267 results about "Upper wing" patented technology

The invention discloses a folding wing structure of an unmanned aerial vehicle, which comprises a rotating shaft embedded in a vehicle body, wherein a lower wing elastic sheet and an upper wing elastic sheet are mounted in an inner cavity of the rotating shaft from bottom to top, a first locking block and a second locking block are respectively arranged at the free ends of the lower wing elastic sheet and the upper wing elastic sheet, the first locking block and the second locking block are respectively matched with a first notch and a second notch which are formed in the rotating shaft, the outer side of the rotating shaft is sequentially sleeved with a lower wing and an upper wing from bottom to top, the upper surface of the lower wing and the lower surface of the upper wing are each provided with a groove, the two grooves are oppositely formed to form a torsional spring groove, a torsional spring is arranged in the torsional spring groove, and the upper inner sides of the lower wingand the upper wing are provided with a first locking groove and a second locking groove correspondingly; and the outer side of the rotating shaft is further sleeved with a roller bearing, a baffle isinstalled at the top of the rotating shaft, and the roller bearing is located between the upper wing and the baffle. The processing cost of the unmanned aerial vehicle is reduced, the folding wing structure is insensitive to the structural size, and the folding wing structure can adapt to a more miniaturized barrel-shooting unmanned aerial vehicle.

Aerodynamic lifting structures, such as aircraft wings, having embedded engines and associated methods and systems are disclosed herein. A wing assemblies configured in accordance with embodiments of the present technology can include, for example, an upper wing portion, a lower wing portion, and a plurality of independent ducts positioned between the upper wing portion and the lower wing portion. Each duct can extend between a corresponding inlet positioned toward a leading portion of the wing assembly and a corresponding outlet positioned toward a trailing portion of the wing assembly. The wing assembly can further include a plurality of fans and a plurality of electric motors operably coupled to the plurality of fans. The fans and electric motors are positioned in the corresponding individual ducts and the fan is rotatable to propel fluid received in the inlet through the duct to create lift.

The invention discloses a variable-elongation sweepback wing scaling wing deformation device and a deformation method thereof, and relates to the technical field of deformation mechanism design of variant aircrafts, the aerodynamic configuration of a variable-elongation sweepback wing scaling wing is composed of a fuselage section, a sweepback fixed section and a telescopic section, the fuselage section is composed of a fuselage shell and an upper hatch cover, and the upper hatch cover is composed of an upper hatch cover and a lower hatch cover. The sweepback fixed section is composed of an upper wing surface shell and a lower wing surface shell, the telescopic section is an independent telescopic wing shell, the fuselage section and the shell of the sweepback wing fixed section are fixed through a sunk screw, and therefore it is guaranteed that the aerodynamic shape meets the aerodynamic design requirement; the linear guide rail is fixedly connected to the lower wing surface shell, and the telescopic wing can move along the linear guide rail; electric push rods are used for driving and are fixed in the fuselage, and inner rods of the electric push rods are connected with the telescopic wings, so that the telescopic wings are controlled to move along the linear guide rails; according to the method, the aerodynamic configuration of the scaled wing is segmented, so that the aerodynamic configuration and internal movement components of the scaled wing are mounted, and the extension length of the wing is changed by driving the telescopic wing to move along the linear guide rail through the electric push rod, so that the lift-drag ratio of the aircraft in the flying process is changed; the method can provide an implementation method for the equivalent scaling experiment of the deformable wing.

The utility model discloses a positioning device for an H-shaped steel assembly machine, which belongs to the technical field of H-shaped steel assembly machines and comprises a base, an inverted U-shaped frame is fixedly connected to the top of the base, and a lower wing plate is arranged in the middle of the top end of the base. According to the utility model, the lower wing plate is limited through the lower wing plate limiting wheel, the web plate is limited through the web plate limiting wheel, and the upper wing plate is limited through the first upper wing plate limiting wheel and the second upper wing plate limiting wheel, so that the lower wing plate, the web plate and the upper wing plate are positioned and the connection positions are welded during movement to form H-shaped steel; when a limiting structure needs to be adjusted according to the sizes of a lower wing plate, a web plate and an upper wing plate, a first motor drives a lead screw to rotate, the lead screw drives supports on the two sides to move in the opposite directions at the same time, positioning mechanisms on the two sides move in the opposite directions at the same time, H-shaped steel can be positioned in the center position, and it is avoided that when the H-shaped steel is positioned, the positioning precision is high. And the position of the H-shaped steel is deviated.

A vertical take-off and landing aircraft with a multi-element lifting system with integrated propulsion. The multi-element lifting system may have an upper wing element, a lower wing element, and a control wing element which is located below the upper wing element and above, and rearward of, the lower wing element. The system uses internal propulsion units, such as internal ducted fans, which flow air below the upper wing element and above the lower wing element such that the air flows through the multi-element lifting system. The control wing element may be articulated to route air vertically downward to allow for short or vertical take-off and landing. An aircraft with a multi-element wing assembly and a multi-element tail assembly raised above the wing assembly. An aircraft which resides on the ground with the wing assembly and the tail assembly pitched up.

A propulsion assembly for an aircraft, the propulsion assembly having a jet engine having a fan casing and a central casing around a longitudinal axis and having a vertical median plane passing through the longitudinal axis, an attachment pylon having a rigid structure that takes the form of a box that has a front wall and an upper spar extending forwardly in respect to the front wall, a front engine attachment fixed between an upper area of the central casing and a lower end of the front wall, and a complementary front engine attachment fixed between an upper area of the fan casing and a front end of the upper spar.

The utility model discloses an integrated power assembly suspension system of an off-highway dumper, which is horizontally arranged and comprises an engine suspension structure, a pair of first connecting pieces, a pair of second connecting pieces, a pair of third connecting pieces, a pair of fourth connecting pieces and a pair of fourth connecting pieces, and the first connecting pieces are symmetrically arranged on two sides of a central surface of an engine flywheel casing in the width direction of a power assembly; the left side and the right side of the front end of the engine are connected with the left frame and the right frame respectively; the gearbox suspension structure comprises a pair of second connecting pieces which are symmetrically arranged on the two sides of the center face of the engine flywheel shell in the width direction of the power assembly, and the left side and the right side of the rear end of the engine and the left side and the right side of the rear end of the gearbox are connected and then connected with the left frame and the right frame. The four-point type suspension system has excellent vibration damping performance, simultaneously avoids stress damage of a flywheel casing caused by insufficient support of a traditional four-point type suspension system on the premise of a large-torque power assembly, thoroughly solves the problem of difficulty in assembly and maintenance, and realizes that a power assembly system can still keep away from an upper wing surface of a frame in a limited frame space. And integrated hoisting and dismounting are completed.

The invention discloses a two-stage friction energy dissipation type self-resetting beam column joint structure, and relates to the technical field of structural damping. The cantilever beam is vertically arranged on the middle-section side wall of the stand column; the splicing beam and the cantilever beam are arranged at an interval, and the free end of the cantilever beam is arranged opposite to the free end of the splicing beam; an upper wing plate of the cantilever beam is connected with an upper wing plate of the splicing beam; a lower wing plate of the cantilever beam is connected with a lower wing plate of the splicing beam; a two-stage friction energy consumption device is arranged between the free end of the cantilever beam and the free end of the splicing beam; two disc spring reset devices are arranged on the two faces of a web of the cantilever beam side by side respectively. Different lengths of the arc-shaped long holes in the friction plate are used for controlling graded friction energy consumption of nodes under different seismic intensities; the friction plate can return to the initial position through the disc spring reset device, the problem of residual displacement of the friction plate is solved, residual deformation of a structure after an earthquake is effectively reduced, and post-earthquake loss of a building structure is reduced.

The invention relates to the technical field of aviation equipment, and discloses a wing-shaped structure suitable for anti-icing and deicing, which comprises a shell and an electric heating piece, an electric heating piece is arranged in a shell, a first heating layer is formed on the upper wing face and the lower wing face of the inner wall of the shell, a second heating layer is formed on the front edge of the inner wall of the shell, the first heating layer and the second heating layer are electrically connected, and the first heating layer and the second heating layer are connected with an external power source through an electrode layer so that power can be supplied to the electric heating piece, and temperature distribution of different parts can be controlled. After the electrode layer conducts electricity, a first temperature area is formed on the first heating layer, a second temperature area is formed on the second heating layer, and the temperature of the first temperature area is lower than that of the second temperature area, so that it is guaranteed that the front edge of the airfoil structure is kept at the high temperature, and the deicing and anti-icing requirements are met. According to the airfoil structure suitable for anti-icing and deicing, differentiated heating can be conducted according to icing characteristics of different parts of the airfoil structure, it is guaranteed that the anti-icing and deicing requirements are met, meanwhile, energy consumption is reduced, and the energy utilization rate is increased.

An aircraft flap comprises an upper wing surface and a lower wing surface which are opposite to each other, and a cavity is defined by the upper wing surface and the lower wing surface; the noise reduction device is arranged in the cavity and comprises a first noise reduction structure, the first noise reduction structure comprises a perforated plate and an upper part and a lower part, the upper part is embedded in the upper wing surface, and the lower part is embedded in the lower wing surface; a second noise reduction structure including foam metal, disposed between the upper portion and the lower portion of the first noise reduction structure, and attached to the first noise reduction structure; and the third noise reduction structure comprises a super-structure partition plate and is embedded into the second noise reduction structure. According to the composite superstructure design integrating the three noise reduction structures together, the structural stability of the noise reduction device can be guaranteed, and meanwhile, the jet flow installation noise of the aircraft engine can be effectively reduced.

The invention relates to a construction method for reinforcing a landslide through prefabricated high-bending-resistance anti-slide piles, and belongs to the technical field of slope reinforcing engineering. In order to solve the problems that a traditional anti-slide pile is insufficient in flexural rigidity and difficult to reinforce after construction, the I-shaped anti-slide pile structure is adopted and is formed by connecting an upper wing plate pile, a lower wing plate pile and a web pile through a mortise and tenon joint structure, and the flexural rigidity is 3.69 times and 4.15 times that of a square pile and a round pile respectively. During construction, the upper wing plate piles are firstly driven to penetrate through the sliding surface, then the unit piles are formed through mortise and tenon connection of the web piles and the lower wing plate piles, and the continuous underground diaphragm wall is formed by repeatedly driving and utilizing the side mortise and tenon structures of the adjacent pile bodies. Water-absorbent resin (the water absorption rate is larger than or equal to 80 g / g) is smeared at the mortise and tenon joint, the functions of sealing and reducing the pore water pressure are achieved, and the slope stability is improved. The anti-slide pile is suitable for landslide reinforcement of soft soil and complex stratums, modular expansion construction can be achieved, adaptability is high, and the mechanical property and engineering applicability of the anti-slide pile are effectively improved.

The invention relates to the technical field of aircrafts, in particular to a telescopic wing type aircraft with a self-adaptive duct and a control method, and the telescopic wing type aircraft comprises a rack, a lifting force assembly, a power assembly and an adjusting assembly; the lifting force assembly comprises a telescopic wing mounted at the top end of the rack and an empennage mounted at the tail end of the rack; the power assembly comprises self-adaptive duct sets installed on the two sides of the rack, and the self-adaptive duct sets are located on the two sides of the bottom ends of the telescopic wings and used for preventing airflow from disturbing the telescopic wings. When the unmanned aerial vehicle ascends and descends vertically, power airflow can be sprayed out vertically and downwards almost and cannot be blocked or turned back by wings above, thrust is utilized to the maximum degree to overcome gravity, the thrust-weight ratio and the hovering efficiency are improved, and attitude control is more direct and accurate; in the cruising state, the positions of the self-adaptive duct sets prevent airflow from directly impacting the surfaces of the wings, smooth airflow on the surfaces of the wings is prevented from being damaged, vortexes are prevented from being generated, the power efficiency is improved, and thrust loss caused by airflow impact is avoided.

1. Name of the designed product: clip set (butterfly). 2. Use of the designed product: for clipping articles. 3. Design points of the designed product: in shape. 4. Picture or photo best indicating the design points: assembly state diagram. 5. Component 4 is the same as component 2, and component 5 is the same as component 3, and the views of component 4 and component 5 are omitted. 6. Other circumstances needing explanation: component 1 is a butterfly base, component 2 and component 4 are butterfly lower wings, and component 3 and component 5 are upper wings.

The utility model belongs to the technical field of pull heads, and particularly relates to a detachable pull head assembly which comprises a lower wing plate, an upper wing plate and a cap arranged on the upper wing plate, a pull piece is arranged on the cap, an assembly convenient to disassemble is arranged between the lower wing plate and the upper wing plate, an insertion hole is formed in the lower wing plate, an insertion column is fixed to the bottom of the upper wing plate, and the insertion column is fixed to the bottom of the upper wing plate. When the pull rod is pulled outwards, the pull rod drives the limiting sliding disc to slide in the limiting sliding cavity and compresses the spring, the limiting head moves along with the limiting sliding disc, at the moment, the limiting head is separated from the limiting hole, limiting between the limiting head and the inserting column is relieved, then the inserting column is pulled outwards and pulled out of the inserting hole, and disassembling of the pull head is completed. When the puller is damaged, the puller does not need to be integrally replaced, only damaged parts need to be independently replaced, and the disassembly process is convenient and fast.

The utility model discloses a magnetic suspension conveying device for side installation of equipment, which comprises a sliding rail system, the sliding rail system comprises two H-shaped sliding rails which are arranged in parallel left and right at an interval, an upper suspension electromagnet is laid on the bottom surface of the upper flange of each H-shaped sliding rail, and a lower suspension electromagnet is laid on the bottom surface of the lower flange of each H-shaped sliding rail. Internal guiding electromagnets are laid on the left side wall and the right side wall of an upper flange of each H-shaped sliding rail respectively, a sliding module is assembled on each H-shaped sliding rail, a main body of each sliding module is of a C-shaped structure, permanent magnets for lower suspension are laid on the inner walls of webs on the left side and the right side of an opening in the bottom face of each C-shaped structure respectively, and the permanent magnets for lower suspension are arranged on the inner walls of webs on the left side and the right side of the opening in the bottom face of each C-shaped structure respectively. Permanent magnets for external guiding are laid on the inner walls of the two side faces in a cavity of the C-shaped structure respectively, and a web of the H-shaped sliding rail is inserted into the cavity of the C-shaped structure through an opening in the bottom face of the C-shaped structure. According to the device, equipment damage is avoided, meanwhile, the construction cost is greatly reduced, and the overall working efficiency is improved.

The utility model discloses a folding type wing-shaped clothes hanger which comprises two U-shaped airing wings, each airing wing comprises two wing rods which are arranged in parallel, a plurality of hanging rods are arranged between the two wing rods at intervals, two wing part connecting pieces are arranged between the two airing wings, and the wing rods of the airing wings are installed on the wing part connecting pieces in a rotating mode. The lower ends of the wing connecting pieces are provided with vertical rods, the vertical rods are provided with supporting discs, the upper ends of the supporting discs are provided with upper connecting pieces, the upper connecting pieces comprise bayonets arranged at the upper ends, the hanging rods are clamped in the bayonets so that the supporting discs can support the airing wings, the number of the supporting discs is two, and the lower ends of the supporting discs are hinged to the vertical rods. The two supporting discs and the two airing wings are arranged in a one-to-one correspondence mode. The foldable drying rack is simple in structure, and the drying wings and the supporting legs are convenient to fold; and materials are saved, and carrying and moving are convenient.

This invention relates to the field of plastic molding, and more particularly to a composite material molding die for a target aircraft fuselage. The die includes a mold base, with a lower wing mold fixedly mounted on one side of the upper end of the mold base. An upper wing mold is positioned above the lower wing mold. A servo push cylinder is fixedly mounted on the rear of the other side of the upper end of the mold base. A connecting frame is fixedly mounted on the output end of the servo push cylinder. A carrier sleeve is fixedly mounted on the end of the connecting frame. Two shell prisms are symmetrically slidably mounted inside the carrier sleeve, extending from the upper and lower ends of the carrier sleeve respectively. Arc-shaped shells are fixedly mounted on opposite ends of the two shell prisms. Arc-shaped wiping cloths are provided on opposite surfaces of the two arc-shaped shells. A return spring is provided between the opposite ends of the two shell prisms and the carrier sleeve. This invention reduces the labor intensity of workers, facilitates use, reduces dead angles for mold release agent wiping, and ensures effective demolding after molding.

The utility model discloses a double-sided puller and a zipper, and relates to the field of zippers. A double-sided pull head comprises a pull head body and a rope used for pulling the pull head body to slide. The puller body comprises an upper wing plate, a lower wing plate and a connecting column, wherein the upper wing plate and the lower wing plate are vertically arranged, and the connecting column is fixed between the upper wing plate and the lower wing plate and located at the front end of the puller body. The upper wing plate is provided with an upper side tunnel which is through in the front-back direction, the lower wing plate is provided with a lower side tunnel which is through in the front-back direction, the front end opening of the upper side tunnel and the front end opening of the lower side tunnel both extend to the front side space of the connecting column, and the upper side tunnel, the lower side tunnel and the front side space of the connecting column form a rope channel; the rope movably penetrates through the rope channel, the head end of the rope can penetrate through the rear port of the upper side tunnel to be exposed, the head end of the rope is provided with an upper blocking part, the tail end of the rope can penetrate through the rear port of the lower side tunnel to be exposed, and the tail end of the rope is provided with a lower blocking part. The problem that the rope is broken due to scraping at least can be solved.

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.

The invisible pull head comprises a pull head body, the pull head body comprises a lower wing plate, a side plate and an upper wing plate, a separation column is arranged on the lower wing plate, a pull piece is hinged to the top of the separation column, a Y-shaped channel is formed among the separation column, the lower wing plate, the side plate and the upper wing plate, a mounting hole is formed in the top of the separation column, and the mounting hole is higher than the upper wing plate. A cloth passing space is formed between the zipper pull and the upper side of the upper wing plate when the zipper pull is horizontally placed; the separation column is provided with a front convex part, and the front convex part is internally provided with a bow-shaped accommodating cavity and a bow-shaped elastic sheet; and the mounting hole is close to the front convex part, so that the mounting hole and the upper wing plate are staggered. On one hand, a cloth passing space is formed between the pull piece and the upper wing plate by lifting the mounting position of the pull piece; and on the other hand, the rotating shaft of the pull tab and the upper wing plate are staggered in a mode that the mounting hole deviates towards the front convex part, so that the rotating shaft of the pull tab is prevented from being propped against the cloth belt, and the movement of the invisible pull head is smoother.

The utility model discloses a medical equipment belt, and belongs to the field of medical equipment. According to the medical equipment belt, a base profile comprises a bottom plate, side plates, an upper wing plate, a lower wing plate and a pipeline base which is fixed to the bottom plate and located between the two side plates, the wing plates and the lower wing plate extend in the direction away from the side plates, the upper wing plate is obliquely arranged relative to the side plates, and the included angle between the upper wing plate and the lower wing plate is an obtuse angle; a profile hole is formed in the pipeline base, linearly extends from one end of the pipeline base to the other end of the pipeline base, directly serves as a gas pipeline and is used for transmitting medical gas, and the bottom plate, the side plate, the upper wing plate, the lower wing plate and the pipeline base are integrally formed. The section bar holes are directly integrated in the base section bar, the section bar holes serve as pipelines for conveying gas and replace copper pipelines in the prior art, welding operation can be omitted, the base section bar can be prefabricated and formed, and the construction period is greatly shortened.

The invention relates to the technical field of fully-mechanized top coal caving face conveying equipment, in particular to a middle trough with a replaceable upper wing plate, which comprises a middle trough body, the upper wing plate, a connecting bolt and a nut. In the operation process of a scraper conveyor on the rear portion of a fully-mechanized top coal caving working face, the upper wing plate of the middle trough is seriously abraded, according to the split structure of the upper wing plate and the trough body of the middle trough, the upper wing plate can be quite conveniently disassembled and replaced underground when the upper wing plate is seriously abraded, and the original notch section matching size of the middle trough of the scraper conveyor is recovered; the scraper chain can operate normally, smooth conveying of raw coal is achieved, and normal production of a fully-mechanized top coal caving working face is guaranteed.

The invention relates to an unmanned aerial vehicle folding wing unfolding and locking mechanism which comprises a fixed wing and a folding wing, a first rotating shaft plate and a second rotating shaft plate are installed at the movable connecting ends of the fixed wing and the folding wing respectively, and the first rotating shaft plate and the second rotating shaft plate of an upper wing face and a lower wing face are provided with a locking mechanism. The wing pressing device is used for providing unfolding power for the folding wings, and the locking mechanism is used for unfolding the folding wings. By adopting the design of the folding wing unfolding locking mechanism comprising the torsional spring, the bolt, the spring, the collision block and the guide groove, the folding wing unfolding locking mechanism has the advantages of small occupied space, reliable action, simple structure, small folding wing unfolding resistance, mature manufacturing process, low processing cost and convenience in installation and maintenance; the device is suitable for various folding unmanned aerial vehicles.

The semitrailer longitudinal beam comprises a web plate, an upper wing plate is fixedly connected to the top end of the web plate, a lower wing plate is fixedly connected to the bottom end of the web plate, a plurality of reinforcing plates are fixedly connected to the two sides of the web plate respectively, and the upper ends and the lower ends of the reinforcing plates are fixedly connected with the surface of the upper wing plate and the surface of the lower wing plate respectively. The end, away from the web plate, of the fixing plate is fixedly connected with a reinforcing frame, the upper end and the lower end of the reinforcing frame are fixedly connected with the surface of the upper wing plate and the surface of the lower wing plate correspondingly, and the two ends of the web plate are fixedly connected with reinforcing blocks correspondingly. The upper wing plate and the lower wing plate can be supported, local deformation of the upper wing plate and the lower wing plate can be limited, the X-shaped reinforcing frame can effectively transmit torque among the web plate, the upper wing plate and the lower wing plate, due to the X-shaped structural characteristics, the X-shaped reinforcing frame can disperse the torque from multiple angles, the upper wing plate and the lower wing plate work cooperatively to resist torsion, and local torsional deformation is reduced.

The utility model relates to a universal type rail hanging basket walking mechanism with a protection device, which comprises I-shaped steel and a pulley mechanism, the I-shaped steel comprises a web plate, an upper wing plate and a lower wing plate, the pulley mechanism comprises side plates, wheel shafts and pulleys, the lower parts of the side plates protrude out of the lower part of the lower wing plate, and the two side plates are fixed through connecting pieces; a hanging basket steel wire rope is arranged on the connecting piece; comprising a C-shaped protection plate, the C-shaped protection plate comprises a first vertical plate, a second vertical plate and a horizontal plate, the horizontal plate is located above an upper wing plate, the first vertical plate and the second vertical plate are located on the two sides of I-shaped steel, the upper end and the lower end of the first vertical plate are fixed to one end of the horizontal plate and the upper end of a side plate on the same side respectively, and the upper end of the second vertical plate is fixed to the other end of the horizontal plate. The end face of the lower end is lower than the lower edge of the upper wing plate; on the basis of an existing universal walking mechanism, the C-shaped protection plate is additionally arranged through the bolt, the walking mechanism can be hung on the upper wing plate of the I-shaped steel no matter a pulley shaft is broken or the lower wing plate of the I-shaped steel is broken, and the anti-falling protection effect is achieved.

A supersonic aircraft is disclosed herein. The supersonic aircraft comprises one or more fuselages, one or more wings, at least one wing-mounted engine, at least one inlet mounted on the upper surface of or above the wing, an upper wing surface propulsion system fairing, and a lower wing surface propulsion system fairing or lower wing surface modification to account for the presence of the engine.

The bucket rod comprises a bucket rod body, a front support is arranged at the front end of the bucket rod body, a rear support is arranged at the rear end of the bucket rod body, and a connecting structure is arranged in the bucket rod body. The bucket rod body comprises an upper wing plate, a lower wing plate, a left web plate and a right web plate, the connecting structure comprises a center body and a plurality of peripheral rib plates, the center body is fixedly connected among the peripheral rib plates, the left end faces of the center body and the peripheral rib plates are fixedly connected with the left web plate, and the right end faces of the peripheral rib plates are fixedly connected with the right web plate. The right end face of the center body and the right end face of the peripheral rib plates are fixedly connected with the right web, and the ends, away from the center body, of the peripheral rib plates are fixedly connected with the upper wing plate, the lower wing plate and the rear support correspondingly. The bucket rod is reasonable in structural design, the overall rigidity and strength level of the bucket rod are obviously improved, and the force flow transmission path of the upper lug plate, the rear support and the lower lug plate hinged hole of the bucket rod is greatly optimized.

The invention relates to a leading edge slat having an upper airfoil surface defining a slat leading edge and a slat trailing edge, a lower airfoil surface defining a slat plane, and a side end surface contoured by a side edge of the upper airfoil surface and a side edge of the lower airfoil surface, characterized in that the upper airfoil surface defines a slat leading edge and a slat trailing edge, and the lower airfoil surface defines a side edge of the upper airfoil surface and a side edge of the lower airfoil surface. At least one of the side end faces includes a first portion extending from the slat leading edge and a second portion, where the second portion is a continuous convex curved portion extending between the first portion and the slat trailing edge. The invention also relates to an aircraft comprising the leading edge slat as described above. The leading edge slat can delay flow separation and increase the maximum lift coefficient.

The present invention relates to a variable wing with an elastic support self-locking function suitable for medium and high-speed flight; it includes a main wing, an extended wing, an extension mechanism, a fixed frame, an elastic support mechanism, a first locking mechanism and a second locking mechanism. The extended wing includes an upper wing plate and a lower wing plate, a leading edge skin, a trailing edge skin, a front wing edge fairing strip and a rear wing edge fairing strip. The front wing edge fairing strip is provided with a front guide groove, and the inner walls of the upper wing plate and the lower wing plate are provided with front guide strips. The rear wing edge fairing strip is provided with a rear guide groove, and the inner walls of the upper wing plate and the lower wing plate are provided with rear guide strips; the outer end of the front wing edge fairing strip is fixedly connected to the leading edge skin; the outer end of the rear wing edge fairing strip is fixedly connected to the trailing edge skin, and the front wing edge fairing strip and the rear wing edge fairing strip are movably connected to the upper wing plate and the lower wing plate; through the above structural design, it is to solve the problem that the existing wing edge is made of flexible materials and can only be suitable for low-speed flight. After exceeding 100 m / s, during the flight, the wing edge is prone to deformation and cannot meet the requirements of medium and high-speed flight.