An aircraft structural component weld detection device

Abstract

The present invention relates to the technical field of weld detection, and particularly to a weld detection device for aviation structural parts, including a base. A first motor is fixedly installed on an outer wall of one side of the base, and an output end of the first motor is rotationally connected to a first screw rod. A moving table is movably arranged above the base. A displacement plate is fixedly installed on a lower surface of the moving table, and the displacement plate is in threaded connection with the first screw rod. A first limiting rod is also fixedly arranged in the base. A limiting plate is fixedly installed on the lower surface of the moving table, and the first limiting rod penetrates through the limiting plate. A bracket is also fixedly arranged on an upper surface of the base. The present invention can achieve stable clamping of irregular aviation structural parts, and through the collaborative work between the probes, it can achieve all-round and multi-level detection of the welds. At the same time, during the detection process, the dust on the surface of the aviation structural parts can be removed by means of the dust removal module, effectively improving the detection accuracy and having a better use effect.

Description

Technical Field

[0001] The present invention relates to the technical field of weld detection, and particularly to a weld detection device for aviation structural parts. Background Art

[0002] In the aviation field, the quality of aviation structural parts is closely related to flight safety. Many aviation structural parts are connected by welding processes. As a key part, the quality of the weld directly determines the overall performance and reliability of the structural part. Since aviation structural parts often withstand extreme temperature, pressure, vibration and other complex working conditions, even tiny defects in the weld, such as cracks, pores, lack of fusion, etc., may cause catastrophic consequences during flight.

[0003] Traditional weld detection methods, such as visual inspection, are difficult to accurately identify some surface micro-defects and internal hidden defects; although ultrasonic inspection can detect internal defects, the operation is complex, requiring professional personnel to hold the probe and scan point by point for a long time, with low efficiency, and it is easy to cause missed detection due to human factors. Moreover, existing general detection devices are difficult to adapt to the complex shapes of aviation structural parts and the high-precision detection requirements, and cannot meet the urgent needs of the rapid development of the aviation industry for efficient and accurate weld detection. At the same time, the dust on the weld surface during the detection process will also affect the detection accuracy. Therefore, it is urgent to design a weld detection device for aviation structural parts to solve the above problems. Summary of the Invention

[0004] The purpose of the present invention is to solve the defects existing in the prior art, and to propose a weld detection device for aviation structural parts.

[0005] In order to achieve the above purpose, the present invention adopts the following technical solutions:

[0006] An aircraft structural component weld detection device includes a base. A first motor is fixedly installed on an outer wall of one side of the base, and an output end of the first motor is rotationally connected to a first screw rod. A moving table is movably arranged above the base. A displacement plate is fixedly installed on a lower surface of the moving table, and the displacement plate is in threaded connection with the first screw rod. A first limiting rod is also fixedly arranged in the base. A limiting plate is fixedly installed on the lower surface of the moving table, and the first limiting rod penetrates through the limiting plate. A support is also fixedly arranged on an upper surface of the base, and a second motor is fixedly installed on an outer wall of the support. A driving end of the second motor is rotationally connected to a second screw rod, and the second screw rod is rotatably arranged between the supports. A moving frame is in threaded connection with an outer side of the second screw rod. A second limiting rod is fixedly installed between adjacent supports, and the second limiting rod penetrates through the moving frame. A third motor is fixedly installed on an upper surface of the moving frame, and a driving end of the third motor is rotationally connected to a third screw rod, and the third screw rod is rotatably arranged in the moving frame. An elevating block is in threaded connection with an outer side of the third screw rod. A third limiting rod is also fixedly arranged in the moving frame, and the third limiting rod penetrates through the elevating block. An installation table is fixedly arranged on an outer wall of one side of the elevating block. An installation hole is formed in an outer wall of the installation table, and a rotating cylinder is rotatably connected in the installation hole. A disc is fixedly installed on a lower surface of the rotating cylinder. A laser vision probe and an ultrasonic probe are symmetrically installed on a lower surface of the disc. It further includes:

[0007] A clamping module, which is arranged above the moving table and is used for adaptively clamping and fixing an irregular aircraft structural component above the moving table;

[0008] An adjustment module, which is arranged above the installation table and is used for rotating the disc to swap the positions of the laser vision probe and the ultrasonic probe;

[0009] A dust removal module, which is arranged in the installation table and is used for blowing off the dust on the surface of the weld first during the detection process.

[0010] As a further scheme of the present invention: The clamping module includes a clamping frame movably arranged above the moving table. Side plates are fixedly installed on outer walls of both sides of the clamping frame, and a hydraulic cylinder is fixedly installed through an outer wall of the side plate. A supporting block is fixedly installed at a telescopic end of the hydraulic cylinder. A resisting component is arranged in the clamping frame and is used for resisting an irregular aircraft structural component placed on the surface of the moving table. A moving component is also arranged in the moving table and is used for driving the supporting block to move to adjust the position of the clamping frame.

[0011] As a further solution of the present invention: The abutting component includes abutting rods that penetrate through the clamping frame at equal distances. A fixing piece is fixedly installed at the top end of the abutting rod. A spring is fixedly installed on the lower surface of the fixing piece, and the end of the spring is fixedly connected to the upper surface of the clamping frame. A rubber block is fixedly arranged at the bottom end of the abutting rod. Ear seats are also fixedly arranged at positions near both sides inside the clamping frame, and a fixing shaft is fixedly arranged in the ear seats. The first clamping plate and the second clamping plate are slidably sleeved on the outer side of the fixing shaft, and rubber sheets are fixedly installed on the outer walls of the first clamping plate and the second clamping plate close to the abutting rod. An electric telescopic rod is fixedly arranged through the outer wall of the second clamping plate, and the telescopic end of the electric telescopic rod is fixedly connected to the outer wall of the first clamping plate.

[0012] As a further solution of the present invention: The moving component includes an electric slide rail fixedly arranged in the moving platform. An electric slider is slidably arranged in the electric slide rail. A column is fixedly installed on the upper surface of the electric slider. A slot is opened on the lower surface of the supporting block, and the top end of the column is inserted into the slot. Side blocks are also fixedly installed on the outer walls of both sides of the electric slide rail. A ring plate is fixedly arranged on the outer wall of the supporting block, and the ring plate is located in the side blocks.

[0013] As a further solution of the present invention: A groove is also opened on the upper surface of the ring plate, and a pressure sensor is fixedly installed in the groove. The pressure sensor is located below the side block.

[0014] As a further solution of the present invention: The position adjustment module includes a fixing frame fixedly arranged on the upper surface of the installation table. A stepping motor is fixedly installed in the fixing frame. The driving end of the stepping motor is rotationally connected to a gear. Tooth grooves are opened on the outer wall of the rotating cylinder at equal distances and distributed in a ring shape, and the gear meshes with the tooth grooves.

[0015] As a further solution of the present invention: The ash removal module includes a guide air duct fixedly arranged through the installation table. The top end of the guide air duct is communicated with a blowing cylinder, and the bottom end of the guide air duct is attached to the upper surface of the disc. Air gathering covers are sleeved on the outer sides of the laser vision probe and the ultrasonic probe, and the air gathering covers are fixedly arranged on the lower surface of the disc. Ventilation holes are opened on the upper surface of the disc at equal distances and distributed in a ring shape, and the ventilation holes are communicated with the air gathering covers.

[0016] Compared with the prior art, the beneficial effects of the present invention are:

[0017] An aviation structural component weld detection device provided by the present invention enables an aviation structural component whose weld needs to be detected to be placed on the surface of a moving platform. An irregular aviation structural component can be stably fixed above the moving platform through a clamping module. By means of a first motor driving a first screw rod to rotate, the moving platform can move left and right above the base. By means of a second motor driving a second screw rod to rotate, the moving frame can move back and forth between the brackets. By means of a third motor driving a third screw rod to rotate, the lifting block can move up and down in the moving frame. As a result, the disc below the installation platform can have the precise moving ability in three directions of the X-axis, Y-axis, and Z-axis relative to the aviation structural component above the moving platform, enabling the laser vision probe below the disc to scan along the weld path on the surface of the aviation structural component. The laser vision probe projects structured laser light to obtain the three-dimensional contour information of the weld, reconstruct the appearance of the weld in real time, accurately locate the weld position, and at the same time can directly image surface defects. After the laser vision probe finishes scanning the weld, the disc can also be driven to rotate through an adjustment module, causing the positions of the laser vision probe and the ultrasonic probe to be exchanged. At this time, the ultrasonic probe can quickly move in the reverse direction along the moving path recorded when the laser vision probe moved before, without having to rescan the aviation structural component again, which can effectively shorten the detection efficiency. The ultrasonic probe uses high-frequency focusing technology and can emit high-resolution ultrasonic beams to penetrate the weld and detect internal defects, and has extremely high sensitivity to defects such as micro-cracks. Through the collaborative work of the probes, comprehensive and multi-level detection of the weld can be achieved. Moreover, during the detection process, the dust on the surface of the aviation structural component can be removed by means of an ash removal module, effectively improving the detection accuracy and having a better use effect. BRIEF DESCRIPTION OF THE DRAWINGS

[0018] Figure 1 is a schematic diagram of the first perspective structure of an aviation structural component weld detection device provided by an embodiment of the present invention;

[0019] Figure 2 is a schematic diagram of the second perspective structure of an aviation structural component weld detection device provided by an embodiment of the present invention;

[0020] Figure 3 is a schematic diagram of the structure of the base in an aviation structural component weld detection device provided by an embodiment of the present invention;

[0021] Figure 4 is a schematic diagram of the internal structure of the moving platform in an aviation structural component weld detection device provided by an embodiment of the present invention;

[0022] Figure 5 is a schematic diagram of the structure of the electric slide rail in an aviation structural component weld detection device provided by an embodiment of the present invention;

[0023] Figure 6Schematic diagram of the half-sectional structure of the clamping frame in a weld detection device for an aviation structural member provided by an embodiment of the present invention;

[0024] Figure 7 Internal structure schematic diagram of the clamping frame in a weld detection device for an aviation structural member provided by an embodiment of the present invention;

[0025] Figure 8 First perspective structure schematic diagram of the mounting table in a weld detection device for an aviation structural member provided by an embodiment of the present invention;

[0026] Figure 9 Second perspective structure schematic diagram of the mounting table in a weld detection device for an aviation structural member provided by an embodiment of the present invention;

[0027] Figure 10 Schematic diagram of the half-sectional structure of the mounting table in a weld detection device for an aviation structural member provided by an embodiment of the present invention;

[0028] Figure 11 Third perspective structure schematic diagram of a weld detection device for an aviation structural member provided by an embodiment of the present invention.

[0029] In the figure: 101 - base, 102 - first motor, 103 - first screw rod, 104 - moving table, 105 - displacement plate, 106 - first limiting rod, 107 - limiting plate, 108 - bracket, 109 - second motor, 110 - second screw rod, 111 - second limiting rod, 112 - moving frame, 113 - third motor, 114 - third screw rod, 115 - third limiting rod, 116 - lifting block, 117 - mounting table, 118 - rotating cylinder, 119 - disc, 120 - laser vision probe, 121 - ultrasonic probe, 201 - clamping frame, 202 - side plate, 203 - hydraulic cylinder, 204 - supporting block, 301 - abutting rod, 302 - fixing piece, 303 - spring, 304 - rubber block, 305 - ear seat, 306 - fixing shaft, 307 - first clamping plate, 308 - second clamping plate, 309 - rubber sheet, 310 - electric telescopic rod, 401 - electric slide rail, 402 - electric slider, 403 - column, 404 - ring plate, 405 - side baffle, 501 - pressure sensor, 601 - fixing frame, 602 - stepping motor, 603 - gear, 604 - tooth groove, 701 - air duct, 702 - air blowing cylinder, 703 - ventilation hole, 704 - air gathering hood. Detailed implementation manners

[0030] In order to make the objectives, technical solutions and advantages of the present invention clearer and more understandable, the present invention will be further described in detail below with reference to the accompanying drawings and embodiments.

[0031] As Figures 1-11As shown in the figure, a weld detection device for an aviation structural member provided by an embodiment of the present invention includes a base 101. A first motor 102 is fixedly installed on an outer wall of one side of the base 101, and a first screw rod 103 is rotatably connected to an output end of the first motor 102. A moving table 104 is movably arranged above the base 101. A displacement plate 105 is fixedly installed on a lower surface of the moving table 104, and the displacement plate 105 is in threaded connection with the first screw rod 103. A first limiting rod 106 is also fixedly arranged in the base 101. A limiting plate 107 is fixedly installed on a lower surface of the moving table 104, and the first limiting rod 106 passes through the limiting plate 107. A bracket 108 is also fixedly arranged on an upper surface of the base 101, and a second motor 109 is fixedly installed on an outer wall of the bracket 108. A second screw rod 110 is rotatably connected to a driving end of the second motor 109, and the second screw rod 110 is rotatably arranged between the brackets 108. A moving frame 112 is in threaded connection with an outer side of the second screw rod 110. A second limiting rod 111 is fixedly installed between adjacent brackets 108, and the second limiting rod 111 passes through the moving frame 112. A third motor 113 is fixedly installed on an upper surface of the moving frame 112, and a third screw rod 114 is rotatably connected to a driving end of the third motor 113, and the third screw rod 114 is rotatably arranged in the moving frame 112. An elevating block 116 is in threaded connection with an outer side of the third screw rod 114. A third limiting rod 115 is also fixedly arranged in the moving frame 112, and the third limiting rod 115 passes through the elevating block 116. An installation table 117 is fixedly arranged on an outer wall of one side of the elevating block 116. An installation hole is formed in an outer wall of the installation table 117, and a rotating cylinder 118 is rotatably connected in the installation hole. A disc 119 is fixedly installed on a lower surface of the rotating cylinder 118. A laser vision probe 120 and an ultrasonic probe 121 are symmetrically installed on a lower surface of the disc 119. The device further includes: a clamping module, which is arranged above the moving table 104 and is used for adaptively clamping and fixing an irregular aviation structural member above the moving table 104; an adjusting module, which is arranged above the installation table 117 and is used for rotating the disc 119 to exchange the positions of the laser vision probe and the ultrasonic probe 121; and a dust removing module, which is arranged in the installation table 117 and is used for blowing away the dust on the surface of the weld during the detection process.

[0032] The aviation structural parts whose welds need to be detected can be placed on the surface of the mobile platform 104, and the irregular aviation structural parts can be stably fixed above the mobile platform 104 through the clamping module. By driving the first screw rod 103 to rotate with the first motor 102, the mobile platform 104 can move left and right above the base 101. By driving the second screw rod 110 to rotate with the second motor 109, the mobile frame 112 can move back and forth between the brackets 108. By driving the third screw rod 114 to rotate with the third motor 113, the lifting block 116 can move up and down in the mobile frame 112. Furthermore, the disc 119 below the mounting table 117 can have the precise moving ability in three directions of the X-axis, Y-axis, and Z-axis relative to the aviation structural parts above the mobile platform 104, so that the laser vision probe 120 below the disc 119 can scan along the weld path on the surface of the aviation structural parts. The laser vision probe 120 projects structured laser light to obtain the three-dimensional contour information of the weld, can reconstruct the appearance of the weld in real time, accurately locate the weld position, and at the same time can directly image the surface defects. When the laser vision probe 120 finishes scanning the weld, the disc 119 can also be driven to rotate through the position adjustment module, so that the positions of the laser vision probe 120 and the ultrasonic probe 121 are exchanged. At this time, the ultrasonic probe 121 can quickly move in the reverse direction along the moving path recorded when the laser vision probe 120 moved before, without having to rescan the aviation structural parts again, which can effectively shorten the detection efficiency. The ultrasonic probe 121 adopts high-frequency focusing technology, can emit high-resolution ultrasonic beams, penetrate the weld to detect internal defects, and has extremely high sensitivity to defects such as micro-cracks. Through the collaborative work of the probes, the all-round and multi-level detection of the weld can be realized. And during the detection process, the dust on the surface of the aviation structural parts can also be removed by means of the dust removal module, effectively improving the detection accuracy and having better use effect.

[0033] As an embodiment of the present invention, please refer to Figure 3 , Figure 4 , Figure 5 and Figure 6, the clamping module includes a clamping frame 201 movably arranged above the moving platform 104. Side plates 202 are fixedly installed on both outer walls of the clamping frame 201, and hydraulic cylinders 203 are fixedly arranged through the outer walls of the side plates 202. A supporting block 204 is fixedly installed at the telescopic end of the hydraulic cylinder 203. A resisting assembly is arranged in the clamping frame 201 for resisting an irregular aviation structural member placed on the surface of the moving platform 104. A moving assembly is further arranged in the moving platform 104 for driving the supporting block 204 to move to adjust the position of the clamping frame 201. By driving the supporting block 204 to move through the moving assembly, the clamping frame 201 can be moved to a suitable position above the aviation structural member, and then the clamping frame 201 can be driven to move downward by the contraction of the hydraulic cylinder 203, and the aviation structural member can be fixedly limited by the resisting assembly in the clamping frame 201, with better use effects.

[0034] As an embodiment of the present invention, please refer to Figure 4 , Figure 5 , Figure 6 and Figure 7, the abutting component includes an abutting rod 301 that penetrates the clamping frame 201 at equal intervals. A fixing piece 302 is fixedly installed at the top end of the abutting rod 301. A spring 303 is fixedly installed on the lower surface of the fixing piece 302, and the end of the spring 303 is fixedly connected to the upper surface of the clamping frame 201. A rubber block 304 is fixedly arranged at the bottom end of the abutting rod 301. At positions near both sides inside the clamping frame 201, there are also fixedly arranged ear seats 305, and a fixing shaft 306 is fixedly arranged in the ear seats 305. A first clamping plate 307 and a second clamping plate 308 are slidably sleeved on the outer side of the fixing shaft 306. Rubber sheets 309 are fixedly installed on the outer walls of the first clamping plate 307 and the second clamping plate 308 on the side close to the abutting rod 301. An electric telescopic rod 310 is fixedly arranged through the outer wall of the second clamping plate 308, and the telescopic end of the electric telescopic rod 310 is fixedly connected to the outer wall of the first clamping plate 307. When the hydraulic cylinder 203 drives the clamping frame 201 to move downward, the rubber block 304 at the bottom end of the abutting rod 301 will first contact the surface of the aviation structural member. And as the clamping frame 201 moves further downward, the abutting rod 301 will move in the clamping frame 201, causing the spring 303 between the fixing piece 302 and the clamping frame 201 to be stretched. When all the abutting rods 301 have displaced, it indicates that the rubber blocks 304 at the bottom ends of all the abutting rods 301 are effectively attached to the surface of the aviation structural member. At this time, by contracting the electric telescopic rod 310, the first clamping plate 307 and the second clamping plate 308 are quickly brought closer together, and the rubber sheet 309 is attached to the abutting rod 301, so that the abutting rod 301 can be clamped and fixed between the first clamping plate 307 and the second clamping plate 308, ensuring that the abutting rod 301 and the clamping frame 201 can no longer move relative to each other. At this time, as the clamping frame 201 moves further downward, the rubber block 304 between the abutting rod 301 and the aviation structural member can be squeezed, thereby playing a role in stably clamping and fixing the aviation structural member. This clamping method can achieve stable clamping of irregular aviation structural members, and the use effect is better.

[0035] As an embodiment of the present invention, please refer to Figure 4 , Figure 5 and Figure 6, the moving component includes an electric slide rail 401 fixedly arranged in the mobile station 104. An electric slider 402 is slidably arranged in the electric slide rail 401. A column 403 is fixedly installed on the upper surface of the electric slider 402. A slot is formed on the lower surface of the support block 204, and the top end of the column 403 is inserted into the slot. Side blocks 405 are also fixedly installed on the outer walls on both sides of the electric slide rail 401. A ring plate 404 is fixedly arranged on the outer wall of the support block 204, and the ring plate 404 is located in the side blocks 405. By moving the electric slider 402 in the electric slide rail 401, the position of the column 403 can be changed, and thus the support block 204 at the top end of the column 403 can be moved together, so that the position adjustment of the clamping frame 201 can be realized. When the hydraulic cylinder 203 contracts and the abutting rod 301 abuts against the aviation structural member, the support block 204 outside the column 403 will move upward accordingly, and the ring plate 404 outside the support block 204 is blocked by the side blocks 405, so that the abutting rod 301 can stably abut against the aviation structural member, effectively avoiding the upward pulling force generated on the support block 204 during the abutting process from being transmitted to the electric slider 402 and affecting the connection between the electric slider 402 and the electric slide rail 401, and the use effect is better.

[0036] As an embodiment of the present invention, please refer to Figure 6 , a groove is also formed on the upper surface of the ring plate 404, and a pressure sensor 501 is fixedly installed in the groove. The pressure sensor 501 is located below the side blocks 405. When the ring plate 404 outside the support block 204 is blocked by the side blocks 405, the pressure sensor 501 between the ring plate 404 and the side blocks 405 will also be squeezed, playing a role in detecting the abutting force. When the pressure value detected by the pressure sensor 501 reaches the set value, the hydraulic cylinder 203 can be immediately prompted to stop telescoping, so that the abutting rod 301 applies an appropriate abutting force to the aviation structural member, avoiding damage to the aviation structural member caused by excessive abutting force, and the use effect is better.

[0037] As an embodiment of the present invention, please refer to Figure 8 , the position adjustment module includes a fixed frame 601 fixedly arranged on the upper surface of the installation table 117. A stepping motor 602 is fixedly installed in the fixed frame 601. The driving end of the stepping motor 602 is rotationally connected with a gear 603. Tooth grooves 604 are formed on the outer wall of the rotating cylinder 118 at equal distances and distributed in a ring shape, and the gear 603 meshes with the tooth grooves 604. When the positions of the laser vision probe 120 and the ultrasonic probe 121 need to be adjusted, the stepping motor 602 can be driven to drive the gear 603 to rotate, the gear 603 drives the rotating cylinder 118 to rotate, and the rotating cylinder 118 drives the disc 119 to rotate, so that the position conversion between the laser vision probe 120 and the ultrasonic probe 121 can be realized, and the use is very convenient.

[0038] As an embodiment of the present invention, please refer to Figure 8 , Figure 9 andFigure 10 , the ash removal module includes an air guide pipe 701 fixedly arranged through the mounting table 117. The top end of the air guide pipe 701 is communicated with a blowing cylinder 702, and the bottom end of the air guide pipe 701 is attached to the upper surface of the disc 119. Air gathering hoods 704 are sleeved outside both the laser vision probe 120 and the ultrasonic probe 121, and the air gathering hoods 704 are fixedly arranged on the lower surface of the disc 119. The upper surface of the disc 119 is provided with ventilation holes 703 evenly distributed in an annular shape at equal intervals, and the ventilation holes 703 are communicated with the air gathering hoods 704. Before the scanning detection, the air guide pipe 701 can be connected to the air blowing equipment, so that clean air is introduced into the blowing cylinder 702 through the air guide pipe 701, and then enters the air gathering hoods 704 through the ventilation holes 703 on the surface of the disc 119 and is blown out. When the air flow is blown out, it just aims at the directly below of the laser vision probe 120 and the ultrasonic probe 121, so that when the laser vision probe 120 and the ultrasonic probe 121 scan the weld seam, the air flow blown out by the air gathering hoods 704 has blown away the dust on the surface of the weld seam, which can effectively improve the detection accuracy and has better use effect.

[0039] During use, the aerospace structural member whose weld needs to be detected can be placed on the surface of the moving platform 104, and the irregular aerospace structural member can be stably fixed above the moving platform 104 through the clamping module. By driving the first screw 103 to rotate with the first motor 102, the moving platform 104 can move left and right above the base 101. By driving the second screw 110 to rotate with the second motor 109, the moving frame 112 can move back and forth between the brackets 108. By driving the third screw 114 to rotate with the third motor 113, the lifting block 116 can move up and down in the moving frame 112. As a result, the disc 119 below the mounting table 117 can have the precise moving ability in three directions of the X-axis, Y-axis, and Z-axis relative to the aerospace structural member above the moving platform 104, enabling the laser vision probe 120 below the disc 119 to scan along the weld path on the surface of the aerospace structural member. The laser vision probe 120 projects structured laser light to obtain the three-dimensional contour information of the weld, reconstructs the appearance of the weld in real time, accurately locates the weld position, and can also directly image the surface defects. When the laser vision probe 120 finishes scanning the weld, the disc 119 can be driven to rotate through the position adjustment module, causing the positions of the laser vision probe 120 and the ultrasonic probe 121 to be exchanged. At this time, the ultrasonic probe 121 can quickly move in the reverse direction along the moving path recorded when the laser vision probe 120 moved before, without having to rescan the aerospace structural member again, which can effectively shorten the detection efficiency. The ultrasonic probe 121 uses high-frequency focusing technology and can emit high-resolution ultrasonic beams to penetrate the weld to detect internal defects, and has extremely high sensitivity to defects such as microcracks. Through the collaborative work of the probes, it is possible to achieve all-round and multi-level detection of the weld. Moreover, during the detection process, the dust on the surface of the aerospace structural member can be removed with the help of the dust removal module, effectively improving the detection accuracy and having a better use effect.

[0040] It should be particularly noted that although this specification is described according to the embodiments, not every embodiment only contains an independent technical solution. This narrative way of the specification is only for clarity. Those skilled in the art should regard the specification as a whole, and the technical solutions in each embodiment can also be appropriately combined to form other embodiments that can be understood by those skilled in the art.

Claims

1. An aviation structural weld inspection device, comprising a base, characterized in that: A first motor is fixedly installed on an outer wall of one side of the base, and a first screw is rotatably connected to an output end of the first motor, a moving platform is movably arranged above the base, a displacement plate is fixedly installed on a lower surface of the moving platform, and the displacement plate and the first screw are threadedly connected, a first limit rod is also fixedly arranged in the base, a limit plate is fixedly installed on the lower surface of the moving platform, and the first limit rod passes through the limit plate, a bracket is also fixedly arranged on the upper surface of the base, and a second motor is fixedly installed on an outer wall of the bracket, a second screw is rotatably connected to a driving end of the second motor, and the second screw is rotatably arranged between the brackets, and the outer side of the second screw is threadably connected to a moving frame, A second limit rod is fixedly installed between the adjacent brackets, and the second limit rod passes through the moving frame, a third motor is fixedly installed on the upper surface of the moving frame, and the driving end of the third motor is rotatably connected to a third screw, and the third screw is rotatably arranged in the moving frame, the outer side of the third screw is threadedly connected to a lifting block, a third limit rod is also fixedly arranged in the moving frame, and the third limit rod passes through the lifting block, a mounting platform is fixedly arranged on an outer wall of one side of the lifting block, a mounting hole is opened on the outer wall of the mounting platform, and a rotating drum is rotatably connected in the mounting hole, a disc is fixedly installed on the lower surface of the rotating drum, and a laser vision probe and an ultrasonic probe are symmetrically installed on the lower surface of the disc, and also include: The clamping module is arranged above the mobile platform and is used for adaptively clamping and fixing irregular aviation structures above the mobile platform. The clamping module includes a clamping frame movably arranged above the mobile platform. Side panels are fixedly installed on the outer walls of both sides of the clamping frame, and a hydraulic cylinder is fixedly installed on the outer wall of the side panel. A support block is fixedly installed on the telescopic end of the hydraulic cylinder. A supporting assembly is arranged in the clamping frame for supporting irregular aviation structures placed on the surface of the mobile platform. The mobile platform is also provided with a moving assembly for driving the support block to move and adjust the position of the clamping frame. The supporting assembly includes a supporting rod that passes through the clamping frame at equal distances. A fixing plate is fixedly installed on the top of the supporting rod. A spring is fixedly installed on the lower surface of the fixing plate, and the end of the spring is fixedly connected to the upper surface of the clamping frame. A rubber block is fixedly arranged at the bottom end of the supporting rod, and ear seats are also fixedly arranged at positions near both sides of the clamping frame, and a fixed shaft is fixedly arranged in the ear seat, and a first clamping plate and a second clamping plate are slidably sleeved on the outer side of the fixed shaft, and a rubber sheet is fixedly installed on the outer wall of one side of the first clamping plate and the second clamping plate close to the supporting rod, and an electric telescopic rod is fixedly arranged on the outer wall of the second clamping plate, and the telescopic end of the electric telescopic rod is fixedly connected to the outer wall of the first clamping plate, and the moving assembly includes an electric slide rail fixedly arranged in the moving platform, an electric slider is slidably arranged in the electric slide rail, a column is fixedly arranged on the upper surface of the electric slider, a slot is opened on the lower surface of the support block, and the top of the column is inserted into the slot, and side stops are also fixedly arranged on the outer walls of both sides of the electric slide rail, and a ring plate is fixedly arranged on the outer wall of the support block, and the ring plate is located in the side stop; A position adjustment module, which is arranged above the mounting platform and is used to rotate the disc to exchange the positions of the laser viewing angle probe and the ultrasonic probe; A dust removal module is arranged in the mounting platform and is used to blow away the dust on the surface of the weld during the detection process.

2. The device for detecting weld seams of aviation structural parts according to claim 1, characterized in that: The upper surface of the ring plate is also provided with a groove, and a pressure sensor is fixedly installed in the groove, and the pressure sensor is located below the side guard.

3. The device for detecting weld seams of aviation structural parts according to claim 1, characterized in that: The positioning module includes a fixing frame fixedly arranged on the upper surface of the mounting platform, and a stepping motor is fixedly installed in the fixing frame. The driving end of the stepping motor is rotatably connected to a gear. The outer wall of the rotating drum is provided with tooth grooves distributed in an annular shape with equal distances, and the gears and the tooth grooves are meshed.

4. The device for detecting weld seams of aviation structural parts according to claim 3, characterized in that: The dust removal module includes an air duct that passes through and is fixed in the mounting platform, the top of the air duct is connected to a hair dryer, and the bottom of the air duct is in contact with the upper surface of the disc, the outer sides of the laser vision probe and the ultrasonic probe are both sleeved with an air hood, and the air hood is fixed on the lower surface of the disc, the upper surface of the disc is provided with air holes that are equidistantly distributed in a ring shape, and the air holes are connected to the air hood.

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