393 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.

The invention discloses an H-shaped steel automatic welding roller way conveying system. Comprising a lower wing plate feeding line, a web feeding line, an upper wing plate feeding line, a lower wing plate and web assembly line, a T-shaped steel assembly welding straightening blanking transition line, a T-shaped steel assembly welding straightening blanking line, a web lifting turnover line, a T-shaped steel upper wing plate assembly line, an H-shaped steel assembly welding straightening blanking transition line and an H-shaped steel assembly welding straightening blanking line which are arranged in parallel in the same direction. The lower wing plate feeding line, the lower wing plate web assembling line, the T-shaped steel assembling, welding and correcting discharging line, the web feeding line, the upper wing plate feeding line, the T-shaped steel upper wing plate assembling line and the H-shaped steel assembling, welding and correcting discharging line are each composed of a plurality of roller bed units. The web lifting turnover line is composed of a plurality of lifting roller bed units; and the T-shaped steel assembling, welding and straightening blanking transition line and the H-shaped steel assembling, welding and straightening blanking transition line are respectively composed of a plurality of transition roller bed units. The problems that an existing H-shaped steel welding production line is high in labor intensity and low in efficiency, and safety factors exist in a working site can be solved.

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 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.

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 invention discloses a wing end standing vortex lift augmentation device which comprises a device upper surface, a device lower surface, a leading edge surface and a wing profile, a wing upper wing surface extends outwards to form the device upper surface, a wing lower wing surface extends outwards to form the device lower surface, and the extension length of the device upper surface is larger than that of the device lower surface. A distance exists between the upper surface and the lower surface of the device, and wingtips do not coincide with each other; the device upper surface, the device lower surface, the front edge surface and the airfoil profile jointly form a semi-closed cavity, when incoming flow exists in the semi-closed cavity, a wing end standing vortex rotating in the direction away from the central axis of the fuselage is formed in the semi-closed cavity, and the rotating direction of the wing end standing vortex is opposite to that of a wingtip vortex. According to the three-dimensional wing, airflow on the lower wing surface of the wing is prevented from flowing to the upper wing surface of the wing through the wing end standing vortex in the semi-closed cavity, so that the trend that the airflow on the lower wing surface of the wing is reversed upwards can be inhibited under the condition of not depending on physical obstruction, the lift force of the three-dimensional wing is effectively increased, and the induced resistance is reduced.

An underframe boundary beam connecting structure suitable for a railway vehicle with a drum-shaped vehicle body is provided. An underframe boundary beam is a through long roll bending piece, a section of the through long roll bending piece is of a channel structure, and has a side face, an upper wing face, and a lower wing face. The side face has an inclination angle consistent with a side wall plate, an upper end of an outer side of the side face is provided with a concave platen, and the side wall plate is lapped on the concave platen and fixed by a butt welding; an inner end of the lower wing face is provided with a downwards vertical flanging, a vertical plate is welded and fixed between the upper wing face and the lower wing face.

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 provides a pressure-torsion test device and a use method thereof, and belongs to the technical field of building structure tests. In the pressure-torsion test device, a foundation ground beam, a middle main beam and a side main beam are detachably connected with three-in-one stand columns on the two sides respectively; the fixed end of the vertical electro-hydraulic servo loading device is installed on the lower flange of the middle main beam, and the movable end of the vertical electro-hydraulic servo loading device is connected with a pressure loading area on the top of the pressure-torsion loading force arm. The horizontal electro-hydraulic servo loading device is connected with the side main beam through a suspension connecting assembly, the fixed end of the horizontal electro-hydraulic servo loading device is installed on a side stand column of the three-in-one stand column in a central symmetry mode, and the movable end of the horizontal electro-hydraulic servo loading device is connected with the two ends of a pressing-twisting loading force arm. The lower flange of the compression-torsion loading force arm and the upper flange of the foundation ground beam are respectively provided with a test piece installation area. The compression-torsion test device provided by the invention is simple and convenient to mount and operate, the load position can be freely configured according to the size of a test piece, the load provided by the device can be self-balanced, and the defects of the existing compression-torsion test device in data accuracy and operation simplicity and convenience are overcome.

The utility model discloses an aluminum alloy girder of a container transportation semitrailer. The aluminum alloy girder comprises a front section structure, a gooseneck structure and a rear section structure, the front section structure and the rear section structure are I-shaped aluminum structures; the gooseneck structure comprises a gooseneck upper wing plate structure and a gooseneck lower wing plate structure; the gooseneck upper wing plate structure comprises an upper wing plate front end part, an upper wing plate arc-shaped part and an upper wing plate rear end part which are connected in sequence; the top surface of the front end part of the upper wing plate is propped against the bottom surface of the front-section upper wing plate, and the bottom surface of the rear end part of the upper wing plate is propped against the top surface of the rear-end upper wing plate; the gooseneck lower wing plate structure comprises a lower wing plate front end part, a lower wing plate arc-shaped part and a lower wing plate rear end part which are connected in sequence; the top face of the front end of the lower wing plate abuts against the bottom face of the front section lower wing plate, and the top face of the rear end of the lower wing plate abuts against the top face of the rear end lower wing plate. Structural structure defects and deformation caused by welding can be reduced, the welding workload is reduced, and compared with a traditional girder, the girder is more reliable and more environmentally friendly.

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.

The utility model provides an external oil storage tank of an automobile hydraulic retarder. The oil storage tank is installed on an upper wing face of a left longitudinal beam of a vehicle frame through a support, the oil conveying hose is installed on the lower portion of an oil outlet pipe at the lower end of the oil storage tank, and the other end of the oil conveying hose is installed on an oil inlet of the hydraulic retarder. The oil storage tank comprises an oil storage tank body, a top cover, an oil outlet pipe and the like. The external automobile hydraulic retarder oil storage tank not only stores a certain amount of retarder oil, but also can ensure that the retarder oil cannot be sprayed out of the retarder oil storage tank, is relatively simple in structure and convenient to install, and can be widely applied to trucks provided with hydraulic retarders.

The utility model discloses a pair of multi-surface protective safety glasses, which comprises a glasses frame, lenses, nose pads and glasses legs, the glasses frame comprises an upper frame and a lower frame; upper lens grooves are formed in the upper frame, pile heads are formed at the left and right ends of the upper frame, and first hinge seats are formed on the pile heads; the lower frame forms a lower lens groove, a nose pad is arranged behind the lower frame, a nose wing seat is further arranged on the lower frame, and a nose wing cover is arranged on the nose wing seat; the lens is arranged in the upper lens groove and the lower lens groove; second hinge seats are formed at the front ends of the glasses legs, and the glasses legs are installed at the left and right ends of the glasses frame through cooperation of the first hinge seats and the second hinge seats. Fasteners are further installed at the positions, close to the second hinge seats, of the front ends of the glasses legs, the fasteners are provided with side strips, upper side wings are formed above the fasteners, lower side wings are installed below the fasteners, and when the glasses legs are unfolded, the upper side wings are connected with the side edges of the upper frame, and the lower side wings are connected with the side strips. The lower side wing and the nose wing cover are made of soft materials. According to the utility model, the all-around protection effect can be achieved, and the anti-collision and anti-impact effects can be provided.

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.