Automatic flaw detection recording device for aircraft leveling component

Abstract

An automatic flaw detection recording device for an aircraft leveling component comprises a loading frame, mounting plates are arranged at all corners of the loading frame, adjustable adsorption structures are arranged on the mounting plates, and a movable frame, a power source structure and a main control box which are movably matched with the loading frame are arranged on the loading frame. A flaw detection structure, a first adjusting seat and a second connecting seat which are movably matched with the movable frame are arranged on the movable frame. By the adoption of the structure, flaw detection operation is conducted on flat-surface components, automatic flaw detection is conducted after positioning installation, consumption of labor cost is greatly reduced, automatic operation is achieved, and more time and labor are saved; synchronous video recording is performed in the flaw detection process, and a damaged area is accurately and quickly found according to records of videos and flaw detection data, so that subsequent analysis and quality control are facilitated; the device is flexible in overall structure, automatic in operation, suitable for being additionally installed on the outer surfaces of various flattening parts for use and high in practicability.

Description

TECHNICAL FIELD

[0001] The utility model relates to the technical field of aircraft maintenance and repair, especially an automatic flaw detection recording device for aircraft flat parts. BACKGROUND

[0002] In the aviation industry, ensuring the safety of the aircraft is of vital importance. In order to ensure the integrity of the aircraft structure, it is essential to regularly inspect each component of the aircraft. Traditionally, flaw detection is usually completed manually by visual, magnetic powder, penetration or ultrasonic wave methods to detect surface and internal defects. This method relies on the experience and technical level of the operator, requiring a large amount of manpower cost. However, in fact, in aircraft maintenance and repair, the surface of many aircraft components is flat, and the flaw detection operation at such locations is easier than that at curved locations. Therefore, how to reduce the consumption of manpower cost and improve the efficiency of flaw detection and repair has become a problem to be solved.

[0003] In addition, the traditional flaw detection recording method is mostly manual recording, which not only consumes time and effort, but also makes data management and traceability difficult, which is not conducive to subsequent analysis and quality control. SUMMARY

[0004] The technical problem to be solved by the utility model is to provide an automatic flaw detection recording device for aircraft flat parts, which is suitable for flaw detection operation on flat surface components, automatically detects flaws after positioning and installation, greatly reduces the consumption of manpower cost, and is more time-saving and labor-saving. The device records videos and flaw detection data simultaneously during the flaw detection process, accurately and quickly finds the damage area according to the video and flaw detection data, is convenient for subsequent analysis and quality control, has a flexible overall structure, is automatically operated, is suitable for being used on the outer surface of various flat parts, and has strong practicality.

[0005] To solve the above technical problems, the utility model adopts the technical scheme of an automatic flaw detection recording device for aircraft flat parts, which comprises a loading frame, each corner of the loading frame is provided with a mounting plate, the mounting plate is provided with an adjustable adsorption structure, the loading frame is provided with a moving frame, a power supply structure and a main control box which move in cooperation with the loading frame, the moving frame is provided with a flaw detection structure, a first adjusting seat and a second connecting seat which move in cooperation with the moving frame, the first adjusting seat is threadedly connected with a first lead screw, the two ends of the first lead screw are connected with the loading frame through the first connecting seat, the first connecting seat is provided with a first motor, the output end of the first motor is connected with the first lead screw, a second lead screw is arranged between the first adjusting seat and the second connecting seat, the second lead screw is threadedly connected with the flaw detection structure, the second connecting seat is provided with a second motor, and the output end of the second motor is connected with the second lead screw.

[0006] In the preferred scheme, the adjustable adsorption structure comprises an adjusting arm, one end of the adjusting arm is provided with a connecting shaft which is hingedly connected with the mounting plate, the connecting shaft is provided with a first locking sleeve, the other end of the adjusting arm is provided with an extension arm which is telescopically matched with the adjusting arm, one end of the extension arm is provided with a positioning shaft which is matched with a positioning groove arranged on the adjusting arm, the positioning shaft is provided with a second locking sleeve, and the other end of the extension arm is connected with the electric suction disc through a mounting head.

[0007] In the preferred scheme, the flaw detection structure comprises a sliding seat matched with the moving frame, the sliding seat is threadedly matched with the second lead screw, the sliding seat is connected with the electric push rod through a fixing seat, and the output end of the electric push rod is provided with a flaw detection head.

[0008] In the preferred scheme, the sliding seat is provided with a connecting frame, the connecting frame is provided with a flaw detection agent storage tank, the bottom of the flaw detection agent storage tank is provided with a discharge pipe, the discharge pipe is provided with an extrusion pump, the discharge pipe is connected with a distribution pipe through an extension pipe, the distribution pipe is provided with a plurality of discharge heads, and the end of the extension pipe away from the discharge pipe is connected with the flaw detection head through a linkage seat.

[0009] In the preferred scheme, the connecting frame is provided with an extension plate, and the extension plate is provided with a camera structure.

[0010] In the preferred scheme, the main control box is internally provided with a control module, a recording module, a storage module and an information receiving and sending module.

[0011] The automatic flaw detection recording device for the aircraft flat component has the following beneficial effects by adopting the above structure:

[0012] (1) The flaw detection operation of the flat surface component is automatically detected after positioning and installation, so that the consumption of labor cost is greatly reduced, and the automatic operation is more time-saving and labor-saving;

[0013] (2) The damage area is accurately and quickly found according to the video and flaw detection data, so that subsequent analysis and quality control are facilitated;

[0014] (3) The device has a flexible overall structure, is automatically operated, is suitable for being used on various flat components, and has high practicability. BRIEF DESCRIPTION OF DRAWINGS

[0015] The utility model will be further described in connection with the drawings and embodiments:

[0016] Fig. 1 It is the whole structure schematic diagram of the utility model.

[0017] Fig. 2 It is the loading frame and the moving adjusting structure schematic diagram thereof.

[0018] Fig. 3 The utility model discloses a flaw detection structure schematic view.

[0019] In the drawing: loading frame 1, mounting plate 2, adjusting arm 3, connecting shaft 4, first locking sleeve 5, positioning groove 6, extension arm 7, positioning shaft 8, second locking sleeve 9, mounting head 10, electric suction cup 11, moving frame 12, first adjusting seat 13, first lead screw 14, first connecting seat 15, first motor 16, second connecting seat 17, second motor 18, flaw detection structure 19, sliding seat 20, fixed seat 21, electric push rod 22, flaw detection head 23, connecting frame 24, flaw detection agent storage tank 25, discharge pipe 26, extruding pump 27, telescopic pipe 28, distribution pipe 29, discharge head 30, linkage seat 31, extension plate 32, camera structure 33, second lead screw 34, power supply structure 35, main control box 36. DETAILED DESCRIPTION

[0020] As Figs. 1-3 In the drawing: loading frame 1, mounting plate 2, adjusting arm 3, connecting shaft 4, first locking sleeve 5, positioning groove 6, extension arm 7, positioning shaft 8, second locking sleeve 9, mounting head 10, electric suction cup 11, moving frame 12, first adjusting seat 13, first lead screw 14, first connecting seat 15, first motor 16, second connecting seat 17, second motor 18, flaw detection structure 19, sliding seat 20, fixed seat 21, electric push rod 22, flaw detection head 23, connecting frame 24, flaw detection agent storage tank 25, discharge pipe 26, extruding pump 27, telescopic pipe 28, distribution pipe 29, discharge head 30, linkage seat 31, extension plate 32, camera structure 33, second lead screw 34, power supply structure 35, main control box 36.

[0021] In the preferred scheme, the adjustable adsorption structure includes adjusting arm 3, one end of adjusting arm 3 is provided with connecting shaft 4 that is hingedly connected with mounting plate 2, connecting shaft 4 is provided with first locking sleeve 5, the other end of adjusting arm 3 is provided with extension arm 7 that is telescopically connected with it, one end of extension arm 7 is provided with positioning shaft 8, positioning shaft 8 is matched with positioning groove 6 arranged on adjusting arm 3, positioning shaft 8 is provided with second locking sleeve 9, the other end of extension arm 7 is connected with electric suction cup 11 through mounting head 10.The overall structure of the device is flexible, automatic operation, and is suitable for various flat parts outer surface installation.

[0022] In the preferred scheme, the flaw detection structure 19 includes sliding seat 20 matched with moving frame 12, sliding seat 20 is threadedly matched with second lead screw 34, sliding seat 20 is connected with electric push rod 22 through fixed seat 21, and the output end of electric push rod 22 is provided with flaw detection head 23.It is flexible to adjust and can be adapted to the flaw detection needs of different parts.

[0023] In the preferred embodiment, the sliding seat 20 is provided with a connecting frame 24, and the connecting frame 24 is provided with a flaw detection agent storage tank 25. The bottom of the flaw detection agent storage tank 25 is provided with a discharge pipe 26, and the discharge pipe 26 is provided with an extrusion pump 27. The discharge pipe 26 is connected to a distribution pipe 29 through an extension pipe 28, and the distribution pipe 29 is provided with a plurality of discharge heads 30. The end of the extension pipe 28 away from the discharge pipe 26 is connected to the flaw detection head 23 through a linkage seat 31. The automatic feeding cooperates with the flaw detection, and the degree of automation is high.

[0024] In the preferred embodiment, the connecting frame 24 is provided with an extension plate 32, and the extension plate 32 is provided with a camera structure 33. The flaw detection record is convenient for subsequent accurate and rapid searching of the damage area, which is convenient for subsequent analysis and quality control.

[0025] In the preferred embodiment, the main control box 36 is provided with a control module, a recording module, a storage module, and an information receiving and sending module. The operation is flexible, the flaw detection path can be designed in advance, and the flaw detection information collection and video recording are matched, and the analysis is convenient.

[0026] The use method of the utility model is:

[0027] Adsorption and positioning:

[0028] The device realizes firm adhesion to the surface of the flat part of the airplane through the mounting plate 2 on the loading frame 1 and the adjustable adsorption structure thereon. The adjusting arm 3 and the extension arm 7 allow the electric suction cup 11 to be adjusted at different positions and angles to adapt to various shapes and flatness of the airplane parts. The first locking sleeve 5 and the second locking sleeve 9 ensure the stability and reliability of the adsorption structure during the working process.

[0029] Establishment of the moving platform:

[0030] The loading frame 1 is provided with a moving frame 12 matched with the movement thereof, and the moving frame provides a movement platform for the flaw detection structure. The power supply structure 35 provides necessary power support for the main control box 36 and other electrical components, and the main control box is responsible for overall coordination and control of the operation of each subsystem.

[0031] Precise positioning of the flaw detection head:

[0032] The flaw detection structure 19 is located above the moving frame 12 and can be moved along the X-axis direction by the first adjusting seat 13 driven by the first motor 16 through the first lead screw 14. At the same time, the flaw detection structure can also be moved along the Y-axis direction by the second motor 18 through the second lead screw 34. Such a double-axis moving system enables the flaw detection head to accurately reach any position in the to-be-detected area.

[0033] Application and recovery of flaw detection agent:

[0034] The probe tank 25 stores the probe agent used to show the defects, the extrusion pump 27 extracts the probe agent from the storage tank and transmits it to the distribution pipe 29 through the telescopic pipe 28. The multiple discharge heads 30 ensure that the probe agent is evenly distributed on the detection surface, so that the probe head 23 can effectively detect defects. The linkage seat 31 connects the end of the telescopic pipe and the probe head, ensuring that the probe agent is accurately applied near the detection point.

[0035] Image capture and data processing:

[0036] The camera structure 33 is installed on the extension plate 32 and moves with the probe head, which can capture image information generated during the detection process. These images are sent to the main control box 36 together with the probe results. The control module, recording module, storage module and information receiving and sending module contained in the main control box 36 work together to process, analyze and save all collected data for subsequent evaluation.

[0037] Automatic operation and remote monitoring:

[0038] The control system integrated in the main control box 36 not only manages the action process of the entire device, but also may have remote communication capability, allowing users to monitor or control the probe process through a network interface, realizing the possibility of unmanned operation.

[0039] The beneficial effects of the utility model are: for the detection operation of flat surface parts, automatic detection after positioning and installation, greatly reducing the consumption of labor cost, automatic operation, more time-saving and labor-saving; synchronous recording during the detection process, according to the video and probe data record, accurately and quickly find the damage area, which is convenient for subsequent analysis and quality control; the overall structure of the device is flexible, automatic operation, suitable for various flat parts, practicality is strong.

Claims

1. An automatic flaw detection recording device for a flat part of an aircraft, comprising a loading rack (1), characterized in that: The mounting plate (2) is provided on each corner of the loading frame (1), and an adjustable adsorption structure is arranged on the mounting plate (2); the loading frame (1) is provided with a moving frame (12), a power supply structure (35) and a main control box (36) which are matched with the movement of the loading frame (1); the moving frame (12) is provided with a flaw detection structure (19), a first adjusting seat (13) and a second connecting seat (17) which are matched with the movement of the moving frame (12); the first adjusting seat (13) is threadedly connected with a first lead screw (14); the two ends of the first lead screw (14) are connected with the loading frame (1) through a first connecting seat (15); the first connecting seat (15) is provided with a first motor (16); the output end of the first motor (16) is connected with the first lead screw (14); the second connecting seat (17) is provided with a second motor (18); the output end of the second motor (18) is connected with a second lead screw (34) which is threadedly connected with the flaw detection structure (19).

2. The automatic flaw detection recording apparatus for a flat part of an aircraft according to Claim 1, characterized by: The adjustable adsorption structure comprises an adjusting arm (3); one end of the adjusting arm (3) is provided with a connecting shaft (4) which is hingedly connected with the mounting plate (2); the connecting shaft (4) is provided with a first locking sleeve (5); the other end of the adjusting arm (3) is provided with an extension arm (7) which is telescopically connected with the adjusting arm (3); one end of the extension arm (7) is provided with a positioning shaft (8) which is matched with a positioning groove (6) arranged on the adjusting arm (3); the positioning shaft (8) is provided with a second locking sleeve (9); the other end of the extension arm (7) is connected with an electric suction cup (11) through a mounting head (10).

3. The apparatus for automatic flaw detection recording of a flattened component of an aircraft according to claim 1, characterized in that: The flaw detection structure (19) comprises a sliding seat (20) which is matched with the moving frame (12); the sliding seat (20) is threadedly connected with the second lead screw (34); the sliding seat (20) is connected with an electric push rod (22) through a fixing seat (21); the output end of the electric push rod (22) is provided with a flaw detection head (23).

4. The apparatus for automatic flaw detection recording of a flattened component of an aircraft according to claim 3, characterized in that: The sliding seat (20) is provided with a connecting frame (24); the connecting frame (24) is provided with a flaw detection agent storage tank (25); the bottom of the flaw detection agent storage tank (25) is provided with a discharge pipe (26); the discharge pipe (26) is provided with an extrusion pump (27); the discharge pipe (26) is connected with a distribution pipe (29) through an extension pipe (28); the distribution pipe (29) is provided with a plurality of discharge heads (30); the end of the extension pipe (28) away from the discharge pipe (26) is connected with the flaw detection head (23) through a linkage seat (31).

5. The automatic flaw detection recording apparatus for a flat part of an aircraft according to Claim 4, characterized by: The connecting frame (24) is provided with an extension plate (32); the extension plate (32) is provided with a camera structure (33).

6. The automatic flaw detection recording apparatus for a flat part of an aircraft according to Claim 1, characterized by: The main control box (36) is provided with a control module, a recording module, a storage module and an information receiving and sending module.

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