389results about "Influencers by generating vortices" patented technology

An aircraft is disclosed having a device and an aircraft wing. The aircraft wing includes a main wing element and a movable wing tip device attached to a tip end of the main wing element. The movable wing tip device includes an accumulator configured to store energy and the movable wing tip device can move relative to the main wing element to vary a span of the aircraft wing. The accumulator is configured to transmit power to the device. The accumulator enables energy to trickle between the main wing element and the movable wing tip device whilst still providing a suitable power source to the device. Additional embodiments include a method of maintenance, and a method of operating the aircraft wing to store energy in the movable wing tip device.

The invention provides a displacement vortex generator and a position regulation and control method, and belongs to the field of active flow control equipment. The VG comprises a belt, a belt guide rail, a belt bearing, a sliding block, a supporting column, a triangular VG body, a guide rail supporting block, a limiting groove, a body connecting plate and a motor. The belt is arranged on the belt guide rail and is driven by the motor; the sliding block is arranged on the belt, is in an inverted concave shape and is connected with the body connecting plate through the supporting column, and the VG bodies are fixed to the two ends of the body connecting plate. The belt guide rail is arranged on the guide rail supporting block, and the sliding block can penetrate through the limiting groove. The motor is controlled to drive the belt to drive the sliding block and the VG body to move, and accurate adjustment of the position of the vortex generator body is achieved. The position of the vortex generator is automatically adjusted according to changes of the incoming flow wind speed and the attack angle, the optimal pneumatic effect is kept under different working conditions, the pneumatic performance and the power generation efficiency of the wind turbine blade are remarkably improved, and the negative influence of the front edge roughness can be effectively weakened.

An active winglet includes a body portion substantially parallel to a wing of an aircraft, as if it were an extension of the wing. The body portion is attachable to an aircraft wing and includes a controllable airflow modification device coupled thereto. By virtue of having a controllable airflow modification device, the winglet is capable of adjusting a control surface of the controllable airflow modification device in response to in-flight conditions, to reduce wing loads, increase range, and / or increase efficiency.

The invention provides a heterogeneous micro-costal membrane and a preparation method thereof.The heterogeneous micro-costal membrane comprises a front face and a back face, the front face is provided with a vortex generator array and a rib array in a protruding mode, the vortex generator array and the rib array are arranged in a continuous mode, the vortex generator array comprises a plurality of vortex generators which are arranged in a tiled mode, and the rib array is arranged on the back face. The rib array comprises a plurality of ribs which are arranged in a tiled mode, the rib array sequentially comprises a first protection layer, a second protection layer, a supporting layer, a back glue layer and a bottom film layer from the front face to the back face, the first protection layer is made of a super-hydrophobic modified material, the second protection layer is formed by bombarding a chromium target through argon ions and depositing chromium atoms, and the supporting layer is made of a super-hydrophobic modified material. The supporting layer is made of an epoxy resin material, and the back glue layer is prepared by performing corona treatment on the surface of the supporting layer and coating glue; the bottom film layer can be removed. The heterogeneous micro-costal membrane provided by the invention has relatively high overall strength, wear resistance, corrosion resistance and a remarkable drag reduction effect.

An active wing extension includes a body portion substantially parallel to a wing of an aircraft, as if it were an extension of the wing. The body portion is attachable to an aircraft wing and includes multiple controllable airflow modification devices coupled thereto. By virtue of having multiple controllable airflow modification devices, the wing extension is capable of adjusting control surfaces of the multiple controllable airflow modification devices in response to in-flight conditions, to reduce wing loads, improve wing fatigue characteristics, increase range, reduce torsional loads, alleviate flutter, and / or increase efficiency.

A method for reducing aerodynamic loads on an aircraft located on the ground includes moving a wing tip relative to a fixed wing to an on-ground configuration in which the span of the wing is reduced. The wing tip includes an airflow channel, which is in an open configuration in which airflow through the channel between upper and lower surfaces of the wing tip is enabled, when the wing tip is in the on-ground configuration. This has been found to reduce aerodynamic loads on the wing tip and / or parts of the aircraft connected thereto during this phase of the aircraft's use.

An aircraft including an aircraft wing wherein the aircraft wing includes a fixed wing, a wing tip device at an end of the fixed wing, and a wing tip device actuator configured to move the wing tip device between a flight configuration and a ground configuration. The wing tip device actuator includes a shaft which is rotatable about a shaft axis to selectively displace respective first and second elbows of the wing tip device actuator towards or away from the shaft. The first elbow is connected to the wing tip device and the second elbow is connected to the fixed wing such that movement of the respective elbows away from the shaft causes the wing tip device to move away from the flight configuration and such that movement of the respective elbows towards the shaft causes the wing tip device to move towards the flight configuration.

The present invention provides an extreme STOL airplane comprising: a fuselage and a wing having port and starboard wing sections. Each wing section has a body with top and bottom surfaces, leading and trailing edges, and a span, i.e., the distance between a wing section tip and root connected to the fuselage, and flap coves. Aerodynamic elements integrated into the wing sections include Fowler flaps, having leading and trailing edges and a span, flap tracks, wherein the flap tracks are external to the wing section body, extend aftward beyond the trailing edge of the wing section, and are configured to enable the Fowler flaps to rotate or deflect and to translate or extend and retract, Frise ailerons, wherein the Frise ailerons are located outboard of the Fowler flaps, and spoilerons located over the leading edge of the Fowler flaps when the flaps are in the fully extended position.

The present invention provides an extreme STOL airplane comprising: a fuselage and a wing having port and starboard wing sections. Each wing section has a body with top and bottom surfaces, leading and trailing edges, and a span, i.e., the distance between a wing section tip and root connected to the fuselage, and flap coves. Aerodynamic elements integrated into the wing sections include Fowler flaps, having leading and trailing edges and a span, flap tracks, wherein the flap tracks are external to the wing section body, extend aftward beyond the trailing edge of the wing section, and are configured to enable the Fowler flaps to rotate or deflect and to translate or extend and retract, Frise ailerons, wherein the Frise ailerons are located outboard of the Fowler flaps, and spoilerons located over the leading edge of the Fowler flaps when the flaps are in the fully extended position.

An aircraft wing is disclosed having a fixed wing with a tip, and a wing tip device rotatably mounted on a hinge at the tip of the fixed wing, such that the wing tip device is rotatable about the hinge, and an actuation system for rotating the wing tip device about the hinge. The actuation system includes a motor, at least one geared rotary actuator, a reduction gearbox, a clutch for selectively decoupling rotation of the motor from rotation of the geared rotary actuator, the geared rotary actuator is driveable by the motor and arranged to convert rotary motion into a different rotary motion and is arranged to rotate the wing tip device relative to the tip of the fixed wing. The clutch is coupled to the geared rotary actuator by a shaft and the shaft is fixed in rotation to a mass disposed radially outwardly from the shaft.

A wing assembly for an aircraft including a fixed wing and a wing tip device rotatable about a joint assembly. The wing assembly is configurable between a flight configuration for use during flight and a ground configuration for use during ground-based operations. The wing assembly includes joint-bordering structure located adjacent the joint assembly, the joint-bordering structure having a rib, an upper cover and a lower cover. The joint assembly includes a moveable panel. The panel includes a first hard stop element, and the joint-bordering structure includes a second hard stop element. The first hard stop element is integrally formed in the panel, and the second hard stop element is integrally formed in one of the rib, the upper cover or the lower cover of the joint-bordering structure. The hard stop elements may be configured to self-align.

A method for reducing aerodynamic loads on an aircraft located on the ground includes moving a wing tip relative to a fixed wing to an on-ground configuration in which the span of the wing is reduced. The wing tip includes an airflow channel, which is in an open configuration in which airflow through the channel between upper and lower surfaces of the wing tip is enabled, when the wing tip is in the on-ground configuration. This has been found to reduce aerodynamic loads on the wing tip and / or parts of the aircraft connected thereto during this phase of the aircraft's use.

An aircraft wing assembly (31) is disclosed. The aircraft wing assembly (31) comprises a wing tip device (11) rotatable about a hinge axis (H) between a flight configuration and a ground configuration and a wing tip device actuation system (20) comprising a bell crank (21) and a linear actuator (23). The bell crank (21) is rotatably mounted to the aircraft wing assembly (31) and is rotatable about a bell crank axis (C) which is offset from the hinge axis (H). The linear actuator (23) is operable to rotate the bell crank (21) about the bell crank axis (C) to thereby move the wing tip device (11) about the hinge axis (H), between the flight configuration and the ground configuration.

High-performance winglets are provided for attachment to an airplane wing. A split blended winglet includes a blended or upper winglet smoothly extending from the wing tip above a chord plane of the wing and a lower winglet including a ventral fin projecting below the chord plane from a lower surface of the upper winglet. The upper winglet includes a blade section that projects vertically along a reverse curve before transitioning to a linear upper blade portion. Upper and lower surfaces of the upper winglet are bound by leading and trailing edges that are swept toward an airstream direction, parallel with the chord plane, and curve toward the airstream direction before terminating at a point distal of the wing tip. Upper and lower surfaces of the lower winglet are bound by leading and trailing edges that curve toward the airstream direction and terminate at a point distal of the wing tip.

A wing (3) for an aircraft (1) including a fixed wing (5), a foldable wing tip portion (9) mounted to the fixed wing (5) via a hinge (11) in a manner rotatable about a hinge axis (13) between an extended position and a folded position, an actuation device (24) for actuating the foldable wing tip portion (9) for movement between the extended position and the folded position, and an arresting device (37) for arresting the foldable wing tip portion (9) in the extended position and / or in the folded position. The arresting device (37) includes a clutch device (39) configured for selectively holding the foldable wing tip portion (9) in a fixed position relative to the fixed wing (7) and releasing the foldable wing tip portion (9) for movement relative to the fixed wing (7) about the hinge axis (13).

Various control surfaces are disclosed that can cause a side force along a lateral axis running through a center of mass of a craft when the control surfaces are deployed in a same direction. The side force can be created without creating a yawing moment on the craft. The control surfaces can be on a winglet of the craft. Also disclosed are a split-flap control surface and stand-alone ailerons.

A wing tip device for fixing to the outboard end of a wing, the wing defining a wing plane, the wing tip device comprising: an upper wing-like element projecting upwardly with respect to the wing plane and having a trailing edge; and a lower wing-like element fixed with respect to the upper wing-like element and having a root chord and a trailing edge, the lower wing-like element root chord intersecting with the upper wing-like element, and the lower wing-like element projecting downwardly from the intersection, wherein the upper wing-like element is larger than the lower wing-like element and the trailing edge of the lower wing-like element is adjacent the trailing edge of the upper wing-like element at the intersection, and wherein an included angle between the upper and lower wing-like elements at the intersection is less than, or equal to, 160 degrees.

The invention provides an automobile airplane with a vertical take-off and landing function and an efficiency improving method. The automobile airplane comprises a wing-shaped automobile body, two main thrust propellers and two wing end trapped vortex generators. The two main thrust propellers and the two wing end trapped vortex generators are symmetrically arranged on the two sides of the wing-shaped vehicle body. The rotating direction of a propeller vortex generated by rotation of the main thrust propeller is the same as that of the vortex of the wing end trapped vortex generator and is opposite to that of a wingtip vortex, so that an active reverse wingtip vortex generator is formed; during takeoff, even if no conventional long-wingspan wing exists, vertical takeoff or ultra-short-distance takeoff can be achieved on a single lane of a highway with the limited spanwise direction or an aircraft carrier deck only through the ultra-short chord ratio showing wing; the front part of the vehicle body is provided with a leading edge slat lease-reducing and lift-increasing device, so that the lift-drag ratio can be further improved, and during level flight, in order to improve the flight efficiency, wings with large span chord can be stretched according to actual conditions to form a fixed-wing flight mechanism type, so that the vehicle and the airplane can fly fast and far and carry more people, and the problem of traffic jam is effectively solved.

The embodiment of the present invention discloses a vortex generator for reducing fuselage drag and delaying airflow separation, which relates to the technical field of rotorcraft manufacturing, and can realize the passive flow control of the flow field near the fuselage of the rotorcraft when encountering strong crosswind or sideways flight, thereby achieving the purpose of reducing drag of the rotorcraft, while reducing the implementation cost and failure rate. The present invention includes: the value of the installation angle (2) of the vortex generator is greater than or equal to 10° and less than or equal to 45°; the second corner (20) of the single-piece vortex generator is the angle between the upper surface (7) of the second section and the connection section (19) between the vortex generator and the object surface, the value of the first corner (9) of the single-piece vortex generator is less than 30°, and the value of the second corner (20) is greater than or equal to 40° and less than or equal to 60°. The present invention is suitable for the passive flow control of the flow field near the fuselage of the rotorcraft when encountering strong crosswind or sideways flight.

The invention belongs to the technical field of aircraft aerodynamic design, and relates to an aircraft nose noise reduction vortex generator device. The device comprises 13 vortex generators, the seventh vortex generator is positioned right behind the central circular light window of the spherical machine head pod; the 13 vortex generators are arranged towards the two sides along the rear edge of the central circular light window of the spherical machine head pod by taking the seventh vortex generator as the center; the two vortex generators which are symmetrically arranged are consistent in appearance, and the first vortex generator, the second vortex generator, the third vortex generator, the fourth vortex generator, the fifth vortex generator, the sixth vortex generator and the seventh vortex generator are sequentially arranged from the two sides to the middle. Wherein the seventh vortex generator is shortest in length, and the vortex generators arranged on the two sides of the seventh vortex generator are increased in sequence; a gap is formed between the front end of each vortex generator and the central circular light window; and each vortex generator is arranged along the heading direction.

A hinge arrangement for an aircraft wing is provided, for providing a folding wingtip. The hinge arrangement comprises a first mount for securing in a first wing section and a second mount for securing to a second relatively foldable wing section, each having a plurality of hinge elements arranged along a hinge axis. The arrangement comprises a latching arrangement for securing the mounts against folding movement, the latch arrangement having a latch axis being spaced from the hinge axis in a substantially spanwise direction for example so as to extend into the wing box. This can provide an efficient arrangement which may be contained within the outer mould line of the wing which can reduce the need for a fairing.

The present invention provides an extreme STOL airplane comprising: a fuselage and a wing having port and starboard wing sections. Each wing section has a body with top and bottom surfaces, leading and trailing edges, and a span, i.e., the distance between a wing section tip and root connected to the fuselage, and flap coves. Aerodynamic elements integrated into the wing sections include Fowler flaps, having leading and trailing edges and a span, flap tracks, wherein the flap tracks are external to the wing section body, extend aftward beyond the trailing edge of the wing section, and are configured to enable the Fowler flaps to rotate or deflect and to translate or extend and retract, Frise ailerons, wherein the Frise ailerons are located outboard of the Fowler flaps, and spoilerons located over the leading edge of the Fowler flaps when the flaps are in the fully extended position.

The application discloses a vortex generator with adjustable interval and angle, and relates to the technical field of vortex generators.The vortex generator with adjustable interval and angle comprises a plurality of vortex generator units, an interval adjusting assembly and an angle adjusting assembly;each vortex generator unit comprises a flow guide plate, a support rod, an interval adjusting sliding block and a rotary rocker arm;one end of each support rod is connected and fixed with the corresponding flow guide plate, and the other end penetrates through a through hole and is rotationally connected with the corresponding interval adjusting sliding block;one end of the rotary rocker arm is connected and fixed with the corresponding support rod;the interval adjusting assembly can drive the plurality of interval adjusting sliding blocks to slide so as to adjust the interval between two adjacent flow guide plates;and the angle adjusting assembly can drive the plurality of rotary rocker arms to rotate around the axial direction of the support rod so as to adjust the angle of the flow guide plate.The application can automatically adjust the interval and angle of the vortex generator, so that the vortex generator can be adapted to more complex air flow environments and the energy efficiency ratio can be optimized.

A winglet system is configured to be secured to a wing of an aircraft. The winglet system includes an upper blade, a lower blade, and a cover plate integrally formed with the upper blade and the lower blade. The cover plate covers an opening within a transition joint between the upper blade and the lower blade. The cover plate remains coupled to the upper blade if the lower blade is separated from the winglet system.

Vortex generators include a vane that rotates between a stowed position and a deployed position. In the deployed position, the vane is configured to reduce noise created by an airflow around or along the aerodynamic surface. A spring controls deployment of the vane and includes an elongate tube formed of a superelastic shape memory alloy. To deploy or stow the vane, the elongate tube is twisted due to a stress-induced response caused by airflow around or along the aerodynamic surface, thereby building up and storing torque in the elongate tube. A mounting base receives the vane when it is in the stowed position, and operatively couples the vortex generator to the aerodynamic surface. To create the torque in the elongate tube, a first end of the elongate tube is fixed with respect to the aerodynamic surface while a second end of the elongate tube is free to rotate.

An aircraft wing (5, fig 1) and tuning the wing comprises a fixed wing (7) and a wing tip device (9) rotatably mounted on a hinge 11 at a tip of the fixed wing. An actuation system 20 rotates the wing

The invention discloses a vortex generator with adjustable spacing and angle, and relates to the technical field of vortex generators. The vortex generator with the adjustable distance and angle comprises a plurality of vortex generator units, a distance adjusting assembly and an angle adjusting assembly. Each vortex generator unit comprises a flow guide plate, a supporting rod, a distance adjusting sliding block and a rotating rocker arm. One end of each supporting rod is fixedly connected with the corresponding flow guide plate, and the other end of each supporting rod penetrates through the corresponding via hole and is rotationally connected with the corresponding interval adjusting sliding block. One end of each rotary rocker arm is fixedly connected with the corresponding supporting rod; the distance adjusting assembly can drive the multiple distance adjusting sliding blocks to slide so as to adjust the distance between every two adjacent flow guide plates. The angle adjusting assembly can drive the multiple rotating rocker arms to rotate in the axial direction of the supporting rod so as to adjust the angle of the flow guide plate. The space and the angle of the vortex generator can be automatically adjusted, so that the vortex generator is adaptive to more complex airflow environments, and the energy efficiency ratio is optimized.

A vortex inducer is applied to the pressure face of a propulsion rotor blade. The vortex inducer defines an aft face located forward of the trailing edge of the blade. In operation, the vortex inducer generates a primary vortex behind its apex, which induces a counterrotating secondary vortex through viscous coupling at the trailing edge. The secondary vortex accelerates and deflects the suction face wake, enhancing overall blade performance. The system is applicable to propellers, helicopter rotors, prop-rotors, fan blades, and marine propellers.

The present invention provides a heterogeneous micro-rib membrane and a preparation method thereof, comprising a front and a back surface, wherein the front surface is provided with a vortex generator array and a rib array, wherein the vortex generator array is arranged in series with the rib array, wherein the vortex generator array includes a plurality of flatly arranged vortex generators, and the rib array includes a plurality of flatly arranged ribs. From the front surface to the back surface, the membrane comprises a first protective layer, a second protective layer, a support layer, a backing layer, and a bottom film layer, wherein the first protective layer is made of a super-hydrophobic modified material, the second protective layer is formed by argon ion bombardment of a chromium target and deposition of chromium atoms, the support layer is made of an epoxy resin material, and the backing layer is prepared by corona treating the surface of the support layer and applying glue; the bottom film layer is removable. The heterogeneous micro-rib membrane provided by the present invention has high overall strength, wear resistance, corrosion resistance, and significant drag reduction effect.