CN221695816U - Welding jig for aircraft pipeline - Google Patents

Abstract

The utility model discloses a welding fixture for aircraft pipelines, comprising a base, on which an aircraft pipeline end clamping device, an aircraft pipeline middle clamping device and an aircraft pipeline box clamping device are arranged; the aircraft pipeline end clamping device comprises a first seat body, a slide seat, a positioning block, a first drive, a second drive and a pressing block, the first seat body is arranged on the base, the second drive is arranged at the upper end of the slide seat, the pressing block is hinged between the output shaft of the second drive and the slide seat, an arc groove is arranged on the pressing block, and the pressing block is located above the positioning block; the aircraft pipeline middle clamping device comprises a second seat body and a clamping plate; the aircraft pipeline box clamping device comprises a third seat body and a pressing plate mechanism, the pressing plate mechanism comprises a support seat and a pressing plate hinged on the support seat, and a pressing plate driving mechanism is arranged between the support seat and the pressing plate. The structure improves positioning accuracy and positioning reliability.

Description

A welding fixture for aircraft pipes

Technical Field

The utility model relates to a welding fixture, in particular to a welding fixture for aircraft pipelines.

Background Art

Welding refers to connecting workpieces through welding guns and welding wires. For welding of workpieces, it is generally necessary to use tooling to position them. The design of the tooling structure is one of the important factors affecting the welding quality. Therefore, reasonable welding tooling will be designed according to the specific structure of the workpiece. For pipe welding, the designed tooling generally needs to be positioned axially and radially. At the same time, it is also necessary to consider reserving the welding operation space when welding a circle of the pipe. For aircraft pipes, the positioning accuracy and reliability are generally required to be good, so that high-precision aircraft pipes can be manufactured to improve the reliability of the aircraft during operation.

Summary of the invention

The utility model aims to provide a welding tool for aircraft pipelines, which can position the end of an aircraft connecting pipeline by means of an aircraft pipeline end clamping device, support the aircraft connecting pipeline by means of an aircraft pipeline middle clamping device to prevent the aircraft connecting pipeline from being completely cantilevered at one end, and position the aircraft pipeline box by means of an aircraft pipeline box clamping device to improve positioning accuracy and positioning reliability.

In order to achieve the above-mentioned purpose, a welding fixture for aircraft pipes is provided, comprising a base, on which an aircraft pipe end clamping device, an aircraft pipe middle clamping device and an aircraft pipe box clamping device are arranged in sequence from one end to the other end of the base; the aircraft pipe end clamping device comprises a first base body, a slide seat, a positioning block, a first drive, a second drive and a pressing block, the first base body is arranged on the base, the slide seat is arranged on the first base body to slide along the length direction of the base, the positioning block is arranged on one end surface of the slide seat, the first drive is arranged between the first base body and the slide seat, the second drive is arranged at the upper end of the slide seat, and the pressing block is hinged at the output of the second drive An arc groove is provided on the pressing block between the shaft and the slide seat, and the pressing block is located above the positioning block; the aircraft pipeline middle clamping device includes a second seat body and a clamping plate, and movable clamping plates are respectively provided on both sides and the lower side of the upper end of the second seat body; the aircraft pipeline box clamping device includes a third seat body and a pressing plate mechanism, the upper end of the third seat body is provided with a positioning groove matched with the bottom of the aircraft pipeline box body, and clamping blocks clamped to the end of the aircraft pipeline box body are respectively provided at the front and rear ends of the third seat body, and the pressing plate mechanism includes a supporting seat provided on the third seat body and a pressing plate hinged on the supporting seat, and a pressing plate driving mechanism is provided between the supporting seat and the pressing plate.

In the above structure, the aircraft pipe box is first placed on the positioning groove, and the positioning groove is used to cooperate with the bottom and both sides of the aircraft pipe box, and the aircraft pipe box is supported by the third seat body. Then, the front and rear ends of the aircraft pipe box are positioned and clamped by the clamping blocks at both ends, and finally, the pressing plate is driven to swing by the pressing plate driving mechanism, and the pressing plate is used to press the top of the aircraft pipe box. In this way, the bottom, both sides, front and rear ends and top of the aircraft pipe box are completely positioned, thereby providing a basis for the connection positioning of the aircraft connecting pipes. After the aircraft pipe box is positioned, the other end of the aircraft connecting pipe is inserted into the connecting hole of the aircraft pipe box. At this time, the middle part of the aircraft connecting pipe is located in the space formed by the clamping plate, and then the first drive is started. The first drive drives the slide to move in the direction of the aircraft connecting pipe, so that the positioning block is inserted into one end of the aircraft connecting pipe. The aircraft connecting pipe is axially positioned by inserting the positioning block and the other end of the aircraft connecting pipe into the aircraft pipe box, and then the second drive is driven. The second drive drives the pressing block to press on the outer circumferential surface of one end of the aircraft connecting pipe, and then the clamping plate is moved to support and limit the middle part of the aircraft connecting pipe by the clamping plate. Therefore, in the utility model, the aircraft pipe box is first installed and positioned to provide a basis for the installation of the aircraft connecting pipe, and then the clamping plate is used to support the middle part of the aircraft connecting pipe to avoid the aircraft connecting pipe being in a completely cantilevered state, effectively avoiding the deformation of the aircraft connecting pipe in the welding structure, and at the same time, with the positioning block and the pressing block, the positioning accuracy of the aircraft pipe is high and the positioning reliability is good.

Further, the first seat body includes a first lower seat body and a first upper seat body, a first guide rail is arranged on the first lower seat body, a first slider is arranged at the bottom of the first upper seat body, the first slider is slidably arranged on the first guide rail, a second slider is arranged on the first guide rail at one end of the first upper seat body, a connecting plate is arranged between the second slider and the first upper seat body, a first threaded hole is arranged on the second slider, a first bolt acting on the first lower seat body is installed in the first threaded hole, and first limit blocks are respectively arranged at both ends of the first lower seat body. This structure can adjust the position of the first upper seat body relative to the first lower seat body by loosening the first bolt, so as to facilitate the adjustment of the position of the slide seat, so as to be suitable for positioning without passing through the aircraft pipeline. When the first bolt acts on the first lower seat body, the first upper seat body can be prevented from moving randomly; by setting the first limit block, the moving stroke of the first upper seat body can be limited, and at the same time, the first upper seat body can be prevented from being separated from the first guide rail.

Furthermore, the first lower seat body includes a first support seat assembly and an adjustment seat, the first support seat assembly includes more than two groups of first support seats, the first support seat is provided with a first waist-shaped groove, and the adjustment seat is provided with a second bolt passing through the second waist-shaped groove. In this structure, by loosening the second bolt, the adjustment seat can be moved up and down under the guidance of the first waist-shaped groove to be suitable for positioning of different aircraft pipes.

Furthermore, a second stop block is provided on the first seat body, and a third stop block capable of interacting with the second stop block is provided on the slide. In this structure, when the slide is moving, the third stop block moves with it, and when the third stop block contacts the second stop block, the movement of the slide is limited, thus limiting the movement stroke of the slide, preventing the slide from moving too far and causing the positioning block to squeeze the aircraft connection pipe, thereby effectively protecting the aircraft connection pipe.

Furthermore, a slot is provided on the side of the slide, one end of the third limit block is inserted into the slot, and a third bolt is installed between the slide and the third limit block. By providing the slot, the third limit block can be positioned and limited.

Further, the positioning block includes a positioning seat and a positioning column arranged on the positioning seat; the first drive is a first cylinder, the cylinder body of the first cylinder is fixed on the first seat body, and the piston rod of the first cylinder is connected to the sliding seat; the second drive includes a cylinder seat and a second cylinder, the cylinder seat is installed on the sliding seat, and the cylinder body of the second cylinder is hinged on the cylinder seat; the pressure block includes a pressure block connecting arm, a pressure block fixing seat and a pressure block body, a first connecting rod is hinged between the piston rod of the second cylinder and the cylinder seat, one end of the pressure block connecting arm is hinged on the cylinder seat, the other end of the pressure block connecting arm is connected to the pressure block fixing seat, the pressure block body is fixed to the bottom of the pressure block fixing seat, an arc groove is arranged at the bottom of the pressure block body, and a second connecting rod is hinged between the piston rod of the second cylinder and the middle part of the pressure block connecting arm. In this structure, the positioning column is inserted into one end of the aircraft connecting pipe to realize the centering of the aircraft connecting pipe, and the aircraft connecting pipe can be axially limited by the step formed between the positioning seat and the positioning column. For the first cylinder, when the first cylinder is working, it can drive the slide seat to slide, thereby driving the positioning block to move, and realize the positioning or positioning removal of the aircraft connecting pipe. Corresponding to the second cylinder, when the piston cylinder of the second cylinder moves forward, the second connecting rod drives the pressure block connecting arm close to the end of the pressure block body to swing downward, thereby driving the pressure block fixing seat to swing downward, and the pressure block positioning seat drives the pressure block body to swing downward, and cooperates with the aircraft connecting pipe through the arc groove, and uses the pressure block body to press the outer circumferential surface of one end of the aircraft connecting pipe. In conjunction with the clamping device in the middle of the aircraft pipe, the aircraft connecting pipe can be clamped and positioned up and down, so the positioning reliability is good. When the piston rod of the second cylinder moves in the opposite direction, under the action of the second connecting rod, the pressure block connecting arm, the pressure block fixing seat and the pressure block body are driven to swing upward, thereby facilitating the disassembly of the aircraft connecting pipe.

Furthermore, the second seat body includes a stand and a U-shaped seat arranged on one side of the upper end of the stand, the opening of the U-shaped seat faces upward, and guide grooves are arranged on both sides and the lower side of the U-shaped seat, respectively. A third waist-shaped groove is arranged on the clamping plate, and the clamping plate is slidably arranged in the guide groove, and the fourth bolt passes through the third waist-shaped groove and is connected to the U-shaped seat. By setting the U-shaped seat, it is convenient to set the sliding clamping plate on both sides and the bottom of the upper end of the second seat body, and by setting the guide groove, the clamping plate has the function of positioning and motion guiding, making the movement of the clamping plate more precise; when the third waist-shaped groove is set, it is convenient to adjust the clamping plate by loosening and locking the fourth bolt.

Furthermore, the pressing plate is hinged on the support seat through a hinge shaft, and the pressing plate driving mechanism includes a pressing plate driving motor, a worm gear and a worm. The pressing plate driving motor is arranged on the support seat, the worm gear is installed on the output shaft of the pressing plate driving motor, and the worm gear is arranged on the hinge shaft, and the worm gear is meshed with the worm gear. In this structure, when the driving motor is working, it drives the worm gear to rotate, and the worm gear drives the gripping rod to rotate, thereby driving the pressing plate to swing. The worm gear structure is adopted, and a self-locking effect can be generated. Therefore, when the pressing plate is pressed onto the aircraft pipeline box, the driving motor does not need to work to ensure that the pressing plate is reliably pressed onto the aircraft pipeline box, thereby saving energy.

Furthermore, a capillary tube support seat is arranged on one side of the aircraft pipe box clamping device on the base, and a limiting groove is arranged on the capillary tube support seat. The two capillary tubes on the aircraft pipe box can be positioned through the limiting groove.

Furthermore, the capillary tube support seat comprises a capillary tube support seat body and a limiting seat body arranged on the capillary tube support seat body. The capillary tube support seat body is installed on the base, and the limiting groove is arranged on the limiting seat body.

BRIEF DESCRIPTION OF THE DRAWINGS

Figure 1 is a three-dimensional diagram of an aircraft pipeline.

Figure 2 is an exploded view of the aircraft piping.

FIG. 3 is a three-dimensional view of the assembled welding fixture for aircraft pipes and the aircraft pipes.

FIG. 4 is an exploded view of the welding fixture for an aircraft pipe and the aircraft pipe after assembly.

FIG. 5 is a front view of a welding fixture for aircraft pipes.

FIG. 6 is a perspective view of a welding fixture for aircraft pipes.

FIG. 7 is a perspective view of the welding fixture for aircraft pipes from another perspective.

FIG. 8 is an exploded view of a welding fixture for aircraft pipes.

FIG. 9 is a perspective view of the base.

FIG. 10 is an exploded view of the base.

FIG. 11 is a perspective view of an aircraft pipe end clamping device.

FIG. 12 is a three-dimensional view of the aircraft pipe end clamping device from another perspective.

FIG. 13 is an exploded view of an aircraft pipe end clamping device.

FIG. 14 is a perspective view of the slide, the first drive and the positioning block.

FIG. 15 is an exploded view of the slide, the first drive and the positioning block.

FIG. 16 is an exploded view of the second drive and pressure block.

FIG. 17 is a perspective view of a clamping device for the middle portion of an aircraft pipe.

FIG. 18 is an exploded view of the aircraft pipe mid-section clamping device.

DETAILED DESCRIPTION

The present invention will be further described in detail below in conjunction with the accompanying drawings and specific implementation methods.

As shown in Fig. 1 and Fig. 2, the aircraft duct 1000 comprises an aircraft connecting duct 100, an aircraft duct box 200 and a capillary 300. One end of the aircraft connecting duct 100 has a curling edge 1001, the other end of the aircraft connecting duct 100 is inserted into a connecting hole 2001 of the aircraft duct box 200, and the capillary 300 is arranged on the aircraft duct box 200. In this embodiment, the step connecting duct 100 needs to be connected to the aircraft duct box 200 by welding.

As shown in FIGS. 3 to 8 , the welding fixture for aircraft pipes comprises a base 1 , on which an aircraft pipe end clamping device 2 , an aircraft pipe middle clamping device 3 and an aircraft pipe box clamping device 4 are sequentially arranged from one end to the other end of the base.

As shown in Fig. 4, Fig. 6 to Fig. 10, the base 1 includes a base body 11, a bearing plate 12, a positioning pin 13 and a locking device 14. The positioning pin 13 is arranged on the base body 11. In this embodiment, six positioning pins are arranged; the bottom of the bearing plate 12 is provided with a positioning hole (not shown in the figure) for inserting the positioning pin 13. In this way, the bearing plate 12 can be positioned by the positioning pin 13 and the positioning hole. The bearing plate 12 is arranged on the top of the base body 11, and locking grooves 121 are respectively arranged on both sides of the bearing plate 12, and the outer side of the locking groove 121 has an opening; the locking device 14 includes a positioning column 141, a locking block 142, a screw 143, a locking pin 144, a gasket 145, a locking rod 146 and a locking nut 147. A positioning column 141 is arranged on the side of the base body 11 below the locking groove 121, and the locking block 142 is installed on the positioning column 141. The locking block 142 is fixed to the base body 11 by the screw 143, and the locking block 142 is positioned by the positioning column 141. The locking pin 144 passes through the locking block 142, and a gasket 145 is installed at the other end of the locking pin 144 and radially passes through the locking pin 144 by a pin to prevent the gasket 145 from detaching from the locking pin 144. The locking rod 146 is rotatably arranged on the locking pin 144, and the locking nut 147 is threadedly connected to the locking pin 144. With this structure, by loosening the locking nut 147 and disengaging the locking rod 146 from the locking pin 121, the bearing plate 12 can be removed from the base body 11. If the bearing plate 12 needs to be installed on the base body 11, the locking rod 146 is swung to allow the locking rod 146 to be inserted into the locking groove 121, and then the locking nut 147 is applied to the bearing plate 12. This makes it convenient to install and remove the bearing plate 12, thereby facilitating the overall installation and removal of the aircraft pipe end clamping device 2, the aircraft pipe middle clamping device 3 and the aircraft pipe box clamping device 4 fixed to the bearing plate 12.

As shown in FIGS. 4 and 6 to 8 , the aircraft pipe end clamping device 2 includes a first seat body 21 , a slide seat 22 , a positioning block 23 , a first drive 24 , a second drive 25 and a pressing block 26 .

As shown in Figures 11 to 13, the first seat body 21 includes a first lower seat body 211 and a first upper seat body 212. The first lower seat body 211 includes a first support seat assembly and an adjustment seat 2112. The first support seat assembly includes more than two groups of first support seats 2111. The first support seats 2111 are fixed to the bearing plate by bolts. In order to position the first support seats 2111, a first corner block 27 is fixed to the bearing plate by bolts. A first waist groove 21111 is provided on the first support seat, and a second bolt (not shown in the figure) passing through the second waist groove 21111 is provided on the adjustment seat 2112. In this structure, by loosening the second bolt, the upper and lower positions of the adjustment seat can be moved under the guidance of the first waist groove to be suitable for the positioning of different aircraft pipelines. A first guide rail 213 is provided on the adjustment seat 2112, a first slider 214 is provided at the bottom of the first upper seat body 212, the first slider 214 is slidably provided on the first guide rail 213, a second slider 215 is provided on the first guide rail 213 at one end of the first upper seat body 212, a connecting plate 216 is provided between the second slider 215 and the first upper seat body 212, a first threaded hole 2151 is provided on the second slider 215, a first bolt (not shown in the figure) acting on the joint seat 2112 is installed in the first threaded hole 2151, and first limit blocks 217 are respectively provided at both ends of the joint seat 2112. By loosening the first bolt, the position of the first upper seat body relative to the first lower seat body can be adjusted, so as to facilitate the adjustment of the position of the slide seat, so as to be suitable for positioning without passing through the aircraft pipeline. When the first bolt acts on the first lower seat body, the first upper seat body can be prevented from moving at will; by providing the first limit block, the moving stroke of the first upper seat body can be limited, and at the same time, the first upper seat body can be prevented from being separated from the first guide rail.

As shown in Figures 11 to 15, a second guide rail 221 is provided on the first upper seat body 212, and a second slider 222 fixed to the bottom of the slide seat 22 is slidably provided on the second guide rail 221. Under the guidance of the second guide rail and the second slider, the movement of the slide seat is more stable. The slide seat 22 is L-shaped. A slot 223 is provided on the side of the slide seat 22, and a third limit block 224 is clamped in the slot 223. A third bolt is installed between the slide seat 22 and the third limit block 224. By providing the slot, the third limit block can be positioned and limited. A second limit block 225 is provided on the first upper seat body 212, and the second limit block 225 acts on the third limit block 224. In this structure, when the slide is moving, the third limit block moves with it. When the third limit block contacts the second limit block, the movement of the slide is limited. Therefore, the movement stroke of the slide can be limited to avoid the slide moving too far and causing the positioning block to squeeze the aircraft connection pipe, which can effectively protect the aircraft connection pipe. The positioning block 23 is installed at the front end of the slide. The positioning block 23 includes a positioning seat 231 and a positioning column 232 arranged on the positioning seat. The positioning seat 231 is fixed at the front end of the slide. A guide surface 233 is arranged at the front end of the positioning column 232. In this way, the positioning column is easier to enter one end of the aircraft connection pipe. The first drive 24 is a first cylinder. The cylinder body of the first cylinder is fixed on the first upper seat body 212, and the piston rod of the first cylinder is connected to the slide 22. As shown in Figures 11 to 16, the second drive 25 includes a cylinder seat 251 and a second cylinder 252. The cylinder seat 251 includes a first articulated seat 2511 installed on the slide 22 and a second articulated seat 2512 installed on the first articulated seat 2511. The cylinder body of the second cylinder 252 is hinged on the first articulated seat 2511. The pressure block 26 includes a pressure block connecting arm 261, a pressure block fixing seat 262 and a pressure block body 263. A first connecting rod 26a is hinged between the piston rod of the second cylinder 252 and the second hinge seat 2512. One end of the pressure block connecting arm 261 is hinged on the second hinge seat 2512, and the other end of the pressure block connecting arm 261 is connected to the pressure block fixing seat 262. The pressure block body 263 is fixed at the bottom of the pressure block fixing seat 262. The bottom of the pressure block body is provided with an arc groove 2631. A second connecting rod 26b is hinged between the piston rod of the second cylinder and the middle part of the pressure block connecting arm. In this structure, the positioning column is inserted into one end of the aircraft connecting pipe to realize the centering of the aircraft connecting pipe. Through the step formed between the positioning seat and the positioning column, the aircraft connecting pipe can be axially limited. For the first cylinder, when the first cylinder is working, it can drive the sliding seat to slide, thereby driving the positioning block to move, and realize the positioning or positioning removal of the aircraft connecting pipe. Corresponding to the second cylinder, when the piston cylinder of the second cylinder moves forward, the second connecting rod drives the end of the pressure block connecting arm close to the pressure block body to swing downward, thereby driving the pressure block fixing seat to swing downward, and the pressure block positioning seat drives the pressure block body to swing downward, and cooperates with the aircraft connecting pipe through the arc groove, and uses the pressure block body to press the outer circumferential surface of one end of the aircraft connecting pipe. In cooperation with the clamping device in the middle of the aircraft pipe, the aircraft connecting pipe can be clamped and positioned up and down, so the positioning reliability is good. When the piston rod of the second cylinder moves in the opposite direction, the pressure block connecting arm, the pressure block fixing seat and the pressure block body are driven to swing upward under the action of the second connecting rod, so that it is easy to disassemble the aircraft connecting pipe.

As shown in Figures 3 to 8 and Figures 17 to 18, the aircraft pipe middle clamping device 3 includes a second seat body 31 and a clamping plate 32. The second seat body 31 includes a stand 311 and a U-shaped seat 312 arranged on one side of the upper end of the stand. The opening of the U-shaped seat 312 faces upward, and guide grooves 3121 are respectively arranged on both sides and the lower side of the U-shaped seat. A third waist-shaped groove 321 is arranged on the clamping plate 32, and the clamping plate 32 is slidably arranged in the guide groove 3121. The fourth bolt passes through the third waist-shaped groove and is connected to the U-shaped seat. By setting the U-shaped seat, it is convenient to set the sliding clamping plate on both sides and the bottom of the upper end of the second seat body. By setting the guide groove, the clamping plate has the function of positioning and motion guiding, so that the movement of the clamping plate is more precise; when the third waist-shaped groove is set, it is convenient to adjust the clamping plate by loosening and locking the fourth bolt. In order to position the second seat body 31, a second corner block 30 is arranged on the bearing plate.

As shown in Figures 3 to 8, the aircraft pipe box clamping device 4 includes a third seat body 41 and a pressure plate mechanism 42. The upper end of the third seat body 41 is provided with a positioning groove 411 that matches the bottom of the aircraft pipe box, and the front and rear ends of the third seat body are respectively provided with clamping blocks 412 that clamp to the end of the aircraft pipe box. The pressure plate mechanism 42 includes a support seat 421 arranged on the third seat body 41 and a pressure plate 422 hinged on the support seat, and a pressure plate driving mechanism 423 is arranged between the support seat and the pressure plate. The pressure plate 422 is hinged on the support seat 421 through a hinge shaft, and the pressure plate driving mechanism includes a pressure plate driving motor 4231, a worm wheel and a worm, the pressure plate driving motor is arranged on the support seat, the worm wheel is installed on the output shaft of the pressure plate driving motor, the worm is arranged on the hinge shaft, and the worm wheel is meshed with the worm. With this structure, when the driving motor is working, it drives the worm gear to rotate, and the worm gear drives the grip rod to rotate, thereby driving the pressure plate to swing. The worm gear structure is adopted and can produce a self-locking effect. Therefore, when the pressure plate is pressed onto the aircraft pipe box, the driving motor does not need to work to ensure that the pressure plate is reliably pressed onto the aircraft pipe box, thereby saving energy.

As shown in Fig. 4 to Fig. 8, a capillary tube support seat 51 is provided on the base at one side of the aircraft pipe box clamping device, and a limiting groove 52 is provided on the capillary tube support seat. The limiting groove can be used to position two capillary tubes on the aircraft pipe box. The capillary tube support seat 51 includes a capillary tube support seat body 511 and a limiting seat body 512 provided on the capillary tube support seat body. The capillary tube support seat body is installed on the base, and the limiting groove is provided on the limiting seat body.

In the above structure, the aircraft pipe box is first placed on the positioning groove, and the positioning groove is used to cooperate with the bottom and both sides of the aircraft pipe box, and the aircraft pipe box is supported by the third seat body. Then, the front and rear ends of the aircraft pipe box are positioned and clamped by the clamping blocks at both ends, and finally, the pressing plate is driven to swing by the pressing plate driving mechanism, and the pressing plate is used to press the top of the aircraft pipe box. In this way, the bottom, both sides, front and rear ends and top of the aircraft pipe box are completely positioned, thereby providing a basis for the connection positioning of the aircraft connecting pipes. After the aircraft pipe box is positioned, the other end of the aircraft connecting pipe is inserted into the connecting hole of the aircraft pipe box. At this time, the middle part of the aircraft connecting pipe is located in the space formed by the clamping plate, and then the first drive is started. The first drive drives the slide to move in the direction of the aircraft connecting pipe, so that the positioning block is inserted into one end of the aircraft connecting pipe. The aircraft connecting pipe is axially positioned by inserting the positioning block and the other end of the aircraft connecting pipe into the aircraft pipe box, and then the second drive is driven. The second drive drives the pressing block to press on the outer circumferential surface of one end of the aircraft connecting pipe, and then the clamping plate is moved to support and limit the middle part of the aircraft connecting pipe by the clamping plate. Therefore, in the utility model, the aircraft pipe box is first installed and positioned to provide a basis for the installation of the aircraft connecting pipe, and then the clamping plate is used to support the middle part of the aircraft connecting pipe to avoid the aircraft connecting pipe being in a completely cantilevered state, effectively avoiding the deformation of the aircraft connecting pipe in the welding structure, and at the same time, with the positioning block and the pressing block, the positioning accuracy of the aircraft pipe is high and the positioning reliability is good.

Claims (10)

1. A welding fixture for aircraft pipes, comprising a base, characterized in that: an aircraft pipe end clamping device, an aircraft pipe middle clamping device and an aircraft pipe box clamping device are sequentially arranged on the base from one end to the other end; the aircraft pipe end clamping device comprises a first base, a slide, a positioning block, a first drive, a second drive and a pressing block, the first base is arranged on the base, the slide is arranged on the first base to slide along the length direction of the base, the positioning block is arranged on one end surface of the slide, the first drive is arranged between the first base and the slide, the second drive is arranged at the upper end of the slide, and the pressing block is hinged at the output of the second drive An arc groove is provided on the pressing block between the shaft and the slide seat, and the pressing block is located above the positioning block; the aircraft pipeline middle clamping device includes a second seat body and a clamping plate, and movable clamping plates are respectively provided on both sides and the lower side of the upper end of the second seat body; the aircraft pipeline box clamping device includes a third seat body and a pressing plate mechanism, the upper end of the third seat body is provided with a positioning groove matched with the bottom of the aircraft pipeline box body, and clamping blocks clamped to the end of the aircraft pipeline box body are respectively provided at the front and rear ends of the third seat body, and the pressing plate mechanism includes a supporting seat provided on the third seat body and a pressing plate hinged on the supporting seat, and a pressing plate driving mechanism is provided between the supporting seat and the pressing plate. 2. The welding fixture for aircraft pipelines according to claim 1 is characterized in that: the first seat body includes a first lower seat body and a first upper seat body, a first guide rail is arranged on the first lower seat body, a first slider is arranged at the bottom of the first upper seat body, the first slider is slidably arranged on the first guide rail, a second slider is arranged on the first guide rail at one end of the first upper seat body, a connecting plate is arranged between the second slider and the first upper seat body, a first threaded hole is arranged on the second slider, a first bolt acting on the first lower seat body is installed in the first threaded hole, and first limit blocks are respectively arranged at both ends of the first lower seat body. 3. The welding fixture for aircraft pipes according to claim 2 is characterized in that: the first lower seat body includes a first support seat assembly and an adjustment seat, the first support seat assembly includes more than two groups of first support seats, a first waist-shaped groove is provided on the first support seat, and a second bolt passing through the second waist-shaped groove is provided on the adjustment seat. 4. The welding fixture for aircraft pipes according to claim 1 is characterized in that a second limit block is arranged on the first seat body, and a third limit block capable of acting with the second limit block is arranged on the slide seat. 5. The welding fixture for aircraft pipes according to claim 4 is characterized in that a slot is provided on the side of the slide seat, one end of the third limit block is inserted into the slot, and a third bolt is installed between the slide seat and the third limit block. 6. The welding fixture for aircraft pipelines according to claim 1 is characterized in that: the positioning block includes a positioning seat and a positioning column arranged on the positioning seat; the first drive is a first cylinder, the cylinder body of the first cylinder is fixed on the first seat body, and the piston rod of the first cylinder is connected to the sliding seat; the second drive includes a cylinder seat and a second cylinder, the cylinder seat is installed on the sliding seat, and the cylinder body of the second cylinder is hinged on the cylinder seat; the pressure block includes a pressure block connecting arm, a pressure block fixing seat and a pressure block body, a first connecting rod is hinged between the piston rod of the second cylinder and the cylinder seat, one end of the pressure block connecting arm is hinged on the cylinder seat, and the other end of the pressure block connecting arm is connected to the pressure block fixing seat, the pressure block body is fixed to the bottom of the pressure block fixing seat, an arc groove is arranged at the bottom of the pressure block body, and a second connecting rod is hinged between the piston rod of the second cylinder and the middle part of the pressure block connecting arm. 7. The welding fixture for aircraft pipes according to claim 1 is characterized in that: the second seat body includes a vertical seat and a U-shaped seat arranged on one side of the upper end of the vertical seat, the opening of the U-shaped seat faces upward, and guide grooves are respectively arranged on both sides and the lower side of the U-shaped seat, and a third waist-shaped groove is arranged on the clamping plate, and the clamping plate is slidably arranged in the guide groove, and the fourth bolt passes through the third waist-shaped groove and is connected to the U-shaped seat. 8. The welding fixture for aircraft pipelines according to claim 1 is characterized in that the pressure plate is hinged on the support seat through a hinge shaft, and the pressure plate driving mechanism includes a pressure plate driving motor, a worm gear and a worm, the pressure plate driving motor is arranged on the support seat, the worm gear is installed on the output shaft of the pressure plate driving motor, the worm gear is arranged on the hinge shaft, and the worm gear is meshed with the worm gear. 9. The welding fixture for aircraft pipelines according to claim 1 is characterized in that a capillary support seat is provided on the base at one side of the aircraft pipeline box clamping device, and a limiting groove is provided on the capillary support seat. 10. The welding fixture for aircraft pipelines according to claim 9 is characterized in that the capillary tube support seat includes a capillary tube support seat body and a limiting seat body arranged on the capillary tube support seat body, the capillary tube support seat body is installed on the base, and the limiting groove is arranged on the limiting seat body.