Aircraft skin damage identification system

Abstract

An aircraft skin damage identification system disclosed by the present invention comprises a road main body and a fixed block, the fixed block is embedded and fixed in the road main body, the top end of the fixed block is fixedly provided with a U-shaped block, the inner side of the U-shaped block is provided with a first detection mechanism, and the center position of the fixed block is provided with a cavity. Normal aircraft skin videos are input and stored in the storage module through the input module, an aircraft moves along a road main body during use and moves along a marking line to pass through the U-shaped block, and at the moment, the unmanned aerial vehicle camera in the cavity and the unmanned aerial vehicle camera on the inner side of the U-shaped block are connected with the unmanned aerial vehicle camera when the aircraft passes through the unmanned aerial vehicle camera. Comprehensive video sampling is carried out on the outer surface of an aircraft, videos are transmitted into the control box, the comparison module compares the collected videos with normal videos, the positions of different points are marked through the marking module, and finally the videos are displayed on the display screen, so that comprehensive detection on the aircraft skin is facilitated, manual detection is not needed, and the labor intensity is reduced.

Description

Technical Field

[0001] The present invention relates to the field of aircraft detection, and in particular to an aircraft skin damage identification system. Background Art

[0002] Aircraft skin refers to a dimensional component that surrounds the aircraft frame structure and is fixed to the frame with adhesives or rivets to form the aircraft's aerodynamic shape. The skin structure formed by the aircraft skin and frame has a large load-bearing capacity and rigidity, but a very light weight, and plays the role of bearing and transmitting aerodynamic loads. After the skin is subjected to aerodynamic forces, it transmits the force to the connected fuselage and wing frames. The force is complex, and the skin is in direct contact with the outside world. Therefore, not only are the skin materials required to have high strength and good plasticity, but also a smooth surface and high corrosion resistance.

[0003] Existing aircraft need to use skin to protect the internal structure. However, after long-term use, the skin will cause serious deformation and some fixing points to fall off due to stress. At this time, the skin cannot effectively protect the internal structure. At this time, the deformed, damaged, and detached skin needs to be repaired and maintained. Before repair, manual inspection is required to select the problematic skin and then concentrate on repair and maintenance work. Manual inspection is time-consuming and labor-intensive, and the aircraft itself is large, so manual inspection is easy to miss inspections. Therefore, a device is urgently needed to solve the above problems. Summary of the Invention

[0004] The purpose of the present invention is to provide an aircraft skin damage identification system to solve the problems raised in the above background technology.

[0005] To achieve the above-mentioned objectives, the present invention provides the following technical solutions: an aircraft skin damage identification system, comprising a road body and a fixed block, the fixed block being embedded and fixed inside the road body, a U-shaped block being fixedly provided on the top of the fixed block, a first detection mechanism being provided on the inside of the U-shaped block, a cavity being opened at the center of the fixed block, a second detection mechanism being provided inside the cavity, a protective mechanism being provided on the top of the cavity, a cleaning mechanism being provided inside the fixed block for facilitating cleaning of the protective mechanism, a marking line being engraved on the top of the road body, a control mechanism being provided on one side of the U-shaped frame, the first detection mechanism comprising a drone camera, a fixing ring and a fixing assembly, the fixing ring being embedded and fixed inside the U-shaped block, the drone camera being slidably provided inside the fixing ring, and the fixing assembly being provided on the outside of the fixing ring;

[0006] The second detection mechanism includes a drone camera and a fixing ring, wherein the fixing ring is fixed at the bottom end of the cavity, and the drone camera is slidably arranged inside the fixing ring.

[0007] Preferably, the control mechanism includes a control box, a display screen is embedded and fixed on one side of the control box, and a storage module, an input module, a comparison module, a marking module and a control chip are arranged inside the control box. The storage module, input module, comparison module and marking module are electrically connected to the control chip, and the drone camera is electrically connected to the control chip inside the control box. The normal aircraft skin video is input through the input module and stored inside the storage module. When in use, the aircraft moves along the main body of the road and moves along the marking line through the U-shaped block. At this time, the drone camera inside the cavity and the drone camera inside the U-shaped block perform comprehensive video sampling of the outer surface of the aircraft when the aircraft passes, and transmit the video to the inside of the control box. The comparison module compares the collected video with the normal video, and marks the different point positions through the marking module, and finally displays it on the display screen. This facilitates comprehensive inspection of the aircraft skin without manual inspection, reducing labor intensity.

[0008] Preferably, the fixing assembly includes a movable ring, a permanent magnet, a limiting hole, a spring, a magnetic metal block and a limiting rod, the movable ring is movably embedded in the inner side of the U-shaped frame, the movable ring is located on the outside of the fixed ring, the limiting hole is opened on the outside of the drone camera, the limiting rod is movably inserted and arranged on the outside of the fixed ring, the magnetic metal block is fixed on one side of the limiting rod, the spring is fixed between the magnetic metal block and the fixed ring, the spring is sleeved on the outside of the limiting rod, and the permanent magnet is embedded and fixed on the inner side wall of the movable ring. When in use, the movable ring is rotated so that the permanent magnet is aligned with the magnetic metal block. At this time, the magnetic force attracts the magnetic metal block to move, pulling the spring to a stretched state, and then the drone camera is inserted into the fixed ring. Thereafter, the movable ring is rotated so that the magnetic metal block is misaligned with the permanent magnet, and the spring drives the limiting rod to reset, so that the limiting rod is inserted into the limiting hole, so that the installation of the drone camera is completed, so that the drone camera is fixed on the inner side wall of the U-shaped frame, which facilitates the installation and disassembly of the drone camera.

[0009] Preferably, the protective mechanism includes a baffle, a transparent plate, a sealing ring and a groove body. The sealing ring is adhesively fixed to the inner wall of the cavity, the transparent plate is slidably arranged on the inner side of the sealing ring, the baffle is fixed on the inner wall of the cavity, two baffles are provided, which are symmetrically installed on both sides of the cavity, the transparent plate is placed on the baffle, and the groove body is opened at the top of the sealing ring. When in use, the transparent plate is used to ensure the normal video acquisition of the drone camera, and the sealing ring is used to seal the position between the transparent plate and the inner wall of the cavity to prevent water from entering the cavity.

[0010] Preferably, the cleaning mechanism includes a motor, a first water diversion trough, a second water diversion trough, a screw, a slider, a cleaning plate and cleaning cotton. The first water diversion trough is provided on a fixed block, the second water diversion trough is provided on a main body of the road, the second water diversion trough is aligned with the first water diversion trough, the motor is fixed on the inner wall of the first water diversion trough, the screw is fixed at the output end of the motor, the slider is threadedly sleeved on the outside of the screw, the slider is slidably arranged inside the first water diversion trough, the cleaning plate is fixed at the top of the slider, the cleaning cotton is fixed at the lower end of the cleaning plate by Velcro, and the bottom end of the cleaning cotton is tightly attached to the top of the transparent plate. When in use, the motor is started, and the motor drives the screw to rotate, so that the slider moves along the screw, thereby moving along the inside of the first water diversion trough, driving the cleaning plate to move, and thereby driving the cleaning cotton to move, which is convenient for cleaning the top of the transparent plate and ensuring the clarity of the video captured by the drone camera inside the cavity.

[0011] Preferably, there is friction between the movable ring and the U-shaped frame to hinder the rotation of the movable ring.

[0012] Preferably, two limit rods are provided, which are symmetrically installed on both sides of the fixing ring, and two limit holes are opened, which are symmetrically opened on both sides of the drone camera, and the limit rods are matched with the limit holes.

[0013] Preferably, two permanent magnets are provided and symmetrically installed on both sides of the movable ring.

[0014] Preferably, there are two grooves, which are symmetrically arranged on both sides of the top of the sealing ring.

[0015] Compared with the prior art, the present invention has the following beneficial effects:

[0016] 1. The present invention inputs a normal aircraft skin video through an input module and stores it inside a storage module. When in use, the aircraft moves along the main road and moves along the marking line through the U-shaped block. At this time, the drone camera inside the cavity and the drone camera inside the U-shaped block perform comprehensive video sampling of the aircraft's outer surface when the aircraft passes, and transmit the video to the inside of the control box. The comparison module compares the collected video with the normal video, and marks the different points through the marking module, and finally displays it on the display screen. This facilitates comprehensive inspection of the aircraft skin, eliminates the need for manual inspection, and reduces labor intensity.

[0017] 2. When in use, the present invention rotates the movable ring to align the permanent magnet with the magnetic metal block. At this time, the magnetic force attracts the magnetic metal block to move, pulling the spring to a stretched state, and then the drone camera is inserted into the fixed ring. Thereafter, the movable ring is rotated to dislocate the magnetic metal block from the permanent magnet. The spring drives the limit rod to reset, so that the limit rod is inserted into the limit hole. In this way, the installation of the drone camera is completed, so that the drone camera is fixed on the inner wall of the U-shaped frame, which facilitates the installation and disassembly of the drone camera.

[0018] 3. When the present invention is in use, the motor is started, and the motor drives the screw to rotate, so that the slider moves along the screw, and thus moves along the inside of the first water diversion trough, driving the cleaning plate to move, thereby driving the cleaning cotton to move, making it convenient to clean the top of the transparent plate and ensure the clarity of the video captured by the drone camera inside the cavity. BRIEF DESCRIPTION OF THE DRAWINGS

[0019] Figure 1 This is a schematic diagram of the overall structure of an aircraft skin damage identification system according to the present invention;

[0020] Figure 2 This is a first cross-sectional view of an aircraft skin damage identification system according to the present invention;

[0021] Figure 3 This is a second cross-sectional view of an aircraft skin damage identification system according to the present invention;

[0022] Figure 4 This is an enlarged schematic diagram of an aircraft skin damage identification system A according to the present invention;

[0023] Figure 5 This is an enlarged schematic diagram of an aircraft skin damage identification system B according to the present invention;

[0024] Figure 6 This is an enlarged schematic diagram of an aircraft skin damage identification system C of the present invention.

[0025] In the figure: 1. Road body; 2. Fixed block; 3. Marking line; 4. U-shaped block; 5. Second water diversion trough; 6. First water diversion trough; 7. Control box; 8. Movable ring; 9. Motor; 10. Screw; 11. Slider; 12. Cleaning plate; 13. Cleaning cotton; 14. Cavity; 15. Fixed ring; 16. UAV camera; 17. Sealing ring; 18. Transparent plate; 19. Trough body; 20. Baffle; 21. Limit hole; 22. Limit rod; 23. Spring; 24. Magnetic metal block; 25. Permanent magnet. DETAILED DESCRIPTION

[0026] The following will clearly and completely describe the technical solutions in the embodiments of the present invention in conjunction with the accompanying drawings. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without making creative efforts are within the scope of protection of the present invention.

[0027] See also Figure 1-6 The present invention provides a technical solution: an aircraft skin damage identification system, comprising a road body 1 and a fixed block 2, the fixed block 2 is embedded and fixed inside the road body 1, a U-shaped block 4 is fixed on the top of the fixed block 2 by bolts, a first detection mechanism is provided on the inside of the U-shaped block 4, a cavity 14 is opened at the center of the fixed block 2, a second detection mechanism is provided inside the cavity 14, a protective mechanism is provided on the top of the cavity 14, a cleaning mechanism for convenient cleaning of the protective mechanism is provided inside the fixed block 2, a marking line 3 is engraved on the top of the road body 1, a control mechanism is provided on one side of the U-shaped frame 4, the first detection mechanism includes a drone camera 16, a fixing ring 15 and a fixing assembly, the fixing ring 15 is embedded and fixed on the inside of the U-shaped block 4, the drone camera 16 is slidably provided inside the fixing ring 15, and the fixing assembly is provided on the outside of the fixing ring 15;

[0028] The second detection mechanism includes a drone camera 16 and a fixing ring 15 . The fixing ring 15 is welded and fixed to the bottom end of the cavity 14 , and the drone camera 16 is slidably arranged inside the fixing ring 15 .

[0029] The control mechanism includes a control box 7, and a display screen is fixedly embedded on one side of the control box 7. A storage module, an input module, a comparison module, a marking module and a control chip are arranged inside the control box 7. The storage module, the input module, the comparison module and the marking module are electrically connected to the control chip. The drone camera 16 is electrically connected to the control chip inside the control box 7. The normal aircraft skin video is input through the input module and stored inside the storage module. When in use, the aircraft moves along the road body 1 and moves along the marking line 3 through the U-shaped block 4. At this time, the drone camera 16 inside the cavity 14 and the drone camera 16 inside the U-shaped block 4 perform comprehensive video sampling of the outer surface of the aircraft when the aircraft passes, and transmit the video to the inside of the control box 7. The comparison module compares the collected video with the normal video, and marks the different point positions through the marking module, and finally displays it on the display screen. This facilitates comprehensive inspection of the aircraft skin without manual inspection, reducing labor intensity.

[0030] The fixing assembly includes a movable ring 8, a permanent magnet 25, a limiting hole 21, a spring 23, a magnetic metal block 24 and a limiting rod 22. The movable ring 8 is movably embedded in the inner side of the U-shaped frame 4, and the movable ring 8 is located on the outside of the fixed ring 15. There is friction between the movable ring 8 and the U-shaped frame 4 that hinders the rotation of the movable ring 8. The limiting hole 21 is provided on the outside of the drone camera 16. The limiting rod 22 is movably inserted and provided on the outside of the fixed ring 15. There are two limiting rods 22, which are symmetrically installed on both sides of the fixed ring 15. There are two limiting holes 21, which are symmetrically provided on both sides of the drone camera 16. The limiting rod 22 fits in the limiting hole 21. The magnetic metal block 24 is welded and fixed on one side of the limiting rod 22. The spring 23 is welded and fixed between the magnetic metal block 24 and the fixed ring 15, the spring 23 is sleeved on the outside of the limit rod 22, and the permanent magnet 25 is embedded and fixed on the inner wall of the movable ring 8. There are two permanent magnets 25, which are symmetrically installed on both sides of the movable ring 8. When in use, the movable ring 8 is rotated to align the permanent magnet 25 with the magnetic metal block 24. At this time, the magnetic force attracts the magnetic metal block 24 to move, pulling the spring 23 to a stretched state, and then the drone camera 16 is inserted into the fixed ring 15. Thereafter, the movable ring 8 is rotated to make the magnetic metal block 24 misaligned with the permanent magnet 25. The spring 23 drives the limit rod 22 to reset, so that the limit rod 22 penetrates into the limit hole 21. In this way, the installation of the drone camera 16 is completed, so that the drone camera 16 is fixed on the inner wall of the U-shaped frame 4, which facilitates the installation and disassembly of the drone camera 16.

[0031] The protective mechanism includes a baffle 20, a transparent plate 18, a sealing ring 17 and a groove body 19. The sealing ring 17 is adhesively fixed to the inner wall of the cavity 14, and the transparent plate 18 is slidably arranged on the inner side of the sealing ring 17. The baffle 20 is welded and fixed to the inner wall of the cavity 14. Two baffles 20 are provided, which are symmetrically installed on both sides of the interior of the cavity 14. The transparent plate 18 is placed on the baffle 20, and the groove body 19 is opened at the top of the sealing ring 17. There are two groove bodies 19, which are symmetrically opened on both sides of the top of the sealing ring 17. When in use, the transparent plate 18 is used to ensure the normal video acquisition of the drone camera 16, and the sealing ring 17 is used to seal the position between the transparent plate 18 and the inner wall of the cavity 14 to prevent water from entering the interior of the cavity 14.

[0032] The cleaning mechanism includes a motor 9, a first water diversion trough 6, a second water diversion trough 5, a screw 10, a slider 11, a cleaning plate 12 and a cleaning cotton 13. The first water diversion trough 6 is opened on the fixed block 2, the second water diversion trough 5 is opened on the road body 1, the second water diversion trough 5 is aligned with the first water diversion trough 6, the motor 9 is fixed to the inner wall of the first water diversion trough 6 through a mounting bracket, the screw 10 is fixed to the output end position of the motor 9 through a coupling, the slider 11 is connected to the outside of the screw 10 by a threaded sleeve, and the slider 11 is slidably arranged in the first water diversion trough 6 Internally, the cleaning plate 12 is fixed to the top of the slider 11 by bolts, and the cleaning cotton 13 is fixed to the lower end of the cleaning plate 12 by Velcro. The bottom end of the cleaning cotton 13 is tightly attached to the top of the transparent plate 18. When in use, the motor 9 is started, and the motor 9 drives the screw 10 to rotate, so that the slider 11 moves along the screw 10, thereby moving along the inside of the first water diversion trough 6, driving the cleaning plate 12 to move, thereby driving the cleaning cotton 13 to move, making it convenient to clean the top of the transparent plate 18 and ensuring the clarity of the video captured by the drone camera 16 inside the cavity 14.

[0033] Working principle: A normal aircraft skin video is input through the input module and stored inside the storage module. When in use, the aircraft moves along the road body 1 and moves along the marking line 3 through the U-shaped block 4. At this time, the drone camera 16 inside the cavity 14 and the drone camera 16 inside the U-shaped block 4 perform comprehensive video sampling of the aircraft's outer surface when the aircraft passes, and transmit the video to the inside of the control box 7. The comparison module compares the collected video with the normal video, and marks the different points through the marking module, and finally displays it on the display screen. This facilitates comprehensive inspection of the aircraft skin without manual inspection, reducing labor intensity.

[0034] During use, the movable ring 8 is rotated so that the permanent magnet 25 is aligned with the magnetic metal block 24. At this time, the magnetic force attracts the magnetic metal block 24 to move, pulling the spring 23 to a stretched state, and then the drone camera 16 is inserted into the fixed ring 15. Thereafter, the movable ring 8 is rotated so that the magnetic metal block 24 and the permanent magnet 25 are misaligned. The spring 23 drives the limiting rod 22 to reset, so that the limiting rod 22 is inserted into the limiting hole 21. In this way, the installation of the drone camera 16 is completed, so that the drone camera 16 is fixed to the inner wall of the U-shaped frame 4, which facilitates the installation and disassembly of the drone camera 16.

[0035] During use, the transparent plate 18 ensures the normal video collection of the drone camera 16, and the sealing ring 17 seals the position between the transparent plate 18 and the inner wall of the cavity 14 to prevent water from entering the cavity 14;

[0036] When in use, the motor 9 is started, and the motor 9 drives the screw 10 to rotate, so that the slider 11 moves along the screw 10, thereby moving along the inside of the first water diversion trough 6, driving the cleaning plate 12 to move, thereby driving the cleaning cotton 13 to move, making it convenient to clean the top of the transparent plate 18 and ensure the clarity of the video captured by the drone camera 16 inside the cavity 14.

[0037] It should be noted that, in this document, relational terms such as first and second, etc., are used only to distinguish one entity or operation from another entity or operation, and do not necessarily require or imply any actual relationship or order between these entities or operations. Moreover, the terms "comprises," "comprising," or any other variations thereof are intended to cover non-exclusive inclusion, such that a process, method, article, or apparatus that includes a list of elements includes not only those elements but also other elements not explicitly listed, or elements inherent to such process, method, article, or apparatus.

[0038] While embodiments of the present invention have been shown and described, it will be appreciated by those skilled in the art that various changes, modifications, substitutions, and variations may be made to these embodiments without departing from the principles and spirit of the invention, and that the scope of the invention is defined by the appended claims and their equivalents.

Claims

1. An aircraft skin damage identification system, comprising a road body (1) and a fixed block (2), characterized in that: The fixed block (2) is embedded and fixed inside the road body (1); a U-shaped block (4) is fixedly provided on the top of the fixed block (2); a first detection mechanism is provided inside the U-shaped block (4); a cavity (14) is provided at the center of the fixed block (2); a second detection mechanism is provided inside the cavity (14); a protective mechanism is provided at the top of the cavity (14); a cleaning mechanism for convenient cleaning of the protective mechanism is provided inside the fixed block (2); a marking line (3) is engraved on the top of the road body (1); a control mechanism is provided on one side of the U-shaped frame (4); the first detection mechanism includes a drone camera (16), a fixing ring (15) and a fixing assembly; the fixing ring (15) is embedded and fixed inside the U-shaped block (4); the drone camera (16) is slidably provided inside the fixing ring (15); and the fixing assembly is provided outside the fixing ring (15); The second detection mechanism comprises a drone camera (16) and a fixing ring (15), wherein the fixing ring (15) is fixed at the bottom end inside the cavity (14), and the drone camera (16) is slidably arranged inside the fixing ring (15).

2. The aircraft skin damage identification system according to claim 1, characterized in that: The control mechanism comprises a control box (7), a display screen is fixedly mounted on one side of the control box (7), a storage module, an input module, a comparison module, a marking module and a control chip are arranged inside the control box (7), the storage module, the input module, the comparison module, the marking module and the control chip are electrically connected, and the drone camera (16) is electrically connected to the control chip inside the control box (7).

3. The aircraft skin damage identification system according to claim 2, characterized in that: The fixing assembly comprises a movable ring (8), a permanent magnet (25), a limiting hole (21), a spring (23), a magnetic metal block (24) and a limiting rod (22); the movable ring (8) is movably embedded in the inner side of the U-shaped frame (4); the movable ring (8) is located outside the fixed ring (15); the limiting hole (21) is opened outside the drone camera (16); the limiting rod (22) is movably inserted and arranged outside the fixed ring (15); the magnetic metal block (24) is fixed on one side of the limiting rod (22); the spring (23) is fixed between the magnetic metal block (24) and the fixed ring (15); the spring (23) is sleeved on the outside of the limiting rod (22); and the permanent magnet (25) is embedded and fixed on the inner side wall of the movable ring (8).

4. The aircraft skin damage identification system according to claim 3, characterized in that: The protective mechanism comprises a baffle (20), a transparent plate (18), a sealing ring (17) and a groove body (19); the sealing ring (17) is bonded and fixed on the inner wall of the cavity (14); the transparent plate (18) is slidably arranged on the inner side of the sealing ring (17); the baffle (20) is fixed on the inner wall of the cavity (14); two baffles (20) are provided and symmetrically installed on both sides of the cavity (14); the transparent plate (18) is placed on the baffle (20); and the groove body (19) is opened at the top of the sealing ring (17).

5. The aircraft skin damage identification system according to claim 4, characterized in that: The cleaning mechanism comprises a motor (9), a first water diversion trough (6), a second water diversion trough (5), a screw (10), a slider (11), a cleaning plate (12) and cleaning cotton (13); the first water diversion trough (6) is provided on a fixed block (2); the second water diversion trough (5) is provided on a road main body (1); the second water diversion trough (5) is aligned with the first water diversion trough (6); the motor (9) is fixed on the inner side wall of the first water diversion trough (6); the screw (10) is fixed at the output end of the motor (9); the slider (11) is sleeved on the outside of the screw (10) by a thread; the slider (11) is slidably arranged inside the first water diversion trough (6); the cleaning plate (12) is fixed on the top of the slider (11); the cleaning cotton (13) is fixed to the lower end of the cleaning plate (12) by means of Velcro; and the bottom end of the cleaning cotton (13) is in close contact with the top of the transparent plate (18).

6. The aircraft skin damage identification system according to claim 5, characterized in that: There is friction between the movable ring (8) and the U-shaped frame (4) that hinders the rotation of the movable ring (8).

7. The aircraft skin damage identification system according to claim 6, characterized in that: There are two limit rods (22) symmetrically mounted on both sides of the fixing ring (15); there are two limit holes (21) symmetrically opened on both sides of the drone camera (16); the limit rods (22) are matched with the limit holes (21).

8. The aircraft skin damage identification system according to claim 7, characterized in that: Two permanent magnets (25) are provided and symmetrically mounted on both sides of the inside of the movable ring (8).

9. The aircraft skin damage identification system according to claim 8, characterized in that: There are two grooves (19) symmetrically arranged at both sides of the top of the sealing ring (17).

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