An automatic detection device and method for internal wear of aircraft landing gear sleeve

Abstract

The invention discloses an automatic detection device and method for internal wear of an aircraft landing gear sleeve. When detecting the inner cavity of an aircraft landing gear sleeve-like part, the automatic detection of the inner cavity of the aircraft landing gear sleeve-like part is realized by the coordinated action of a linear motion module and a rotary motion module; the adaptive action of a probe detection device in a closed cavity is realized by an adaptive chuck, and various motion controls in the detection process can be realized by inputting digital quantities on an operating table; the entire device is fully controlled through the operating table, and the operation is simple, and the detection efficiency and detection coverage are high, which solves the problems of high labor intensity, low detection efficiency and low detection coverage brought about by the existing handheld probe detection method, and the device can be widely used in the detection of closed cavities of aircraft landing gear sleeve-like parts.

Description

Technical Field

[0001] The invention relates to the field of aircraft parts detection, in particular to an automatic detection device and a detection method for aircraft landing gear sleeve parts with the need to detect internal wear conditions. Background Art

[0002] In recent years, the domestic aviation sector has developed rapidly, with a large number of aircraft of various types put into production and delivered, and the frequency of aircraft use has also increased rapidly. In order to ensure flight safety, the easily worn parts of the landing gear need to be regularly tested for part wear using a probe detection device. However, most landing gear products are parts with cylindrical closed cavities, which are characterized by a small cavity diameter, a narrow and long closed passage, and the inability to manually visually inspect the wear area. Therefore, it is difficult to use a probe detection device to detect part wear.

[0003] At present, the wear detection of aircraft landing gear sleeve parts uses a handheld probe to perform reciprocating sliding detection in the inner cavity of the part. This method has many defects: high labor intensity and low detection efficiency: since the length of the measured parts is more than 1 meter, manual detection requires uninterrupted measurement work for several hours, which is very labor-intensive and inefficient for workers; low detection coverage: due to the reciprocating rotary motion of the handheld probe detection device, the probability of missed detection is very high, and if the detection is stopped halfway, it will be difficult to return to the position where the detection was paused. In the actual operation process, it can only rely on manual repeated detection to improve the coverage. Therefore, it is particularly important to realize the automatic detection of aircraft landing gear sleeve parts with internal wear. Summary of the invention

[0004] The purpose of the present invention is to provide an automatic detection device for the internal wear of an aircraft landing gear sleeve. During the product detection process, the device can use a linear motion module to support the product for linear feed motion, and use a rotary motion module to carry a probe detection device for rotary motion according to different working conditions. All movements are controlled by an operating table located at the end of the device. It has the characteristics of convenience, speed and full coverage, and completely avoids manual detection steps.

[0005] The technical solution adopted by the present invention to solve its technical problem is: an automatic detection device for internal wear of an aircraft landing gear sleeve includes a linear motion module, a rotary motion module, an adaptive chuck, a probe, a movable workbench, a control system, and an operating table. The upper surface of the movable workbench is provided with a slide rail, the linear motion module is connected to the slide block of the movable workbench slide rail, and can move along the length direction of the movable workbench, the aircraft landing gear sleeve parts are placed on the linear motion module, the operating table is placed at one end of the movable workbench, one end of the rotary motion module is connected to the operating table, and the other end is fixed with an adaptive chuck and can rotate around the central axis, the probe is clamped on the adaptive chuck, the control system drives the linear motion module to approach the rotary motion module until the probe penetrates into the interior of the aircraft landing gear sleeve parts, the control system drives the rotary motion module to rotate in the cavity for internal detection, and the operating table reads and displays internal status data.

[0006] The movable workbench includes a table top, pillars, adjustable supports, and a universal wheel group. The table top is an I-shaped plate welded structure. A groove is provided in the middle of one end of the table top, and the upper part of the other end is a trapezoidal structure. Pillars are provided below both ends of the table top. The pillars are a U-shaped structure. Adjustable supports are provided on the outside of each pillar, and a universal wheel group is provided below the pillar. The movable workbench can be moved by the universal wheel group and fixed at the working position by the adjustable support.

[0007] The linear motion module includes a bracket, a guide rail, a nut, a screw assembly, a limit block, a bearing seat, a first motor, and a first motor bracket. The bracket is a concave structure composed of plate-like parts. The bottom of the bracket is installed on the guide rail, and the guide rail is installed on the upper surface of the movable workbench. A limit block is provided at the end of the guide rail, and the limit block is fixed on the movable workbench. A screw assembly is provided on the inner side of the guide rail. The screw assembly is placed in a groove of the movable workbench and is connected to the nut provided at the bottom of the bracket. Bearing seats are provided at both ends of the screw assembly. A first motor is provided outside the bearing seat close to the end of the movable workbench. The first motor is connected to the first motor bracket, and the first motor shaft is connected to the bearing seat. The bearing seat and the first motor bracket are fixed in the groove of the movable workbench. Aircraft landing gear sleeve parts are fixed on the bracket, and the first motor drives the screw to move the bracket along the guide rail.

[0008] The rotary motion module includes a rotating shaft, a sleeve, a bearing sleeve, a second motor, a second motor bracket, an electromagnet, and an electromagnet support. The rotating shaft is a cylindrical structure. The end of one side of the rotating shaft is fixed to the end of the sleeve. Two parallel mounting surfaces are provided at the upper and lower relative positions of the end of the sleeve. An adaptive chuck is fixed to the upper mounting surface. An electromagnet support is provided on the lower mounting surface. The electromagnet is screwed to the electromagnet support. The end of the other side of the rotating shaft is connected to the bearing sleeve. The bearing sleeve is embedded in a circular hole on one side of the second motor bracket and fixed to the outer end surface of the second motor bracket. The outer end surface of the other side of the second motor bracket is connected to the second motor. The motor shaft passes through the inner hole of the second motor bracket and is connected to the bearing sleeve. The bottom of the second motor bracket is fixed to the upper surface of the trapezoidal structure of the movable workbench. The second motor drives the rotating shaft to rotate.

[0009] The adaptive chuck includes a chuck, a chuck docking plate, a pad, a baffle, a guide shaft, a spring, a taper pin, a locking pin, and a screw. The chuck is a Z-shaped structure. A slot is opened at the end of the chuck, and a threaded hole is arranged on the side wall of the slot. A probe is placed in the slot and clamped by a locking pin through the threaded hole arranged on the side wall of the slot. The bottom of the chuck is connected to the chuck docking plate through a taper pin and a screw. A pad is arranged under the docking plate, and a baffle is arranged under the pad. The guide shaft passes through the chuck docking plate, the pad and the baffle and is welded and fixed to the chuck docking plate and the baffle. The spring is sleeved on the outside of the guide shaft between the chuck docking plate and the pad. The rigid body after the guide shaft, the chuck docking plate and the baffle are welded and fixed can float along the guide shaft under the action of the spring.

[0010] The method for detecting using the device structure comprises the following steps:

[0011] Step 1: Place the aircraft landing gear sleeve part on the bracket of the linear motion module, and then install the adaptive chuck on the mounting surface at the end of the rotary motion module sleeve.

[0012] Step 2: Loosen the locking pin on the head of the adaptive chuck, place the probe in the groove of the head of the adaptive chuck, and then clamp the locking pin.

[0013] Step 3: Through the operating table, first turn on the electromagnet to generate magnetic force to adsorb the adaptive chuck on the surface of the electromagnet.

[0014] Step 4: The linear motion module then performs linear feeding.

[0015] Step 5: When the adaptive chuck approaches the wear detection area, the electromagnet is powered off, and the adaptive chuck fits into the inner cavity of the landing gear under the action of the spring.

[0016] Step 6: The linear motion module and the rotary motion module perform step-by-step rotary motion under the control of the system, and finally complete the automatic detection of the full coverage inside the aircraft landing gear sleeve.

[0017] Step 7: After completing the internal inspection of the aircraft landing gear sleeve, exit the inner cavity.

[0018] Beneficial effects of the invention: The invention proposes an automatic detection device for internal wear of an aircraft landing gear sleeve. In view of the current problems in parts detection, the problem of automatic parts detection is solved by cooperating between a linear motion module and a rotational motion module, and the problem that the probe detection device needs to always keep in contact with the surface to be tested in a closed cavity is solved by using an adaptive chuck, while various motion controls in the detection process can be achieved through digital input on the operating table; the entire device is fully controlled through the operating table, and the operation is simple, and the detection efficiency and detection coverage are high, which solves the problems of high labor intensity, low detection efficiency and low detection coverage brought about by the existing handheld probe detection method, and the device can be widely used in the detection of closed cavities of aircraft landing gear sleeve parts. BRIEF DESCRIPTION OF THE DRAWINGS

[0019] Figure 1 Schematic diagram of an automatic detection device for internal wear of an aircraft landing gear sleeve

[0020] Figure 2 Movable workbench

[0021] Figure 3 Schematic diagram of linear motion module

[0022] Figure 4 Rotational motion module schematic

[0023] Figure 5 Schematic diagram of adaptive chuck

[0024] Explanation of the numbers in the figure: 1. Linear motion module; 2. Rotary motion module; 3. Adaptive chuck; 4. Movable workbench; 5. Control system; 6. Operating table; 7. Probe; 8. Aircraft landing gear sleeve parts; 9. Table; 10. Pillar; 11. Adjustable support; 12. Universal wheel set; 13. Bracket; 14. Guide rail; 15. Nut; 16. Screw assembly; 17. Limit block; 18. Bearing seat; 19. First motor; 20. First motor bracket; 21. Rotating shaft; 22. Sleeve; 23. Bearing sleeve; 24. Second motor; 25. Second motor bracket; 26. Electromagnet; 27. Electromagnet support; 28. Chuck; 29. ​​Chuck docking plate; 30. Pad; 31. Baffle; 32. Guide shaft; 33. Spring; 34. Taper pin; 35. Locking pin; 36. Screw. DETAILED DESCRIPTION

[0025] from Figure 1In the figure, an automatic detection device for internal wear of an aircraft landing gear sleeve comprises a linear motion module 1, a rotary motion module 2, an adaptive chuck 3, a movable workbench 4, a control system 5, an operating table 6, and a probe 7. A slide rail 14 is provided on the upper surface of the movable workbench 4. The linear motion module 1 is connected to the slider of the slide rail 14 of the movable workbench 4 and can move along the length direction of the movable workbench 4. Aircraft landing gear sleeve parts 8 are placed on the linear motion module 1, and the operating table 6 is placed at one end of the movable workbench 4. One end of the rotary motion module 2 is connected to the operating table 6, and the other end is fixed with an adaptive chuck 3 and can rotate around the central axis. The probe 7 is clamped on the adaptive chuck 3, and the control system 5 drives the linear motion module 1 to rotate. The linear motion module 2 approaches until the probe 7 penetrates into the aircraft landing gear sleeve-type parts 8, the control system 5 drives the rotary motion module 2 to rotate in the cavity for internal detection, and the operating table 6 reads and displays the internal status data; the movable workbench 4 enables the automatic detection device for internal wear of the aircraft landing gear sleeve to have a mobile function, which can not only meet the needs of indoor fixed detection areas, but also cope with emergencies in outdoor detection; at the same time, the linear motion module 1 and the rotary motion module 2 are linked to realize automatic detection of parts, improve detection efficiency, and avoid problems such as manual missed detection; and the coordinated use of the adaptive chuck 3 and the rotary motion module 2 enables the probe 7 to always keep in contact with the measured surface in the closed cavity and avoid the internal groove structure of the part.

[0026] from Figure 2 From the middle, the movable workbench 4 includes a table top 9, pillars 10, adjustable supports 11, and a universal wheel set 12. The table top 9 is an I-shaped plate welding structure, which reduces the weight while meeting the structural rigidity. A groove is provided in the middle of one end of the table top 9, and the upper part of the other end is a trapezoidal structure. Pillars 10 are provided below both ends of the table top. The pillars 10 are a U-shaped structure. An adjustable support 11 is provided on the outside of each pillar 10, and a universal wheel set 12 is provided below the pillar 10. The movable workbench 4 can be moved by the universal wheel set 12, and the movable workbench 4 can be fixed at the working position by the adjustable support 11.

[0027] from Figure 3In the middle view, the linear motion module 1 includes a bracket 13, a guide rail 14, a nut 15, a screw assembly 16, a limit block 17, a bearing seat 18, a first motor 19, and a first motor bracket 20. The bracket 13 is a concave structure composed of plate-like parts. The bottom of the bracket 13 is installed on the guide rail 14, and the guide rail 14 is installed on the upper surface of the movable workbench 4. A limit block 17 is provided at the end of the guide rail 14, and the limit block 17 is fixed on the table 9 of the movable workbench 4. A screw assembly 16 is provided on the inner side of the guide rail 14. The screw assembly 16 is placed in the groove of the movable workbench and is connected to the nut 15 provided at the bottom of the bracket 13. The two ends of the screw assembly 16 are provided with a bearing seat 1 8. A first motor 19 is arranged outside the bearing seat 18 near the end of the movable workbench 4. The first motor 19 is connected to the first motor bracket 20. The rotating shaft of the first motor 19 is connected to the bearing seat 18. The bearing seat 18 and the first motor bracket 20 are fixed in the groove of the movable workbench. The aircraft landing gear sleeve parts 8 are fixed on the bracket 13. The first motor 19 drives the screw assembly 16 to move the bracket 13 along the guide rail 14; the screw assembly 16, the bearing seat 18 and the first motor bracket 20 are built into the groove of the movable workbench, which can reduce the overall height of the automatic detection device for internal wear of the aircraft landing gear sleeve, and the human-machine operability of the detection personnel is better.

[0028] from Figure 4 In the middle view, the rotary motion module 2 includes a rotary shaft 21, a sleeve 22, a bearing sleeve 23, a second motor 24, a second motor bracket 25, an electromagnet 26, and an electromagnet support 27. The rotary shaft 21 is a cylindrical structure. One end of the rotary shaft 21 is fixed to the end of the sleeve 22. Two parallel mounting surfaces are provided at the upper and lower relative positions of the end of the sleeve 22. The upper mounting surface is fixed with an adaptive chuck 3. The lower mounting surface is provided with an electromagnet support 27. The electromagnet 26 is screwed to the electromagnet support 27. The other end of the rotary shaft 21 is connected to the bearing sleeve 23. The bearing sleeve 23 is embedded in the circular hole on one side of the second motor bracket 25 and is connected to the outer surface of the second motor bracket 25. The end face is fixed, and the outer end face on the other side of the second motor bracket 25 is connected to the second motor 24. The motor shaft passes through the inner hole of the second motor bracket 25 and is connected to the bearing sleeve 23. The bottom of the second motor bracket 25 is fixed on the upper surface of the trapezoidal structure of the movable workbench 4. The second motor 24 drives the rotating shaft 21 to rotate, which solves the need for full coverage circumferential detection inside the aircraft landing gear sleeve part 8. By turning the electromagnet 26 on and off, the adaptive chuck 3 can be adsorbed and released, thereby ensuring that the probe 7 on the adaptive chuck 3 can avoid the internal groove structure of the part when detecting the inside of the aircraft landing gear sleeve part 8, thereby avoiding the probe from breaking.

[0029] from Figure 5In the middle view, the adaptive chuck 3 includes a chuck 28, a chuck docking plate 29, a pad 30, a baffle 31, a guide shaft 32, a spring 33, a taper pin 34, a locking pin 35, and a screw 36. The chuck 28 is a Z-shaped structure. A notch is opened at the end of the chuck 28, and a threaded hole is provided on the side wall of the notch. The probe 7 is placed in the notch and is clamped by the locking pin 35 through the threaded hole provided on the side wall of the notch. The bottom of the chuck 28 is connected to the chuck docking plate 29 by the taper pin 34 and the screw 36. The chuck docking plate 29 is connected to the chuck by the taper pin 34 and the screw 36. A pad 30 is provided under the plate 29, and a baffle 31 is provided under the pad 30. The guide shaft 32 passes through the chuck docking plate 29, the pad 30 and the baffle 31 and is welded and fixed with the chuck docking plate 29 and the baffle 31. The spring 33 is sleeved on the outside of the guide shaft 32 between the chuck docking plate 29 and the pad 30. After the guide shaft 32, the chuck docking plate 29 and the baffle 31 are welded and fixed, the rigid body can float along the guide shaft 32 under the action of the spring 33, thereby realizing the adaptive function of the structure.

[0030] The method for detecting using the device structure comprises the following steps:

[0031] The first step: the aircraft landing gear sleeve-type parts 8 are placed on the bracket 13 of the linear motion module 1, and then the adaptive chuck 3 is installed on the mounting surface at the end of the sleeve 22 of the rotary motion module 2.

[0032] Step 2: Loosen the locking pin 35 on the head of the adaptive chuck 3, place the probe 7 in the notch on the head of the adaptive chuck 3, and then clamp the locking pin 35.

[0033] Step 3: First, turn on the electromagnet 26 through the operating table 6 to generate magnetic force to adsorb the adaptive chuck 3 on the surface of the electromagnet 26.

[0034] Step 4: The linear motion module 1 then performs linear feeding.

[0035] Step 5: When the adaptive chuck 3 approaches the wear detection area, the electromagnet 26 is powered off, and the adaptive chuck 3 fits into the inner cavity of the landing gear under the action of the spring 33 .

[0036] Step 6: The linear motion module 1 and the rotary motion module 2 perform step-by-step rotary motion under the control of the system, and finally complete the automatic detection of the full coverage inside the aircraft landing gear sleeve.

[0037] Step 7: After completing the internal inspection of the aircraft landing gear sleeve, exit the inner cavity.

[0038] The present invention proposes an automatic detection device and method for the internal wear of an aircraft landing gear sleeve, which have a high degree of automation and informatization, have mobile and adaptive detection functions, good adaptability to detection sites and tested parts, simple operation, high detection efficiency and detection coverage, and solve the problems of high labor intensity, low detection efficiency and detection coverage brought about by the existing handheld probe detection method.

Claims

1. An automatic detection device for internal wear of an aircraft landing gear sleeve, characterized in that It includes a linear motion module, a rotary motion module, an adaptive chuck, a probe, a movable workbench, a control system, and an operating table. A slide rail is provided on the upper surface of the movable workbench. The linear motion module is connected to the slide rail of the movable workbench and can move along the length direction of the movable workbench. Aircraft landing gear sleeve parts are placed on the linear motion module. The operating table is placed at one end of the movable workbench. One end of the rotary motion module is connected to the operating table, and the other end is fixed with an adaptive chuck and can rotate around the central axis. The probe is clamped on the adaptive chuck. The control system drives the linear motion module to approach the rotary motion module. Until the probe penetrates into the interior of the aircraft landing gear sleeve-like parts, the control system drives the rotary motion module to rotate in the cavity for internal detection, and the operating table reads and displays the internal status data. The linear motion module includes a bracket, a guide rail, a nut, a screw assembly, a limit block, a bearing seat, a first motor, and a first motor bracket. The bracket is a concave structure composed of plate-like parts. The bottom of the bracket is installed on the guide rail, and the guide rail is installed on the upper surface of the movable workbench, and a limit block is provided at the end of the guide rail, and the limit block is fixed on the movable workbench surface. A screw assembly is provided on the inner side of the guide rail, and the screw assembly is placed on the movable workbench surface. The first motor is connected to the first motor bracket, and the first motor shaft is connected to the bearing seat. The bearing seat and the first motor bracket are fixed in the groove of the movable worktable. The aircraft landing gear sleeve parts are fixed on the bracket. The first motor drives the screw to move along the guide rail with the bracket. The rotary motion module includes a rotary shaft, a sleeve, a bearing sleeve, a second motor, a second motor bracket, an electromagnet, and an electromagnet support. The rotary shaft is a cylindrical structure. The end of one side of the shaft is fixed to the end of the sleeve, and two parallel mounting surfaces are provided at the upper and lower relative positions of the end of the sleeve, an adaptive chuck is fixed to the upper mounting surface, and an electromagnet support is provided on the lower mounting surface, and the electromagnet is screwed to the electromagnet support; the end of the other side of the rotating shaft is connected to the bearing sleeve, the bearing sleeve is embedded in the circular hole on one side of the second motor bracket and fixed to the outer end surface of the second motor bracket, the outer end surface on the other side of the second motor bracket is connected to the second motor, the motor shaft passes through the inner hole of the second motor bracket and is connected to the bearing sleeve, the bottom of the second motor bracket is fixed to the upper surface of the trapezoidal structure of the movable workbench, and the second motor drives the rotating shaft to rotate.

2. The automatic detection device for internal wear of an aircraft landing gear sleeve according to claim 1, characterized in that The movable workbench includes a table top, pillars, adjustable supports, and a universal wheel group. The table top is an I-shaped plate welding structure. A groove is provided in the middle of one end of the table top, and the upper part of the other end is a trapezoidal structure. Pillars are provided below both ends of the table top. The pillars are a U-shaped structure. An adjustable support is provided on the outside of each pillar. A universal wheel group is provided below the pillar. The movable workbench can be moved by the universal wheel group, and the movable workbench can be fixed at the working position by the adjustable support.

3. The automatic detection device for internal wear of an aircraft landing gear sleeve according to claim 1, characterized in that The adaptive chuck comprises a chuck, a chuck docking plate, a pad, a baffle, a guide shaft, a spring, a taper pin, a locking pin and a screw. The chuck is a Z-shaped structure, a notch is formed at the end of the chuck, a threaded hole is formed on the side wall of the notch, a probe is placed in the notch and clamped by a locking pin through the threaded hole formed on the side wall of the notch, the bottom of the chuck is connected to the chuck docking plate by a taper pin and a screw, a pad is provided under the docking plate, a baffle is provided under the pad, the guide shaft passes through the chuck docking plate, the pad and the baffle and is welded and fixed to the chuck docking plate and the baffle, the spring is sleeved on the outside of the guide shaft between the chuck docking plate and the pad, and the rigid body after the guide shaft, the chuck docking plate and the baffle are welded and fixed can float along the guide shaft under the action of the spring.

4. A method for automatically detecting internal wear of an aircraft landing gear sleeve, characterized in that Using the automatic detection device for internal wear of an aircraft landing gear sleeve as described in claim 1 to detect the inside of an aircraft landing gear sleeve specifically comprises the following steps: 4-1. Place the aircraft landing gear sleeve part on the bracket of the linear motion module, and then install the adaptive chuck on the mounting surface at the end of the rotary motion module sleeve; 4-2. Loosen the locking pin on the head of the adaptive chuck, place the probe in the notch of the head of the adaptive chuck, and then clamp the locking pin; 4-3. Through the operating table, first turn on the electromagnet to generate magnetic force to adsorb the adaptive chuck on the surface of the electromagnet; 4-4. Then the linear motion module performs linear feeding; 4-5. When the adaptive chuck approaches the wear detection area, the electromagnet is powered off, and the adaptive chuck fits into the inner cavity of the landing gear under the action of the spring; 4-6. The linear motion module and the rotary motion module perform step-by-step rotary motion under the control of the system, and finally complete the automatic detection of the full coverage inside the aircraft landing gear sleeve; 4-7. After completing the internal inspection of the aircraft landing gear sleeve, withdraw from the inner cavity.

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