An aircraft part contour inspection device

Abstract

The utility model discloses an appearance inspection device of aircraft parts, including outer frame, the upper end of outer frame is provided with the water tank, the inside bottom of water tank is provided with the support rod, the upper end of support rod is fixedly connected with the placing plate, the upper end of placing plate is placed with the aircraft parts, the top wall of outer frame is provided with the slot, the horizontal direction of slot is slidably provided with the sliding block, be provided with horizontal sliding device in the outer frame and with sliding block power connection, be provided with elevating gear in the sliding block, the lower end of elevating gear is connected with the spraying inspection device. The utility model belongs to the field of aircraft parts inspection technology, and specifically solves the appearance crack detection of aircraft parts in the prior art, adopts the naked eye observation mode, and the tiny crack is not easy to observe, and the observation failure problem is easy to cause, and an appearance inspection device of aircraft parts is provided.

Description

Technical Field

[0001] This utility model belongs to the field of aircraft parts inspection technology, specifically referring to an aircraft parts shape inspection device. Background Technology

[0002] External shape inspection of aircraft parts is a core quality control process in aircraft manufacturing, maintenance and modification. The main contents of the inspection include geometry, dimensional accuracy, surface quality and whether there are surface cracks.

[0003] In the existing technology, when inspecting cracks on the surface of parts, it is often necessary to observe whether there are cracks by human eyes. However, there is a drawback: tiny cracks on the surface of metal parts cannot be seen with the naked eye, which can easily lead to inspection errors. Therefore, improvements are needed. Utility Model Content

[0004] The technical problem this invention aims to solve is that in the prior art, when inspecting the appearance cracks of aircraft parts, visual observation is used, which makes it difficult to observe tiny cracks and easily leads to observation errors.

[0005] To solve the above problems, the technical solution adopted by this utility model is as follows: an aircraft parts shape inspection device, including an outer frame, a water tank at the upper end of the outer frame, a support rod at the bottom of the water tank, a placement plate fixed to the upper end of the support rod, an aircraft part placed on the upper end of the placement plate, a slot in the top wall of the outer frame, a slider slidably disposed horizontally in the slot, a horizontal sliding device in the outer frame and poweredly connected to the slider, a lifting device in the slider, and a spray inspection device connected to the lower end of the lifting device.

[0006] Furthermore, the spraying inspection device includes a connecting plate, which is horizontally connected to the lower end of the lifting device. The connecting plate is equipped with a water tank and three sets of nozzles for storing penetrant, water, and developer, respectively. Three sets of nozzles are arranged in a straight line at the lower end of the connecting plate. The nozzles can cover the aircraft parts. The nozzles are connected to the water tank by a pipeline and controlled by a pump.

[0007] Furthermore, the lifting device includes a bracket, which is fixed to the upper end of the slider. A second motor is mounted on the bracket. The output end of the second motor is connected to a vertically downward lead screw and rotates on the slider. A lifting rod passes vertically downward through the slider. The lower end of the lifting rod is fixed to a connecting plate, and the upper end of the lifting rod is horizontally fixed to a connecting rod and threadedly connected to the second lead screw.

[0008] Furthermore, the horizontal sliding device includes a motor, which is fixed to the side wall of the outer frame. The output end of the motor is connected to a lead screw, which is threadedly connected to the slider. A sliding rod is horizontally fixed in the slot and passes through the slider. By driving the slider to slide on the sliding rod through the lead screw, the nozzle can move left and right to complete the coverage spraying of the aircraft parts.

[0009] Furthermore, the slide rod is parallel to lead screw one, and the lifting rod is parallel to lead screw two.

[0010] Furthermore, a drain valve is provided at the bottom of the water tank.

[0011] The beneficial effects achieved by adopting the above-described structure are as follows:

[0012] 1. This utility model uses a spray inspection device to spray penetrant onto aircraft parts through a nozzle. Then, the residual penetrant on the surface is rinsed off with clean water. Finally, a developer is sprayed. If there are cracks, they will show color, allowing the cracks on the aircraft parts to be seen directly. This method can inspect even very small cracks.

[0013] 2. This utility model, by setting up a lifting device, uses a motor to drive a lead screw to rotate, which in turn drives a lifting rod to move up and down, thereby adjusting the height of the nozzle to spray the aircraft parts evenly.

[0014] 3. This utility model, by setting up a horizontal sliding device, drives a lead screw to rotate, and the lead screw drives a slider to slide in the slot, thereby adjusting the left and right position of the nozzle to spray and cover the aircraft parts from left to right. Attached Figure Description

[0015] Figure 1 This utility model relates to the overall structure of an aircraft parts shape inspection device. Figure 1 ;

[0016] Figure 2 This utility model relates to the overall structure of an aircraft parts shape inspection device. Figure 2 ;

[0017] Figure 3 This utility model relates to the overall structure of an aircraft parts shape inspection device. Figure 3 ;

[0018] Figure 4 This utility model relates to the overall structure of an aircraft parts shape inspection device. Figure 4 .

[0019] The components are as follows: 1. Outer frame; 2. Water tank; 3. Slot; 4. Slider; 5. Support rod; 6. Placement plate; 7. Aircraft parts; 8. Lifting device; 9. Horizontal sliding device; 10. Spraying inspection device; 11. Connecting plate; 12. Water bucket; 13. Nozzle; 14. Bracket; 15. Motor II; 16. Lead screw II; 17. Lifting rod; 18. Connecting rod; 19. Motor I; 20. Lead screw I; 21. Slide rod; 22. Drain valve. Detailed Implementation

[0020] The technical solution of this utility model will now be clearly and completely described with reference to the accompanying drawings. Obviously, the described embodiments are only some, not all, of the embodiments of this utility model. Based on the embodiments of this utility model, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of this utility model.

[0021] In the description of this utility model, unless otherwise explicitly specified and limited, the terms "set," "install," "connect," and "link" should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral connection; they can refer to a mechanical connection or an electrical connection; they can refer to a direct connection or an indirect connection through an intermediate medium; and they can refer to the internal connection of two components. Those skilled in the art can understand the specific meaning of the above terms in this application based on the specific circumstances.

[0022] like Figure 1-4 This utility model discloses an aircraft parts shape inspection device, including an outer frame 1, a water tank 2 at the upper end of the outer frame 1, a drain valve 22 at the bottom of the water tank 2, a support rod 5 at the bottom of the water tank 2, a placement plate 6 fixedly connected to the upper end of the support rod 5, an aircraft part 7 placed on the upper end of the placement plate 6, a slot 3 in the top wall of the outer frame 1, a slider 4 slidably arranged horizontally in the slot 3, a horizontal sliding device 9 in the outer frame 1 and poweredly connected to the slider 4, a lifting device 8 in the slider 4, and a spray inspection device 10 connected to the lower end of the lifting device 8.

[0023] like Figure 1-4 The spray inspection device 10 includes a connecting plate 11, which is horizontally connected to the lower end of the lifting device 8. A water tank 12 is provided on the connecting plate 11, and three sets of nozzles are provided to store penetrant, water and developer respectively. Three sets of nozzles 13 are arranged in a straight line at the lower end of the connecting plate 11. The nozzles 13 can cover the aircraft parts 7. The nozzles 13 are connected to the water tank 12 by a pipeline and controlled by a pump. Penetrant can be sprayed onto the aircraft parts 7 through the nozzles 13. The penetrant can penetrate into the tiny cracks. The surface of the aircraft parts 7 can be rinsed clean with water. Then the developer is sprayed onto the surface of the aircraft parts 7. If there are cracks, the penetrant will seep out and form red lines.

[0024] like Figure 1-4 The lifting device 8 includes a bracket 14, which is fixed to the upper end of the slider 4. A motor 15 is mounted on the bracket 14. The output end of the motor 15 is connected to a vertically downward lead screw 16 and rotates on the slider 4. A lifting rod 17 passes vertically downward through the slider 4. The lower end of the lifting rod 17 is fixed to the connecting plate 11, and the upper end of the lifting rod 17 is horizontally fixed to a connecting rod 18 and threadedly connected to the lead screw 16. The lifting rod 17 is parallel to the lead screw 16. By rotating the lead screw 16, the connecting plate 11 is raised or lowered, thereby adjusting the height of the nozzle 13.

[0025] like Figure 1-3 The horizontal sliding device 9 includes a motor 19, which is fixed to the side wall of the outer frame 1. The output end of the motor 19 is connected to a lead screw 20, which is threadedly connected to the slider 4. A slide rod 21 is horizontally fixed in the slot 3 and passes through the slider 4. The slide rod 21 is parallel to the lead screw 20. The slider 4 is driven to slide on the slide rod 21 by the lead screw 20, which can realize the left and right movement of the nozzle 13 to complete the coverage spraying of the aircraft parts 7.

[0026] In practical use, when it is necessary to inspect the appearance of aircraft part 7 for external cracks, place aircraft part 7 on the placement plate 6, and then drive the connecting rod 18 to slide by starting motor 15 and lead screw 16. The lifting rod 17 will rise and fall in the slider 4, thereby adjusting the height of the nozzle 13. The water tank 12 containing penetrant sprays penetrant into the nozzle 13. By starting motor 19 and lead screw 20, the slider 4 is driven to slide in the slot 3, and the nozzle 13 can spray penetrant evenly and comprehensively onto aircraft part 7. If aircraft part 7 has cracks, the penetrant will penetrate into the cracks. Then, the aircraft part 7 is rinsed by spraying clean water through the water tank 12 containing clean water. The penetrant on the surface of the part will be washed away. Then, the aircraft part 7 is sprayed with developer through the water tank 12 containing developer. The developer and penetrant combine to form a red color, which indicates that there are tiny cracks in aircraft part 7.

[0027] The solution in the water tank 2 can be drained through the drain valve 22. Raise the nozzle 13 and remove the aircraft part 7 from the placement plate 6.

[0028] It should be noted that the motor 19, motor 2 15, and all pumps involved in the solution need to be connected to the power supply via cables and controlled to start and stop via control switches. This is existing technology, and those skilled in the art can clearly understand its principles and use it, so it will not be described in detail here.

[0029] The present invention and its embodiments have been described above. This description is not restrictive, and the accompanying drawings are only one embodiment of the present invention; the actual structure is not limited thereto. In conclusion, if those skilled in the art are inspired by this description and design similar structures and embodiments without departing from the inventive spirit of the present invention, such designs should fall within the protection scope of the present invention.

Claims

1. A device for inspecting the shape of aircraft parts, comprising an outer frame (1), characterized in that: The upper end of the outer frame (1) is provided with a water tank (2), the bottom of the water tank (2) is provided with a support rod (5), the upper end of the support rod (5) is fixed with a placement plate (6), the upper end of the placement plate (6) is placed with an aircraft part (7), the top wall of the outer frame (1) is provided with a slot (3), a slider (4) is slidably provided in the slot (3) in the horizontal direction, the outer frame (1) is provided with a horizontal sliding device (9) and is poweredly connected to the slider (4), the slider (4) is provided with a lifting device (8), and the lower end of the lifting device (8) is connected to a spray inspection device (10).

2. The shape inspection device for aircraft parts according to claim 1, characterized in that: The spraying inspection device (10) includes a connecting plate (11), which is horizontally connected to the lower end of the lifting device (8). The connecting plate (11) is provided with three water tanks (12) for storing penetrant, water and developer respectively. The lower end of the connecting plate (11) has three nozzles (13) that can cover the aircraft parts (7) arranged in a straight line. The nozzles (13) are connected to the corresponding water tanks (12) through pipelines and pumps.

3. The shape inspection device for aircraft parts according to claim 2, characterized in that: The lifting device (8) includes a bracket (14), which is fixed to the upper end of the slider (4). A second motor (15) is provided on the bracket (14). The output end of the second motor (15) is connected to a vertically downward lead screw (16), and the lead screw (16) is rotatably mounted on the slider (4). A lifting rod (17) is vertically downward through the slider (4). The lower end of the lifting rod (17) is fixed to the connecting plate (11), and the upper end of the lifting rod (17) is horizontally fixed to a connecting rod (18) threadedly connected to the lead screw (16).

4. The shape inspection device for aircraft parts according to claim 3, characterized in that: The horizontal sliding device (9) includes a motor (19), which is fixed to the side wall of the outer frame (1). The output end of the motor (19) is connected to a lead screw (20), which is threadedly connected to the slider (4). A slide rod (21) parallel to the lead screw (20) is horizontally fixed in the slot (3), and the slide rod (21) passes through the slider (4).

5. The shape inspection device for aircraft parts according to claim 4, characterized in that: The lifting rod (17) is parallel to the lead screw (16).

6. The shape inspection device for aircraft parts according to claim 1, characterized in that: A drain valve (22) is provided at the bottom of the water tank (2).

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