Phased array detection device for checking internal cracks of aircraft skin
By designing a phased array detection device for cracks inside the aircraft skin, the shortcomings of traditional detection devices in detecting cracks inside the aircraft skin are solved, and the convenience, stability and high accuracy of detection are achieved, and suitable for the detection of complex surfaces.
Patent Information
- Application Number
- CN202421177292.1
- Authority / Receiving Office
- CN · China
- Patent Type
- Utility models(China)
- Current Assignee / Owner
- Filing Date
- 2024-05-28
- Publication Date
- 2025-05-09
- Estimated Expiration
- 2034-05-28
AI Technical Summary
Traditional detection devices cannot effectively detect cracks inside the aircraft skin, especially in the arc shape of the chemical milling structure, the probe angle is difficult to control, the uniformity of the coupling agent is poor, and the rough surface cannot be detected, which affects the reliability and accuracy of the detection results.
A phased array detection device is designed, including a base, an ultrasonic probe, a limiting plate, a positioning plate, an adjustment mechanism and an encoder. Through the adjustment mechanism, the spacing and angle between the probe and the skin are accurately adjusted. The encoder records the probe position, ensuring the accuracy and stability of the detection, and detecting the rough surface through an automatic coupling agent system.
It realizes the convenience and stability of crack detection in the aircraft skin, improves the reliability and accuracy of the detection results, and can effectively detect complex surfaces including arc shapes of chemical milling structures.
Smart Images
Figure CN222850565U_ABST
Abstract
Description
Technical Field
[0001] The utility model relates to the technical field of aircraft maintenance tools, in particular to a phased array detection device for inspecting cracks inside aircraft skins. Background Art
[0002] The aircraft skin is an aluminum alloy metal structure. If the fatigue cracks in the chemically milled steps in the original skin or the modified skin (the adjacent areas of chemical milling and non-chemical milling) are not discovered, repaired or prevented in time, the aircraft will be rapidly decompressed.
[0003] Traditional detection devices cannot adjust or fix the distance between the detection probe and the inspected area. Manual control of the detection distance is inefficient. The probe angle is easily deviated, resulting in missed detection, which affects the reliability of the detection results. In the curved area of the chemical milling structure of the aircraft skin, it is difficult to implement the traditional detection device to check for cracks. The sliding stability of the probe and the skin joint surface is poor. The probe has no fulcrum and the sliding angle is difficult to control. At the same time, the traditional detection probe uses the method of hand-coating the coupling agent, which has a poor uniform coupling effect on the inspected surface. The inspected surface must be clean and smooth, and it is impossible to detect a relatively rough surface. Summary of the invention
[0004] In order to overcome the deficiencies of the above technologies, the utility model provides a detection device which ensures that the detection process of detecting cracks inside aircraft skin is convenient and stable, and improves the reliability of the detection result and the detection accuracy.
[0005] The technical solution adopted by the utility model to overcome the technical problems is:
[0006] A phased array detection device for detecting cracks inside aircraft skin, comprising:
[0007] A base, which is sealed on all sides and has an opening at the bottom;
[0008] An ultrasonic probe is installed at the rear end of the base, with the detection end of the ultrasonic probe facing the opening at the bottom of the base;
[0009] A limiting plate, which is fixed to the front end of the base by screw III;
[0010] The positioning plate is installed at the front end of the limit plate through the adjustment mechanism I. The positioning plate moves forward and backward relative to the limit plate through the adjustment mechanism. A hook head is arranged at the lower part of the front end of the positioning plate.
[0011] A slide is arranged outside the base through an adjustment mechanism II, a rotating shaft I is arranged on the slide, an encoder is rotatably mounted on the rotating shaft I, an axis of the encoder is horizontally arranged along the front-rear direction, and a roller is installed on the rotating shaft of the encoder.
[0012] Furthermore, the above-mentioned adjustment mechanism I includes a long hole II arranged on the positioning plate along the front-to-back direction, and the screw IV passes through the long hole II and is screwed into the limiting plate.
[0013] Furthermore, it also includes a torsion spring mounted on the rotating shaft I, one end of the torsion spring is connected to the rotating shaft I, and the other end of the torsion spring is connected to the encoder.
[0014] Furthermore, it also includes clamping plates respectively arranged on the left and right sides of the base, wherein the clamping plates are provided with through holes, and the bolts pass through the through holes of the clamping plates and are screwed onto the corresponding side end surfaces of the base, a plurality of coupling agent channels are arranged in the clamping plates along the vertical direction, a pipe joint is arranged at the upper end of the clamping plates, and the lower end of the pipe joint is connected to each coupling agent channel, and a liquid reservoir for accommodating the coupling agent is arranged at the upper end of the base, one pipe mouth of the tee is connected to the outlet end of the liquid reservoir, and the other two pipe mouths of the tee are respectively connected to shunt pipes, and the lower end of the shunt pipe is connected to the corresponding pipe joint on the same side.
[0015] Furthermore, the above-mentioned adjustment mechanism II includes a screw hole I arranged on a clamping plate, a long hole I arranged on a sliding seat along the front-to-back direction, and a connecting plate. The screw II passes through the connecting plate and is screwed into the screw hole I. The sliding seat is located at the upper end of the connecting plate, and the screw I passes through the long hole I and is screwed into the connecting plate.
[0016] Furthermore, it also includes an L-shaped auxiliary guide plate, a plurality of suction cups are arranged at the lower end of the auxiliary guide plate, the auxiliary guide plate is fixed to the aircraft skin by suction through the suction cups, a quarter-circular arc groove is arranged inside the auxiliary guide plate, and when the base turns, its front end face contacts with the arc groove.
[0017] Furthermore, it also includes a limiter for locking the encoder and the base to each other.
[0018] Furthermore, the above-mentioned limiter includes a connecting seat I installed on the splint, a rotating shaft II arranged on the connecting seat I, a connecting seat II installed on the upper end of the encoder, a sleeve and a sliding rod slidably inserted in the sleeve, the lower end of the sliding rod is connected to the connecting seat II, the upper end of the sleeve is provided with a pin hole, the rotating shaft II is inserted in the pin hole, the lower end of the sleeve is a conical structure, the cone is provided with an external thread, the conical part is provided with a groove in the vertical direction, a locking sleeve is mounted on the sliding rod, and the upper end of the locking sleeve is provided with a conical screw hole II matching the cone of the sleeve, and the locking sleeve is screwed onto the external thread through the screw hole II.
[0019] The beneficial effects of the utility model are as follows: the base is placed on the surface of the detected area of the aircraft skin, the position of the positioning plate is adjusted by the adjusting mechanism I so that the hook head is hooked on the edge of the skin overlap belt, the position of the encoder is adjusted by the adjusting mechanism II, and then the base 1 is manually driven to move smoothly along the skin overlap belt. At this time, the ultrasonic probe detects the edge area of the skin chemical milling, and the roller rotates synchronously when the base moves, so that the encoder sends a pulse signal, and the position of the ultrasonic probe can be accurately recorded, ensuring that the detection of cracks inside the aircraft skin is domestically convenient and stable, and improving the reliability and detection accuracy of the detection results. BRIEF DESCRIPTION OF THE DRAWINGS
[0020] Figure 1 It is a three-dimensional structural schematic diagram of the utility model;
[0021] Figure 2 This is a schematic diagram of the detection without auxiliary guide plate of the utility model;
[0022] Figure 3 This is a schematic diagram of the auxiliary guide plate detection of the utility model;
[0023] Figure 4 It is a longitudinal cross-sectional structural diagram of the splint part of the utility model;
[0024] Figure 5 It is a three-dimensional structural diagram of the encoder part of the utility model;
[0025] Figure 6 It is a structural schematic diagram of the tension regulator of the utility model;
[0026] In the figure, 1. base 2. ultrasonic probe 3. clamping plate 4. connecting plate 5. sliding seat 6. long hole I 7. screw I 8. screw II 9. encoder 10. roller 11. pipe joint 12. liquid reservoir 13. tee 14. shunt pipe 15. limit plate 16. screw III 17. positioning plate 18. hook head 19. long hole II 20. screw IV 21. auxiliary guide plate 22. suction cup 23. arc groove 24. limiter 25. skin 26. chemical milling edge of skin 27. edge of skin lap joint 28. through hole 29. screw hole I 30. coupling agent channel 31. rotating shaft I 32. torsion spring 33. connecting seat I 34. rotating shaft II 35. connecting seat II 241. sleeve 242. sliding rod 243. locking sleeve 244. pin hole 245. external thread 246. slot 247. screw hole II. DETAILED DESCRIPTION
[0027] The following is combined with Figure 1 To Attachment Figure 6 The utility model is further described.
[0028] As attached Figure 1 As shown, a phased array detection device for inspecting cracks inside aircraft skins comprises: a base 1 which is sealed on all sides and has an opening at the bottom; an ultrasonic probe 2 which is mounted at the rear end of the base 1, with the detection end of the ultrasonic probe 2 facing the opening at the bottom of the base 1; a limit plate 15 which is fixed to the front end of the base 1 by means of a screw III 16; a positioning plate 17 which is mounted at the front end of the limit plate 15 by means of an adjustment mechanism I, the positioning plate 17 moves forward and backward relative to the limit plate 15 by means of the adjustment mechanism, and a hook 18 is provided at the lower front end of the positioning plate 17; a slide 5 which is arranged at the outer side of the base 1 by means of an adjustment mechanism II, a rotating shaft I 31 is provided on the slide 5, an encoder 9 is rotatably mounted on the rotating shaft I 31, the axis of the encoder 9 is horizontally arranged along the front-back direction, and a roller 10 is installed on the rotating shaft of the encoder 9. As shown in the attached figure Figure 2 As shown, when in use, the base 1 is placed on the surface of the detected area of the aircraft skin 25, and the position of the positioning plate 17 is adjusted by the adjustment mechanism I so that the hook head 18 is hooked on the edge 27 of the skin overlap belt. The position of the encoder 9 is adjusted by the adjustment mechanism II, and then the base 1 is manually driven to move smoothly along the skin overlap belt. At this time, the ultrasonic probe 2 detects the area of the chemical milling edge 26 of the skin. When the base 1 moves, the roller 10 rotates synchronously, so that the encoder 9 sends a pulse signal, and the position of the ultrasonic probe 2 can be accurately recorded, ensuring that the detection of cracks inside the aircraft skin 25 is convenient and stable, and the reliability and detection accuracy of the detection results are improved.
[0029] In one embodiment of the utility model, the adjustment mechanism I includes a long hole II 19 provided on the positioning plate 17 along the front-back direction, and a screw IV 20 passes through the long hole II 19 and is screwed into the limiting plate 15. Loosening the screw IV 20 allows the positioning plate 17 to slide to a suitable position under the guidance of the long hole II 19 by means of the screw IV 20, so that the hook head 18 of the positioning plate 17 is hooked on the edge 27 of the skin lap band, and after the positioning plate 17 is adjusted in place, the screw IV 20 is tightened to lock the positioning plate 17 relative to the limiting plate 15. The structure is simple and the adjustment is convenient.
[0030] In one embodiment of the utility model, a torsion spring 32 is also included which is mounted on the rotating shaft I 31, one end of the torsion spring 32 is connected to the rotating shaft I 31, and the other end thereof is connected to the encoder 9. The elastic force of the torsion spring 32 acts on the encoder 9, so that the encoder 9 generates downward pressure, ensuring that the roller 10 is in contact with the aircraft skin 25, thereby ensuring that the roller 10 can roll when the base 1 moves.
[0031] As attached Figure 4As shown, in one embodiment of the utility model, it also includes a clamping plate 3 respectively arranged on the left and right sides of the base 1, and a through hole 28 is set on the clamping plate 3. The bolt passes through the through hole 28 of the clamping plate 3 and is screwed on the corresponding side end surface of the base 1. A plurality of coupling agent channels 30 are arranged in the clamping plate 3 along the vertical direction. A pipe joint 11 is arranged at the upper end of the clamping plate 3, and the lower end of the pipe joint 11 is connected to each coupling agent channel 30. A liquid reservoir 12 for accommodating a coupling agent is arranged at the upper end of the base 1, and one pipe mouth of the tee 13 is connected to the outlet end of the liquid reservoir 12, and the other two pipe mouths of the tee 13 are respectively connected to the shunt pipe 14, and the lower end of the shunt pipe 14 is connected to the corresponding pipe joint 11 on the same side. The coupling agent in the liquid reservoir 12 flows into the two shunt pipes 14 through the tee 13, and finally flows into the corresponding coupling agent channels 30 inside the clamping plate 3 through the pipe joint 11, and finally flows downward to the surface of the aircraft skin 25 through the coupling agent channel 30, so as to realize automatic wetting of the coupling agent, provide a coupling agent that can evenly wet the detection surface, detect rough surfaces, effectively improve the stability and reliability of detection, reduce safety hazards, improve work efficiency, and save aircraft operators' maintenance costs.
[0032] In one embodiment of the utility model, the adjustment mechanism II can be the following structure, which includes a screw hole I 29 provided on a clamping plate 3, a long hole I 6 provided on the slide 5 along the front-back direction, and a connecting plate 4. The screw II 8 passes through the connecting plate 4 and is screwed into the screw hole I 29. The slide 5 is located at the upper end of the connecting plate 4. The screw I 7 passes through the long hole I 6 and is screwed into the connecting plate 4. After loosening the screw I 7, the slide 5 can be moved forward and backward under the guidance of the long hole I 6 by the screw I 7, so as to adjust the position of the encoder 9. After the encoder 9 is adjusted in place, the screw I 7 can be locked and fixed to the slide 5 relative to the connecting plate 4, which is convenient to operate.
[0033] In one embodiment of the utility model, an L-shaped auxiliary guide plate 21 is also included. A plurality of suction cups 22 are provided at the lower end of the auxiliary guide plate 21. The auxiliary guide plate 21 is fixed to the aircraft skin 25 by suction through the suction cups 22. A quarter-circular arc groove 23 is provided inside the auxiliary guide plate 21. When the base 1 turns, its front end surface contacts the arc groove 23. Figure 3 As shown, when the base 1 moves along the left-right direction to the head end and needs to be converted to the vertical direction, the auxiliary guide plate 21 is fixed to the skin 25 by a suction cup, and the front end surface of the base 1 is switched to the vertical movement state along the guidance of the arc groove 23. The arc groove 23 acts as a guide rail to facilitate the turning of the base 1 in the corner area.
[0034] In one embodiment of the utility model, a stopper 24 is also included for locking the encoder 9 and the base 1. The position of the encoder 9 can be fixed by the stopper, and the position of the encoder 9 can be locked and fixed in certain circumstances to ensure reliable movement of the roller 10 and prevent the encoder 9 from moving freely.
[0035] As attached Figure 5 and attached Figure 6 As shown, in this embodiment, the limiter 24 includes a connecting seat Ⅰ 33 installed on the splint 3, a rotating shaft Ⅱ 34 arranged on the connecting seat Ⅰ 33, a connecting seat Ⅱ 35 installed on the upper end of the encoder 9, a sleeve 241 and a slide rod 242 slidably inserted in the sleeve 241, the lower end of the slide rod 242 is connected to the connecting seat Ⅱ 35, the upper end of the sleeve 241 is provided with a pin hole 244, the rotating shaft Ⅱ 34 is inserted in the pin hole 244, the lower end of the sleeve 241 is a conical structure, the cone is provided with an external thread 245, the conical part is provided with a slot 246 along the vertical direction, the slide rod 242 is sleeved with a locking sleeve 243, the upper end of the locking sleeve 243 is provided with a conical screw hole Ⅱ 247 matching the cone of the sleeve 241, and the locking sleeve 243 is screwed on the external thread 245 through the screw hole Ⅱ 247. After the locking sleeve 243 is loosened, the slide bar 242 slides freely in the sleeve 241. At this time, the sleeve 241 can rotate around the rotating shaft 34 to realize the rotation of the encoder 9 at the lower end around the rotating shaft I 31. When the angle condition of the encoder 9 is in place, the locking sleeve 243 is rotated. Since the screw hole II 247 is a tapered hole and the tapered structure of the outer thread 245 matched therewith, the locking sleeve 243 will squeeze the conical part of the lower end of the sleeve 241 inward when tightening. Since the conical part of the lower end of the sleeve 241 is provided with a groove 246, the inner diameter of the conical part gradually decreases due to the extrusion force, thereby locking the slide bar 242. The operation is simple and convenient.
[0036] Finally, it should be noted that the above description is only a preferred embodiment of the utility model and is not intended to limit the utility model. Although the utility model is described in detail with reference to the above embodiments, those skilled in the art can still modify the technical solutions recorded in the above embodiments or replace some of the technical features therein by equivalents. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the utility model shall be included in the protection scope of the utility model.
Claims
1. A phased array detection device for internal crack inspection of aircraft skin, characterized in that: include: A base (1) which is sealed on all sides and has an opening at the bottom; An ultrasonic probe (2) is mounted on the rear end of the base (1), with the detection end of the ultrasonic probe (2) facing the opening at the bottom of the base (1); A limit plate (15) fixed to the front end of the base (1) by means of screws III (16); The positioning plate (17) is mounted on the front end of the limiting plate (15) through the adjusting mechanism I. The positioning plate (17) moves forward and backward relative to the limiting plate (15) through the adjusting mechanism. A hook head (18) is provided below the front end of the positioning plate (17). A slide (5) is arranged on the outside of the base (1) through an adjustment mechanism II, a rotating shaft I (31) is arranged on the slide (5), an encoder (9) is rotatably mounted on the rotating shaft I (31), an axis of the encoder (9) is arranged horizontally along the front-rear direction, and a roller (10) is mounted on the rotating shaft of the encoder (9).
2. The phased array detection device for internal crack inspection of aircraft skin according to claim 1, characterized in that: The adjustment mechanism I comprises a long hole II (19) arranged on the positioning plate (17) along the front-rear direction, and a screw IV (20) passes through the long hole II (19) and is screwed into the limiting plate (15).
3. The phased array detection device for internal crack inspection of aircraft skin according to claim 1, characterized in that: It also includes a torsion spring (32) sleeved on the rotating shaft I (31), one end of the torsion spring (32) is connected to the rotating shaft I (31), and the other end of the torsion spring (32) is connected to the encoder (9).
4. The phased array detection device for internal crack inspection of aircraft skin according to claim 1, characterized in that: The invention also comprises clamping plates (3) respectively arranged on the left and right sides of the base (1), wherein the clamping plates (3) are provided with through holes (28), and bolts are screwed onto the corresponding side end surfaces of the base (1) after passing through the through holes (28) of the clamping plates (3). A plurality of coupling agent channels (30) are arranged in the clamping plates (3) along the vertical direction, and a pipe joint (11) is arranged at the upper end of the clamping plates (3), and the lower end of the pipe joint (11) is connected to each coupling agent channel (30). A liquid reservoir (12) for accommodating the coupling agent is arranged at the upper end of the base (1), and one pipe opening of the tee (13) is connected to the outlet end of the liquid reservoir (12), and the other two pipe openings of the tee (13) are respectively connected to shunt pipes (14), and the lower end of the shunt pipe (14) is connected to the corresponding pipe joint (11) on the same side.
5. The phased array detection device for internal crack inspection of aircraft skin according to claim 4, characterized in that: The adjusting mechanism II comprises a screw hole I (29) provided on a clamping plate (3), a long hole I (6) provided on a slide seat (5) along the front-rear direction, and a connecting plate (4); the screw II (8) passes through the connecting plate (4) and is screwed into the screw hole I (29); the slide seat (5) is located at the upper end of the connecting plate (4); the screw I (7) passes through the long hole I (6) and is screwed into the connecting plate (4).
6. The phased array detection device for internal crack inspection of aircraft skin according to claim 1, characterized in that: The auxiliary guide plate (21) is also provided with an L-shaped auxiliary guide plate (21). A plurality of suction cups (22) are provided at the lower end of the auxiliary guide plate (21). The auxiliary guide plate (21) is fixed to the aircraft skin (25) by adsorption through the suction cups (22). A quarter-circular arc groove (23) is provided inside the auxiliary guide plate (21). When the base (1) turns, its front end surface contacts the arc groove (23).
7. The phased array detection device for internal crack inspection of aircraft skin according to claim 4, characterized in that: It also includes a limiter (24) for locking the encoder (9) and the base (1) with each other.
8. The phased array detection device for internal crack inspection of aircraft skin according to claim 7, characterized in that: The limiter (24) comprises a connection seat I (33) mounted on the clamping plate (3), a rotating shaft II (34) arranged on the connection seat I (33), a connection seat II (35) mounted on the upper end of the encoder (9), a sleeve (241), and a slide rod (242) slidably inserted into the sleeve (241), wherein the lower end of the slide rod (242) is connected to the connection seat II (35), the upper end of the sleeve (241) is provided with a pin hole (244), and the rotating shaft II (34) is inserted into the sleeve (241). Installed in the pin hole (244), the lower end of the sleeve (241) is in a conical structure, an external thread (245) is provided on the cone, and a groove (246) is provided in the conical portion along the vertical direction. A locking sleeve (243) is sleeved on the slide bar (242), and a conical screw hole II (247) matching the cone of the sleeve (241) is provided on the upper end of the locking sleeve (243), and the locking sleeve (243) is screwed onto the external thread (245) through the screw hole II (247).