264 results about "Lower 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.

A detachable multi-stage automotive fastener clip attaches a body panel to a chassis slot. The fastener clip includes a U-shaped upper clip having at least two wings laterally spaced apart. The wings include: a wing tip, a bent wing, an inclined plane. A flex point is formed on a lower wing portion operative to engage and detach with the chassis slot. A U-shaped lower clip removably attaches to the U-shaped upper clip. At least two walls are laterally spaced apart at an open wall end. A ramp, a shoulder and a retaining ledge are formed on the at least two walls away from the open wall end operative to engage the inclined plane. A base at a closed end opposite the open wall end is formed such that the base is formed between a lower wall portion from each of the at least two walls forming a U shape.

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 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 utility model provides a cable guiding and anti-falling festoon balancing device under the condition of rotation of a chute tube of a ship loader, which comprises an annular track and a plurality of slide rail cars matched on the annular track in a rolling way, each slide rail car comprises two oppositely arranged pulley plates, a rolling shaft vertical to the pulley plates is fixedly arranged on the pulley plates, and the rolling shaft is connected with the annular track. Rollers are installed on the rolling shafts, the section of the annular rail is of an I-shaped structure, the rollers are arranged on the upper surface of a lower wing plate of the I-shaped structure in a rolling fit mode, a web plate is fixedly arranged between the two oppositely-arranged pulley plates, a sponge fixing plate is arranged below the web plate, and a sponge plate is installed on the sponge fixing plate. A U-shaped plate is installed below the sponge plate, and a plurality of clamping grooves arranged at intervals in the length direction of the sponge plate are formed in the lower surface of the sponge plate. Under the rotation working condition of the ship loader chute tube, the sliding rail vehicle and the annular rail are not prone to being jammed, disengaged and damaged, and the safety of the ship loader chute tube under the rotation working condition can be improved.

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.

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 belongs to a marine container battery frame in the technical field of marine power batteries. Comprising two bottom side beams (1), the two bottom side beams (1) are each of an I-shaped structure, a plurality of box bottom beams (2) are arranged between the two bottom side beams (1), one end of each box bottom beam (2) is fixedly connected with a web (13) and a lower wing plate (14) of one bottom side beam (1), the other end of each box bottom beam (2) is fixedly connected with a web (13) and a lower wing plate (14) of the other bottom side beam (1), and a bottom plate (3) is arranged on the box bottom beams (2). The container battery frame for the ship is simple in structure and convenient to manufacture, the overall strength is effectively guaranteed, the problem that a container battery is damaged due to plastic deformation in the transportation process is solved, meanwhile, the bottom side beams are of an I-shaped structure, materials are reduced, the weight is prevented from being increased, and light weight of the container battery is achieved.

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.

The utility model provides a puller for an invisible zipper, which reduces contact stress between a flange and a zipper tape and is easy to pull upwards, and the top end of the flange is difficult to be clamped on the zipper tape. The slider for the invisible slide fastener is provided with a lower wing plate, a pair of left and right guide rails vertically arranged along the side edges of the lower wing plate in the left-right direction, left and right flanges extending from the upper ends of the pair of left and right guide rails in the direction of approaching each other, a guide column, and a front mounting column and a rear mounting column which protrude upwards from the guide column at intervals in the front-back direction, the front end portion of the flange is located forward of the front end portion of the guide rail, and the starting point of the front curve portion on the inner side of the flange is located rearward of the front end portion of the guide rail.

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 present application relates to the technical field of hydraulic engineering construction, and discloses a lifting appliance for underwater hoisting of flexible gabion, which comprises a frame body, wings on the top and bottom of the frame body, and a limiting throwing assembly on the frame body. The frame body is welded from a rectangular steel plate and a channel steel, and is matched with a limiting hoop and upper and lower wings, so that the overall rigidity is strong, the carrying capacity is prominent, the double adjustment mechanism of main steel wire rope hoisting and manual control angle of traction rope can be used to flexibly adjust the underwater posture of the lifting appliance, the frame body provides a stable operation platform during the gabion filling stage, additional binding and fixing are not needed, the stone filling speed is effectively improved, the deformation of the flexible gabion during the filling, hoisting and launching process can be effectively constrained through the cooperation of the frame body, bottom plate, side plate and extension plate, and the displacement of the gabion due to the influence of water flow can be avoided, so that the flexible gabion can be thrown into the required area.

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 provides an electric skateboard chassis of a light commercial vehicle. The electric skateboard chassis comprises a frame, a domain control battery pack, an electric drive axle, an electric steering gear, a cooling module, a front suspension, a Chiller, a PTC, an electric compressor, a super kettle, a storage battery, a spare tire and a charging port. The frame longitudinal beam adopts a uniform-section uniform-width straight-through design; independent suspension fixing points and non-independent suspension fixing points are arranged on the frame longitudinal beams in an X direction in a staggered manner; the domain control battery pack adopts an integrated domain control pack PTC (Positive Temperature Coefficient) scheme; the domain control battery pack integrates a battery pack bracket, an all-in-one device, a VCU, an MCU and a BMS; a battery pack mounting cushion block is arranged on the lower wing surface of the frame longitudinal beam, and a domain control battery pack is mounted on the battery pack mounting cushion block through a bolt; the electric drive axle is a parallel shaft type coaxial electric drive axle. According to the method, the research and development cost and the production cost of new vehicle types are greatly reduced, personalized customization of consumers can be met, and rapid iteration of the vehicle types can be achieved.

The present invention discloses a device for removing cracks from an aircraft wing skin, belonging to the technical field of aircraft maintenance equipment. The device comprises an outer shell, a removal tool, and a clamping mechanism. The device is characterized in that: a clamping mechanism and an elastic protective mechanism are installed inside the outer shell, the elastic protective mechanism is connected to the clamping mechanism, and the removal tool is clamped and installed inside the clamping mechanism; a guide sleeve is sleeved on the upper end of the clamping mechanism and slidably engages with the clamping mechanism; a guide blind hole is provided at the lower end of the outer shell, the upper end of the guide sleeve is inserted into the guide blind hole of the outer shell and slidably engages with the guide blind hole, and the upper end of the guide sleeve is connected to the top wall of the guide blind hole of the outer shell via a compression spring; the guide sleeve is connected to the elastic protective mechanism, and a pressure sensor is connected to a control valve of a telescopic cylinder via a circuit. Compared with the prior art, the device has the advantage of preventing damage to the wing rear beam when removing cracks from the lower wing skin.

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.

The utility model discloses a walking mechanism for R-VR-R space station experience, which is mounted on an annular track at the top in a cabin of a space station environment experience area, the lower part of the annular track is connected with a suspension mechanism, and the cross section of the track is I-shaped; the walking mechanism comprises a walking trolley frame which is arranged on the track and can walk along the track so that an experiencer can experience space floating walking in the space station environment experience area. The driving motor is mounted on one side of the traveling trolley frame; the driving walking mechanism is mounted on a frame of the traveling trolley, is positioned above a lower wing plate of the track and is in transmission connection with an output shaft of a driving motor so as to enable the traveling trolley to walk along the track; wherein the R-VR-R refers to the process from reality to virtual reality and then to reality. The walking mechanism for R-VR-R space station experience enables people to experience floating and walking in a space station floating simulation environment.

A flip-and-swing multi-stage deformable wing suitable for cross-domain flight belongs to the field of aircraft technology. The present invention solves the problem that the existing cross-domain flight deformable wing technology cannot simultaneously solve the problems of heavy driving and transmission devices, low wing surface deformation expansion and contraction ratio, and poor continuity of the aerodynamic shape of the multi-stage deformable wing surface. It includes an aircraft base and a deformable wing skeleton, and the aircraft base and the deformable wing skeleton are connected by a flip assembly. The deformable wing skeleton includes a bottom beam, a first-level wing leading edge, a first-level folding assembly, a second-level wing leading edge and a second-level folding assembly. The front end of the first-level wing leading edge is hinged to the front end of the bottom beam. Based on the geometric layout of the folding assembly combined with the wing leading edge and the idea of ​​graded arrangement and continuous expansion of the second-level swinging wing, a second-level swinging wing surface structure is proposed. The deformable wing has aerodynamic shapes under four different flight conditions: fully folded wing, wing surface flipping, first-level swinging wing, and second-level swinging wing, and is suitable for cross-domain flight.

The utility model discloses a zipper which comprises a first zipper tooth and a second zipper tooth which are oppositely arranged, and a puller used for locking or separating the first zipper tooth and the second zipper tooth. The puller comprises a lower wing plate, and the sides, facing the lower wing plate, of the first zipper teeth and the sides, facing the lower wing plate, of the second zipper teeth are correspondingly bent to form a first bent part and a second bent part respectively. When the first zipper teeth and the second zipper teeth are locked, the first bending part and the second bending part abut against the two sides of the lower wing plate respectively, flexible cloth is prevented from entering the space between the two zipper teeth, and the selvage clamping prevention effect is well achieved.

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 application discloses a kind of single-box three-chamber cross-section girder bridge shear lag effect analysis method, belong to bridge construction control technical field.The method includes the following steps: S1. with quadratic parabola function to build shear lag warping displacement function, select the coordinate at the location of half of box girder section, i.e. the wing plate longitudinal displacement function of single-box three-chamber thin-walled box girder considering shear lag effect is obtained;S2. calculate the normal strain and shear strain of upper and lower wing plate and web of thin-walled box girder;S3. calculate the strain energy of upper and lower wing plate and web of thin-walled box girder;S4. calculate the total potential energy of single-box three-chamber girder system;S5. according to the principle of minimum potential energy, simplification is carried out using the method of partial integration, and the control differential equation set and boundary conditions of single-box three-chamber thin-walled box girder considering shear lag effect are obtained.The application discloses a kind of single-box three-chamber cross-section girder bridge shear lag effect analysis method, and the prediction result of main girder stress and deformation is more in line with actual situation, improves the accuracy of single-box three-chamber cross-section girder bridge construction process, and higher safety.