord length, has a first turning point (WP1) with a trailing-edge thickness (TET) and a subsequent second turning point (WP2).
... |
| Method and system for measuring the aerodynamic noise of a vehicle | 20110015879 | 20110120 |
| A method and a system for measuring the aerodynamic noise of a vehicle; the system is provided with: a measuring station, which is adapted to receive the vehicle and is provided with a supporting element; at least one blower carried by the supporting element and adapted to generate an air jet towards the vehicle; an actuating device for displacing the supporting element with respect to the vehicle; at least one phonometer for measuring the aerodynamic noise produced by the vehicle struck by the air jet generated by the blower; a position sensor for detecting the position of the supporting element with respect to the vehicle; and a processing unit connected to the phonometer and to the position sensor for correlating the aerodynamic noise measurements supplied by... |
| Locking system for air intake structure for turbojet engine nacelle | 20110014044 | 20110120 |
| The invention relates to a nacelle for a turbojet engine that comprises an air intake structure (2) capable of directing an air flow towards a fan of the turbojet engine, and an intermediate structure for surrounding said fan and to which the air intake structure is attached in order to ensure aerodynamic continuity, wherein the air intake structure includes, on the one hand, at least one inner panel (21) attached to the intermediate structure and defining with the latter a fixed nacelle structure and, on the other hand, at least one longitudinal outer panel (20) removably attached to the fixed structure and including an air intake lip (2a) in order to form a removable air intake structure, characterised in that the air intake structure is provided... |
| Aerodynamic sports toy, game and method of play | 20110012309 | 20110120 |
| An aerodynamic sports toy ball, sports goal system, game utilizing both toy and game, and a method of playing such game (with rule book) between opposing teams divided into team zones and including a goal box at each end through which the ball is to be kicked, thrown, flipping laterally or run by one or the other opposing team or two or more players; and wherein the playing surface of the ball is formed of a multi-pointed star-folding to enable the ball to be thrown, caught, flipped laterally, bounced and kicked within the playing field or court through designated goals at either end of the field or court of play, as well as to provide a surface off of which the ball may be bounced as... |
| Method for manufacturing a core composite provided with cover layers on both sides | 20110011521 | 20110120 |
| The invention relates to a method for manufacturing flat, single or double curved core composites 1, 23 with at least one folded honeycomb core 4, 19. Prior to applying the initially not yet hardened cover layers 2, 3, 13, 22 a curable and later removable core filler material 15, 16 is introduced into full-length drainage-enabling channels 5, 6 of the folded honeycomb core 4, 19 in order to prevent telegraphing of the cover layers 2, 3, 13, 22 into the channels 5, 6 of the folded honeycomb core when arranging and/or hardening the cover layers 2, 3, 13, 22 and to produce edge-free and polygon-free surfaces of the core composite 1, 23. The core composites 1, 23 made according to the method have optimum structural mechanical... |
| Turbofan engine | 20110011058 | 20110120 |
| With a turbofan engine the inner sidewall (2) of the bypass duct (3) features, downstream of the flow divider (11), a straight, conically widening form which, downstream of the supports, struts and guide vanes (7), smoothly transits into a circular-arc transition area (22). The form of the engine fairing (1) is adaptable to the shape of the inner sidewall (2), so that the bypass duct (3) has a conically flaring shape. In the interior of the engine, the gearbox (14) and/or other installations are arranged in a space existing between the inner sidewall (2) and a separating wall (4) confining the core-flow duct (5). The conical design of the bypass duct with the circular-arc transition area enables the gearbox and other installations to be arranged in... |
| Flush-mount, blind fastener | 20110010919 | 20110120 |
| A threaded blind fastener intended for installation in aerodynamically smooth or aesthetically critical panels, further adapted to minimize discontinuities on paintable surfaces of the head resulting from clearances between male and female threads that may adversely affect the quality of paint coverage.
... |
| Application of elastomeric vortex generators | 20110008174 | 20110113 |
| A method of improving aerodynamic performance of foils by the application of conformal, elastomeric vortex generators. The novel use of elastomers allows the application of various forms of vortex generators to sections that have been problematic from engineering and cost considerations. A novel and efficient vortex generator profile is identified, which develops an additional co rotating vortex at low energy expenditure. The mechanisms allow for the application of transverse vortex generators, or Gurney Flaps/Lift Enhancement Tabs/Divergent Trailing Edges, to propellers, rotorblades, and to wings/flaps/control trailing edges. Cove Tabs are additionally described using an elastomeric transverse vortex generator to achieve performance improvements of a high lift device.
... |
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| Application of conformal sub boundary layer vortex generators to a foil or aero/ hydrodynamic surface | 20110006165 | 20110113 |
| A method of improving aerodynamic performance of foils by the application of conformal, low drag vortex generators. A film of erosion protection material or other conformal material is placed on the foil to provide a medium for the incorporation of planform edge vortex generators. The form edge is shaped to achieve submerged vortex generating shapes of chevron or ogival planforms, extending primarily chordwise on the foil surface. The vortex generators promote improved boundary layer dynamics by mixing free stream flow into the boundary layer while minimising separation and fluid losses. At the trailing edge, the shape formed with the chevrons applied apex forward, acts as a vented gurney tab series and additionally as disruptors to the Von Karman Street wake, delaying sheet rollup into the tip... |
| Vehicle grille including adjustable louvers, and/or method of making the same | 20110005851 | 20110113 |
| In certain example embodiments of this invention, there is provided a grille for a vehicle (e.g., a car, truck, SUV, or the like). In certain example embodiments, the vehicle grille includes adjustable louvers. In certain example embodiments, the louvers are configured to change position relative to the grille (e.g., to rotate, slide, or otherwise move) when a predetermined condition is met (e.g., vehicle speed above/below a predefined threshold, wind speed above/below a predefined threshold, etc.). This configuration advantageously may result in better vehicle performance (such as, for example, better fuel efficiency), e.g., related to less drag and/or improved aerodynamics.
... |
| Aerodynamic swept vanes for fuel injectors | 20110005232 | 20110113 |
| A fuel nozzle for a gas turbine engine includes a nozzle body having a longitudinal axis. An elongated annular air passage is defined within the nozzle body. A plurality of circumferentially spaced apart axially extending swirl vanes is disposed within the annular air passage. Each swirl vane has an axially swept cross-sectional profile along the radial extent thereof.
... |
| Control device and method for an aerodynamic brake of a wind energy converter | 20110002772 | 20110106 |
| A wear-free, self-contained control device for an aerodynamic emergency brake of a wind energy converter is presented that comprises multiple components in order to provide a most effective means to control the rotation of a vertical axis wind turbine by a brake, which is able to activate itself without external actuation in malfunction situations and is able to shut down the vertical axis wind turbine. Therefore, a mass element is utilised to store mechanical energy which in turn is used to deploy an aerodynamic braking operation. It also represents a means to control and limit the amount of torque, as absorbed by the turbine in high-wind conditions, and thus provides the ability to harvest electrical/mechanical energy, beyond the normal operational wind speeds of turbines.
... |
| Aerodynamic structure for vehicle | 20110001334 | 20110106 |
| An aerodynamic structure for a vehicle that can effectively adjust airflow within a wheel house is provided. An aerodynamic structure for a vehicle has an airflow collision wall provided at a rear in a vehicle body longitudinal direction with respect to a front wheel in a wheel house, and extending in a vehicle width direction and facing a lower side in a vehicle body vertical direction, an airflow guiding wall extending downward in the vehicle body vertical direction from an end portion of the airflow collision wall which end portion is at a side that is far from the front wheel, and a step portion formed at a portion in the vehicle width direction of at least one of the airflow guiding wall and the airflow... |
| Quad tilt rotor aerial vehicle with stoppable rotors | 20110001020 | 20110106 |
| The disclosed invention consists of several improvements to well known Quad Tilt-Rotor (QTR) aircraft. The first is that during a wing-borne flight, one pair of tilt-rotors, which can be substantially larger than the other pair, is feathered and stopped. This can promote vehicle aerodynamic efficiency and can be utilized to increase vehicle speed. Second is that the wings are not attached to the fuselage at a fixed angle of incidence like on conventional QTR aircraft, but can also be tilted in respect to the fuselage independently of the tilt-rotors. Furthermore, each rotor and each wing can be tilted with respect to fuselage to any tilt-angle without limit, which gives the vehicle unprecedented ability to position the fuselage in any attitude in respect to the vehicle direction... |
| Flying-wing aircraft | 20110001001 | 20110106 |
| A vertical take-off and landing (VTOL) flying-wing aircraft has a pair of thrust-vectoring propulsion units (2, 3; 4, 5) mounted fore and aft of the aircraft pitch axis (PA) on strakes (6, 7) at opposite extremities of the wing-structure (1), with the fore unit (2; 4) below, and the aft unit (3; 5) above, the wing-structure (1). The propulsion units (2-5) are pivoted to the strakes (6, 7), either directly or via arms (56), for individual angular displacement for thrust-vectored maneuvering of the aircraft in yaw, pitch and roll and for hover and forward and backward flight. When arms (56) are employed, the arms (56) of fore and aft propulsion units (52,54; 53,55) are intercoupled via chain drives (57-60) or linkages (61). The wing-structure (1; 51... |
| High efficiency vehicle | 20110000723 | 20110106 |
| Here invented are efficient road vehicles having special aerodynamic shapes, with stabilizing provisions that enable aerodynamic efficiency. It is a vehicle that is configured to include a carriage part that encloses a driver and passenger riding in tandem. This car width is for persons seated in single file, enabling a narrow width that makes a body shaped like an airship practical, where that shape is characterized by a very low drag coefficient in free flow conditions. This body is elevated on struts above a wheel system to enable such free flow aerodynamic conditions, thus, the drag coefficient of the airship is made applicable to this road vehicle. The wheel system includes wheels on each side of the vehicle that are arranged in horizontal columns, to which... |
| Airflow separation initiator | 20110000548 | 20110106 |
| A supersonic inlet includes a cowl and an innerbody. An airflow duct entrance, between the cowl and the centerbody, receives an incoming airflow. An airflow duct exit, between the cowl and the centerbody, delivers a subsonic airflow. A controlled airflow separation initiator, on the innerbody and upstream of a lip of the cowl, which, when actuated, creates a separation in the incoming airflow. The separation region changes the local flow field aerodynamics such that an airflow weight flow at the cowl lip matches an airflow weight flow at a duct minimum area, between the airflow duct entrance and the airflow duct exit.
... |
| Vehicle with drag-reducing outer surface | 20100330329 | 20101230 |
| A vehicle with a drag-reducing outer surface. A method of reducing aerodynamic or hydrodynamic drag on a vehicle includes the steps of: providing an outer surface on a body of the vehicle, with the outer surface including spaced apart turbulence-inducing structures thereon. The structures cause boundary layer separation to be delayed along a length of the body, thereby reducing a drag coefficient of the body. A vehicle wrapping product for reducing aerodynamic or hydrodynamic drag on a vehicle includes an outer surface for applying onto an opaque portion of a body of the vehicle. The outer surface includes a plurality of structures which induce turbulence and thereby delay separation of a boundary layer along a length of the body, to thereby reduce a drag coefficient of... |
| Respiratory dispersion for metered dose inhalers | 20100329984 | 20101230 |
| A respiratory dispersion for pulmonary delivery comprises one or more bioactive agents, a suspension medium, and a plurality of perforated microstructures having a mean aerodynamic diameter of less than 5 μm. The suspension medium comprises at least one propellant and permeates the perforated microstructures.
... |
| Shroudless blade | 20100329848 | 20101230 |
| A shroudless blade for use in a compressor or fan of an axial flow gas turbine engine includes a treatment to the tips of the blades to improve the surge margin of the compressor. A series of cross bleed holes are formed at the tip of the blade, which may be a stator or rotor component, extending between the pressure and suction sides of the blades. Notches are provided at the tip of the blades to provide initiation sites for any fatigue cracks such that the cracks propagate from the base of these slots or notches and radially inwards into the body of the blades. The present invention provides an arrangement, which by provision of the cross bleed holes the propagation of the cracks is arrested.... |
| Aerodynamic performance enhancements using discharge plasma actuators | 20100329838 | 20101230 |
| The current invention provides significant performance improvements or significant energy savings for fans used in these applications: personal, industrial and automotive cooling, ventilation, vacuuming and dust removal, inflating, computer component cooling, propulsors for unmanned and manned air vehicles, propulsors for airboats, air-cushion vehicles, airships and model aircraft. Additionally, the invention provides higher performance such as higher lift and higher lift efficiency to small air vehicles. These advantages are achieved by using plasma actuators to provide active flow control effectors into thin fan blades and wing.
... |
| Automotive air deflector, and a system thereof | 20100327625 | 20101230 |
| An automotive air deflector is substantially V-shaped with a pair of opposed wing panels configured such that impinging air is directed around the deflector. The deflector is configured for placement at various locations on a vehicle, including on the front end of the vehicle, on the rear end of the vehicle, and in front of the tires of the vehicle. The air deflector is constructed of a lightweight material that is sufficiently rigid for the service environment but is flexible enough to be configured in varying shapes so as to accommodate being placed on various types of vehicles and in the various locations on those vehicles. By reducing turbulence and providing for the smooth flow of air around the vehicle, the air deflector reduces the effect... |
| Cross-bleed dam | 20100327121 | 20101230 |
| A panel assembly for an aircraft including a panel having an upper aerodynamic surface and a leading edge, and a hinge fitting connected to an underside of the panel, defining a hinge line for the direction of rotation of the panel. The upper surface of the leading edge has an arcuate portion centered about the hinge line, and has an upturned portion forward of the arcuate portion. The panel assembly is pivotally connected to its hinge fitting to the trailing edge of the fixed wing portion and rotatable between a first position wherein the upper surfaces of the fixed wing portion and the panel are substantially flush, and a second position wherein the panel is rotated downwardly from the first position. A seal member attached to... |
| Air-vehicle augmented kinesthetic control system | 20100327122 | 20101230 |
| An augmented kinesthetic control system for use with a lift platform, the lift platform comprising first and second longitudinally-spaced thrust generating means, is provided. The first and second lift planes defined by the first and second thrust generating means are positioned below the lift platform center of gravity. The kinesthetic control means are coupled to means for aerodynamically altering the air flow from the first and second thrust generating means such that the intuitive and balancing movements of the pilot are magnified to allow kinesthetic control of a vehicle of greater size and utility.
... |
| Air outlet system for aircraft leading edge | 20100327120 | 20101230 |
| An aircraft leading edge is extended by an aerodynamic surface providing an aerodynamic flow and where air discharges are arranged preventing separation of the aerodynamic flow. The air discharges are arranged in at least two rows essentially parallel to the leading edge and in an offset manner for at least two consecutive rows. At least one block is inserted between two walls that form the aerodynamic surface. The block includes, on the one hand, an outside surface extending the aerodynamic surface, a first inclined surface contacting the first wall forming the aerodynamic surface, and a second inclined surface contacting the second wall that forms the aerodynamic surface, and, on the other hand, projecting and/or hollow shapes that are made at the inclined surfaces and that are... |
| Method and system for measuring the aerodynamic noise of a vehicle | 20110015879 | 20110120 |
| A method and a system for measuring the aerodynamic noise of a vehicle; the system is provided with: a measuring station, which is adapted to receive the vehicle and is provided with a supporting element; at least one blower carried by the supporting element and adapted to generate an air jet towards the vehicle; an actuating device for displacing the supporting element with respect to the vehicle; at least one phonometer for measuring the aerodynamic noise produced by the vehicle struck by the air jet generated by the blower; a position sensor for detecting the position of the supporting element with respect to the vehicle; and a processing unit connected to the phonometer and to the position sensor for correlating the aerodynamic noise measurements supplied by... |
| Locking system for air intake structure for turbojet engine nacelle | 20110014044 | 20110120 |
| The invention relates to a nacelle for a turbojet engine that comprises an air intake structure (2) capable of directing an air flow towards a fan of the turbojet engine, and an intermediate structure for surrounding said fan and to which the air intake structure is attached in order to ensure aerodynamic continuity, wherein the air intake structure includes, on the one hand, at least one inner panel (21) attached to the intermediate structure and defining with the latter a fixed nacelle structure and, on the other hand, at least one longitudinal outer panel (20) removably attached to the fixed structure and including an air intake lip (2a) in order to form a removable air intake structure, characterised in that the air intake structure is provided... |
| Aerodynamic sports toy, game and method of play | 20110012309 | 20110120 |
| An aerodynamic sports toy ball, sports goal system, game utilizing both toy and game, and a method of playing such game (with rule book) between opposing teams divided into team zones and including a goal box at each end through which the ball is to be kicked, thrown, flipping laterally or run by one or the other opposing team or two or more players; and wherein the playing surface of the ball is formed of a multi-pointed star-folding to enable the ball to be thrown, caught, flipped laterally, bounced and kicked within the playing field or court through designated goals at either end of the field or court of play, as well as to provide a surface off of which the ball may be bounced as... |
| Method for manufacturing a core composite provided with cover layers on both sides | 20110011521 | 20110120 |
| The invention relates to a method for manufacturing flat, single or double curved core composites 1, 23 with at least one folded honeycomb core 4, 19. Prior to applying the initially not yet hardened cover layers 2, 3, 13, 22 a curable and later removable core filler material 15, 16 is introduced into full-length drainage-enabling channels 5, 6 of the folded honeycomb core 4, 19 in order to prevent telegraphing of the cover layers 2, 3, 13, 22 into the channels 5, 6 of the folded honeycomb core when arranging and/or hardening the cover layers 2, 3, 13, 22 and to produce edge-free and polygon-free surfaces of the core composite 1, 23. The core composites 1, 23 made according to the method have optimum structural mechanical... |
| Turbofan engine | 20110011058 | 20110120 |
| With a turbofan engine the inner sidewall (2) of the bypass duct (3) features, downstream of the flow divider (11), a straight, conically widening form which, downstream of the supports, struts and guide vanes (7), smoothly transits into a circular-arc transition area (22). The form of the engine fairing (1) is adaptable to the shape of the inner sidewall (2), so that the bypass duct (3) has a conically flaring shape. In the interior of the engine, the gearbox (14) and/or other installations are arranged in a space existing between the inner sidewall (2) and a separating wall (4) confining the core-flow duct (5). The conical design of the bypass duct with the circular-arc transition area enables the gearbox and other installations to be arranged in... |
| Flush-mount, blind fastener | 20110010919 | 20110120 |
| A threaded blind fastener intended for installation in aerodynamically smooth or aesthetically critical panels, further adapted to minimize discontinuities on paintable surfaces of the head resulting from clearances between male and female threads that may adversely affect the quality of paint coverage.
... |
| Application of elastomeric vortex generators | 20110008174 | 20110113 |
| A method of improving aerodynamic performance of foils by the application of conformal, elastomeric vortex generators. The novel use of elastomers allows the application of various forms of vortex generators to sections that have been problematic from engineering and cost considerations. A novel and efficient vortex generator profile is identified, which develops an additional co rotating vortex at low energy expenditure. The mechanisms allow for the application of transverse vortex generators, or Gurney Flaps/Lift Enhancement Tabs/Divergent Trailing Edges, to propellers, rotorblades, and to wings/flaps/control trailing edges. Cove Tabs are additionally described using an elastomeric transverse vortex generator to achieve performance improvements of a high lift device.
... |
| Application of conformal sub boundary layer vortex generators to a foil or aero/ hydrodynamic surface | 20110006165 | 20110113 |
| A method of improving aerodynamic performance of foils by the application of conformal, low drag vortex generators. A film of erosion protection material or other conformal material is placed on the foil to provide a medium for the incorporation of planform edge vortex generators. The form edge is shaped to achieve submerged vortex generating shapes of chevron or ogival planforms, extending primarily chordwise on the foil surface. The vortex generators promote improved boundary layer dynamics by mixing free stream flow into the boundary layer while minimising separation and fluid losses. At the trailing edge, the shape formed with the chevrons applied apex forward, acts as a vented gurney tab series and additionally as disruptors to the Von Karman Street wake, delaying sheet rollup into the tip... |
| Vehicle grille including adjustable louvers, and/or method of making the same | 20110005851 | 20110113 |
| In certain example embodiments of this invention, there is provided a grille for a vehicle (e.g., a car, truck, SUV, or the like). In certain example embodiments, the vehicle grille includes adjustable louvers. In certain example embodiments, the louvers are configured to change position relative to the grille (e.g., to rotate, slide, or otherwise move) when a predetermined condition is met (e.g., vehicle speed above/below a predefined threshold, wind speed above/below a predefined threshold, etc.). This configuration advantageously may result in better vehicle performance (such as, for example, better fuel efficiency), e.g., related to less drag and/or improved aerodynamics.
... |
| Aerodynamic swept vanes for fuel injectors | 20110005232 | 20110113 |
| A fuel nozzle for a gas turbine engine includes a nozzle body having a longitudinal axis. An elongated annular air passage is defined within the nozzle body. A plurality of circumferentially spaced apart axially extending swirl vanes is disposed within the annular air passage. Each swirl vane has an axially swept cross-sectional profile along the radial extent thereof.
... |
| Control device and method for an aerodynamic brake of a wind energy converter | 20110002772 | 20110106 |
| A wear-free, self-contained control device for an aerodynamic emergency brake of a wind energy converter is presented that comprises multiple components in order to provide a most effective means to control the rotation of a vertical axis wind turbine by a brake, which is able to activate itself without external actuation in malfunction situations and is able to shut down the vertical axis wind turbine. Therefore, a mass element is utilised to store mechanical energy which in turn is used to deploy an aerodynamic braking operation. It also represents a means to control and limit the amount of torque, as absorbed by the turbine in high-wind conditions, and thus provides the ability to harvest electrical/mechanical energy, beyond the normal operational wind speeds of turbines.
... |
| Aerodynamic structure for vehicle | 20110001334 | 20110106 |
| An aerodynamic structure for a vehicle that can effectively adjust airflow within a wheel house is provided. An aerodynamic structure for a vehicle has an airflow collision wall provided at a rear in a vehicle body longitudinal direction with respect to a front wheel in a wheel house, and extending in a vehicle width direction and facing a lower side in a vehicle body vertical direction, an airflow guiding wall extending downward in the vehicle body vertical direction from an end portion of the airflow collision wall which end portion is at a side that is far from the front wheel, and a step portion formed at a portion in the vehicle width direction of at least one of the airflow guiding wall and the airflow... |
| Quad tilt rotor aerial vehicle with stoppable rotors | 20110001020 | 20110106 |
| The disclosed invention consists of several improvements to well known Quad Tilt-Rotor (QTR) aircraft. The first is that during a wing-borne flight, one pair of tilt-rotors, which can be substantially larger than the other pair, is feathered and stopped. This can promote vehicle aerodynamic efficiency and can be utilized to increase vehicle speed. Second is that the wings are not attached to the fuselage at a fixed angle of incidence like on conventional QTR aircraft, but can also be tilted in respect to the fuselage independently of the tilt-rotors. Furthermore, each rotor and each wing can be tilted with respect to fuselage to any tilt-angle without limit, which gives the vehicle unprecedented ability to position the fuselage in any attitude in respect to the vehicle direction... |
| Flying-wing aircraft | 20110001001 | 20110106 |
| A vertical take-off and landing (VTOL) flying-wing aircraft has a pair of thrust-vectoring propulsion units (2, 3; 4, 5) mounted fore and aft of the aircraft pitch axis (PA) on strakes (6, 7) at opposite extremities of the wing-structure (1), with the fore unit (2; 4) below, and the aft unit (3; 5) above, the wing-structure (1). The propulsion units (2-5) are pivoted to the strakes (6, 7), either directly or via arms (56), for individual angular displacement for thrust-vectored maneuvering of the aircraft in yaw, pitch and roll and for hover and forward and backward flight. When arms (56) are employed, the arms (56) of fore and aft propulsion units (52,54; 53,55) are intercoupled via chain drives (57-60) or linkages (61). The wing-structure (1; 51... |
| High efficiency vehicle | 20110000723 | 20110106 |
| Here invented are efficient road vehicles having special aerodynamic shapes, with stabilizing provisions that enable aerodynamic efficiency. It is a vehicle that is configured to include a carriage part that encloses a driver and passenger riding in tandem. This car width is for persons seated in single file, enabling a narrow width that makes a body shaped like an airship practical, where that shape is characterized by a very low drag coefficient in free flow conditions. This body is elevated on struts above a wheel system to enable such free flow aerodynamic conditions, thus, the drag coefficient of the airship is made applicable to this road vehicle. The wheel system includes wheels on each side of the vehicle that are arranged in horizontal columns, to which... |
| Airflow separation initiator | 20110000548 | 20110106 |
| A supersonic inlet includes a cowl and an innerbody. An airflow duct entrance, between the cowl and the centerbody, receives an incoming airflow. An airflow duct exit, between the cowl and the centerbody, delivers a subsonic airflow. A controlled airflow separation initiator, on the innerbody and upstream of a lip of the cowl, which, when actuated, creates a separation in the incoming airflow. The separation region changes the local flow field aerodynamics such that an airflow weight flow at the cowl lip matches an airflow weight flow at a duct minimum area, between the airflow duct entrance and the airflow duct exit.
... |
| Vehicle with drag-reducing outer surface | 20100330329 | 20101230 |
| A vehicle with a drag-reducing outer surface. A method of reducing aerodynamic or hydrodynamic drag on a vehicle includes the steps of: providing an outer surface on a body of the vehicle, with the outer surface including spaced apart turbulence-inducing structures thereon. The structures cause boundary layer separation to be delayed along a length of the body, thereby reducing a drag coefficient of the body. A vehicle wrapping product for reducing aerodynamic or hydrodynamic drag on a vehicle includes an outer surface for applying onto an opaque portion of a body of the vehicle. The outer surface includes a plurality of structures which induce turbulence and thereby delay separation of a boundary layer along a length of the body, to thereby reduce a drag coefficient of... |
| Respiratory dispersion for metered dose inhalers | 20100329984 | 20101230 |
| A respiratory dispersion for pulmonary delivery comprises one or more bioactive agents, a suspension medium, and a plurality of perforated microstructures having a mean aerodynamic diameter of less than 5 μm. The suspension medium comprises at least one propellant and permeates the perforated microstructures.
... |
| Shroudless blade | 20100329848 | 20101230 |
| A shroudless blade for use in a compressor or fan of an axial flow gas turbine engine includes a treatment to the tips of the blades to improve the surge margin of the compressor. A series of cross bleed holes are formed at the tip of the blade, which may be a stator or rotor component, extending between the pressure and suction sides of the blades. Notches are provided at the tip of the blades to provide initiation sites for any fatigue cracks such that the cracks propagate from the base of these slots or notches and radially inwards into the body of the blades. The present invention provides an arrangement, which by provision of the cross bleed holes the propagation of the cracks is arrested.... |
| Aerodynamic performance enhancements using discharge plasma actuators | 20100329838 | 20101230 |
| The current invention provides significant performance improvements or significant energy savings for fans used in these applications: personal, industrial and automotive cooling, ventilation, vacuuming and dust removal, inflating, computer component cooling, propulsors for unmanned and manned air vehicles, propulsors for airboats, air-cushion vehicles, airships and model aircraft. Additionally, the invention provides higher performance such as higher lift and higher lift efficiency to small air vehicles. These advantages are achieved by using plasma actuators to provide active flow control effectors into thin fan blades and wing.
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| Automotive air deflector, and a system thereof | 20100327625 | 20101230 |
| An automotive air deflector is substantially V-shaped with a pair of opposed wing panels configured such that impinging air is directed around the deflector. The deflector is configured for placement at various locations on a vehicle, including on the front end of the vehicle, on the rear end of the vehicle, and in front of the tires of the vehicle. The air deflector is constructed of a lightweight material that is sufficiently rigid for the service environment but is flexible enough to be configured in varying shapes so as to accommodate being placed on various types of vehicles and in the various locations on those vehicles. By reducing turbulence and providing for the smooth flow of air around the vehicle, the air deflector reduces the effect... |
| Cross-bleed dam | 20100327121 | 20101230 |
| A panel assembly for an aircraft including a panel having an upper aerodynamic surface and a leading edge, and a hinge fitting connected to an underside of the panel, defining a hinge line for the direction of rotation of the panel. The upper surface of the leading edge has an arcuate portion centered about the hinge line, and has an upturned portion forward of the arcuate portion. The panel assembly is pivotally connected to its hinge fitting to the trailing edge of the fixed wing portion and rotatable between a first position wherein the upper surfaces of the fixed wing portion and the panel are substantially flush, and a second position wherein the panel is rotated downwardly from the first position. A seal member attached to... |
| Air-vehicle augmented kinesthetic control system | 20100327122 | 20101230 |
| An augmented kinesthetic control system for use with a lift platform, the lift platform comprising first and second longitudinally-spaced thrust generating means, is provided. The first and second lift planes defined by the first and second thrust generating means are positioned below the lift platform center of gravity. The kinesthetic control means are coupled to means for aerodynamically altering the air flow from the first and second thrust generating means such that the intuitive and balancing movements of the pilot are magnified to allow kinesthetic control of a vehicle of greater size and utility.
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| Air outlet system for aircraft leading edge | 20100327120 | 20101230 |
| An aircraft leading edge is extended by an aerodynamic surface providing an aerodynamic flow and where air discharges are arranged preventing separation of the aerodynamic flow. The air discharges are arranged in at least two rows essentially parallel to the leading edge and in an offset manner for at least two consecutive rows. At least one block is inserted between two walls that form the aerodynamic surface. The block includes, on the one hand, an outside surface extending the aerodynamic surface, a first inclined surface contacting the first wall forming the aerodynamic surface, and a second inclined surface contacting the second wall that forms the aerodynamic surface, and, on the other hand, projecting and/or hollow shapes that are made at the inclined surfaces and that are... |
| Spacecraft afterbody device | 20100327108 | 20101230 |
| An afterbody device for a spacecraft fitted with at least one rocket engine at the rear of the craft includes at least one movable cover element designed to take a first position, masking and reducing the vehicle's rear drag, where it prolongs the vehicle's fuselage around at least one part of a rocket engine nozzle of the vehicle and extends beyond the rear of the vehicle's fuselage, and to take a second position fully deployed, increasing the vehicle's aerodynamic drag.
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| Drag reducing devices for a locomotive | 20100326316 | 20101230 |
| Disclosed is a locomotive of a train with a plurality of aerodynamic drag reducing devices. A locomotive may have a plurality of drag reducing devices attached to a longitudinal end of the locomotive adjacent a walkway of the locomotive. Each drag reducing device may be positioned at an angle with respect to a centerline of the locomotive so as to reduce drag on the locomotive. The drag reducing devices may be mounted to a handrail included on the walkway using separate or single assemblies. Drag reducing devices may also be provided on an opposite or back end of the locomotive, as well as retrofit to a face of the locomotive to reduce drag. Angled winglets may be provided on the drag reducing devices to assist in... |
| Air bus transportation system | 20100326311 | 20101230 |
| A transportation system includes a vehicle having wings, a propulsion system, a lifting gear coupling the vehicle to an undercarriage, and a guidance assembly movably connecting the undercarriage to guide rails. The wings generate aerodynamic lift when the vehicle exceeds a first speed. The lifting gear supports a load of the vehicle in a first position in relation to the undercarriage when the vehicle travels at less than the first speed, allows the vehicle to lift to a second position in relation to the undercarriage as the vehicle accelerates beyond the first speed, and maintains the vehicle in the second position when the vehicle exceeds the first speed. The guidance assembly shiftingly engages the guide rails through rollers that are in rolling contact with the guide... |
| Active field polarized media air cleaner | 20100326279 | 20101230 |
| Improvements in active field polarized media air cleaner include an aerodynamic front cowling to reduce static air resistance, a rear double hinge to reduce blow by, a resistive center screen permitting the sharing of high voltage power supplies while reducing the tendency to arc and allowing for a higher operational voltage, a dielectric media support frame to produce a more uniform electrostatic field and reduce blow by, while at the same time reducing the tendency to spray corona and/or arc at the edges of the center screen, a substantially flat conductive outer screen to produce a more uniform electrostatic field throughout the filter media and a high-voltage shield to reduce high-voltage arcing and the spraying of corona where the high-voltage probe contacts the center screen.
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| Apparatus and method for determining forces acting on a vehicle in a wind tunnel | 20100326209 | 20101230 |
| A system for resolving the measured forces and moments at VRS attachment points and tire contact patches to a standard format for a wheeled vehicle in a windtunnel. The system reduces the data to arrive at the aerodynamic forces, moments and coefficients. The test vehicle is equipped with one or more wheel force transducers installed between the wheels and the corresponding hubs. A VRS rod or strut attaches to the wheel so that loads through the hub and into the wheel are sensed at both the VRS strut and the tire contact patch. The force transmitted through the hub into the wheel is sensed and measured directly by the wheel force transducer. The combination of measurements from the VRS load cells and the wheel transducers allows... |
| Aerodynamic test stand | 20100326178 | 20101230 |
| An aerodynamic test stand (1) is provided for determining forces acting on a vehicle. The test stand has a stationary floor (2), at least two supporting devices (4) for supporting the motor vehicle, and at least one band unit moving in relation to the floor, for influencing air flow behavior in the floor region. The band unit is composed, segment-like, of runway sections (9, 10, 11, 20, 21, 22, 23, 24, 25, 26, 27, 28) to accurately detect forces acting on the vehicle.
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| Aerodynamic structural safety barrier design | 20090322192 | 20091231 |
| A barrier disposed within a computer housing includes a frame adapted to be secured to the computer housing; and a plurality of elongated members attached to the frame. The plurality of elongated members are disposed across the frame such that the plurality of elongated members are attached to an inner surface of the frame. The barrier defines separate compartments within the computer housing and at least one fan is disposed in a compartment separated by the barrier from another compartment in which at least one electronic component is disposed. A method of manufacturing a barrier includes providing a frame; attaching a plurality of elongated members to the frame; disposing the frame within the housing such that the frame defines separate compartments within the housing; disposing at... |
| Method for making, positioning and securing dummy elements in models tested in wind tunnels | 20090321995 | 20091231 |
| Once the geometry is known that the dummy element has to have on account of flight conditions, atmospheric conditions and the original aerodynamic surface, the shape of the dummy element (1) is reproduced by stereolithography, at the same time forming certain extensions (4) which follow the aerodynamic geometry of the object (3) and which are located in strategically selected positions, the whole acting by way of a negative template which is restricted to and follows the shapes of the leading edge. An adhesive is then applied to the surface of the dummy element (1) without it affecting the extensions (4) since they then have to be removed.
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| Translating active gurney flap to alleviate aircraft wake vortex hazard | 20090321582 | 20091231 |
| A wake vortex alleviator is provided. The wake vortex alleviator produces rapid variations in the position of vortices emanating from aerodynamic surfaces by using an active flap that moves span-wise back and forth along the outboard section of the surface. Rapidly moving the flap back and forth in a slot at an appropriate frequency will cause the vortex to oscillate, resulting in interaction between other vortices and subsequent destruction much earlier than it would occur naturally. The slot is positioned near the aerodynamic surface trailing edge and generally transverse to a chord line of the aerodynamic surface. The flap can be moved using a variety of actuators to position, translate and stow the flap. The oscillation frequency and position are guided by information feedback according variations... |
| Vernier active flow control effector | 20090321580 | 20091231 |
| 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 aerodynamic surface with the flowing fluid. Another embodiment provides an aerodynamic member of a mobile platform. The aerodynamic member includes an aerodynamic surface, an orifice, an actuator, and a fluid moving member. The orifice is in the aerodynamic surface and the actuator is subject to friction and backlash. The fluid moving member communicates with the orifice and causes the fluid to flow through the orifice to modify the boundary layer of aerodynamic surface.
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| System, method and apparatus for windblast reduction during release or ejection from aircraft | 20090321570 | 20091231 |
| The invention reduces the impact of flowfield forces on objects launched from high speed aircraft during flight. For example, the invention provides a solution for overcoming ejection windblast injuries to pilots and increases the probability of injury-free or low-injury ejection. The gas flow is used to rapidly create a very short duration protective “bubble” in the incoming air flow ahead of the ejecting pilot. The bubble reduces the local flow velocity and aerodynamic forces on the pilot during the injury-critical time period of ejection. The invention also is suitable for reducing the intensity of flowfield forces that act on released military aircraft ordnance, such as bombs and missiles.
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| Active twisting of an aircraft lifting surface via modulated clamping of substructure | 20090321558 | 20091231 |
| A system and method for enabling controlled twisting of a tip of a wing in response to the aerodynamic forces experienced by the wing. The structural stiffness of the wing is modulated to modulate the twist of the wing in the presence of aerodynamic forces.
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| Hybrid device for vibration control | 20090321555 | 20091231 |
| Disclosed herein are control systems relating generally to the field of aerodynamics and more particularly to the control of vibration of rotor blades such as helicopter blades. Such systems involve devices for vibration control of each rotor blade, which incorporate control systems of the flow control type (e.g. actively controlled flap) and structural control type (e.g. active pitch link). Also disclosed are related methods of controlling vibration in a rotor blade, wherein the rotor blade is coupled to a rotor hub and has at least a torsional stiffness and a pitch angle associated therewith.
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| Aerodynamic standoffs to air cool disc type auto brake rotors | 20090321197 | 20091231 |
| The invention includes a mounting hat for a brake rotor having a lower section connected to an upper section. Also included is a plurality of aerodynamically shaped standoff vanes each having a leading edge, a trailing edge, a top and a bottom connected to the upper section. Further, a plurality of vents are formed between adjacent aerodynamically shaped standoff vanes. The vents are circumferentially distributed on the upper section. Air flow is induced to flow through the plurality of vents. Alternatively included is a mounting hat for a brake rotor having a lower section connected to an upper section. Also included is a plurality of first aerodynamically shaped standoff vanes each having a leading edge, a trailing edge, a top and a bottom connected to the... |
| Multifunctional device for carrying out automatic riveting process by numerical control and method thereof | 20090320271 | 20091231 |
| The device comprises a robot (1) provided with a head (3) which comprises a plurality of single-function modules, each of them with the function of carrying out different and consecutive operations on the working zone of the pieces to rivet or fasten. The robot can be a precise articulated robot, a Cartesian machine, a parallel kinematics robot or other, while said modules can be located transversally, longitudinally or in a matrix in the head. The method provides operations for drilling, reaming and countersinking of different diameters, quality control of drill-holes, thickness checking of pieces, application of sealant, selection and supply of rivet, fastener or pin to rivet or fasten, fitting of the rivet, fastener or pin, riveting and/or fastening, fitting checking of the rivet, fastener or... |
| Power-assisted control system for a rotorcraft | 20090317252 | 20091224 |
| An assisted control system for controlling the attitude of a rotorcraft comprises a flight control device; at least one control member configured to act on an aerodynamic element of the rotorcraft; a mechanical connection connecting the flight control device to the at least one control member, the mechanical connection including at least one connecting rod moveable in translation, a crank device pivotably disposed about a stationary support shaft passing through the crank device, and a motor including a drive rotor and a stator configured to facilitate a pivoting movement of the crank device about the stationary support; a motor control device configured to control a rotation of the drive rotor relative to the stator; and at least one sensor configured to measure information representative of an... |
| Guide vane arrangement for a driving mechanism | 20090317246 | 20091224 |
| The invention relates to a guide-vane arrangement (1) for deviating the flow present in the by-pass flow channel (2) of an engine (3), said arrangement comprising an outer ring (4) and an inner ring (5) and guide vanes (6) arranged therebetween in a substantially radial manner, wherein the outer ring (4) has elements (7) for connecting to an outer engine structure (8), and the inner ring (5) has elements (9) for connecting to an inner engine structure (10), with a plurality of segments (11) being provided. In order to create a guide-vane arrangement (1) which is sufficiently stable and has optimum aerodynamic properties, each segment (11) is integrally produced from at least one guide vane (6) with a part (12) of the outer ring (4) having... |
| Wind turbine with mixers and ejectors | 20090317231 | 20091224 |
| A Mixer/Ejector Wind Turbine (“MEWT”) system is disclosed which routinely exceeds the efficiencies of prior wind turbines. Unique ejector concepts are used to fluid-dynamically improve many operational characteristics of conventional wind turbines for potential power generation improvements of 50% and above. Applicants' preferred MEWT embodiment comprises: an aerodynamically contoured turbine shroud with an inlet; a ring of stator vanes; a ring of rotating blades (i.e., an impeller) in line with the stator vanes; and a mixer/ejector pump to increase the flow volume through the turbine while rapidly mixing the low energy turbine exit flow with high energy bypass wind flow. The MEWT can produce three or more time the power of its un-shrouded counterparts for the same frontal area, and can increase the productivity of wind... |
| Devices and methods to improve wing aerodynamics at low airspeeds | 20090314898 | 20091224 |
| Aircraft wings are provided with aerodynamic devices that improve the wing's low airspeed aerodynamics. In preferred embodiments, the aircraft wings include a slat operatively positioned at the wing's leading edge for movement between a retracted position for relatively high airspeed aircraft operations, and a deployed position for relatively low airspeed aircraft operations. An aerodynamic device is positionally fixed to the wing laterally adjacent the leading edge slat, the device having a forward end extending forwardly of the wing leading edge. The device is operable in response to movement of the slat into the deployed position thereof so as to improve the aerodynamics of the wing at low airspeed aircraft operations, but provides substantially no aerodynamic improvement when the slat is in the retracted position thereof during... |
| Collapsible shape memory alloy (sma) nose cones for air vehicles, method of manufacture and use | 20090314890 | 20091224 |
| A nose cone formed from a shape memory alloy (SMA) having a recoverable strain of at least 2% collapses about the dome for storage, deploys at launch to protect the sensor dome and reduce drag during atmospheric flight and is shed to allow sensing for terminal maneuvers. The SMA is shape-set at elevated temperatures in its Austenite phase with a memorized shape having a radius of curvature greater than that of the sensor dome to reduce aerodynamic drag. The temperature is reduced and the SMA collapsed to conform to the curvature of the sensor dome within the recoverable strain for storage. A first mechanism is configured to return the collapsed SMA to its memorized shape at launch or prior to going supersonic. In one embodiment, the... |
| Pet toy | 20090314222 | 20091224 |
| An improved pet toy has a toy body composed of polyolefin having good flexibility and resiliency, which is an ethylene vinylacetate copolymer. The pet toy can be cylindrical in shape, toroidal in shape, spherical in shape, or can have a saucer-shape having an aerodynamic form for gliding.
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| Hybrid method for estimating the ground effect on an aircraft | 20090314076 | 20091224 |
| A method for assessing the aerodynamic ground effects on an aircraft. The method includes determining the variation of at least one aerodynamic coefficient of the aircraft as a function of the height for a range of heights extending from an aerodynamically infinite height to a zero height. In the method, (i) the range of heights is subdivided into at least two consecutive sets of heights; (ii) for one of the sets of heights, the variation of said aerodynamic coefficient is determined by wind tunnel tests using a model of the aircraft; and (iii) for the other of the sets of heights, the variation of said aerodynamic coefficient is determined by digital simulation reproducing by computation the physical reality of the air flow around said aircraft.
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| Pneumatic hybrid turbo transmission | 20090313990 | 20091224 |
| A pneumatic hybrid turbo transmission for reduced energy consumption is disclosed. A pneumatic hybrid turbo transmission configured as a multi-purpose unit (MPU). The MPU recovers energy from the cooling system, exhaust system, ram pressure and the breaking system. The MPU unit is an automatic transmission, supercharger, air compressor for other uses, and starter for the engine using a multi-purpose unit that will eliminate the need for a torque converter or clutch, flywheel, catalytic converter, starter and supercharger. The MPU reduces pollution to near zero and reduces the aerodynamic drag coefficient on the vehicle. The MPU uses two or more in-line compressors to transfer power from the power source, such as an internal combustion engine (ICE) to a turbine or multi-stage turbine that acts as an automatic... |
| Free-fall simulator capable of displaying a simulated visual environment | 20090312111 | 20091217 |
| A simulator of free-fall containing air power generators (1) and appreciably cylindrical aerodynamic vein (2), in which evolve the persons (6) in state of free-fall, the wall (24) of which is realized by means of a film of flexible material stretched only by means of two frames (28) (29) fixed at the extremities of the aerodynamic vein (2) and to the superstructure (5) maintaining the aerodynamic vein (2). In particular the film of flexible material forming the wall (24) of the aerodynamic vein (2) is translucent and serves as screen to display from the outside of the vein (2) real or simulated images intended to be seen from inside of the aforementioned vein (2). In a particular mode of realization the air power generators (1) are... |
| Novel optical sensor for the instantaneous detection and identification of bioaerosols | 20090310128 | 20091217 |
| A novel apparatus comprising three main systems: air sampling, detection and computerized electric system; and method of using the same in the sampling, detection and identification of bioaerosols, wherein the identification of the said bioaerosol is base on a multiphoton laser diagnostic technique along with the velocity and aerodynamic size of the particular bioaerosol. After exposing the said bioaerosols with near infrared wavelength laser, the obtained fluorescence spectra has been shown to be unique and particular for each bioaerosol, thus allowing the characterization of the said particles.
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| Cover panel for an aircraft, more particularly a landing gear cover panel for a cargo plane | 20090308976 | 20091217 |
| As a result of the mechanical play which increases within the multi-articulated joint 8, 9, 13 from the middle individual joint 14 to the two outer individual joints 15, 16 in the direction of the x-axis or aircraft longitudinal axis, a substantial mechanical isolation of the cover panel from any possible fuselage cell movements is provided. The flap 7 has at least in the area of one side edge an anti-lift security mechanism 26 in order to prevent aerodynamically conditioned flapping and lifting movements of the flap 7 in the direction of the aircraft vertical axis or z-axis.
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| Method and system for detecting the risk of icing on aerodynamic surfaces | 20090306928 | 20091210 |
| The invention relates to a method and a system for detecting the risk of icing on aerodynamic surfaces lapped by a fluid flow (F), in particular on load-bearing surfaces of fluid machines, of the type comprising a temperature sensor (20). The system is characterized in that the temperature sensor (20) is located close to the aerodynamic surface (5S) to be monitored for detecting the temperature of the surface (5S), and that the system comprises a rain sensor (30) located close to the surface (5S) for detecting the presence of water on said surface (5S). The system can thus detect the risk of icing on aerodynamic surfaces in a very effective, simple and inexpensive manner.
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| Aerodynamic shroud having textured surface | 20090304511 | 20091210 |
| An aerodynamic shroud positionable surrounding a hub to which blades are attached is disclosed. The shroud has a textured outer surface that is configured so as to create a turbulent boundary layer for fluid flowing over the surface. The turbulent boundary layer delays flow separation from the shroud and reduces drag. The shroud may be formed from a domed shell mounted on the hub and have skirts that surround the hub. The textured surface is provided by dimples in the surface or projections from the surface. The shroud is intended to reduce main and tail rotor hub drag on helicopters but is also useful on marine propellers, aircraft propellers and jet engine fans.
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| Method for the milling of blisks | 20090304473 | 20091210 |
| When milling blisk blades (13) on a disk blank, side faces of the blades are finish milled and machined by flank milling. Cutting strips (8) of equal width are produced, whose orientation agrees with a flow direction between the blisk blades, such that aerodynamic losses at suction and pressure sides of the blades can be reduced.
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| Vehicle having aerodynamic fan elements | 20090302639 | 20091210 |
| A vehicle is provided with fan housings having inlets and an outlets. Fan are rotatably supported in the housings. The inlets intersect an airflow path along outer surfaces of the vehicle body such that a portion of the airflow is directed through each housing, causing the fans to rotate. A flow of spinning air exits each outlet and is directed toward a central plane of the vehicle.
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| Thin-walled container with sidewall protrusions and reinforced cavities | 20090301991 | 20091210 |
| Disclosed herein are aerodynamic beverage bottles that incorporate fins or protrusions that are molded in to a bottle sidewall, having concavities or valleys between those fins or protrusions that are reinforced to be stiff and otherwise resisting deformation from, for example, pressures generated within the bottle. The sidewall in the region of the fins, protrusions, valleys or concavities may be thinner than other parts of the bottle; fins may be located on one end of a bottle which is thinner than the other end. Such a bottle may have a cylindrical section to which a label may be attached. Such a bottle may be blow-molded. Detailed information on various example embodiments of the inventions are provided in the Detailed Description below, and the inventions are defined... |
| Ventilated cvt | 20090298627 | 20091203 |
| The invention provides apparatus for cooling at least one sheave and/or an endless belt of a continuously variable transmission (CVT). As previously mentioned, the CVT is comprised of a drive clutch, a driven clutch, and the endless belt disposed about the drive and driven clutches. Both the drive and driven clutches include an axially stationary sheave and an axially movable sheave. Certain embodiments provide a ventilation air path through at least one sheave of at least one clutch of the CVT. In addition, certain embodiments provide a ventilation air path through both sheaves of at least one clutch of the CVT. Further, certain embodiments provide apparatus adapted to direct air proximate to an outer face of at least one sheave of at least one clutch inward... |
| Thin-walled blow-formed tossable bottle with reinforced intra-fin cavities | 20090298383 | 20091203 |
| Disclosed herein are aerodynamic beverage bottles that incorporate fins or protrusions that are molded in to a bottle sidewall, having concavities or valleys between those fins or protrusions that are reinforced to be stiff and otherwise resisting deformation from, for example, pressures generated within the bottle. The sidewall in the region of the fins, protrusions, valleys or concavities may be thinner than other parts of the bottle; fins may be located on one end of a bottle which is thinner than the other end. Such a bottle may have a cylindrical section to which a label may be attached. Such a bottle may be blow-molded. Detailed information on various example embodiments of the inventions are provided in the Detailed Description below, and the inventions are defined... |
| Debris removal system and method for wind turbine blades | 20090297352 | 20091203 |
| A system is provided for cleaning debris from horizontal axis wind turbine blades. The system includes a wiper with arms extending partially around the blade adjacent the leading edge and a line engaging the leading edge so as to scrape debris from the blade edge as the arms move along the length of the blade. The arms are carried outwardly along the blades by aerodynamic and centripetal forces, and are retracted by cables attached to the arms. The system is activated by a PLC in response to sensors on the turbine to automatically clean the blade when wind conditions typically allow insects to fly and contaminate the blades. A grease control system is also provided on the blades to prevent grease or oil from the turbine... |
| Asymmetric flow extraction system | 20090297335 | 20091203 |
| A system for asymmetric flow extraction is described and claimed, the system comprising a flow path, a bleed slot in the flow path, a bleed cavity for receiving at least a portion of the fluid extracted from the flow path and a bleed passage in flow communication with the bleed slot and the bleed cavity wherein the bleed passage has at least one deflector having a shape such that the width of the bleed passage cross section varies in a direction normal to the direction of fluid flow in the bleed passage. In another embodiment, the deflector has an aerodynamic surface having a shape such that the flow passage between the aerodynamic surface and a surface located away from it has a cross sectional shape that... |
| Aerodynamically activated front skirt for a vehicle | 20090295190 | 20091203 |
| An active front skirt for a vehicle includes an airfoil positioned in an air stream existing when the vehicle is moving forward. An airfoil positioning mechanism attached to the vehicle and the airfoil allows the airfoil to move between a first position when the vehicle is at rest and a second position when the vehicle has attained an upper limit velocity, the airfoil being moved to the second position through interaction with the air stream. A retracting mechanism returns the airfoil to the first position. A movable front skirt connected to the airfoil correspondingly moves with the airfoil between raised and lowered positions. In the raised position, ground clearance of the skirt is increased. In the lowered position, the skirt deflects an increased portion of the... |
| Aerodynamic sampler for chemical/biological trace detection | 20080314166 | 20081225 |
| An aerodynamic sampler for sampling particles from a surface or a flowing gas stream is provided. The sampler can include an arcuate-shaped shroud having a first opening and a second opening, the first opening being directed in a first direction and the second opening oppositely disposed and spaced apart from the first opening. A gas nozzle having at least one gas outlet directed generally in the first direction can be included and may or may not be located at least partially within the shroud. The gas nozzle is operable to supply a gas jet to a surface that is proximate the first opening of the shroud. In addition, a suction device operable to pull or suck the gas proximate the first opening through the second opening... |
| Turbocharger with stepped two-stage vane nozzle | 20080317593 | 20081225 |
| A turbocharger having a variable nozzle with stepped two-stage vanes (50), the variable nozzle comprising a tubular piston (70) disposed in the bore (44) of the turbine housing (38) such that the piston (70) is axially slidable adjacent to the vanes (50) that extend across the nozzle. Each vane defines a first vane stage (50a) proximate the free end of the vane, the second vane stage (50b) having a different aerodynamic contour in comparison with the first vane stage (50a), each vane comprising a step (60) transitioning from the first vane stage (50a) to the second vane stage (50b). The piston (70) in a closed position closes the second vane stage (50b) so that exhaust gas flows only through the first vane stage (50a). The second... |
| Power loss reduction in turbulent wind for a wind turbine using localized sensing and control | 20080317598 | 20081225 |
| A wind turbine blade assembly includes at least one local load sensor disposed on and/or within a surface of the wind turbine blade and at least one active flow modification device disposed on and/or within a surface of the wind turbine blade and configured to alter the aerodynamics of the wind turbine blade in response to real time local load sensor measurements such that a difference between a current angle of attack and an optimum angle of attack on the wind turbine blade is substantially minimized.
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| Blade for a horizontal-axis wind generator | 20080317599 | 20081225 |
| The invention relates to a blade for a horizontal-axis wind generator consisting of two flattened bodies which are arranged opposite one another in longitudinal convergence towards the tip without making contact with one another, said bodies being attached by means of an intermediate latticework formed by ties (3) with an aerodynamic profile, which ties are joined to the flattened bodies by means of hinged attachments providing flexibility to the structural assembly for preventing fatigue fractures.
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| Power generating system including modular wind turbine-generator assembly | 20080309090 | 20081218 |
| A power generating system for generating electricity from the kinetic energy of a wind flow. The power generating system includes a turbine assembly, and a generator assembly, and may be also provided with a main brake assembly, as well as an emergency brake assembly. The system includes a series of modular components which can be built and adjusted in a modular manner so as to alter the configuration of the system, and thus maximize a generation of electricity by the system, depending on the particular conditions of the wind flow. Other improvements reside in the mounting spokes and aerodynamic blades of the system, as well as in its main brake assembly.
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| System for the reduction of aerodynamic drag on vehicles | 20080309121 | 20081218 |
| The system is designed to reduce the aerodynamic drag on the box type of trucks such as semi-trailer or full truck vans. The system consists of a series of ductwork that gathers airflow from the front of the van and conducts the flow to the rear end of the van where it is released in proportional amounts at the back end of the truck, so as to alleviate the drag.
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| Rear-mounted aerodynamic structure for truck cargo bodies | 20080309122 | 20081218 |
| This invention provides an aerodynamic structure attached to the rear face of a truck cargo body, which rear typically contains a door assembly, with a plurality of doors that swing open on hinges, or a single, full-width door, which rolls upwardly. The various embodiments of the invention allow an aerodynamic structure to be permanently attached to the rear of the trailer in a manner that would obscure access to the door(s) in a deployed position, in which the aerodynamic structure generates reduced drag on the trailer body, yet enables ready access to the door(s) in a folded position. The folded position still allows the rear of the trailer to be fully accessible for loading and unloading, and in the case of swinging, hinged doors (among others),... |
| Vehicle air dam system | 20080303309 | 20081211 |
| An air dam is made of flexible cells installed adjacent to one another so that the air dam is capable of installation in many deflecting configurations on a vehicle and can also deflect under impact. The air dam system may be capable of being deployed at higher speeds while being stowed under the frame of the truck when the truck is operating on rough road surfaces to reduce the potential for air dam damage. The air dam system can be actuated pneumatically and when deployed tends to reduce aerodynamic drag by altering the path of airflow under and/or immediately around a vehicle. Other methods of actuation such as hydraulic or mechanical components may also be used with the air dam system. Alternatively, the air dam cells... |
| Aerodynamic drag reducing apparatus | 20080303310 | 20081211 |
| An aerodynamic drag reducing apparatus is provided for use with vehicles having surfaces that are not streamlined. The apparatus including an exterior cover supported by moveable frames which in turn are supported by sets of supporting linkages. The moveable frames extend rearward and together with the exterior cover form a drag reducing shape for use in a drag reducing configuration and collapse for use in a space saving configuration.
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| Crash attenuating underride guard | 20080303311 | 20081211 |
| An aerodynamic underride guard comprising an angled front section located ahead of the trailer landing gear, a crash attenuating middle section located between the trailer landing gear and the trailer wheel assembly, and an angled rear section located in proximity to the trailer wheel assembly. The front angled section deflects air away from the non-aerodynamic features of the trailer landing gear. The rear angled section deflects air away from the non-aerodynamic features of the trailer wheel assembly, and the crash attenuating middle section can prevent vehicles from under riding the trailer.
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| System and method for side vision detection of obstacles for vehicles | 20080304705 | 20081211 |
| This invention provides a system and method for object detection and collision avoidance for objects and vehicles located behind the cab or front section of an elongated, and possibly tandem, vehicle. Through the use of narrow-baseline stereo vision that can be vertically oriented relative to the ground/road surface, the system and method can employ relatively inexpensive cameras, in a stereo relationship, on a low-profile mounting, to perform reliable detection with good range discrimination. The field of detection is sufficiently behind and aside the rear area to assure an adequate safety zone in most instances. Moreover, this system and method allows all equipment to be maintained on the cab of a tandem vehicle, rather than the interchangeable, and more-prone-to-damage cargo section and/or trailer. One or more cameras... |
| Trailer keel | 20080296930 | 20081204 |
| A trailer fairing for reducing aerodynamic drag from trailer landing gear and/or wheel assembly is disclosed. The fairing may be directly connected to the forward facing structural supports of the landing gear, and an air tank may be located between the fairing and the cargo storage area. A single fairing may be used to reduce the drag from both the trailer landing gear and wheel assembly. The fairing may include a tapered front section and/or a rear section. The fairing may have rounded, oval, angled, and/or tapered sections. A plurality of fairings may also be used.
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| Method and apparatus for reducing bird and fish injuries and deaths at wind and water-turbine power-generation sites | 20080298962 | 20081204 |
| A simple system is provided to dramatically reduce the number of bird fatalities and injuries, as these are bird-kills that man should be able to do something about. Essentially, the inventive apparatus comprises one or more instantaneously inflatable mini-airbags on turbine blade leading edges which, in the “stowed position” are tightly conformally elastically wrapped around or juxtaposed to the turbine blade surface(s) and/or edges(s) thereby not affecting the blade's aerodynamic efficiency. The airbag(s) can be activated and restowed or recollapsed very rapidly, thereby not significantly negatively impacting the operational efficiency of the wind machine. In a similar manner, fish-kills or injuries taking place in the turbine impellers of hydroelectric power-generator facilities may be avoided (as opposed to ameliorated) using another inventive system and method taught herein,... |
| Method and device for controlling load reduction for a wind turbine rotor | 20080298963 | 20081204 |
| A method for controlling load reduction for a wind turbine rotor with rotor blades comprising an aerodynamic active element responsive to a control signal for modifying its setting is provided. The loads acting on the rotor blades in relation to the rotor's azimuth are detected and individual control signals based on a PI control system are established. Each individual control signal is a complex number containing an amplitude defining the degree of modification of the respective setting and an angle defining the phase of the modification of the respective setting with respect to the rotor's azimuth. The angle of the complex number is corrected by a phase correction factor. The elements are provided with the individual control signals. The input to the PI-control system is a... |
| Wind turbine blade with anti-noise devices | 20080298967 | 20081204 |
| A wind turbine comprising at least a blade (11) having an aerodynamic profile with a leading edge (13), a trailing edge (15) and suction and pressure sides between the leading edge (13) and the trailing edge (15) that includes an anti-noise device (31) placed on the suction side formed by elements (33) that modify the frequency spectra of the boundary layer noise. Preferably the anti-noise device (31) is placed on the suction side between two sections corresponding to chord positions in the range of 40%-95% of -the chord length, measured from the leading edge (13).
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| Anisometric particles in the form of nanofibers/mesofibers,nanopipes, nanocables/mesocables, nanobands/mesobands, and the curved or branched variations thereof | 20080299208 | 20081204 |
| The invention relates to novel anisometric mesoparticles and nanoparticles in the form of anisometric mesofibers/nanofibers, mesopipes/nanopipes, mesobands/nanobands, mesocables/nanocables, and the curved and branched or superimposed variations thereof as well as a novel method for the production thereof. The invention particularly relates to anisometric mesoparticles and nanoparticles which have an aerodynamic diameter <5 μm, the production thereof, loading thereof with active substances if the same cannot directly be utilized as an active substance, and the use thereof especially for producing medicaments against lung diseases or systemic diseases in humans and animals if the particles cannot directly be utilized as medicaments without carriers.
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| Aerodynamic windshield wiper arm | 20080289137 | 20081127 |
| An aerodynamic windshield wiper arm that includes an integrated aerodynamic element that causes down force to be applied to the wiper arm as the air speed across the wiper arm increases, such as in high winds and/or at high speeds. The aerodynamic element is integrally formed with the wiper arm such that it is not easily removed, unlike aerodynamic attachments. The wiper arm is formed using an injection molding process and a plastic material. The aerodynamic element may be in the form of an airfoil or a lip or any other shape capable of causing down force when high winds contact the wiper arm. The one-piece wiper arm provides improved functionality and improved aesthetics over previous wiper arms.
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| Gravity driven fluid supply vessel for dispensing an aromatic odor neutralizer | 20080290186 | 20081127 |
| An aromatic odor neutralizer includes a vaporization chamber containing a wick with an end part immersed in fluid in a storage cup that is gravity fed from an airtight vessel by the use of air pathways exposed when the liquid level in the cup is reduced. The vaporization chamber is located in a dispenser housing with an internal passage between end walls and communicating with vents in the sides for aerodynamic airflow to efficiently absorb vapors from a vaporizer chamber.
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| Personal propulsion device with hands free control | 20080290616 | 20081127 |
| An improved personal propulsion device that generally imparts thrust directly to the user. The device allows hands free control of thrust magnitude and direction so both hands can grasp and control bicycle handlebars and brakes, watercraft paddles, ski poles or other apparatuses. The device is adjustable vertically, on the users' back, higher to allow sitting in a canoe or wheelchair and lower for standing on skates, skis, kick scooters etc. A user on a bicycle may prefer to lean forward for comfort and aerodynamics, a device adjustment compensates and delivers level thrust. A user on a snowboard or skateboard stands oblique to the direction of travel, a device adjustment allows in line thrust. Both users' hands and arms are free to balance, protect others by pushing... |
| Gravity driven fluid supply vessel for dispensing an aromatic odor neutralizer | 20080292294 | 20081127 |
| An aromatic odor neutralizer includes a vaporization chamber containing a wick with an end part immersed in fluid in a storage cup that is gravity fed from an airtight vessel by the use of air pathways exposed when the liquid level in the cup is reduced. The vaporization chamber is located in a dispenser housing with an internal passage between end walls and communicating with vents in the sides for aerodynamic airflow to efficiently absorb vapors from a vaporizer chamber.
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| Apparatus for dispensing an aromatic odor neutralizer | 20080292508 | 20081127 |
| An aromatic odor neutralizer includes a dispenser housing with an internal passage between end walls and communicating with vents in the sides for aerodynamic airflow to efficiently absorb vapors from a vaporizer chamber within the dispenser housing. The vaporization chamber contains a wick with an end part immersed in fluid in a storage cup that is gravity fed from an air tight vessel by the use of air pathways exposed when the liquid level in the cup is reduced.
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| Flexible insulation blanket having a ceramic matrix composite outer layer | 20080292838 | 20081127 |
| A flexible insulation blanket having a ceramic matrix composite (CMC) outer layer, and a method of producing a flexible insulation blanket having a smooth, aerodynamically suitable, outer surface by infiltrating ceramic material within the outer ceramic fabric layer of the flexible insulation blanket and curing the ceramic material to form a CMC layer. The CMC layer is cured while the blanket is under compression such that the resulting CMC layer has a smooth surface.
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| Liftgate exterior module for an automotive vehicle | 20080284204 | 20081120 |
| The technology described herein provides a molded trim assembly located externally at the top of a liftgate structure to provide an aerodynamic and stylish overhang above the liftgate glass. Furthermore, the technology also provides a liftgate exterior module including a plug-in module containing a motorized window wiper arm assembly, a central high mounted stop light, and a washer fluid spray nozzle.
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| Course of leading edges for turbomachine components | 20080286107 | 20081120 |
| where sweeptip or sweephub, respectively, represents the sweep angle at the tip or at the hub, determined in accordance with the operating conditions, and the extension represents the height of the blade in percent, by which the sweep angle departs from 0° relative to the coordinate extending normal to the axial coordinate.
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| Method for improving the surface smoothness of planar textile structures | 20080287637 | 20081120 |
| A method for improving the surface smoothness of planar textile structures, in particular sails, sunblinds, or textiles used in vehicles by applying at least one aminopolysiloxane. In this way it becomes possible to achieve individual and, in particular, new combinations of properties and effects, such as better aerodynamic properties, reduced air permeability, good soil repellence, increased elasticity, good water repellence, reduction of frictional forces during use.
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| Bobber | 20080276522 | 20081113 |
| A bobber has a float and sail. The sail catches the wind and stealthily moves the bait over to the area where the fish are, such as under the overhanging trees or branches near the shore of a lake. The sail also makes the bobber more aerodynamic and allows for more accurate casting. The sail may be attached to a stem that is attached to the float. The sail may be removable from the stem. This allows the fisherman to put on larger or smaller sails and also directional sails. The stem and/or the float may have a passage way so that the bobber can be used a slip bobber or a fixed bobber.
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| Fan powered silencing terminal unit | 20080271945 | 20081106 |
| An apparatus and method for attenuating the sound generated by a fan powered terminal unit in an HVAC (heating, ventilating, and air conditioning) system. The apparatus utilizes internal geometry to minimize noise due to air disturbances and aerodynamic effects within the apparatus.
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| Ducted fan air vehicle with deployable wings | 20080272226 | 20081106 |
| A ducted fan air vehicle and method of operation is disclosed for obtaining aerodynamic lift and efficiency in forward flight operation without significantly impacting hover stability. One or more retractable wings are included on the ducted fan air vehicle and are deployed during forward flight to provide aerodynamic lift. The wing or wings are retracted when the vehicle hovers to reduce the impact the wings have on stability in a wind. Each wing may conform to the curvature or profile of the vehicle when retracted, and may be constructed in one or more wing sections. The wing or wings may be deployed and retracted automatically or at the command of an operator. Each wing and related components may be integrated into the vehicle or may be... |
| Trailer with aerodynamic rear door | 20080272617 | 20081106 |
| An aerodynamic cargo container with rounded rear doors is disclosed. The aerodynamic cargo container includes an angled rear area that reduces base drag when the container is transported. The rear sliding door allows for partial opening of the door and allows for operation of the door when the rear of the container is in close proximity to another object. The crash attenuating skirt deflects vehicles away from the cargo container. A pair of cargo doors may define the curved contour of the trailer rear section. These doors may have a plurality of pivoted and segmented sections that assume the curved contour of a stationary edge when the doors are moved to a closed position.
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| Blower and air conditioner outdoor unit with the blower | 20080273973 | 20081106 |
| A blower is provided with an axial flow impeller 7, a fan motor 8 positioned in a suction side of the axial flow impeller 7, and a motor stay 9 supporting the fan motor 8. The motor stay 9 is substantially formed to have a linear shape and attached in parallel to a rotating surface of the axial flow impeller 7. An impeller blade front edge 17 of the axial flow impeller 7 is positioned in a region X which is closer to the motor stay 9 than a region Y in which an air flow turbulence in a wake flow of the motor stay 9 is expanded, and in which region X a range of the air flow turbulence is reduced. Accordingly, it is possible... |
| Aerodynamic lift enhancement gate valve | 20070295254 | 20071227 |
| An aerodynamic lift enhancement gate valve including a valve blade shaped as an airfoil or as a sail and is disposed at the leading edge of an airfoil. Or as a sail, in such a way as to form a fluid gate formed between the trailing edge (at the chord) of the gate valve blade, and the leading edge (nose) of the airfoil or sail, (at the chord). The gate valve blade catches the wind, and will cause a wind velocity surface pressure to build against the upwind surface of the gate valve blade, which pressure is regulated by springs and or elastic. When in operation, the chord of the gate valve blade will remain substantially parallel to the chord of the airfoil, or sail. The... |
| Individual survival module | 20070296605 | 20071227 |
| This invention is directed toward an individual protective module which provides protection against earthquakes, cyclones, terrorist attacks, acts of war and other natural and criminal disasters. The module comprises a parallelepiped frame with a dimensionally-stable structure which is constructed of highly fire resistant and structurally robust material with an outer, resistant, aerodynamic cover. Five faces of the module are closed, which the sixth, front face had a sliding protective shield through which the user can enter and exit. The module is equipped with oxygen and water reserves, electronic lighting, communication means, an electronic tracking system, and a battery. Because the module is dimensionally stable of difficult to deform or crush, it can be anchored to a fixed point of a building.
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| Oscillating fluid power generator | 20070297903 | 20071227 |
| A system and method for harvesting the kinetic energy of a fluid flow for power generation with a vertically oriented, aerodynamic wing structure comprising one or more airfoil elements pivotably attached to a mast. When activated by the moving fluid stream, the wing structure oscillates back and forth, generating lift first in one direction then in the opposite direction. This oscillating movement is converted to unidirectional rotational movement in order to provide motive power to an electricity generator. Unlike other oscillating devices, this device is designed to harvest the maximum aerodynamic lift forces available for a given oscillation cycle. Because the system is not subjected to the same intense forces and stresses as turbine systems, it can be constructed less expensively, reducing the cost of electricity... |
| Golf club | 20070293333 | 20071220 |
| An aerodynamic force generated in a downward direction by the loft of the club face is compensated by asymmetric wings applying an aerodynamic lifting force to an upper direction of the club head during a swing of the club. Even when a golfer has a swing speed or posture problem when swinging a club, the head of the club is guided to rotate along a desired proper orbit. A golf ball can be hit by a sweet spot of the head face of the club due to the stability and compensating force for achieving a straight drive, and enhanced flying distance.
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| Location signaling device | 20070284476 | 20071213 |
| A location signalling device comprising a wing balloon for signalling a location. The wing balloon is fixed to a tether line that itself is fixed to the location to be signalled. The wing balloon has an inflatable aerodynamically shaped hollow body to be at least partly be filled with a lighter-than-air gas and having a wing attack surface for air flowing relative to said wing balloon. The floating aloft of said wing balloon is supported by said air flow. When the wing balloon is inflated, a flexible wing portion is passively variable. The stronger the wind, the less attack is given. Thus, the dragging force on the tether line is generally static.
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| Stator blade airfoil profile for a compressor | 20070286718 | 20071213 |
| Tenth stage stator vanes for a compressor comprise airfoil profiles substantially in accordance with Cartesian coordinate values of x, Y and Z set forth in inches in Table I, wherein the Z coordinate values are perpendicular distances from planes normal to a radius from the compressor centerline and containing the X and Y values with the Z value commencing at zero in the X, Y plane at a radial aerodynamic section of the airfoil. X and Y are coordinate values defining the airfoil profile at each distance Z. The X, Y and Z values may be scaled to provide a scaled-up or scaled-down airfoil section for each stator vane.
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| Low pressure impact separator for separation, classification and collection of ultra-fine particles | 20070277486 | 20071206 |
| Impact type gas-particle separation is applied to ultra-fine particles by judiciously altering the aerodynamic drag on the particles with respect to their inertia by operation at sub-atmospheric pressures. An impact separator has a housing having a channel in which particles flow in a fluid such as air, a purified gas or mixtures thereof. A plurality of blades are placed in the channel for affecting the motion of the particles and the fluid with respect to each other. A second channel branches from the first channel to receive particles diverted and separated from the flow of the fluid in the first channel. A flow mechanism creates a sub-atmospheric pressure in the channel.
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| Athletic hydration system for bicyclists | 20070278273 | 20071206 |
| The present invention provides an athletic hydration system for cyclists which includes up to four containers having inverted fluid-filled bottles contained therein, in which the containers are placed either within the frame of a bicycle or at the rear of the bicycle behind the bicycle seat. A system of valves determines whether a cyclist drinks from one, two, three or all four fluid-filled bottles simultaneously. The athletic hydration system is hygienic, versatile and flexible, and provides adequate hydration over extended periods of time in which quick removal and installation of hydration products are possible by the cyclist while maintaining the speed, cadence and aerodynamic posture of the cyclist.
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| Amphibious recreational vessel | 20070281559 | 20071206 |
| A recreational vessel for carrying a plurality of passengers capable of movement on land and in water. The recreational vessel includes an upper section with passenger seating, and lower section having an engine, a transmission, a marine propulsion unit, and at least two sets of wheels joined by axles. The upper and lower sections are separated by a deck plate. The lower section forms a pod-free and watertight hull which is designed to maximize both the aerodynamic and hydrodynamic efficiency of the vessel. Located between the deck plate and the inner bottom surface of the hull is an engine, which is centered within the hull and is coupled to a transfer case. The transfer case is coupled to a first drive shaft and to a second... |
| Support and positioning system for miniature radioactive sources by aerodynamic levitation and application to a device for continuous characterisation of prostate implants | 20070282153 | 20071206 |
| The invention relates to a support and positioning system for at least one miniaturised element in the form of a cylinder. The system comprises a tube comprising an upper part, a median part and a lower part, the upper part being provided with an orifice into which the element is inserted and enabling displacement of the element as far as the median part that has a diameter slightly greater than the diameter of the cylinder forming the element, the lower part being connected to means for controlled injection of a gas to inject a gas inside the tube so as to levitate the element to the required height in the median part of the tube, the lower part of the tube being provided with an element... |
| Set of conjugated components to build a ultralight type airplane | 20070272793 | 20071129 |
| A The set of conjugated components to build a ultralight type airplane, in particular a constructive concept that has as end product a ultralight type airplane with a general configuration visually similar to the DEMOISELLE. In summary, the inventive concept has as purpose to enable that a handcrafted and ancient concept airplane is mass-produced, using modern resources, which characterizes by a better aerodynamical sustentation, in particular as a result of parts which are specially designed to carry out the known functions with extraordinarily improved results. In a general concept, without detailing the components in their specific constructions, we define the airplane obtained based on the conjugated components such as the fuselage (1); wings (2); empennages (3); landing gear (4); systems (5) which include the control (6)... |
| Ducted open rotor apparatus and method | 20070272796 | 20071129 |
| A propulsor apparatus for a mobile platform, for example an aircraft is provided. The propulsor apparatus includes an aerodynamically shaped propeller duct that houses at least a portion of a turboprop engine, and fully houses a propeller driven by the engine. Inside the propeller duct is a circumferential ring that closely surrounds the propeller such that only a small clearance is provided between the outermost tips of the propeller blades and an inner surface of the circumferential ring. The circumferential ring includes sound deadening material that attenuates noise generated by the tip vortices created at the outermost tips of the propeller blades. The propeller duct and circumferential ring are supported by a plurality of structural rods that couple to structure of the mobile platform, for example... |
| Reactor design to reduce particle deposition during process abatement | 20070274876 | 20071129 |
| The present invention relates to systems and methods for controlled combustion and decomposition of gaseous pollutants while reducing deposition of unwanted reaction products from within the treatment systems. The systems include a novel thermal reaction chamber design having stacked reticulated ceramic rings through which fluid, e.g., gases, may be directed to form a boundary layer along the interior wall of the thermal reaction chamber, thereby reducing particulate matter buildup thereon. The systems further include the introduction of fluids from the center pilot jet to alter the aerodynamics of the interior of the thermal reaction chamber.
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| Hockey stick having a single, hollow primary tube | 20070275799 | 20071129 |
| A handle is adapted to be held by a player and a striking end is adapted to contact and propel an object A structure for a hockey stick is described by using a single, hollow tube of composite material, wherein tubular “ports” extend through the hollow tube. The ends of the ports are bonded to the walls of the hollow tube. The ports improve the stiffness, strength, aerodynamics and comfort of the hockey stick.
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| Airlaid method with an improved through-put rate | 20070266503 | 20071122 |
| The invention relates to a method for producing a fibrous nonwoven by applying an aerodynamic process providing an improved throughput, a fibrous nonwoven produced according to said process, as well as a short fiber suitable for use in said method.
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| Three-stage dust sampler | 20070269349 | 20071122 |
| A three-stage dust sampler makes use of a porous foam as the impactor substrates. The sampler includes an annular inlet which conforms to ISO/CEN/ACGIH inhalable sampling criteria, two impactor stages to classify thoracic and respirable particles and a final filter to collect respirable particles after the impactors. For 100 ppi polymer foam substrates, and a flow rate of 3.2 lpm, the collection efficiency curves of the thoracic and respirable dust matches ISO/CEN/ACGIH criteria when the jet-to-plate distance is 1.0. The cut-off aerodynamic diameter is 9.6 and 4.0 μm for the first and second impactor stages, respectively, and √{square root over (stk50)} is 0.39 for both stages. The collection efficiencies for solid particles is equal to that for liquid particles, indicating that there is no solid particle... |
| Hockey stick system having a multiple tube structure | 20070270253 | 20071122 |
| A handle is adapted to be held by a player and a striking end is adapted to contact and propel an object A structure for a hockey stick is described by using multiple composite tubes bonded to one another, wherein apertures, or “ports,” are molded between the tubes to improve the stiffness, strength, aerodynamics and comfort of the hockey stick.
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| Aerodynamic vented rotor | 20070261929 | 20071115 |
| An aerodynamic vented rotor comprises an outboard disc, an inboard disc spaced from the outboard disc, and fins extending between the outboard disc and the inboard disc and defining vents therebetween. The fins have an airfoil-shaped cross section with a leading edge facing radially inwardly on the rotor. The fins constitute an inner core, and a hat section extends from the inner core of the rotor.
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| Shelton wing in ground effect | 20070262199 | 20071115 |
| Wing in ground effect vehicles operate near the surface to acquire benefits in aerodynamic performance. However, a lack of sufficient stability has been a frequent limitation for such vehicles. The disclosed invention is a wing in ground effect vehicle that comprises a plurality of mechanical devices to acquire stability in roll and height with respect to the surface. Each device comprises a pivotally mounted aerodynamic lifting surface, surface contacting element, and interconnecting structure. The disclosed arrangement of these components actively determines the angle of attack of the aerodynamic lifting surfaces and produces vehicle stability in roll and height with respect to the surface.
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| Wing employing leading edge flaps and winglets to achieve improved aerodynamic performance | 20070262207 | 20071115 |
| A wing for use on a supersonic aircraft that includes an inboard section a central section of the wing outboard of the inboard portion, and an outboard section. The outboard section can be a winglet oriented anhedrally relative to a lateral axis of the supersonic aircraft. Leading edge segments on the inboard section, central section and outboard winglet may have mounted thereon leading-edge flaps. These flaps are adjusted by a control system operable to reposition the leading-edge flaps in order to improve the aerodynamic performance of the supersonic aircraft. This winglet promotes sonic boom minimization. Further, the wing tip anhedral allows greater inboard dihedral. This effectively pushes lift aft for sonic boom and control purposes while minimizing the movement of control surfaces.
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| Propulsion kit | 20070256587 | 20071108 |
| The present invention is a propulsion kit that is attached to a gliding air to surface bomb. The kit of the invention comprises one or more engines and, when activated, allows a significant extension of the length of the flight path of the bomb. The engines can be any type of air-breathing engine for example jet engines. The kit can be designed to be retrofitted to an existing gliding bomb. The kit of the invention allows the original bomb to function in one of the three following modes, depending on the bomb size and the aerodynamic characteristics: the original operation mode, an improved gliding ratio mode, and a cruise trajectory mode.
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| Covering device for a hinge of an aircraft | 20070257151 | 20071108 |
| Hinges, in particular in doors of aircraft, have poor aerodynamics. According to one embodiment of the present invention, a covering device for a hinge of an aircraft is provided with a flexible covering, which for example is stretched, with a closed hinge, over the outer contour of the hinge. Advantageously, this makes possibly the covering of openings between first and second hinge parts, whereby an improved aerodynamic can be achieved.
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| Fuel efficient dynamic air dam system | 20070257512 | 20071108 |
| Active, aerodynamic controller that describes a method for dynamically controlling airflow using computer controlled movable air dams and airfoils on motor vehicles. It is well known that motor vehicles generally have a great deal of aerodynamic friction also known as drag. Fuel efficiency is greatly affected by a vehicle's aerodynamic drag. Aerodynamic drag is caused by both induced drag and parasitic drag. Parasite drag is somewhat fixed by the overall design and shape of a vehicle. Parasite drag is caused primarily by the laminar flow of air over the smooth surfaces of the vehicle's hood, roof, windows, side mirrors and door panels. Induced drag is much more variable and is primarily created by the differential pressure effects of air flowing over, under and around a vehicle,... |
| Aerodynamic air deflection system | 20070257513 | 20071108 |
| A tractor and trailer coupled together in tandem towing relationship is provided with an air deflector system attached to the tractor for aerodynamically reducing the drag on such combination by enclosing the space between the cab of the tractor and the trailer. A support means is attached to the frame of the tractor or body of the trailer. Two side fairings are movably attached to the support means for extending from the rear of the cab to the trailer, and wherein the side fairings mate with a top fairing. A means is provided for moving the side fairings from one position to another based upon the alignment between the trailer and the tractor.
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| Axial fan | 20070258822 | 20071108 |
| An axial fan (1) rotating in a plane (XY) about an axis (2) comprises a central hub (3), a plurality of blades (4), which have a root (5) and a tip (6), the blades (4) being delimited by a convex leading edge (7) and by a concave trailing edge (8), their projections in the fan rotation plane each being formed by circular arc segments; the blades (4) are made from sections with aerodynamic profiles, each with decreasing length and more curved from the perimeter to the hub.
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| Golf ball | 20070259738 | 20071108 |
| The invention provides a golf ball having numerous dimples on a surface thereof, wherein at least one dimple cross-sectional shape is a cycloid curve or a trochoid curve. By thus optimizing the cross-sectional shape of the dimples, the aerodynamic performance due to the dimple effect is enhanced, enabling the distance traveled by the ball to be increased.
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| Passive aerodynamic sonic boom suppression for supersonic aircraft | 20070252028 | 20071101 |
| An aircraft capable of supersonic flight comprises a body portion including a fuselage, a wing, and an engine nacelle mounted below the wing. The aircraft may also include a high-mounted aft, tail. The area/lift distribution of the body portion is tailored to reduce sonic boom disturbance. The body portion further includes a blunt nose and a gull dihedral wing configuration that further reduces sonic boom disturbance and eases constraints on area/lift distribution tailoring. The gull dihedral wing or tail is configured to carry lifting force to its trailing edge to create an expansion at the aft end of the aircraft that reduces aft sonic boom ground shock strength. The volume of the mid-portion of the fuselage can be reduced above the wing to create a sloped... |
| Wing tip devices | 20070252031 | 20071101 |
| A tip device to act as an outboard continuation of an aircraft wing or other aerodynamic lifting surface has a downward cant angle, a leading edge swept back in relation to the leading edge of the inboard lifting surface, and a chord reducing in the outboard direction of the device. A favourable balance between induced drag reduction and increased wing root bending moment can thereby be achieved. Preferably the device also has an upwardly canted portion at its root end so that the downward cant commences from a relatively elevated spanwise location, thereby alleviating any ground clearance problems.
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| Seal assemblies for use with drooped spoilers and other control surfaces on aircraft | 20070252040 | 20071101 |
| Aerodynamic seals for use with control surfaces on aircraft are described herein. In one embodiment, a seal assembly for use with an aircraft includes a first seal member and a second seal member. The first seal member has a first proximal portion configured to be attached to a fixed airfoil portion of the aircraft, and a first distal portion configured to extend outwardly from the fixed airfoil portion toward a movable control surface. The second seal member has a second proximal portion configured to be attached to the movable control surface, and a second distal portion configured to extend outwardly from the control surface toward the fixed airfoil portion. In this embodiment, the second distal portion is further configured to movably contact the first distal portion... |
| Promotional item | 20070252043 | 20071101 |
| A promotional item (10) includes a central member (12) having one or more receiving features (14, 16) adapted to removable secure one or more substantially rectangular card-like objects (18), such as business cards, credit cards, baseball cards, and the like. In an embodiment, the flying promotional item (10) comprises an aircraft (10, 100, 200, 300, 400, 500, 600, 700) in which the central member (12) forms a fuselage and the cards or card-like objects (18) form aerodynamic surfaces for providing aerodynamic capability to the promotional item (10). Thus, the one or more card-like objects (18) provide a plurality of independent functional uses. An instrument (22), such as a pen, pencil or stylus, made be disposed within the aircraft such that the tip (24) of the instrument... |
| System for detecting and compensating for aerodynamic instabilities in turbo-jet engines | 20060288703 | 20061228 |
| The present invention relates to a system for detecting aerodynamic instabilities in a jet turbine engine having a pressure transducer mounted in the engine. The pressure transducer, welded to a circuit in signal communication with a controller, is adapted to send measured pressure readings from air in a combustion chamber to the controller. The controller, located in spaced apart relation from the engine, is adapted by software to detect pressure patterns from the pressure signals generated by the transducer that are indicative of a stall or surge. A series of fuel and air valves located with compression and combustion chambers of the engine are in signal communication with the controller. The controller in response to detecting pressure signals indicating a stall or surge is operative to... |
| Device with remote motor for controlling an aerodynamic control surface of a missile | 20060289695 | 20061228 |
| An aircraft comprising at least one aerodynamic control surface (26) controlled using a remote motor (4), through a transmission comprising a linear device (7) rigid in torsion but flexible in bending and in tension and compression, to absorb thermomechanical deformations. This transmission comprises small clearances, good flexibility, does not require any additional support and makes favourable use of a reduction gear (9) located near the control surface (26) rather than near the motor (4).
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| High pulse repetition rate gas discharge laser | 20060291517 | 20061228 |
| A pulsed gas discharge laser operating at an output laser pulse repetition rate of greater than 4 kHz and a method of operating same is disclosed which may comprise a high voltage electrode having a longitudinal extent; a main insulator electrically insulating the high voltage electrode from a grounded gas discharge chamber; a preionizer longitudinally extending along at least a portion of the longitudinal extent of the high voltage electrode; a preionization shim integral with the electrode extending toward the preionizer. The preionizer may be formed integrally with the main insulator. The preionization shim may substantially cover the gap between the electrode and the preionizer. The apparatus and method may comprise the high voltage electrode being disposed in an electrode receiving pocket in the main insulator... |
| Impeller for supercharger and method of manufacturing the same | 20060291996 | 20061228 |
| [Problems]To provide a lost-wax cast impeller for a supercharger having no parting line corresponding part on a hub surface and a blade surface in each space demarcated by pairs of long blades adjacent to each other and having excellent aerodynamic performance. [Means for Solving Problems]This method of manufacturing the impeller comprises a step for forming a lost form pattern formed in the substantially same shape as the impeller for the supercharger, a step for forming a mold by eliminating and removing the lost form pattern after the lost form pattern is coated with a refractory, and a step for pouring a molten metal in the mold for casting. In the step for molding the lost form pattern, a lost material is injection-molded in a space demarcated... |
| Medicaments | 20060292085 | 20061228 |
| There is described a bimodal pharmaceutical composition comprising effective amounts of a first active ingredient which substantially comprises a coarse fraction and a second active ingredient which substantially comprise a fine fraction characterized in that the coarse fraction possesses a greater mass median aerodynamic diameter than the fine fraction. There is also described a method of delivering a therapeutically effective amount of a substantially fine active ingredient to the lung of a patient by co-administration with a substantially coarse active ingredient.
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| Rotating filter screen with baffle | 20060283157 | 20061221 |
| A rotating filter screen assembly is provided for filtering debris from cooling and combustion air provided to an engine system having an engine fan adapted to draw air through the filter screen assembly. The filter screen assembly includes a rotating filter screen having an upstream side and a downstream side. The filter screen is adapted to collect debris on the upstream side from air passing through the filter screen. A stationary cleaning chamber is mounted in the filter screen assembly and has an open face adjacent the upstream side of the filter screen. A vacuum source is connected to the cleaning chamber and is adapted to remove collected debris from the upstream side of the filter screen as the filter screen rotates relative to the cleaning... |
| Apparatus and method for automatically fabricating tape with threads for visualization of air streams on aerodynamic surfaces | 20060283541 | 20061221 |
| Apparatus and method for visualizing air stream by little threads on aerodynamic surfaces such that strips of adhesive tape populated with threads are automatically fabricated.
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| Unmanned urban aerial vehicle | 20060284002 | 20061221 |
| The proposed UUAV provides a small, agile vehicle that leverages the unique principals of remote controlled model aviation. The UUAV also encompasses an aerodynamically shaped, gas filled wing that can be used to provide buoyancy for lift assistance both through the use of the lighter than air gas and by its aerodynamic shape in forward flight.
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| Hybrid unmanned vehicle for high altitude operations | 20060284003 | 20061221 |
| A hybrid aerial vehicle is optimized, for example, and not by way of limitation, to operate above 100,000 feet in altitude and provide persistent and maneuverable flight while carrying a wide array of communications and sensing payloads. The hybrid vehicle may use the high altitude winds to gain altitude by pitching up with the center of gravity (CG) control and using its propulsion drive to thrust into the wind to create aerodynamic lift to rise above the neutral buoyancy altitude. The hybrid vehicle will pitch down with the CG control so as to use gravity and propulsion to accelerate. Yaw control directs the flight towards any compass direction by rotating the gondola. This maneuvering capability permits the vehicle to station operate persistently, even in high winds.... |
| Hydrofoil for an amphibious aircraft | 20060284010 | 20061221 |
| A control apparatus, such as a hydrofoil, for general aviation class amphibious aircraft which include at least one fuselage having a hydrodynamic surface, the fuselage including a primary flight surface and a ducted power plant located aft and above the fuselage. The power plant location removes the fan/propeller arc from water and spray during water-borne taxiing, takeoff and landing. The combination of the hydrofoil, fuselage, lifting surface and ducting provides an aerodynamically efficient design with a lower center of gravity and protected powerplant for yielding improved performance including increased range and airspeed, together with favorable maneuverability, stability and control characteristics both aerodynamically and hydrodynamically.
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| Sealed structural passenger window assembly and method of forming same | 20060284016 | 20061221 |
| A window assembly and method for use with a mobile platform, and particularly with commercial or military aircraft. The window assembly includes a composite window panel that is secured to the fuselage skin of the aircraft. A tempered glass fairing is used in connection with a retainer clip and a plurality of sealing components to seal the fairing over the window panel in a manner that provides a sealed air gap between the inner surface of the fairing and the outer surface of the window panel. The fairing and the sealed air gap help to thermally isolate the window panel from the significant ambient temperature changes that are encountered during flight of the mobile platform. The fairing also provides a hazard barrier to protect the composite... |
| Apparatus and method for installing lines in conduits | 20060284148 | 20061221 |
| An apparatus for placing lines in a conduit is disclosed. The apparatus uses a battery powered electric fan in an aerodynamically shaped body to fly through the conduit pulling a jet line. The apparatus is used instead of “fish” tape, vacuum, or compressed air to draw a jet line through the conduit.
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| Axial flow fan improvements | 20060286924 | 20061221 |
| An energy efficient and compact axial fan with a housing comprising a fan assembly comprising a drive motor and a propeller coupled thereto. The inlet opening and/or the outlet opening of the fan housing are provided with a shutter assembly positioned adjacent the propeller and having a plurality aerodynamically shaped pivoted louvers working in tandem for less air obstruction and noise. The propeller comprises a plurality of radial blades comprising means for straitening the air flow and reducing the vortex flow of the propeller thereby permitting the shutter to be mounted adjacent the propeller to lessen the dept of the fan housing for making the fan more compact.
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| Cricket conditions simulator | 20060287024 | 20061221 |
| The cricket conditions simulator is an educational development system for cricketers and coaches, with means of simulating a plurality of outdoor cricket competition conditions relative to cricket pitch scenarios during practice sessions, by utilizing specially designed building structures equipped with capabilities to simultaneously create a plurality of outdoor temperatures and relative humidity, illumination, visual and spectator cultural sounds as distractions, wind speeds, means to record cricketers' performances, cricket pitch deterioration and cricket ball aerodynamics; and a heat exchanger equipped with pressure, moisture content and thermal sensors located within the cricket pitch to modify cricket pitch conditions. Designed activities in the simulator build mental fortitude as a necessary requirement in order to bat, field and bowl under different environmental and cricket pitch conditions for extended periods; and... |
| In-flight refueling system, damping device and method for damping oscillations in in-flight refueling system components | 20060278762 | 20061214 |
| An in-flight refueling system, damping device and method are provided for substantially reversing a change in the disposition of an elongate hose extending from a first aircraft during an in-flight refueling operation. The various embodiments of the present invention provide a compact, lightweight, and easily installed damping device that may act to minimize the occurrence of oscillations within the elongate hose that may act to produce a change in the disposition of the elongate hose. In addition, the embodiments of the present invention facilitate the detuning of the elongate hose and, for instance, an attached drogue that may oscillate uncontrollably at a resonant frequency in response to aerodynamic forces exerted on the hose and drogue during an in-flight refueling operation.
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| Method and apparatus for mesoscale deposition of biological materials and biomaterials | 20060280866 | 20061214 |
| Methods and apparatus for the direct deposition or patterning of biological materials and compatible biomaterials. The method is capable of depositing biological materials and biomaterials in a computer defined pattern, and uses aerodynamic focusing of an aerosol stream to deposit mesoscale patterns onto planar or non-planar targets without the use of masks or modified environments. The aerosolized compositions may be processed before deposition (pre-processing) or after deposition on the target (post-processing). Depositable materials include, not are not limited to conductive metal precursors, nanoparticle metal inks, dielectric and resistor pastes, biocompatible polymers, and a range of biomolecules including peptides, viruses, proteinaceous enzymes, extra-cellular matrix biomolecules, as well as whole bacterial, yeast, and mammalian cell suspensions. The targets may be planar or non-planar, and are optionally biocompatible. Applications... |
| Aerodynamic-hybrid vertical-axis wind turbine | 20060275105 | 20061207 |
| An aerodynamic-hybrid, vertical-axis wind turbine which includes a rotor airfoil and stator blade combination which maximizes energy production by increasing wind velocity and pressure while eliminating back pressure and improving the laminar flow of wind both around and through the device. The rotor airfoils have a horizontal cross-section with a crescent shape including a convex leading side and a concave trailing side with a thicker middle section that tapers to narrower sections at ends. The stator blades have a horizontal cross-section with a planar side and a convex side. Rotor airfoil and stator blade combinations are secured between upper and lower annular sails.
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| Forward tilted turbine nozzle | 20060275111 | 20061207 |
| A turbine nozzle includes a row of vanes joined to radially outwardly inclined outer and inner bands. Each vane has camber and an acute twist angle for importing swirl in combustion gases discharged at trailing edges thereof. The trailing edges are tilted forwardly from the inner band to the outer band for increasing aerodynamic efficiency.
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| Vortex cooling for turbine blades | 20060275119 | 20061207 |
| A near wall cooling technique for cooling the pressure and suction sides of a turbine airfoil that includes a matrix of cells oriented chord-wise and extending longitudinally having vortex chambers with vortex creating passages feeding coolant from interior of the blade to each of the cells, interconnecting passageways interconnecting each of the vortex chambers and discharge film cooling passageway discharging coolant adjacent the outer surface of the pressure and suction sides. The alternate passageways are staggered and each are tangentially oriented to introduce a swirling motion in the coolant as it enters each of the vortex chambers. The cells may be oriented to be in a staggered or in an in-line array and the number of cells, the number of vortex chambers and the dimension of... |
| Vertical takeoff and landing aircraft using a redundant array of independent rotors | 20060266881 | 20061130 |
| A vertical takeoff and landing aircraft, using for vertical lift and lateral thrust a redundant plurality of essentially similar electrically-powered and electronically-controlled thrust units mounted in a mechanically static or fixed fashion relative to one another in a substantially horizontal plane. The thrust units are situated in this planar array in aerodynamically approximate pairs, such that a complete failure of a single thrust unit would not substantially compromise the ability of the aircraft to maintain flight.
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| Rotor hub fairing system for a counter-rotating, coaxial rotor system | 20060269411 | 20061130 |
| A rotor hub fairing system includes an upper hub fairing, a lower hub fairing and a shaft fairing therebetween. The rotor hub fairing system is sized and configured to reduce the overall drag on a dual, counter-rotating, coaxial rotor system. Preferably, the rotor hub fairing is fully integrated. The shaft fairing preferably includes a minimal thickness at the midsection to reduce drag with an increasing thickness adjacent the upper and lower hub fairings to reduce the flow separation on the hub fairing surfaces without overly excessive drag. Other aerodynamic structures, such as a horizontal splitter and/or a plurality of turning vanes may be mounted to the shaft fairing to facilitate flow around the upper and lower hub fairings to reduce flow separation and drag.
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| Bowling practice device | 20060270482 | 20061130 |
| A bowling practice device for regularizing and perfecting bowling technique. An aerodynamically designed hollow body includes an outer wall and a cylindrical inner wall. The opposed ends of the outer wall taper to meet the cylindrical inner wall. The outer wall preferably comprises a plurality of foam panels, one of which includes at least two finger holes suitable for personalization to the hand of the bowler.
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| Co-deployed optical referencing for responsive dust-based sensing system | 20060262299 | 20061123 |
| Apparatus and methods for calibrating an optical detector. In a preferred embodiment, the present invention provides a reference that includes a body and a surface of the body. At least a portion of the surface has a reflectance that can vary. The reference is adapted to be deployed with a cloud of optical sensors and has a terminal velocity that is about the same as the terminal velocity of the sensors. Further, the variation of the reflectance can be caused by a rotation of the reference (caused by an aerodynamic member) or by a controller that controls an electo optic material of the surface. In a preferred embodiment, the sensors are porous silicon optical sensors and the reference includes a retroreflector. The invention also provides a... |
| Method and aircraft system for active suppression of aircraft low frequency aerostructure lateral bending modes | 20060255206 | 20061116 |
| An aircraft with an aircraft elastic aerostructure body inflight aerodynamically initiated transient lateral modal bending response suppression system is provided. The aircraft elastic aerostructure body has an inflight aerodynamically initiated transient lateral modal bending response which is suppressed by the transient lateral modal bending response suppression system. The aircraft transient lateral modal bending response suppression system includes a sensor for sensing the inflight aerodynamically initiated transient lateral modal bending response and an electromagnetic moving mass shaker, the electromagnetic moving mass shaker having a moving mass and a mounting base, with the moving mass shaker mounted to the elastic aerostructure body with the mounting base. The system includes a controller wherein the first sensor outputs a sensed lateral modal bending response signal into the controller and the... |
| Method and apparatus for mixing fluids for particle agglomeration | 20060256649 | 20061116 |
| An aerodynamic agglomerator (10) promotes mixing and agglomeration of pollutant particles in a gas stream, to facilitate the subsequent removal of the particles from the gas stream. The agglomerator (10) is mounted in a duct (11) through which the gas stream flows. The agglomerator (10) comprises a plurality of parallel plates (12) which extend in the overall direction of flow of the gas stream, and are spaced transversely across the width of the duct (11) to divide the duct into multiple parallel passages. The duct (11) is configured and/or has formations therein for creating large scale turbulence in the gas stream upstream of the passages. A vane assembly (13) is provided in each passage for generating a zone of small scale turbulence of such size and/or... |
| Cascade rotor blade for low noise | 20060257261 | 20061116 |
| Low-noise airfoils and methods of reducing noise. One embodiment provides an aerodynamic member that includes two body portions coupled to each other. The second body portion includes a plurality of airfoil members in a fixed relationship with each other. Optionally, the airfoil members may define an open end of the second body portion. In the alternative, the member can include a third body portion that has an airfoil shape and that is coupled to the second body portion opposite the first body portion. Preferably, the first portion, the airfoil members, and third portion are 12%, 8%, and 2% thickness/chord airfoils respectively. Further, the aerodynamic member may be a rotor blade on a tandem helicopter. Another embodiment provides a cambered airfoil with two coupled body portions one... |
| Ocean-going vessels | 20060249066 | 20061109 |
| Ocean-going vessels having a load carrying module supported from a pair of spaced apart hulls by legs. The legs may be articulated in two places to provide control of the spacing of the two hulls and to control the elevation of the module off the water. Dynamic control of the articulation may control the response of the vessel, such as to sea conditions. The legs may include aerodynamic surfaces, fixed or controllable, that may be used to aide buoyancy and/or enhance stability, such as by assuring the bow of the hulls does not rise excessively. The hulls preferably are at least partially inflatable, with techniques for installing flexible fuel tanks within a preexisting inflatable hull being disclosed. Also disclosed are modular pressure control systems for controlling... |
| Ultrasonic aerosol generator | 20060249144 | 20061109 |
| An ultrasonic aerosol generator for delivering a liquid formulation in an aerosolized form at a high output rate of greater than 0.5 mL/minute, preferably greater than 1.0 mL/minute, and with diameters in a respirable size range, methods of using this device and kits including the device are described herein. The ultrasonic aerosol generator (10) contains at least (a) a liquid reservoir/aerosolization chamber (11), (b) a piezoelectric engine (12), (c) a relief aperture (13), and (d) an aerosol delivery element (20). Preferably the aerosolized particles that are delivered to the user through the aerosol delivery element have an average aerodynamic diameter of between 1 and 20 μm, more preferably between 1 and 10 μm, and most preferably between 1 and 5 μm. Optionally, the ultrasonic aerosol generator... |
| Reinforced cover for cut-outs in an aeordynamic contour | 20060249627 | 20061109 |
| Reinforced cover for cut-outs in an aerodynamic contour of a vehicle, with a first attachment section 1a attachable to a structural element (2,5) of the vehicle (11); a second elastic section 1c which covers the cut-out (4) which is located between a fixed part 5 and a moving part (6, 12) of the vehicle (11), and provided with a low-friction layer (8) on its inner surface (1e), which comprises a first area (1i) in a rectangular configuration and a second area (1j) with a second cross-section smaller than that of the first area (1i); an outer surface (1k) with a fiberglass layer (7a); a main internal body (9) of a flexible material, a transition section (1g) thickened between the first and the second section, (1a, 1c);... |
| Fourteen inch x-band antenna | 20060250306 | 20061109 |
| An X-Band microstrip antenna for use on a fourteen inch diameter projectile to transmit telemetry data. The X-Band microstrip antenna is configured to wrap around the projectile's body without interfering with the aerodynamic design of the projectile. The X-Band microstrip antenna operates at 7900 to 8100 MHz telemetry frequency band. Sixteen microstrip antenna elements equally spaced around the projectile provide for linear polarization and a quasi-omni directional radiation pattern.
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