83 results about "Wing section" patented technology

An aircraft wing tip that is movable by an actuator between a flight configuration, and a ground configuration which has a shorter wingspan for use in ground-based operations. Lugs that connect to arms of the actuator are integrally formed as part of the primary structure of either the fixed wing or outboard wing section, such as a folding tip section.

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 chord-wise folding and quick unfolding wing structure and relates to the technical field of aircraft design technology.The chord-wise folding and quick unfolding wing structure comprises chord-wise folding and unfolding wing sections, the chord-wise folding and unfolding wing sections are divided into a plurality of wing sections along the chord direction, the division surfaces of two adjacent wing sections are both planes, grooves are formed in the separation planes of the two adjacent wing ribs, buffer gaskets and strong magnets are arranged in the grooves, and the two adjacent wing sections are connected through a film hinge; and flow guides are arranged above the connecting gaps of the two adjacent wing ribs.The chord-wise folding and quick unfolding wing structure can be divided into a plurality of wing sections which can rotate around the lower surface division lines along the chord direction, so that the wing fully utilizes the circumferential storage size and can break through the limitation of the cylinder diameter on the chord length and area of the wing; the two adjacent wing sections are connected through the film hinge, so that the air resistance during flight is reduced; the automatic positioning and locking between the two adjacent wing sections are realized by using the suction force of the permanent magnet, and the structure is simple and has high reliability.

The invention relates to the technical field of aircraft wing folding, in particular to an aircraft wing large-angle folding mechanism and method.The aircraft wing large-angle folding mechanism comprises a fixed wing section connected with an aircraft body, a movable wing section connected with the fixed wing section in a folding mode and a folding drive connected with the fixed wing section and the movable wing section; the bottom of the folding end of the fixed wing section is rotationally connected with the bottom of the folding end of the movable wing section; the folding drive is used for driving the movable wing section to turn over and fold downwards to be close to the lower surface of the fixed wing section; the bottom of the folding end of the fixed wing section is rotationally connected with the bottom of the folding end of the movable wing section, and the movable wing section is driven by folding drive to turn downwards around the rotating connection position to be close to the lower surface of the fixed wing section, so that the movable wing section is folded downwards, the space below the fixed wing section is fully utilized, the space utilization rate is increased, and the fuselage width is reduced; the space occupied by the aircraft is reduced; the overall structure is simple, cost is low, and operation is easy and convenient.

A row crop header for harvesting crop in a field comprises a header frame having a center section and a pair of side wing sections operatively coupled to the center section. An upper link is pivotally coupled between the center section and each one of the side wing sections adjacent the top portion thereof. A lower link is pivotally coupled between the center section and each one of the side wing sections adjacent the bottom portion thereof. The upper links and lower links provide independent pivotal movement of the side wing sections relative to the center section to contour to the surface of the field of crops to be harvested. An automatic float system is operatively coupled between the center section and each one of the side wing sections to adjust the weight of the side wing sections on the surface of the field and allow the side wing sections to float relative to the center section.

The invention relates to a propeller blade for an aircraft propeller, comprising a wing section (10) and a propeller blade root (20) connected thereto, as well as a method for repairing such a propeller blade. The wing section (10) can have a foam and / or honeycomb core (11, 12, 13) with a sheath (14) made of a fiber-reinforced polymer material. The propeller blade root (20) can be made of a metallic material and comprise a shaft (21) extending into and connected to the wing section (10), at least one outer bearing ring (23), and an adjustment pin (22). It is preferred that the bearing ring (23) has a running surface consisting of a layer (26) of a steel material welded or remelted onto the bearing ring (23), which has a yield strength Rp0.2 of over 750 N / mm² and a tensile strength Rm of over 1,000 N / mm².The bearing ring (23) with the running surface can have a core Vickers hardness HV10 of over 430.

The invention relates to the technical field of computer simulation, and discloses a rapid modeling simulation method and system for a deformed wing structure, and the method comprises the steps: recognizing wing section key points of wing section data, fitting an upper surface curve and a lower surface curve of the deformed wing structure, and determining a parameterized wing section of the deformed wing structure; analyzing key change parameters, corresponding to the wingspan direction, of the deformed wing structure so as to construct a parameter change curve in the wingspan direction, and fitting a wing geometric model of the deformed wing structure; determining a deformation mode of the deformed wing structure, calculating an airfoil variable quantity and a torsion angle variable quantity of the deformed wing structure in a deformation process, and fitting an initial deformed wing model of the deformed wing structure; carrying out simulation calculation on an aerodynamic coefficient of the initial deformation wing model, and determining aerodynamic performance of the initial deformation wing model; and optimizing the initial deformation wing model to obtain a target deformation wing model. According to the method, the modeling simulation accuracy and design efficiency of the deformed wing structure can be improved.

The axial flow fan comprises a hub and a plurality of blades fixedly arranged on the surface of the hub, the blades are variable-cross-section blades, the ends, close to the hub, of the blades are blade roots, the ends, away from the hub, of the blades are blade tops, and the blades are fixed to the hub. The blade is sequentially divided into a plurality of parallel cross sections from the blade root to the blade top, the cross sections are in different shapes, the cross section close to the blade root is formed by arranging large-camber airfoils and medium-camber airfoils at intervals, the cross section close to the blade top is formed by arranging small-camber airfoils, and the mounting angles of the cross sections are gradually reduced from the blade root to the blade top. The blade section close to the hub adopts the wing section with larger camber so as to improve the thrust of the fan, and the blade section far away from the hub adopts the wing section with smaller camber so as to weaken the air flow leakage near the top of the blade and further reduce the noise. The air flow dynamic performance of the axial flow fan during rotation is improved, and the aims of providing enough thrust and reducing noise of the leaf blower are achieved.

Underwater wing device for diving to compensate for the natural buoyancy of the diver and their equipment. The invention relates to a device that generates force in the water using the speed produced by the user. It consists of a wing section extruded over a span adapted to generate sufficient force to compensate for the user's buoyancy, thus avoiding the use of weights, which are cumbersome, potentially dangerous, and polluting. The device according to the invention is particularly intended for freediving or diving with a breathing apparatus, underwater tourism, water sports, and as a swimming aid. Figure 1.

An aircraft 310 has a pair of swept wings 314A meeting at a central region 312. Each wing has an inner wing section 326A containing an integrated payload fuselage (fig.1,20); a thinner thickness oute

The application relates to the technical field of aircraft design, and discloses a continuous variable-camber rigid wing driven by multiple rudders and a control method thereof, wherein the continuous variable-camber rigid wing comprises a wing leading edge section, multiple rigid wing sections, a distributed rudder driving mechanism and a transmission mechanism; the multiple rigid wing sections comprise a first wing section, a second wing section and a third wing section which are sequentially hinged through rotating shafts; the distributed rudder driving mechanism is arranged in the wing leading edge section and is used for independently driving the deflection of each rigid wing section; and the transmission mechanism is connected between the distributed rudder driving mechanism and the corresponding rigid wing section and is used for converting the output motion of the distributed rudder driving mechanism into the deflection motion of the corresponding rigid wing section. According to the application, the rigid wing is segmented, multiple rudders are used for independent driving, an advanced aerodynamic analysis model and a closed-loop feedback control are combined, the wing camber is self-adaptively, continuously and accurately regulated within a full flight envelope, and thus the optimal aerodynamic performance can be maintained at all times.

The invention discloses a wing quadrilateral unit structure finite element model automatic construction method and device, equipment and a medium, and relates to the technical field of aerospace, and the method comprises the steps: determining third coordinate data of a wing middle section based on a target control parameter, first coordinate data of a wing root section and second coordinate data of a wing tip section; based on the first coordinate data, the second coordinate data and the third coordinate data, constructing an airfoil geometric parameterized model by utilizing a preset interpolation method, generating target grid control points and target grid control edges corresponding to the wing root section, the wing tip section and the wing middle section respectively, and determining a first grid control edge connecting the wing root section and the wing middle section, the second grid control edge is connected with the wing middle section and the wing tip section; and determining a wing quadrilateral unit structure finite element model file based on the first quadrilateral mesh of the skin, the second quadrilateral mesh of the wing rib and the third quadrilateral mesh of the wing spar. And a high-fidelity structural finite element model is efficiently constructed.

The invention belongs to the field of aeroelastic mechanics of airplanes, and particularly relates to a rapidly-formed low-speed wing flutter model. According to the aerofoil flutter model, an aerofoil beam frame comprises a plurality of aerofoil beam sections which are arranged in a crisscross manner; a plurality of pneumatic dimensional frames are arranged on the wing beam frame, the pneumatic dimensional frames are shaped like a Chinese character'tian ', the upper surfaces and the lower surfaces of the pneumatic dimensional frames are matched with wing sections of wings, mounting grooves and avoiding grooves are formed in the pneumatic dimensional frames, the pneumatic dimensional frames are bonded with the wing beam sections through the mounting grooves in a single-point mode, and the pneumatic dimensional frames are connected with the wing beam sections through the avoiding grooves in a single-point mode. Through the avoiding grooves, the pneumatic dimensional frame is not in contact with and does not interfere with the wing beam frame except for the bonding points; a plurality of counterweights are fixedly mounted on the wing beam frame; the skin is laid and attached to the upper surface and the lower surface of the pneumatic dimensional frame through gum. The low-speed wing flutter model has the advantages of being short in machining period, high in product appearance precision and high in reliability, and the defects of a traditional low-speed wing flutter model are overcome.

The invention relates to an emergency power generation system for an aircraft, an aircraft fuselage section, an aircraft wing section and an aircraft. The invention belongs to the field of aircrafts. The aircraft fuselage section comprises the emergency power generation system, the aircraft wing section comprises the emergency power generation system, and the aircraft comprises the aircraft fuselage section and / or the aircraft wing section.

The invention relates to an airbag (100) for restraining a vehicle occupant in a motor vehicle, comprising a side panel (10) and a main panel (20), the edges (11, 21) of which are stitched to one another in such a way that an airbag volume is formed, the lateral webs (10) have two wing sections (13), each forming a lateral wall of the airbag (100), and a middle section (14) connecting the wing sections (13), and the main webs (20) have an upper section (25) and a lower section (24), which are stitched to the wing sections (13) and are connected to each other by means of a front section (23), according to the invention, the wing section (13) and the lower and upper sections (24, 25) each have an extension section (26, 27, 28, 29) which are stitched to one another in such a way that a deployment neck region (30) for deploying the airbag in a gap (132) between the windshield (140) and the instrument panel (110) is formed.

The utility model relates to the technical field of aircrafts, in particular to a foldable wing which comprises a first wing section, second wing sections, connecting structures, a switching assembly and a driving device, and the two ends of the first wing section are rotationally connected with the two second wing sections through the connecting structures respectively. The driving device is connected with the second wing section through the switching assembly and drives the second wing section to be folded or unfolded relative to the first wing section. Under the driving of the driving device, the switching assembly drives the two sections of the wings to be folded or unfolded through the connecting structure, so that the modes of the wings are flexibly changed, and the diversity and flexibility of the wings are improved.

This invention provides a vertical takeoff and landing (VTOL) compound wing unmanned aerial vehicle (UAV), comprising a fuselage, with wings on both sides of the middle section of the fuselage. Each wing includes a middle wing section and an outer wing section. One end of the middle wing section is connected to the fuselage, and the outer wing section is connected to the other end of the middle wing section. A foldable cantilever is mounted on the side of the middle wing section, and a central propeller is mounted at the end of the foldable cantilever. A tail fin and a tail propeller are located at the tail of the fuselage, and a vertical tail is located at the bottom of the fuselage. This invention offers the following advantages: the cantilever of the VTOL compound wing UAV features a multi-level self-locking connection, ensuring reliable locking and excellent anti-loosening performance. The self-locking connection mechanism integrates multiple locking structures such as hinges, self-locking nuts, self-locking rods, and locking arc plates. After deployment, it achieves mechanical self-locking, effectively resisting flight vibrations, strong wind loads, and maneuvering impacts, preventing loosening, and ensuring high safety.

The present application belongs to the technical field of aircraft icing wind tunnel test, and relates to an icing wind tunnel test device and method of an airbag deicing system with pressure measurement function. The device comprises a pressure measurement leading edge assembly (1), a deicing leading edge assembly (2) and a wing box assembly (3). The pressure measurement leading edge assembly (1) and the deicing leading edge assembly (2) are interchangeable leading edge modules, and the wing box assembly (3) comprises a wing box and a trailing edge part. The pressure measurement leading edge assembly (1) and the deicing leading edge assembly (2) have the same shape, and the pressure measurement leading edge assembly (1) or the deicing leading edge assembly (2) and the wing box assembly (3) jointly form a complete wing section and are connected into one body by fasteners for pressure measurement test or deicing test. By comparison and matching with a target pressure distribution, an accurate test attack angle is determined, so that the test state is closer to the real flight state, and the reliability of the deicing test result is improved.

A row crop header for harvesting crop in a field comprises a header frame having a center section and a pair of side wing sections operatively coupled to the center section. An upper link is pivotally coupled between the center section and each one of the side wing sections adjacent the top portion thereof. A lower link is pivotally coupled between the center section and each one of the side wing sections adjacent the bottom portion thereof. The upper links and lower links provide independent pivotal movement of the side wing sections relative to the center section to contour to the surface of the field of crops to be harvested. An automatic float system is operatively coupled between the center section and each one of the side wing sections to adjust the weight of the side wing sections on the surface of the field and allow the side wing sections to float relative to the center section.

The application belongs to the field of aircraft structure strength test, and is a flat wing section center of rigidity position determination method and device. The weight of a loading device is recorded first, and then the loading device is controlled to load the test wing after checking and judging that each system or device is normal. The test wing is first loaded to an initial value, and then is loaded to different loading points according to settings. The variable amount of the test wing is fed back through a load sensor, and the average value of the load sensor is obtained through calculation. Then, the center of rigidity position of the test wing corresponding to the section can be determined according to the load ratio. The center of rigidity positions of different sections of the test wing can be obtained by loading different loading points of the test wing respectively. After the test is completed, unloading and pressure relief are performed. The electric drive actuator has the performance characteristics of high positioning accuracy, fast response speed, accurate control and high synchronism, and is better than the hydraulic actuator.

Rubble mound structures requires an armor layer to reduce wave force. This concrete armor unit consists of a nose section (A), a body section (C), and a tail section (D). On the right and left sides, there are wing parts (B1 and B2) that protrude in the YZ plane. The wing section (B) is integrated with the body section (C) with additional concrete thickening at the junction to reduce stress. Two interlocking systems include the wing section (B) lock as the basis for placing the nose section (A) of the other armor unit and the tail section (D) designed so the wing section (B) can rest on it.

The invention relates to the technical field of aviation aircraft design, and discloses a continuous variable camber rigid wing driven by multiple steering engines and a control method thereof, and the continuous variable camber rigid wing comprises a wing leading edge section, a plurality of rigid wing sections, a distributed steering engine driving mechanism and a transmission mechanism; the plurality of rigid wing sections comprise a first wing section, a second wing section and a third wing section which are sequentially hinged through a rotating shaft; the distributed steering engine driving mechanism is arranged in the front edge section of the wing and is used for independently driving each rigid wing section to deflect; the transmission mechanisms are connected with the distributed steering engine driving mechanisms and the corresponding rigid wing sections and used for converting output motion of the distributed steering engine driving mechanisms into deflection motion of the corresponding rigid wing sections. According to the invention, the rigid wing is segmented and is independently driven by a plurality of steering engines, and an advanced pneumatic analysis model and closed-loop feedback control are combined, so that the camber of the wing is adaptively, continuously and accurately adjusted in a full flight envelope, and the optimal pneumatic performance is always maintained.

This invention discloses a wide-speed-range aircraft with a large payload bay, belonging to the field of supersonic aircraft design technology. It addresses the problem that when a large payload bay is installed on a carrier aircraft and enters supersonic cruise, the strong shock wave generated at the nose causes a significant increase in overall drag, resulting in the ineffective utilization of the resulting localized high-pressure flow. The invention includes a fuselage, structural connectors, a large payload bay, a left wing, a right wing, a horizontal stabilizer, and a vertical stabilizer. The fuselage comprises a nose, a mid-fuselage section, and a tail section connected sequentially. The large payload bay is connected to the upper side of the mid-fuselage section via structural connectors. The left wing includes a left inner wing section and a left outer wing section, and the right wing includes a right inner wing section and a right outer wing section. During high-speed cruise, the payload bay of this invention can compress the incoming airflow and reflect the shock wave from the aircraft's nose, thereby generating a localized high-pressure zone below the large payload bay. This significantly improves transport efficiency and single-load capacity, resulting in excellent supersonic aerodynamic performance.

The present application relates to a pivot wing (1) for use as an outwardly opening wing about a vertical axis of rotation (2) of a vertically oriented room boundary element (3), comprising a rectangular wing frame (4) formed by four wing profiles (6, 7, 8, 9) extending in a common wing plane (5), a planar infill (10) oriented parallel to the wing plane (5) and a wing seal (11) attached to the wing frame (4), wherein the wing seal (11) is provided and arranged to come into contact with the sealing system on a fixed frame (12) of the room boundary element (3) when the pivot wing (1) is in a closed position in a direction perpendicular to the wing plane (5), wherein an upper section (41) of the at least one wing seal (11) is attached to an upper horizontal wing profile (6) of the wing frame (4). To provide a casement window that also prevents water from entering the building under the described load conditions, an elongated, channel-shaped drainage profile (14) is proposed, which is arranged in a force-transmitting manner on the upper horizontal sash profile (6) and extends parallel to its profile axis (25) at least substantially over the entire length of the upper horizontal sash profile (6), wherein the drainage profile (14) is arranged on the upper horizontal sash profile (6) such that it is located below the upper section (41) of the sash seal (11), so that water can fall from the upper section (41) of the sash seal (11) onto the drainage profile (14), wherein the drainage profile (14) is closed at its longitudinally opposite ends with end caps (15).wherein a fluid-flow connection exists between the drainage profile (14) and at least one hollow chamber (16) of the upper horizontal wing profile (6).

Clutch (10) for selectively preventing the rotational movement of a gear (12) about an axis, wherein the clutch (10) comprises: an actuator (20); a pivotably movable pawl (40), wherein the pawl (40) interacts with the gear (12); a plunger (24) which is radially movable within and through the actuator (20), wherein the plunger (24) is oriented perpendicular to the axis in order to control the pawl movement; a pair of axially spaced side walls (16, 18), each side wall (16; 18) comprising an opposing radially extending slot (52); a pawl push element (50) that is radially movable between the plunger (24) and the pawl (40), wherein the pawl push element (50) includes a pair of axially extending wing sections (54, 56), each wing section (54; 56) being slidably mounted in one of the opposing slots (52) to limit the movement of the pawl push element (50) to a purely radial movement; wherein axial and / or circumferential force loads, which are transmitted by the pawl (40) to the pawl push element (50), are not transmitted to the radially movable plunger (24).

The invention belongs to the field of bionic deformation wing design, and relates to a three-section collaborative deformation high bionic wing. The bionic deformation wing is mainly composed of a driving assembly, an upper arm section, a front arm section and a hand wing section. The whole mechanism only has one degree of freedom and is driven by a servo motor, a deformation mechanism composed of three parallelogram fence type structures and a wingtip fan-shaped structure is pulled through a gear and a rack, and cooperative deformation of the three bionic wing sections is achieved. Cooperative movement of three joints of the shoulder, the elbow and the wrist of the bird wing is simulated, the wing is stretched and folded like the bird wing, the wing area change is large, transverse control over the unmanned aerial vehicle can be carried out instead of an aileron, and the overall bionic degree is high.

An aircraft (10) comprising: a starboard swept wing (14A) and a port swept wing (14B), each swept wing having an inner wing section (26A) comprising an integrated payload fuselage (20) and an outer wing section (30A) for extending the wingspan and providing lift; the inner wing section comprising: a rear spar (40) disposed close to a trailing edge (22A) of each inner wing section to carry loads along each inner wing section; a wing surface (30), in which the wing surface is substantially shaped as an aerofoil, and in which the wing surface comprises a rear fairing (62) disposed behind the rear spar, and near to the trailing edge, and in which the wing surface comprises an upper curved portion (50) which has a substantially arcuate cross section, a front curved portion (52) which has a substantially arcuate cross section, and a lower wing surface, the upper curved portion meeting the rear spar at a rear of the upper curved portion, and the upper curved portion meeting the front curved portion at a front of the upper curved portion, and the front curved portion meeting the lower wing surface at a front of the lowerwing surface, a cabin structure (32) in each inner wing, in which the cabin structure comprises one or more floor beams (36) and a rear wall defined by the rear spar; in which the lowerwing surface comprises a front lower curved portion (117), in which the front lower curved portion is substantially arcuate in profile and extends from a front edge of the floor beam(s) of the cabin structure towards the rear wall; in which the lower wing surface of each inner wing extends below a first line A, the first line being a line on the rear wall of the cabin structure where a projection of the arcuate front lower curved portion of the wing surface meets the rear wall, and in which a rear lower portion of the lower wing surface meeting the front lower portion and continuing the lowerwing surface to a second line, which is spaced from and below the first line.

The invention provides an airship capable of modularly installing a rescue patrolling device launching cabin. Comprising an airship capsule body (1), a main airship cabin and power cabin (3), a vector propulsion device (4), an undercarriage (5) and a rescue patrolling device launching airship cabin (6), the airship capsule body (1) is filled with helium serving as light gas to provide buoyancy; the main airship cabin and power cabin (3) is connected to the lower end of the airship capsule body (1) in a suspended mode, the vector propulsion devices (4) are symmetrically installed on the side faces of the power cabin in the main airship cabin and power cabin (3), motor cabins of the vector propulsion devices (4) are connected with a main airship cabin of the main airship cabin and power cabin (3) through linkage wing sections, and propellers of the vector propulsion devices (4) are arranged behind the motor cabins. And the rescue patrolling device launching boat cabin (6) is arranged at a reserved position of the main boat cabin and the power cabin (3). The task execution efficiency of an emergency rescue unit is improved.

The present application relates to a kind of for aircraft sacrificial layer and laying method, the sacrificial layer is laid on the body to be laid of the aircraft, the body to be laid is the wing spar, skin and wing rib in the wing, tail wing and central wing section of aircraft;The sacrificial layer includes unidirectional tape and / or fabric, the unidirectional tape and / or fabric is multilayer, and each layer unidirectional tape and / or fabric laying coordinate system is consistent with the laying coordinate system of body to be laid, and the unidirectional tape and / or fabric is laid according to the designed laying angle in laying coordinate system when laying.The sacrificial layer of the present application is laid at a specific angle, so that the composite material structure body is little and controllable;In addition, the material of sacrificial layer is selected according to the material of body to be laid, to ensure that all surfaces or profiles are not deformed during laying processing, and the actual position is consistent with the theoretical position, and the deviation is within the allowable range.

The invention provides an efficient low-noise bionic propeller blade of an unmanned aerial vehicle based on an owl wing airfoil, which comprises a rotor hub, rotor blades and bionic airfoils, the two ends of the rotor hub are connected with the rotor blades, the main bodies of the rotor blades are formed by the bionic airfoils, and the basic curves of the bionic airfoils are cathead wing sections. The airfoil profile at 70% of the section in the wingspan direction of the owl wing is taken as the basic bionic airfoil profile of the propeller, the thickness of the front edge and the rear edge of the airfoil profile changes gently, and the airfoil profile still has the characteristics of high lift-drag ratio and low torque under the condition that the overall airfoil profile thickness is smaller than that of a conventional airfoil profile. In addition, the bionic airfoil has the characteristics of low speed and large lift force, a vortex system structure generated at the trailing edge is small, and the pressure pulsation amplitude is small, so that the thrust and efficiency of the unmanned aerial vehicle rotor wing can be improved, and meanwhile, the unmanned aerial vehicle rotor wing can guarantee a high lift-drag ratio, and noise generated by the rotor wing is reduced. The invention can be widely applied to the technical field of low-altitude aircraft power systems.