138 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 invention provides a folding wing force measuring device, a calibration structure of the force measuring device and a calibration method, and relates to the technical field of wind tunnel tests. The folding wing force measuring device comprises a wing root connecting piece, a folding wing inner section, a folding wing force measuring balance, a folding wing outer section, a plurality of angle connecting blocks and a plurality of folding patch blocks, wherein the angle connecting blocks and the folding patch blocks are matched with the folding angle of a folding wing. According to the invention, the balance and the wing part are fused into a whole and are integrally designed and processed, the connecting surface of the balance and the wing is canceled, the measuring end of the balance, namely the folding wing part section, is shaped by the cover plate, and the shape is kept consistent with that of the wing part section. Therefore, the load of the force measuring balance tends to be reasonable, the balance coordinate system changes along with the folding wing, the precision of the force measuring balance with the folding wing is improved, the data conversion difficulty of a wind tunnel test is reduced, and the precision of the wind tunnel test is improved.

The invention discloses a novel tilting dual-rotor unmanned aerial vehicle, which belongs to the technical field of unmanned aerial vehicles, and comprises a wing body fusion fuselage and two outer wing sections, the two tilting rotor assemblies are used for providing power, controlling rolling, pitching and yawing in a vertical flight mode and controlling yawing in a horizontal flight mode, the two pitching and rolling rudder assemblies are used for controlling pitching and rolling in a horizontal flight state, and the two tilting rotor assemblies are symmetrically arranged in front of the wing body fusion fuselage; the pitching rolling rudder assembly is arranged in the middle of the outer wing section; the outer wing section is of a structure capable of being folded in the tail direction, so that the center of gravity is moved backwards to the position behind a stop point of the tail after the outer wing section is folded, and the unmanned aerial vehicle stably stops on a rod-shaped object with the diameter being 13 cm or less under the unpowered condition. On one hand, the problems that a tailstock type unmanned aerial vehicle is difficult to take off and land and a traditional unmanned aerial vehicle needs an undercarriage to take off and land are solved, and the problems that an existing unmanned aerial vehicle needs to be additionally provided with a parking actuator and needs to be parked with power are solved.

A bag for carrying a set of golf clubs while playing golf and while traveling. The bag includes first, second, third and fourth panels. Each panel has a middle section with first and second opposing faces, and with first and second opposite sides edges; a first wing section extending at a first angle from the first side edge of each panel; and a second wing section extending at a second angle from the second side edge of each panel. A first hinge connects the second wing section of the first panel to the first wing section of the second panel. A second hinge connects the second wing section of the second panel to the first wing section of the third panel. A third hinge connects the second wing section of the third panel to the first wing section of the fourth panel. At least one closure releasably connects the first wing section of the first panel to the second wing section of the fourth panel. The bag also includes first, second, and third club holding components, each connected to one of the first, second, third and fourth panels, each of the club holding components comprising at least three sleeves for receiving shafts of golf clubs. All of the hinges and the closure allow the bag to be folded into a playing mode with the connected wing sections touching each other and the first faces of the middle sections and the club holding components facing outward. All of the hinges and the closure also allow the bag to be folded into a travel mode with two of the first, second, third and fourth panels being adjacent with the middle sections facing and club holding components facing inward and with an other two of the first, second, third and fourth panels are adjacent with the middle sections and club hold components facing inward.

The invention provides a hovercar which comprises a hovercar body, folding wings, a folding duct and a telescopic empennage, the folding wing on each side comprises a plurality of wing sections hinged in sequence, and the adjacent wing sections are connected with folding assemblies used for enabling the wing sections to be folded in a Z shape; the folding duct comprises two duct bodies, two short cabin doors, a lengthened cabin door and a driving device. The driving device is used for driving the lengthened cabin door to move up and down so as to drive the two duct bodies to be unfolded out of the hovercar body or stored in the hovercar body. The telescopic empennage comprises a shell, an empennage assembly, a locking assembly and a telescopic assembly, wherein the empennage assembly is slidably inserted into the shell; in the process of stretching out and locking the empennage, after the telescopic assembly pushes the empennage assembly to move to the clamping position of the shell, the locking assembly continues to slide relative to the empennage assembly till interference fit is achieved so as to lock the empennage assembly. According to the implementation mode, different design requirements of the flying state and the land running state on the flying car can be met.

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 method for adjusting a header mounted on an agricultural harvester. The header includes a central section and at least one side wing section. The at least one side wing section extends between an inner portion and an outer portion, where the inner portion of the at least one side wing section is pivotally coupled to the central section. A ground engaging device is mounted on the at least one side wing section adjacent the outer portion. The ground engaging device has an adjustable height. The method comprises the steps of determining a flex position of the at least one side wing section relative to the central section, determining whether the flex position of the at least one side wing section exceeds a first threshold, and if it is determined that the flex position of the at least one side wing section exceeds the first threshold, decreasing the flex position.

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.

To provide a presentation-type cream container for applying a suitable amount of a coating material such as cream, which can prevent the cream from deteriorating by minimizing contact with the outside air during use, and which can look good on social media or the like by forming a discharge hole in any shape, and is likely to be featured in the media. [Solution] By fitting the inner tray 5, rotor 4, and container 6 together, and then fitting the winged cap 2 after filling with cream, contact with outside air can be minimized during use. Furthermore, the winged cap's wings 3 and wing-over-wing section 8 allow rotation to be unidirectional, limiting the amount used and preventing reverse rotation. This ensures rotation in the direction that ensures reliable dispensing. The amount dispensed can be adjusted by changing the screw pitch of the rotor to match the amount used. Conventionally, when using a spatula or fingers to dispense the appropriate amount of cream or other dispensed material, there was a risk of the cream deteriorating due to bacteria or moisture on the spatula or fingers. Furthermore, the product lacked a distinctive appearance, making it difficult to create a visual impact on social media.

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 a multi-degree-of-freedom deformable wingtip, belongs to the technical field of aircraft design and aeroelasticity design, and solves the problem that a deformable wingtip in single-degree-of-freedom design in the prior art cannot maintain high aerodynamic efficiency in a wider flight envelope, the multi-degree-of-freedom deformable wingtip comprises: a root wing section (100) connected to a wing main body; the middle wing section (200) is rotatably connected to the outer end of the root wing section (100); the winglet (300) is connected to the outer end of the middle wing section (200) in a twisting manner; and the power assembly comprises a bending servo motor (400) for driving the middle wing section (200) to rotate and a torsion servo motor (500) for driving the winglet (300) to twist.

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 present application belongs to the technical field of vertical axis wind turbines, and specifically relates to a deformable wing and a wind-current power generation device including the wing. The wing includes a main wing, the wing section of the main wing has an airfoil profile line, the airfoil profile line extends from the leading edge to the trailing edge and forms a suction side and a pressure side, and is characterized in that: the wing also includes a leading edge plate and a telescopic mechanism connected to the leading edge plate, the leading edge plate and the telescopic mechanism are installed at the leading edge position inside the main wing, and the leading edge plate can extend or retract the main wing along the chord length direction of the main wing under the action of the telescopic mechanism. The leading edge plate can generate counter-rotating vortex belts, suppress flow separation near the leading edge of the main wing, and significantly improve the vortex structure of the leading edge of the main wing, thereby greatly improving the power generation efficiency of the wing in the ocean current energy, so that the power generation device in extreme weather can continue to use ocean current energy to generate electricity efficiently, and at the same time can ensure that wind energy can continue to be obtained under conditions where self-starting is difficult, with the advantages of simple structure and high energy acquisition efficiency.

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.

The invention relates to the field of road sweeping, in particular to a wingspan type road snow remover. The snow remover is characterized in that a bearing at the front end of the snow remover and a hydraulic power telescopic device connect two groups of snow shoveling fins into a large included angle-shaped machine, a snow shoveling protective cap (shovel) is arranged at the front end of the outer side of the included angle of the fins, the two groups of fins incline inwards in a trapezoidal closing-up shape from bottom to top, and the upper parts of the fins are arc-shaped and reversely bent outwards. Each group of fins consists of a plurality of wing sections which can be folded towards the inner side by a hydraulic power telescopic device; and the lower end of the inner side of each fin is provided with a wheel which is used for supporting a wing body and can be lifted and a brush-shaped roller which is used for cleaning accumulated snow. The snow cleaning machine is combined with a power machine through a power conversion device (a brush-shaped roller is arranged on the lower side) in front of the snow cleaning machine, so that a driver can complete various operations on the wingspan type road snow cleaning machine through an operation system on the power machine.

A stripper header for combine includes a header frame carrying a stripper rotor with crop stripper elements and a transfer rotor or auger behind to transfer the collected heads to the feeder house. The header, stripper rotor and transfer auger are all divided into at least two typically three sections arranged end to end to pivot about a hinge line to accommodate changes in ground level. The hinge line passes through the axis of each of the stripper rotor and the transfer rotor. The stripper rotor has at the outer end of the center section a support plate spaced from the hinge line and a short portion with a coupling joint which connects to the inboard end of the wing section. The crop engaging elements of the sections of the stripper rotor are arranged so that they intermesh at the junction between the sections where this prevents interference and ensures no gaps.

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.

An aircraft (10) comprising: a starboard swept wing (14) and a port swept wing, each swept wing having an inner wing section (32) comprising an integrated payload fuselage (20) and an outer wing section (30) for extending the wingspan, in which each outer wing section has a thickness less than a thickness of the corresponding inner wing section; and in which a sweep angle of the inner wing section is greater than a sweep angle of the outer wing section a front spar 36 close to a leading edge (18) of each wing, in at least the outer wing section, and a rear spar (38) close to a trailing edge (22) of each wing, for carrying loads along each wing; a central region (12) where the starboard swept wing meets the port swept wing; a starboard transition region where the starboard inner wing section meets the starboard outer wing section; a port transition region where the port inner wing section meets the port outer wing section; and a load-bearing structural element (40) disposed across each wing from the front spar to the rear spar in the transition region for carrying loads between the front spar and the rear spar of each wing.

The invention belongs to the technical field of aviation aircrafts, and particularly discloses a multi-dimensional continuous variant wing structure which comprises a fixed plate, an inner wing section, an outer wing section, a sweepback actuating mechanism and a telescopic actuating mechanism, the inner wing section is driven by a sweepback actuating mechanism to rotate around the wing root in a spanwise plane so as to change the sweepback angle of the wing; the outer wing section is slidably connected to the inner wing section and is driven by a telescopic actuating mechanism to stretch in the spanwise direction so as to change the extension length of the wing; the front end and the tail end of the rear side of the inner wing section are connected with the flexible rear edge and the rigid rear edge correspondingly, and the flexible rear edge is used for changing the bending degree of the rear edge. The rigid trailing edge is used for changing the trailing edge deflection angle; the sweepback actuating mechanism comprises a rotating disc, a push rod motor and a rocker arm, and the push rod motor drives the rocker arm to enable the inner wing section to rotate around the rotating disc to achieve sweepback changing. According to the invention, the multi-dimensional variation of the wings can be realized through simple mechanism combination, and the aerodynamic performance of the aircraft is improved, so that the aircraft can adapt to different flight conditions, and various flight task requirements are realized.