84 results about "Wingtip device" patented technology

An aircraft comprises a wing tip device, for example a winglet, a raked-tip device, a wing tip fence or a planar wing extension, mounted in the region of the tip of a wing on the aircraft. The wing tip device is rotatably moveable between a first position and a second position, in which the upward lift produced by the wing or the wing tip device is reduced. During flight, the bending moment at the root of the aircraft wing therefore changes in dependence on the position of the wing tip device. The maximum bending moment in the aircraft wing sustained during high-load conditions is thereby reduced, allowing the structural mass of the aircraft to be reduced.

A flying-wing double-ducted vertical take-off and landing aircraft. It mainly consists of five parts. The first part is the fuselage 1, the second part is the No. 1 ducted engine 4, the No. 2 ducted engine 5 and the rear engine 6, the third part is the vertical tail 16, the No. 1 horizontal tail 12, the No. 2 horizontal tail 13, No. 3 horizontal stabilizer 14, No. 4 horizontal stabilizer 15, No. 1 winglet 10, No. 2 winglet 11. The fourth part is the support rod 19 , and the fifth part is the externally mounted pan/tilt head and the camera or photoelectric sensor 20 . The fuselage 1 is a flying wing type, the fuselage 1 can be folded, and the fold line 17 and the fold line 2 18 are the folding points of the fuselage. There are No. 1 duct 2 and No. 2 duct 3 distributed on the fuselage 1. No. 1 ducted engine 4 and No. 2 ducted engine 5 are located in the center of No. 1 duct 2 and No. 2 duct 3, respectively, and are connected by connecting The rod 22 is fixed. The No. 1 ducted engine 4 and the No. 2 ducted engine 5 are respectively equipped with a No. 1 propeller 7 and a No. 2 propeller 8 . The rear engine 6 is located in the center of the tail of the fuselage 1 , and a rear propeller 9 is installed on the rear engine 6 . The No. 1 horizontal stabilizer 12 , the No. 2 horizontal stabilizer 13 , the No. 3 horizontal stabilizer 14 , and the No. 4 horizontal stabilizer 15 of the aircraft are respectively located at the rear of the fuselage 1 . The No. 1 winglet 10 and the No. 2 winglet 11 of the aircraft are located on the left and right sides of the fuselage 1 respectively, and are bent downward. The vertical tail 16 of the aircraft is located in the middle of the tail of the fuselage 1 , on the upper part of the fuselage 1 . The support rod 19 is located in the middle of the front part of the fuselage 1 , and is located in the lower part of the fuselage 1 . The camera or photoelectric sensor is located in the middle of the front of the body 1 and is installed under the body 1 . The sweep angle 21 is the sweep angle of the flying wing fuselage 1 .

The invention relates to a solar unmanned aircraft. In order to overcome the problems of difficult flight control and bad stability of the flying wing solar unmanned aircrafts, the invention adopts the configuration of tip winglets(5) arranged at the outer segments of a large aspect-ratio high wing, a V shaped empennage and a wing(4); the wing(4) is connected with and a fuselage(7) through a bridge wing(3) and a controlling rudder(9) is arranged on the V shaped empennage(8) to realize the pitching and yawing control of the aircraft. Combining the characteristic of the high energy conversion efficiency of a flexible thin film solar battery, the invention lays the flexible thin film solar battery(6) on the wing(4). An engine and propeller propulsion system (1) adopts a haul-in-type, and an equipment cabin (2) is arranged at the front part of the fuselage(7). The solar unmanned aircraft improves the lift-drag ratio of the aerial vehicle, prolongs the operation time and effectively improves the horizontal and the vertical stabilities and maneuverability of the aircraft, thus relieving the problems of bad stability and bad maneuverability of the flying wing configuration.

A rakelet comprises a raked portion and a winglet portion that selectively integrate features of raked wingtips and winglets into a wingtip device that improves aircraft endurance and range over standard wings and over other wingtip devices such as raked wings, winglets, and the like. The features of the rakelet can be configured to improve and maximize the range and endurance for any particular aircraft.

The various embodiments of the present invention provide an unmanned aerial vehicle comprising a hemispherical body, a brushless type electrical, a propeller, a plurality of wingtip devices, a plurality of servomotors and each of the plurality of the servomotors is connected to each of the plurality of the wingtip devices respectively, a plurality of carbon rods, and a casing. The brushless type electrical motor provides a lifting force for a Vertical take-off and landing (VTOL) and the plurality of wing tip devices are classified into three types of wing tip devices and the three types of wing tip devices are controlled by the respective servomotors to control yaw, pitch and roll movements thereby stabilizing and controlling the movement of an aircraft.

The invention relates to a pneumatic layout of dual flying wings of a UAV (Unmanned Aerial Vehicle). The pneumatic layout is characterized by comprising a pneumatic layout of a blended wing body flying wing, a layout of installing a turbofan engine above the rear section of the blended wing body flying wing and a pneumatic layout of installing a stabilator at two sides of a nacelle on the outer wall of the turbofan engine, wherein the blended wing body flying wing with a high lift-to-drag ratio is formed by a fuselage, wings, wingtip winglets and direction ailerons together; the stabilator which is used for providing a positive lifting force during flight trimming of the UAV is formed by horizontal tails and horizontal tail winglets, and the dual flying wings are formed by the blended wing body flying wing and the stabilator together. According to the pneumatic layout of the dual flying wings of the UAV, disclosed by the invention, the UAV has high lift-to-drag ratio, good operability and high stability, and the pneumatic layout has the advantage of good stealth performance.

A passenger aircraft including a wing (1) and a wing tip device (3). The wing tip device (3) is moveable between a flight configuration for use during flight and a ground configuration for use during ground-based operations. In the ground configuration the wing tip device is folded downwardly from the flight configuration such that the span of the aircraft is reduced. The wing tip device (3) is connected to the wing along a hinge (9) defining a hinge line (11). The hinge (9) may be arranged to prevent the wing tip device (3) rotating upwardly beyond the flight configuration. The hinge line (11) may be orientated at an angle to the flight direction such that the wing tip device (3) presents a larger frontal area when it is in the ground configuration than when it is in the flight configuration, such that aerodynamic forces urge it to rotate about the hinge line (11) away from the ground configuration and towards the flight configuration.

The invention discloses a novel rotor aerodynamic structure for an unmanned aerial vehicle. The novel rotor aerodynamic structure comprises a rotor shaft and blades connected with the rotor shaft. The front edge of each blade is in a sine wave structure, the tail edge of each blade is in an isosceles right triangle shaped sawtooth structure, and the tail end of each blade is provided with a winglet which is perpendicularly mounted at the tail end of the corresponding blade. By the winglets mounted at tips of the blades respectively, streaming around of air on upper and lower surfaces can be inhibited, induced drag caused by wingtip vortexes is reduced, lift force damages caused by streaming around are reduced, lift-drag ratio is increased, and accordingly lift force is increased; in addition, due to adoption of the sine wave structured front edges and the sawtoothed rear edges according to a bionic design, low air resistance and low noise are realized. The novel rotor aerodynamic structure for the unmanned aerial vehicle has advantages of high lift force of the blades, high cruising power and low air resistance and noise in operation.

The invention discloses a vertical take-off and landing unmanned aerial vehicle with vectored thrust duct engines. The unmanned aerial vehicle includes a vehicle body, wings and a vertical tail are separately fixedly installed at the middle and the tail of the vehicle body, the tail ends of the wings are provided with wingtips, vectored thrust duct engines are installed below the wings, and the vertical tail and the wingtips are provided with take-off and landing buffering mechanism. The vertical take-off and landing unmanned aerial vehicle with the vectored thrust duct engines uses the take-off and landing buffering mechanism to vertically take off and land, the flight speed of fixed wing unmanned aerial vehicle is possessed on the one hand, the vertical take-off and landing unmanned aerial vehicle with the vectored thrust duct engines can vertically take off and land and hang in the air like a rotor unmanned aerial vehicle, and the dependency of the unmanned aerial vehicle for sitesand runways is greatly reduced.

An aircraft (2) including a wing (1), the wing (1) having a fixed wing (3) and a wing tip device (4) at the tip of the fixed wing (3), the wing tip device (4) being rotatable relative to the fixed wing (3) between flight and ground configurations, the aircraft including a rotational joint (10) with a rotation mechanism (11) that rotatably couples the wing tip device (4) to the fixed wing (3) and a locking mechanism including a locking bore (53, 54) and a locking pin (51) that is receivable in the locking bore to lock the wing tip device (4) in one of the flight or ground configurations, wherein the rotational joint includes an alignment mechanism including an alignment pin (61) and an alignment bore (62, 63) and at least one of the alignment pin and alignment bore is tapered such that engagement of the alignment pin (61) in the alignment bore acts to guide the locking bore and locking pin into alignment.

An aircraft (5) including a wing (7) having a wing tip device (1) configurable between: a flight configuration and a ground configuration in which the span of the wing (7) is reduced. The aircraft (5) further includes a lock (13) for locking the wing tip device (1) in the flight configuration, and an actuator (3) for unlocking the lock (13) and for subsequently actuating the wing tip device (1) to the ground configuration. The actuator (3) is a two-stage hydraulic actuator, including a first hydraulic actuator stage (21) arranged to unlock the lock and a second hydraulic actuator stage (23) arranged to actuate the wing tip device (1) to the ground configuration. The first and second hydraulic actuator stages (21, 23) are arranged in series such that the second actuator stage (23) is unable to receive a hydraulic input feed until the first actuator stage (21) unlocks the lock (13).

An aircraft (102) including a wing (101), having a fixed wing (105) with a wing tip device (103) moveably mounted at the outer end thereof. The wing tip device (103) is moveable between: a flight configuration; and a ground configuration. The wing tip device (103) and the fixed wing (105) are separated along an oblique primary cut plane (113). The wing tip device (103) and the fixed wing (105) meet along an interfacing cut line (135). The interfacing cut line (135) comprises a first length (137) offset from the primary cut plane (113) in a first direction; a second length (141) offset from the primary cut plane (113) in a second direction, opposite to the first direction; and a transition section (139) over which the interfacing cut line (135) transitions from the first length to the second length.

The invention provides overall design of a tilt-rotor aircraft. According to the technical scheme, a wing arrangement structure and power distribution of the aircraft are provided. The aircraft comprises a fuselage, front wings, T-shaped emages, winglets and a rear wing. The ends of the front wings are provided with the winglets. The rear wing is connected with the main wings through a connecting plate and connected with the fuselage. The T-shaped emages are arranged on the rear portion of the whole aircraft. Three engines are further mounted and independently move. The included angles between the axial directions of the engines and the horizontal plane during vertical take-off and landing of the aircraft are 80-100 degrees. The rotating speeds and the angles of the engines are adjusted through a flight control system. The engines assist to control the posture of the aircraft. When the aircraft tilts, the engines forward rotate till the included angles between the axial directions of the engines and the horizontal plane are zero degree.

The invention discloses an airplane wingtip device, which comprises a transition part and a wingtip part, wherein the end part of the inner side of the transition part is connected with the far end of an airplane wing; the end part of the outer side of the transition part is connected with the wingtip part; the wingtip part comprises a plurality of wingtip sections; each wingtip section comprises a wingtip and a wing root respectively; the wing root of the first wingtip section is connected with the end part of the outer side of the transition part, and is aligned with the back edge of the end part of the outer side of the transition part; the wing root of the (n+1)th wingtip section is positioned on the wingtip of the nth wingtip section; the chord length of the wing root of the (n+1)th wingtip section is smaller than or equal to that of the wingtip of the nth wingtip section; and n is more than 0. The wingtip device disclosed by the invention is arranged in a step form, and each wingtip is provided with more than one discontinuity surface, so that wingtip vortexes induced from the wingtips suppress one another, the vortex intensity is weakened, and the resistance reducing effect is achieved; moreover, the bending moment increment of the wing roots is smaller, so that the structural weight of the airplane is lightened, and the influence on flutter characteristic is smaller.

The invention discloses a helicopter with a separated tip jet device and a main rotor wing. The tip jet device is arranged at the front end of a power wing, an output shaft of the power wing is connected with the main rotor wing through a decelerator system so that the rotating speed of the main rotor wing is lower than that of the power wing; and the output shaft of the power wing, a deceleratorand an output shaft of the decelerator are hinged with a helicopter body. The helicopter solves the problem that the tip jet device of the known tip jet type helicopter has high efficiency at supersonic speed while the propulsive efficiency of the main rotor wing declines when the wing tip linear speed is at the supersonic speed; and the working efficiency of the tip jet device and the propulsiveefficiency of the main rotor wing achieve best states.

A rotatable locking member for locking an aircraft wing with a movable wing tip device. The rotatable locking member including a U-shaped receiving portion arranged such that in an unlocked position the locking pin may be moved into and out of the U-shaped receiving portion, and in a locked position the locking pin is not able to be moved out of the U-shaped receiving portion, and the rotatable locking member is configured to be moved between the unlocked and locked position by rotational movement around the longitudinal central axis of the locking pin.

The invention discloses an unmanned aerial vehicle, comprising wings and tip small wings or pendant tails at two ends of the wings; the tip small swings or pendant tails can be quickly released and fitted manually without tools and can be automatically positioned and locked to the ends of the wings. By designing the releasable tip small wings or pendant tails, it is convenient to release the tip small wings or pendant tails while they are fastened, and tool-free quick manual release and fitting and automatic positioning and locking are achieved; the released tip small wings or pendant tails may be stacked and horizontally placed in a transport box, the height of the transport box for receiving the tip small wings or pendant tails extending in the height direction is reduced, and the size is reduced; the horizontally placed tip small wings and pedant tails are mutually released from the wings, there is no need to concern stress damage due to mutual staggering during transporting, transport weight is reduced, and portability of the unmanned aerial vehicle is improved.

The invention discloses a four-duct flying-wing type unmanned aerial vehicle which comprises ducts, fans, winglets and a flying-wing type wing, wherein symmetric winglets are mounted on the tip of the flying-wing type wing; four duct fan power systems are mounted on the winglets respectively; and the fans are arranged in the ducts. The invention has the following effects: (1) the four-duct flying-wing type unmanned aerial vehicle has the advantages of fast cruise, vertical take-off and landing, hovering, low noise, autonomous flight and easiness in control; and (2) control of multiple attitudes can be realized, the control method is simpler with high flexibility and is more helpful to implementing specific tasks in complicated special conditions.

The new wing or blade design for wingtip device, rotor, propeller, turbine, and compressor blades with energy regeneration can be used to generate lift, propel vehicles more efficiently, compress fluids more efficiently, harness energy more efficiently. This system can be used as a wing, as a wingtip device, as a propeller for aircraft or boats or any vehicle moving through a fluid, in a compressor, as a rotor for wind turbine or helicopter, in a gas turbine. The new wing or blade design for wingtip device, rotor, propeller, turbine, and compressor blades with energy regeneration is a series of low aspect ratio wings placed in parallel with gaps between them connected by smaller wings that are placed in the gaps to harness the energy and produce forces; the gaps are shaped to decelerate the fluid and/or accelerate the fluid by varying the cross-sectional area of the gaps. Even if the small aspect ratio makes those wings inefficient, the strength of the vortices is smaller in the gaps.

The invention provides an airplane wingtip device which comprises a transition part and a wingtip part. The inner end part of the transition part is connected with the far end of an airplane wing, and the outer end part of the transition part is connected with the wingtip part; the wingtip part comprises a plurality of wingtip sections; and each wingtip section comprises a wingtip and a wing root respectively, the wing root of the first wingtip section is connected with the outer end part of the transition part, and arranged between the first edge and rear edge of the outer end part of the transition part, the wing root of the (n+1)th wingtip section is placed on the wingtip of the nth wingtip section, and the wing root chord length of the (n+1)th wingtip section is smaller than the wingtip chord length of the nth wingtip section, wherein n is larger than 0. The wingtip device provided by the invention is arranged in a step shape, so that more than one discontinuity surface is added on each wingtip of the wingtip device, wingtip vortexes induced by the wingtips are mutually inhibited, the vortex intensity is weakened, and the effect of reducing resistance is achieved. In addition, the wing root bending moment increment is smaller, the structural weight of an airplane is reduced, and the influence on the flutter characteristic is smaller as well.

The invention discloses a wingtip rotor wing applied to an unmanned aerial vehicle, belonging to the technical field of unmanned aerial vehicles. The wingtip rotor wing comprises a first rotor wing, and a first rotating blade of the first rotor wing is fixedly connected with a first rotor wing shaft of a steering engine; a first weight balancing block is fixedly connected with the first rotor wingshaft, and the first rotating blade and the first weight balancing block are symmetrically arranged relative to the first rotor wing shaft; a second rotating blade of a second rotor wing is fixedly connected with a second rotor wing shaft of the steering engine; the second weight balancing block is fixedly connected with the second rotor wing shaft, and the second rotating blade and the second weight balancing block are symmetrically arranged relative to the second rotor wing shaft. Meanwhile, a first wingtip small wing is intersected with a first rear arranged wing; a first wingtip fasteningend is fixedly connected with a first rear opening end; a second wingtip small wing is intersected with a second rear arranged wing; and a second wingtip fastening end of the second wingtip small wing is fixedly connected with a second rear opening end. The wingtip rotor wing has the technical effects that a rotor wing structure is simplified, daily maintenance is convenient, and the stability ofthe unmanned aerial vehicle is improved.