178 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.

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 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.

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 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.

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 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 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 utility model relates to the technical field of automobile parts, disclose a quick installation structure of automobile exhaust system heat shield, including upper cover body and lower cover body, the outside of upper cover body is provided with installation mechanism, the outside of upper cover body is provided with heat abstractor, the outside of upper cover body is provided with reinforcing mechanism, the outside of upper cover body is provided with connecting mechanism, the installation mechanism includes upper wing board, the outer wall fixed connection in the left side of upper cover body of upper wing board, the left side fixed connection of lower cover body has lower wing board, the bottom fixed connection of upper wing board has two fixed blocks, the front and back of two fixed blocks all are fixedly connected with elastic gasket. In the utility model, the heat shield is installed through the fixed block of upper wing board and is engaged with lower wing board, is inserted into the plug pin fixed from the embedded entry to the through hole inside, the plug pin tail connects the limiting ring and the supplementary pin, and the plug pin is prevented from popping out by abutting against, has good steady attribute, and the convenient installation and replacement are facilitated.

The utility model provides an orthodontic bracket which comprises a bottom plate, a fixing block is arranged on the bottom plate, the fixing block comprises an upper wing and a lower wing, a sliding groove is formed in the top surface of the upper wing in a penetrating mode, a lock cover is connected in the sliding groove in a sliding mode, a first groove is formed in the sliding groove, and the first groove is formed in the vertical inner wall of the side, close to the bottom plate, in the sliding groove. A through hole is formed in the position, corresponding to the first groove, of the lock cover, a shaft wire is arranged in the through hole, one end of the shaft wire is located in the first groove, a limiting protruding block is arranged on the vertical inner wall of one side of the first groove and divides the first groove into two symmetrical containing grooves, and the shaft wire is made of deformable materials. The first groove with the limiting bump in the sliding chute is matched with the deformable shaft wire, so that the shaft wire is adjusted between the two placing grooves and is blocked and fixed by the limiting bump when the lock cover is opened and closed, stress concentration of a traditional sliding rail is avoided, the risk that the lock cover falls off is reduced, and stable transmission and effect of correction force are guaranteed.

The application discloses a manufacturing method and a column head of a multi-ledge steel column, and the manufacturing method comprises the following steps: S1, manufacturing a round pipe column; S2, manufacturing a top cover unit and a pipe side unit; S3, sequentially assembling and welding a plurality of pipe side units with the round pipe column, the plurality of pipe side units are distributed at intervals around the round pipe column and second inner partition plates and second process partition plates are arranged between the pipe side units; S4, respectively assembling and welding the top cover unit with the round pipe column and the pipe side unit; S5, welding and arranging third inner partition plates and third process partition plates in the round pipe column; S6, arranging second side plates between every two adjacent pipe side units to form corresponding prisms by combined welding; S7, manufacturing a ledge unit, the upper wing plate of the ledge unit is not welded first, and the remaining components are welded; and S8, sequentially assembling and welding a plurality of ledge units with the prisms, the box-shaped body of the ledge unit is welded first, and then the upper wing plate is assembled and welded. By decomposing the component into a multi-unit combined structure form, the component assembly process design is optimized, the assembly and welding of the ledge unit are facilitated, and the component is convenient to use.

The utility model relates to the field of cargo compartment design, and discloses a cargo compartment structure which comprises a bottom plate, the bottom plate is rotationally connected with a breast board assembly, a fixed beam is arranged at the bottom end of the bottom plate, an edge beam is arranged on the edge of the bottom plate, one end, away from a web plate, of an upper wing plate of the edge beam downwards forms a first flanged plate, and the end of the fixed beam is embedded into a groove of the edge beam and fixedly connected with the first flanged plate. The top end of the fixing beam is flush with the edge beam, the outer side of the bottom end of the breast board assembly is arranged in a downward protruding mode, an L-shaped groove allowing the end of the bottom plate to be embedded is formed between the outer side of the bottom end of the breast board assembly and the inner side of the bottom end of the breast board assembly, and when the breast board assembly rotates to be vertical, the edge of the bottom plate is embedded into the L-shaped groove in the bottom end of the breast board assembly. Rainwater is prevented from entering the cargo compartment from the gap between the breast board assembly and the bottom board, gaps exist between the fixing beams and the edge beams through the first flanged boards, flowing of electrophoresis liquid is facilitated, the fixing beams and the edge beams can be fully coated, and the bottom board structure has the effects of enhancing the corrosion resistance of the bottom board structure and preventing cargoes in the cargo compartment from being wetted.

The present invention is a zipper (1) having left and right zipper tapes (10), at least one slider (20), and a stopper (30) for the slider (20) to abut against, the stopper (30) being fixed across the left and right zipper tapes (11) and having a shape in which a portion of the stopper (30) can be inserted between the upper wing plate (22) and the lower wing plate (23) of the slider (20), the interval in the tape width direction between the left and right zipper teeth (13) in a state in which the left and right zipper tapes (10) are separated is defined as a tooth interval (A), the maximum value of the dimension in the tape width direction of the connecting column (24) of the slider (20) is defined as a column maximum width (B), and the tooth interval (A) is a size of 100% or more and 150% or less of the column maximum width (B). Thus, when the slider (20) is caused to slide toward the stopper (30), it is difficult for the zipper teeth (13) to fall over in the vicinity of the stopper (30), and it is possible to suppress the zipper teeth (13) from being caught in the slider (20).

A slider for a slide fastener includes a slider body (11) and two pullers (20, 21) pivotally attached to the slider body (11). The slider body (11) forms an upper wing (12), a lower wing (13), a connecting post (14) connecting the upper and lower wings, and side flanges (15). The side flanges protrude from side edges of the upper and lower wings towards a geometrical mid-plane (P) that lies between the wings (12, 13), so as to form a Y-shaped channel (19) between the upper and lower wings. The upper wing (12) and the lower wing (13) have respective opposite outer surfaces (23, 24) which are substantially flat, and are symmetrical with respect to the geometrical mid-plane (P). At least one locking protrusion (30) protrudes inwardly into the Y-shaped channel (19) from at least one of the side flanges (15) of the slider body (11).

The present application relates to the technical field of aircraft design, and particularly relates to a wide-speed-range aircraft based on a variable high-pressure capture wing shape and a control method thereof, which comprises a fuselage, an upper wing surface, a lower wing surface, a foldable canard, a variable high-pressure capture wing and a control system. The variable high-pressure capture wing is arranged above the fuselage and the upper wing surface, and is used for switching between a subsonic forward-swept configuration and a supersonic backward-swept configuration according to a flight speed range; the foldable canard is arranged at a leading edge of the wing surface, and is used for unfolding in a subsonic stage and folding to be attached to the lower wing surface in a supersonic stage; and the control system determines a current stage according to flight state parameters, and cooperatively drives the high-pressure capture wing and the canard to perform a configuration switching action. The present application realizes adaptive matching of an aerodynamic shape and a flight speed range through variable design.

An articulated machine 100 has a body portion 105 and a wing portion 110 comprising an active member and mounted on body portion 105. Wing portion 110 is moveable between a first (for example, lowered

The invention provides a hip joint surface replacement prosthesis suitable for severe acetabulum defects, and belongs to the technical field of medical instruments. The three-wing acetabulum outer cup prosthesis is made of metal cobalt-chromium-molybdenum materials, a titanium alloy coating and a hydroxyapatite coating are arranged on the surface of the three-wing acetabulum outer cup prosthesis, and the coatings are of a micropore structure. The upper wing, the middle wing and the lower wing are connected to the circumferential surface of the three-wing acetabulum outer cup prosthesis in a sliding mode; the upper wing, the middle wing and the lower wing of the hip joint surface replacement prosthesis are designed into shapes matched with a bone anatomical structure of a patient, so that the prosthesis can be tightly attached to an acetabulum area of the patient. According to the personalized adaptive design, necessary initial stability is immediately provided after an operation, a solid foundation is laid for early movement and recovery of a patient after the operation through a multi-point fixing mechanism, and the risk of complications caused by prosthesis looseness is reduced.

The present invention provides a zipper pull. The zipper pull (1) of the present invention has a zipper pull body (10) having an upper wing plate (20) and a lower wing plate (30). A pair of groove portions (50, 60) are provided on the inner surface of the upper wing plate (20) and / or the lower wing plate (30). In a cross-sectional view of the zipper pull body (10), with the outermost position in the zipper pull width direction of the outer periphery of the connecting post (40) defined as the outermost position (41), the inner groove side edge portion (52a) of each groove portion (50, 60) is positioned inside the zipper pull width direction than the outermost position (41), and the outer groove side edge portion (52b) of each groove portion (50, 60) is positioned outside the zipper pull width direction than the outermost position (41). Therefore, even with repeated sliding operations, it is not easy to cause scraping of the zipper teeth caused by the inner surface of the zipper pull body (10).

1. Name of this design: Upper wing plate of pull head base. 2. Application of this design: The zipper pull base is used for zipper pull accessories; the upper wing plate of the zipper pull base is used for zipper pull accessories. 3. The key design features of this product are the combination of shape and color. 4. The image or photograph that best illustrates the design's key points: a 3D model. 5. The design for which protection is sought includes color. 6. Other situations requiring explanation: Other explanation: The parts covered in red are protected parts, and the parts not covered are unprotected parts.

A kind of steel bridge distortion fatigue carbon fiber cloth and multi-limb angle steel composite reinforcing structure and process, vertical steel plate beam web is arranged between upper wing plate and lower wing plate, vertical stiffening rib is arranged between steel plate beam web and wing plate, horizontal node plate is vertically arranged in the height direction of steel plate beam web, vertical stiffening rib vertically passes through horizontal node plate, and horizontal node plate web gap area and vertical stiffening rib web gap area are reinforced using carbon fiber reinforced resin base and multi-limb angle steel composite structure;When reinforcing using the reinforcing process, before the strength of composite structure glue layer is not consolidated to form, auxiliary device needs to be fixed, after removing auxiliary reinforcing device, carbon fiber cloth is pasted on the surface of angle steel to form composite reinforcing structure layer.The reinforcing structure is suitable for 50-100mm long distortion fatigue crack reinforcement, can effectively improve the stress performance of web gap, improve the ability of inhibiting detail distortion fatigue crack initiation and expansion, has the advantages of convenient construction, low cost and excellent performance.