Aviation structural member welding seam detection device

Abstract

The invention relates to the technical field of welding seam detection, in particular to an aviation structural member welding seam detection device which comprises a base, a first motor is fixedly installed on the outer wall of one side of the base, the output end of the first motor is rotationally connected with a first screw rod, and a moving table is movably arranged above the base. A first screw rod is fixedly arranged in the base, a moving table is fixedly arranged in the base, a displacement plate is fixedly arranged on the lower surface of the moving table, the displacement plate is in threaded connection with the first screw rod, a first limiting rod is further fixedly arranged in the base, a limiting plate is fixedly arranged on the lower surface of the moving table, the first limiting rod penetrates through the limiting plate, and a support is further fixedly arranged on the upper surface of the base. According to the device, the irregular aviation structural part can be stably clamped, all-directional and multi-layer detection of a welding seam can be realized through cooperative work of the probes, meanwhile, dust on the surface of the aviation structural part can be removed by means of the dust removal module in the detection process, the detection precision is effectively improved, and the use effect is better.

Description

Technical Field

[0001] The present invention relates to the technical field of weld detection, and in particular 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. The quality of welds, as key parts, directly determines the overall performance and reliability of the structural parts. Since aviation structural parts are often subjected to extreme temperature, pressure, vibration and other complex working conditions, even tiny defects in the welds, such as cracks, pores, and lack of fusion, may cause catastrophic consequences during flight.

[0003] Traditional weld inspection methods, such as visual inspection, are difficult to accurately identify some subtle surface defects and internal hidden defects. Although ultrasonic inspection can detect internal defects, the operation is complicated and requires professionals to hold the probe for a long time to scan point by point, which is inefficient and prone to missed inspections due to human factors. The existing general inspection devices are difficult to adapt to the complex shape and high-precision inspection requirements of aviation structural parts, and cannot meet the urgent needs of the rapid development of the aviation industry for efficient and accurate weld inspection. At the same time, dust on the weld surface during the inspection process will also affect the inspection accuracy. Therefore, it is urgent to design an aviation structural weld inspection device to solve the above problems. Summary of the invention

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

[0005] In order to achieve the above object, the present invention adopts the following technical solutions: A weld detection device for aviation structural parts comprises a base, a first motor is fixedly installed on an outer wall of one side of the base, and the output end of the first motor is rotatably connected to a first screw rod, a moving platform is movably arranged above the base, a displacement plate is fixedly installed on the lower surface of the moving platform, and the displacement plate and the first screw rod 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 the outer wall of the bracket, a driving end of the second motor is rotatably connected to a second screw rod, and the second screw rod is rotatably arranged between the brackets, and the outer screw of the second screw rod is fixedly arranged on the outer surface of the second screw rod. A moving frame is connected with the thread, a second limit rod is fixedly installed between 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 the 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, and the moving frame is also fixedly provided with a third limit rod, and the third limit rod passes through the lifting block, a mounting platform is fixedly provided on the 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: A clamping module, which is disposed above the moving platform and is used to adaptively clamp and fix the irregular aviation structure above the moving platform; 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.

[0006] As a further solution of the present invention: 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 hydraulic cylinders are fixedly installed on the outer walls of the side panels, and support blocks are fixedly installed on the telescopic ends of the hydraulic cylinders. A supporting component is arranged in the clamping frame for supporting irregular aviation structures placed on the surface of the mobile platform. A moving component is also arranged in the mobile platform for driving the support block to move and adjust the position of the clamping frame.

[0007] As a further solution of the present invention: 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 provided at the bottom end of the supporting rod, ear seats are also fixedly provided at positions near both sides of the clamping frame, and a fixed shaft is fixedly provided in the ear seat, 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 the first clamping plate and the second clamping plate on one side close to the supporting rod, an electric telescopic rod is fixedly provided 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.

[0008] 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 support block, and the top of the column is inserted into the slot, side guards are also fixedly installed 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 guard.

[0009] As a further solution of the present invention: a groove is further provided on the upper surface of the ring plate, and a pressure sensor is fixedly installed in the groove, and the pressure sensor is located below the side baffle.

[0010] As a further solution of the present invention: the positioning module includes a fixing frame fixedly arranged on the upper surface of the mounting table, 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 at equal distances, and the gears and the tooth grooves are meshed.

[0011] As a further solution of the present invention: the dust removal module includes an air duct that passes through and is fixed in the mounting platform, the top end of the air duct is connected to a hair dryer, and the bottom end 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.

[0012] Compared with the prior art, the present invention has the following beneficial effects: The present invention provides an aviation structural component weld inspection device. The aviation structural component whose weld needs to be inspected can be placed on the surface of a moving platform, and the irregular aviation structural component can be stably fixed above the moving platform through a clamping module. The first motor drives the first screw to rotate, so that the moving platform can move left and right above the base. The second motor drives the second screw to rotate, so that the moving frame can move back and forth between the brackets. The third motor drives the third screw to rotate, so that the lifting block can move up and down in the moving frame, so that the disk under the mounting platform can have accurate movement capabilities in three directions of X-axis, Y-axis and Z-axis relative to the aviation structural component above the moving platform, so that the laser vision probe under the disk can scan along the weld path on the surface of the aviation structural component. The laser vision probe obtains three-dimensional contour information of the weld by projecting structured laser, and real-time Reconstruct the appearance of the weld, accurately locate the weld position, and intuitively image the surface defects. After the laser vision probe finishes scanning the weld, the positioning module can also drive the disc to rotate, so that the positions of the laser vision probe and the ultrasonic probe are exchanged. At this time, the ultrasonic probe can quickly move in the opposite direction along the movement path recorded when the laser vision probe moved before. There is no need to re-scan the aviation structure, which can effectively shorten the detection efficiency. The ultrasonic probe adopts high-frequency focusing technology and can emit high-resolution ultrasonic beams to penetrate the weld to detect internal defects. It has extremely high sensitivity to defects such as tiny cracks. Through the collaborative work between the probes, all-round and multi-level detection of the weld can be achieved. In the detection process, the dust on the surface of the aviation structure can be removed with the help of the dust removal module, which effectively improves the detection accuracy and achieves better results. BRIEF DESCRIPTION OF THE DRAWINGS

[0013] Figure 1 A schematic diagram of the structure of a first-viewing angle of view of a weld detection device for an aviation structural component provided by an embodiment of the present invention; Figure 2 A schematic diagram of the structure from a second viewing angle of a device for detecting welds of aviation structural parts provided by an embodiment of the present invention; Figure 3 A schematic structural diagram of a base in a weld detection device for an aviation structural component provided by an embodiment of the present invention; Figure 4 A schematic diagram of the internal structure of a moving platform in an aviation structural weld inspection device provided by an embodiment of the present invention; Figure 5 A schematic diagram of the structure of an electric slide rail in a weld detection device for an aviation structural part provided by an embodiment of the present invention; Figure 6 A schematic diagram of a half-section structure of a clamping frame in a weld detection device for an aviation structural part provided by an embodiment of the present invention; Figure 7A schematic diagram of the internal structure of a clamping frame in a weld detection device for an aviation structural part provided by an embodiment of the present invention; Figure 8 A schematic diagram of the structure from a first perspective of a mounting platform in a weld detection device for an aviation structural component provided by an embodiment of the present invention; Fig. 9 A schematic structural diagram of a second viewing angle of a mounting platform in an aviation structural component weld inspection device provided by an embodiment of the present invention; Fig.10 A schematic diagram of a half-section structure of a mounting platform in a weld detection device for an aviation structural component provided by an embodiment of the present invention; Fig.11 A schematic diagram of the structure from a third viewing angle of a device for detecting welds of aviation structural parts provided in an embodiment of the present invention.

[0014] In the figure: 101-base, 102-first motor, 103-first screw, 104-moving platform, 105-displacement plate, 106-first limit rod, 107-limit plate, 108-bracket, 109-second motor, 110-second screw, 111-second limit rod, 112-moving frame, 113-third motor, 114-third screw, 115-third limit rod, 116-lifting block, 117-mounting platform, 118-rotating drum, 119-disc, 120-laser vision probe, 121-ultrasonic probe, 201-clamping frame, 202-side plate, 203-liquid Pressure cylinder, 204-support block, 301-retaining rod, 302-fixed sheet, 303-spring, 304-rubber block, 305-ear seat, 306-fixed shaft, 307-first clamping plate, 308-second clamping plate, 309-rubber sheet, 310-electric telescopic rod, 401-electric slide rail, 402-electric slide block, 403-column, 404-ring plate, 405-side stop, 501-pressure sensor, 601-fixed frame, 602-stepping motor, 603-gear, 604-tooth groove, 701-air duct, 702-hair dryer, 703-air vent, 704-wind hood. DETAILED DESCRIPTION

[0015] In order to make the purpose, technical solutions and advantages of the present invention more clearly understood, the present invention is further described in detail below in conjunction with the accompanying drawings and embodiments.

[0016] like Figure 1-Figure 11As shown, an aviation structural weld inspection device 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 the output end of the first motor 102 is rotatably connected to a first screw 103, a moving platform 104 is movably arranged above the base 101, a displacement plate 105 is fixedly installed on the lower surface of the moving platform 104, and the displacement plate 105 and the first screw 103 are threadedly connected, and a first limit rod 106 is also fixedly arranged in the base 101, and a limit rod 106 is fixedly installed on the lower surface of the moving platform 104. The first limiting rod 106 penetrates the limiting plate 107, a bracket 108 is fixedly arranged on the upper surface of the base 101, and a second motor 109 is fixedly installed on the outer wall of the bracket 108, a second screw 110 is rotatably connected to the driving end of the second motor 109, and the second screw 110 is rotatably arranged between the brackets 108, and the outer side of the second screw 110 is threadedly connected to a moving frame 112, a second limiting rod 111 is fixedly installed between adjacent brackets 108, and the second limiting rod 111 penetrates the moving frame 112, and the upper surface of the moving frame 112 is fixedly installed A third motor 113 is provided, and a driving end of the third motor 113 is rotatably connected to a third screw rod 114, and the third screw rod 114 is rotatably arranged in the moving frame 112, and the outer side of the third screw rod 114 is threadedly connected to a lifting block 116, and a third limiting rod 115 is also fixedly arranged in the moving frame 112, and the third limiting rod 115 penetrates the lifting block 116, and a mounting platform 117 is fixedly arranged on an outer wall of one side of the lifting block 116, and a mounting hole is opened on the outer wall of the mounting platform 117, and a rotating drum 118 is rotatably connected in the mounting hole, and a disc is fixedly installed on the lower surface of the rotating drum 118 119, a laser vision probe 120 and an ultrasonic probe 121 are symmetrically mounted on the lower surface of the disk 119, and further comprises: a clamping module, the clamping module is arranged above the moving platform 104, and is used to adaptively clamp and fix irregular aviation structural parts above the moving platform 104; a positioning module, the positioning module is arranged above the mounting platform 117, and is used to rotate the disk 119 to exchange the positions of the laser vision probe and the ultrasonic probe 121; and a dust removal module, the dust removal module is arranged in the mounting platform 117, and is used to blow away the dust on the surface of the weld during the detection process.

[0017] The aviation structure parts whose welds need to be inspected can be placed on the surface of the moving platform 104, and the irregular aviation structure parts can be stably fixed above the moving platform 104 through the clamping module. The first motor 102 drives the first screw 103 to rotate, so that the moving platform 104 can move left and right above the base 101. The second motor 109 drives the second screw 110 to rotate, so that the moving frame 112 can move forward and backward between the brackets 108. The third motor 113 drives the third screw 114 to rotate, so that the lifting block 116 can move up and down in the moving frame 112, so that the disk 119 under the mounting platform 117 can have the ability to move accurately in the three directions of X-axis, Y-axis and Z-axis relative to the aviation structure parts above the moving platform 104, so that the laser vision probe 120 under the disk 119 can scan along the weld path on the surface of the aviation structure parts. The laser vision probe 120 obtains the three-dimensional information of the weld by projecting structured laser. dimensional contour information, can reconstruct the appearance of the weld in real time, accurately locate the weld position, and intuitively image the surface defects. When the laser vision probe 120 completes scanning the weld, it can also drive the disk 119 to rotate through the 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 opposite direction along the moving path recorded when the laser vision probe 120 moved before. There is no need to re-scan the aviation structure, which can effectively shorten the detection efficiency. The ultrasonic probe 121 adopts high-frequency focusing technology and can emit high-resolution ultrasonic beams to penetrate the weld to detect internal defects. It has extremely high sensitivity to defects such as tiny cracks. Through the collaborative work between the probes, all-round and multi-level detection of the weld can be achieved. In the detection process, the dust on the surface of the aviation structure can also be removed with the help of the dust removal module, which effectively improves the detection accuracy and achieves better use effect.

[0018] As an embodiment of the present invention, please refer to Figure 3 , Figure 4 , Figure 5 and Figure 6The clamping module includes a clamping frame 201 movably arranged above the moving platform 104, and side panels 202 are fixedly installed on the outer walls of both sides of the clamping frame 201, and a hydraulic cylinder 203 is fixedly installed on the outer wall of the side panel 202, and a support block 204 is fixedly installed on the telescopic end of the hydraulic cylinder 203. A supporting component is arranged in the clamping frame 201 for supporting the irregular aviation structure placed on the surface of the moving platform 104. The moving platform 104 is also provided with a moving component for driving the support block 204 to move and adjust the position of the clamping frame 201. By driving the support block 204 to move by the moving component, the clamping frame 201 can be moved to a suitable position above the aviation structure, and then the clamping frame 201 can be driven to move downward by the contraction of the hydraulic cylinder 203, and the aviation structure is fixed and limited by the supporting component in the clamping frame 201, so that the use effect is better.

[0019] As an embodiment of the present invention, please refer to Figure 4 , Figure 5 , Figure 6 and Figure 7The holding assembly includes a holding rod 301 that passes through the clamping frame 201 at equal distances, a fixing plate 302 is fixedly installed on the top of the holding rod 301, a spring 303 is fixedly installed on the lower surface of the fixing plate 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 installed at the bottom end of the holding rod 301, and an ear seat 305 is fixedly installed near the two sides of the clamping frame 201, and a fixed shaft 306 is fixedly installed in the ear seat 305, and the fixed shaft 306 The first clamping plate 307 and the second clamping plate 308 are slidably sleeved on the outside, and the outer walls of the first clamping plate 307 and the second clamping plate 308 close to the push rod 301 are fixedly installed with a rubber sheet 309. The outer wall of the second clamping plate 308 is fixedly provided with an electric telescopic rod 310, 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 of the push rod 301 will first contact with the outer wall of the aviation structure. The surface of the aerospace structure is in contact with the support rod 301, and as the clamping frame 201 moves further downward, the support rod 301 moves in the clamping frame 201, so that the spring 303 between the fixing plate 302 and the clamping frame 201 is stretched, until all the support rods 301 are displaced, indicating that the rubber blocks 304 at the bottom of all the support rods 301 are effectively in contact with the surface of the aerospace structure. At this time, the electric telescopic rod 310 is contracted to make the first clamping plate 307 and the second clamping plate 308 quickly close together, and the rubber sheet 309 is By fitting with the support rod 301, the support rod 301 can be clamped and fixed between the first clamp plate 307 and the second clamp plate 308, ensuring that the support 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 support rod 301 and the aviation structure can be squeezed, thereby playing a role in stably clamping and fixing the aviation structure. This clamping method can achieve stable clamping of irregular aviation structures, and the use effect is better.

[0020] As an embodiment of the present invention, please refer to Figure 4 , Figure 5 and Figure 6The moving assembly includes an electric slide rail 401 fixedly arranged in the moving platform 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 opened on the lower surface of the support block 204, and the top of the column 403 is inserted into the slot, and side blocks 405 are also fixedly installed on the outer walls of both sides of the electric slide rail 401, and 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 block 405. By moving the electric slider 402 in the electric slide rail 401, the position of the column 403 can be changed, so that The support block 204 at the top of the column 403 moves together, so that the position of the clamping frame 201 can be adjusted. When the hydraulic cylinder 203 contracts, so that the support rod 301 abuts against the aviation structure, the support block 204 on the outside of the column 403 will move up together, and the ring plate 404 on the outside of the support block 204 is blocked by the side block 405, so that the support rod 301 can stably abut the aviation structure, which can effectively prevent the upward pulling force generated on the support block 204 during the abutting process from being transmitted to the electric slider 402, affecting the connection between the electric slider 402 and the electric slide rail 401, and achieving a better use effect.

[0021] As an embodiment of the present invention, please refer to Figure 6 A groove is also provided 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 block 405. When the ring plate 404 outside the support block 204 is blocked by the side block 405, the pressure sensor 501 between the ring plate 404 and the side block 405 will be squeezed, which plays a role in detecting the resisting 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 extending and retracting, so that the resisting rod 301 applies a suitable resisting force to the aviation structure, thereby avoiding damage to the aviation structure caused by excessive resisting force, and having a better use effect.

[0022] As an embodiment of the present invention, please refer to Figure 8 The positioning module includes a fixing frame 601 fixedly arranged on the upper surface of the mounting platform 117, and a stepping motor 602 is fixedly installed in the fixing frame 601, and a driving end of the stepping motor 602 is rotatably connected to a gear 603, and an outer wall of the rotating drum 118 is provided with tooth grooves 604 distributed in an annular shape at equal distances, and the gears 603 and the tooth grooves 604 are meshed with each other. When the positions of the laser vision probe 120 and the ultrasonic probe 121 need to be adjusted, the stepping motor 602 can drive the gear 603 to rotate, the gear 603 drives the rotating drum 118 to rotate, and the rotating drum 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, which is very convenient to use.

[0023] As an embodiment of the present invention, please refer to Figure 8 , Fig. 9 and Fig.10 The dust removal module includes an air duct 701 that passes through and is fixedly arranged in the mounting platform 117. The top of the air duct 701 is connected to a blower 702, and the bottom of the air duct 701 is in contact with the upper surface of the disc 119. The outer sides of the laser vision probe 120 and the ultrasonic probe 121 are both sleeved with an air condenser 704, and the air condenser 704 is fixedly arranged on the lower surface of the disc 119. The upper surface of the disc 119 is provided with air holes 703 that are equidistantly distributed in an annular shape, and the air holes 703 are connected to the air condenser 704. Before the test, the air duct 701 can be connected to the blowing equipment so that the clean air is introduced into the hair dryer 702 through the air duct 701, and then enters the wind hood 704 along the air holes 703 on the surface of the disk 119 and is blown out. When the airflow is blown out, it is just aimed at the bottom 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, the airflow blown out of the wind hood 704 has blown away the dust on the surface of the weld, which can effectively improve the detection accuracy and achieve better results.

[0024] When in use, the aviation structure parts whose welds need to be inspected can be placed on the surface of the moving platform 104, and the irregular aviation structure parts can be stably fixed above the moving platform 104 through the clamping module. The first motor 102 drives the first screw 103 to rotate, so that the moving platform 104 can move left and right above the base 101. The second motor 109 drives the second screw 110 to rotate, so that the moving frame 112 can move back and forth between the brackets 108. The third motor 113 drives the third screw 114 to rotate, so that the lifting block 116 can move up and down in the moving frame 112, so that the disk 119 under the mounting platform 117 can have the ability to accurately move in the three directions of X-axis, Y-axis and Z-axis relative to the aviation structure parts above the moving platform 104, so that the laser vision probe 120 under the disk 119 can scan along the weld path on the surface of the aviation structure parts. The laser vision probe 120 obtains the weld by projecting structured laser. The three-dimensional contour information of the weld can be used to reconstruct the appearance of the weld in real time, accurately locate the weld position, and intuitively image the surface defects. After the laser vision probe 120 has completed scanning the weld, the disk 119 can be driven to rotate through the positioning 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 opposite direction along the moving path recorded when the laser vision probe 120 moved before. There is no need to re-scan the aviation structure, which can effectively shorten the detection efficiency. The ultrasonic probe 121 adopts high-frequency focusing technology and can emit high-resolution ultrasonic beams to penetrate the weld to detect internal defects. It has extremely high sensitivity to defects such as tiny cracks. Through the collaborative work between the probes, all-round and multi-level detection of the weld can be achieved. In the detection process, the dust on the surface of the aviation structure can be removed with the help of the dust removal module, which effectively improves the detection accuracy and achieves better results.

[0025] It should be particularly noted that although this specification is described in terms of implementation methods, not every implementation method contains only one independent technical solution. This narrative method of the specification is only for the sake of clarity. Those skilled in the art should regard the specification as a whole. The technical solutions in each embodiment may also be appropriately combined to form other implementation methods 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: A clamping module, which is disposed above the moving platform and is used to adaptively clamp and fix the irregular aviation structure above the moving platform; 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 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, and a support block is fixedly installed on the telescopic end of the hydraulic cylinder. A supporting component is arranged in the clamping frame for supporting an irregular aviation structure placed on the surface of the mobile platform. A moving component is also arranged in the mobile platform for driving the support block to move and adjust the position of the clamping frame.

3. The device for detecting weld seams of aviation structural parts according to claim 2, characterized in that: 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 provided at the bottom end of the supporting rod, ear seats are also fixedly provided at positions near both sides of the clamping frame, and a fixed shaft is fixedly provided in the ear seat, a first clamping plate and a second clamping plate are slidably sleeved on the outer side of the fixed shaft, and rubber sheets are fixedly installed on the outer walls of the first clamping plate and the second clamping plate on one side close to the supporting rod, an electric telescopic rod is fixedly provided 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.

4. The device for detecting weld seams of aviation structural parts according to claim 3, characterized in that: 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 support block, and the top 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, and a ring plate is fixedly arranged on the outer wall of the support block, and the ring plate is located in the side block.

5. The device for detecting weld seams of aviation structural parts according to claim 4, 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.

6. 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.

7. The device for detecting weld seams of aviation structural parts according to claim 6, 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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