Aviation shaft sleeve part roundness detection device

Abstract

The utility model relates to the field of roundness detection of aviation shaft sleeve type parts, in particular to a roundness detection device for aviation shaft sleeve type parts. The utility model provides the aviation shaft sleeve part roundness detection device which can clamp aviation shaft sleeve parts with different sizes, can replace the mounting block, is convenient for detecting the aviation shaft sleeve parts with different sizes, and is high in use flexibility. An aviation shaft sleeve type part roundness detection device comprises a bottom frame, a lead screw and the like, and the lower portion of the bottom frame is rotationally connected with the lead screw. According to the clamping device, the rotating disc rotates, so that a second sliding frame moves inwards, a clamping frame makes contact with the outer side of a part for clamping, then a mounting block is rotated, so that the mounting block moves rightwards to be taken out for replacement, aviation shaft sleeve parts of different sizes can be clamped, the mounting block can be replaced, and the clamping efficiency is improved. Aviation shaft sleeve parts of different sizes can be detected conveniently, and the use flexibility is high.

Description

Technical Field

[0001] This utility model relates to the field of roundness detection of aircraft bushing parts, and in particular to a roundness detection device for aircraft bushing parts. Background Technology

[0002] Roundness inspection of aerospace bushing parts refers to the process of evaluating the degree of deviation of the inner or outer diameter surface of the bushing from an ideal circle using specific measurement techniques and equipment. Existing roundness inspection of aerospace bushing parts usually involves first fixing the aerospace bushing parts with a fixture, and then rotating the roundness inspection instrument in contact with the inner side of the aerospace bushing parts for inspection. However, the current device is not easy to adjust, can only clamp aerospace bushing parts of a fixed size, and the inspection instrument is a one-piece structure, which is inconvenient to adjust and replace. It is not convenient to inspect aerospace bushing parts of different sizes, and its use is not flexible enough and is quite inconvenient.

[0003] Therefore, it is necessary to design a roundness detection device for aerospace bushing parts of different sizes that can clamp them, allows for the replacement of mounting blocks, facilitates the inspection of aerospace bushing parts of different sizes, and offers high flexibility. Utility Model Content

[0004] To overcome the shortcomings of current devices, such as inconvenience in adjustment, limited ability to clamp fixed-size aerospace bushing parts, and the inconvenience of adjusting and replacing the integrated testing instrument, making it difficult to test aerospace bushing parts of different sizes and lacking flexibility in use, this utility model provides an aerospace bushing part roundness testing device that can clamp aerospace bushing parts of different sizes, allows for the replacement of mounting blocks, facilitates the testing of aerospace bushing parts of different sizes, and offers greater flexibility in use.

[0005] The technical implementation scheme of this utility model is as follows: a roundness detection device for aerospace bushing parts, comprising a base frame, a lead screw, a common motor, a guide rod, a first sliding frame, a detection component, an opening and closing component, and a clamping and buffering component. The lead screw is rotatably connected to the lower part of the base frame, and a common motor is connected to the lower left side of the base frame. The output shaft of the common motor is connected to the lead screw. Guide rods are connected to both the front and rear parts of the base frame, and the first sliding frame is slidably connected between the guide rods. The first sliding frame is threadedly connected to the lead screw. The upper part of the first sliding frame is provided with a detection component capable of detecting the roundness of aerospace bushing parts of different sizes. The right side of the base frame is provided with an opening and closing component capable of synchronous opening and closing. The opening and closing component is provided with a clamping and buffering component capable of clamping and buffering aerospace bushing parts of different sizes.

[0006] As a further preferred embodiment, the testing assembly includes a mounting block, an electric push rod, and a roundness detector. The mounting block is threadedly connected to the upper part of the first sliding frame. Electric push rods are connected to both the front and rear parts of the mounting block. Each extension end of the electric push rod is provided with a connecting block, and a roundness detector is rotatably connected to each connecting block.

[0007] As a further preferred embodiment, it also includes an opening and closing assembly, which includes a first motor, a rotating disk, a guide disk, a second motor, a gear, and a second sliding frame. The first motor is connected to the upper right side of the base frame, and the guide disk is connected to the output shaft of the first motor. The rotating disk is rotatably connected to the right side of the guide disk, and the second motor is connected to the lower front part of the guide disk. The gear is connected to the output shaft of the second motor, and a large gear ring is provided on the outer side of the rotating disk. The large gear ring meshes with the gear, and the second sliding frame is slidably connected to the upper, lower, front, and rear parts of the guide disk.

[0008] As a further preferred option, the rotating disk has multiple grooves, and the second sliding frame slides with the rotating disk through the grooves.

[0009] As a further preferred embodiment, it also includes a clamping buffer assembly, which includes a clamping frame and a telescopic spring. The clamping frames are slidably connected to each other on a portion of the second sliding frames that are close to each other, and each clamping frame is connected to an adjacent second sliding frame by a telescopic spring.

[0010] As a further preferred option, all clamping frames are arc-shaped structures.

[0011] The present invention has the following advantages: 1. The present invention rotates the rotating disk, causing the second sliding frame to move inward, so that the clamping frame contacts the outside of the part for clamping. Then, by rotating the mounting block, the mounting block moves to the right to be removed for replacement. This achieves the effect of being able to clamp aviation bushing parts of different sizes and replace the mounting block, which is convenient for testing aviation bushing parts of different sizes and has high flexibility of use.

[0012] 2. When the second sliding frame continues to move inward, it drives the clamping frame to move outward on the second sliding frame. The telescopic spring is compressed and contracted, and the part is buffered under the action of the telescopic spring. This achieves the ability to buffer and clamp aviation bushing parts, avoiding excessive clamping force that could damage the aviation bushing parts and affect the testing effect. Attached Figure Description

[0013] Figure 1 This is a three-dimensional structural diagram of the present invention.

[0014] Figure 2 This is a cross-sectional three-dimensional structural diagram of the lead screw and guide rod components of this utility model.

[0015] Figure 3 This is a three-dimensional structural diagram of the mounting block and electric push rod of this utility model.

[0016] Figure 4 This is a cross-sectional three-dimensional structural diagram of the rotating disk and guide disk and other components of this utility model.

[0017] Figure 5 This is a three-dimensional structural diagram of the second sliding frame and clamping frame of this utility model.

[0018] Among them: 1-base frame, 2-lead screw, 21-ordinary motor, 3-guide rod, 4-first sliding frame, 5-mounting block, 6-electric push rod, 7-roundness detector, 8-first motor, 9-rotary disk, 10-guide disk, 11-second motor, 12-gear, 13-second sliding frame, 14-clamping frame, 15-telescopic spring. Detailed Implementation

[0019] The present invention will be further described below with reference to specific embodiments. It should also be noted that, unless otherwise explicitly specified and limited, terms such as "setting," "installing," "connecting," and "linking" 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 the present invention based on the specific circumstances.

[0020] A roundness detection device for aircraft bushing parts, such as Figure 1 and Figure 2 As shown, it includes a base frame 1, a lead screw 2, a common motor 21, a guide rod 3, a first sliding frame 4, a detection component, an opening and closing component, and a clamping and buffering component. The lead screw 2 is rotatably connected to the lower part of the base frame 1. The common motor 21 is connected to the lower left side of the base frame 1. The output shaft of the common motor 21 is connected to the lead screw 2. Guide rods 3 are connected to both the front and rear parts of the base frame 1. The first sliding frame 4 is slidably connected between the guide rods 3. The first sliding frame 4 is threadedly connected to the lead screw 2. The detection component is provided on the upper part of the first sliding frame 4. The opening and closing component is provided on the right side of the base frame 1. The clamping and buffering component is provided on the opening and closing component.

[0021] like Figures 1-3 As shown, the detection assembly includes a mounting block 5, an electric push rod 6, and a roundness detector 7. The mounting block 5 is threadedly connected to the upper part of the first sliding frame 4. The electric push rod 6 is connected to both the front and rear parts of the mounting block 5. A connecting block is provided on the telescopic end of the electric push rod 6, and the roundness detector 7 is rotatably connected to the connecting block.

[0022] like Figure 1 and Figure 4As shown, it also includes an opening and closing assembly, which includes a first motor 8, a rotating disk 9, a guide disk 10, a second motor 11, a gear 12, and a second sliding frame 13. The first motor 8 is connected to the upper right side of the base frame 1. The guide disk 10 is connected to the output shaft of the first motor 8. The rotating disk 9 is rotatably connected to the right side of the guide disk 10. The rotating disk 9 has four sliding grooves. The second motor 11 is connected to the lower front part of the guide disk 10. The gear 12 is connected to the output shaft of the second motor 11. A large gear ring is provided on the outer side of the rotating disk 9. The large gear ring meshes with the gear 12. The second sliding frame 13 is slidably connected to the upper, lower, front, and rear parts of the guide disk 10. The second sliding frame 13 slides with the rotating disk 9 through the sliding grooves.

[0023] like Figure 1 , Figure 4 and Figure 5 As shown, it also includes a clamping buffer assembly, which includes a clamping frame 14 and a telescopic spring 15. The clamping frames 14 are slidably connected to the adjacent parts of the second sliding frames 13. The clamping frames 14 are all arc-shaped structures, which facilitate clamping and fixing. The clamping frames 14 are all connected to the adjacent second sliding frames 13 by a telescopic spring 15.

[0024] When using this device, first place the base frame 1 in the roundness detection area for aerospace bushing parts, then place the parts between the clamping frames 14. Next, start the second motor 11, driving the gear 12 to rotate. The gear 12 meshes with the large gear ring, causing the rotating disk 9 to rotate. This causes the second sliding frame 13 to move inward along the guide disk 10, making the clamping frame 14 contact the outside of the parts, thus clamping different aerospace bushing parts. As the second sliding frame 13 continues to move inward, it causes the clamping frame 14 to move outward on the second sliding frame 13. The telescopic spring 15 is compressed and contracts, buffering the parts under the action of the telescopic spring 15. This buffers the clamping of aerospace bushing parts, preventing excessive clamping force from damaging them and affecting the detection. Then, start the ordinary motor 21, driving the lead screw 2 to rotate, causing the first sliding frame 4 to move to the right along the guide rod 3 under the action of the thread, allowing the mounting block 5 to pass through the parts. Finally, start the electric push rod 6, driving the connecting block to move outward, thus allowing the roundness detection... The measuring instrument 7 contacts the inner side of the part, and then the first motor 8 is started, driving the guide plate 10 to rotate, causing the roundness measuring instrument 7 to rotate. The roundness measuring instrument 7 is used to inspect the aerospace bushing parts. When it is necessary to inspect aerospace bushing parts of different sizes, the mounting block 5 can be rotated, causing the mounting block 5 to move to the right under the action of the thread and be taken out. Then, the mounting block 5 with a similar size to the aerospace bushing part is connected to the first sliding frame 4. Then, the mounting block 5 is rotated, causing the mounting block 5 to move to the left under the action of the thread. This allows for clamping aerospace bushing parts of different sizes and allows for the replacement of the mounting block 5, which is convenient for inspecting aerospace bushing parts of different sizes and has high flexibility. After the inspection is completed, the second motor 11 is started in reverse, driving the gear 12 to rotate. The gear 12 meshes with the large gear ring, driving the rotating plate 9 to rotate, causing the second sliding frame 13 to move outward on the guide plate 10. The telescopic spring 15 returns to its original position, driving the clamping frame 14 to move and reset, so that the clamping frame 14 no longer contacts the outer side of the part.

[0025] Although this disclosure has been described with respect to only a limited number of embodiments, those skilled in the art who benefit from this disclosure will understand that various other embodiments can be devised without departing from the scope of this invention. Therefore, the scope of this invention should be limited only by the appended claims.

Claims

1. An apparatus for detecting roundness of an aviation bushing part, characterized in that, The utility model relates to a kind of aviation shaft sleeve class parts roundness detection device, including chassis (1), screw rod (2), ordinary motor (21), guide rod (3), first sliding frame (4), detection assembly, open-close assembly and clamping buffer assembly, screw rod (2) is rotatably connected in the lower part of chassis (1), ordinary motor (21) is connected in the left side of the lower part of chassis (1), ordinary motor (21) output shaft is connected with screw rod (2), guide rod (3) is connected in the front and rear of chassis (1), first sliding frame (4) is slidably connected between guide rod (3), first sliding frame (4) is screw thread connected with screw rod (2), detection assembly capable of carrying out roundness detection to different sizes aviation shaft sleeve class parts is equipped in the upper portion of first sliding frame (4), open-close assembly capable of carrying out synchronous opening and closing is equipped in the right part of chassis (1), clamping buffer assembly capable of carrying out clamping and buffering to different sizes aviation shaft sleeve class parts is equipped on open-close assembly.

2. The roundness detecting device for an aero bearing bushing part according to claim 1, wherein Detection assembly includes mounting block (5), electric push rod (6) and roundness detector (7), mounting block (5) is screw thread connected in the upper portion of first sliding frame (4), electric push rod (6) is connected in the front and rear of mounting block (5), connecting block is equipped on the telescopic end of electric push rod (6), roundness detector (7) is rotatably connected on connecting block.

3. The roundness detection device for aerospace bushing parts according to claim 1, characterized in that, It further includes open-close assembly, and the open-close assembly includes first motor (8), rotating disc (9), guide disc (10), second motor (11), gear (12) and second sliding frame (13), first motor (8) is connected in the right side of the upper portion of chassis (1), guide disc (10) is connected on the output shaft of first motor (8), rotating disc (9) is rotatably connected in the right part of guide disc (10), second motor (11) is connected in the front lower part of guide disc (10), gear (12) is connected on the output shaft of second motor (11), large gear ring is equipped on the outside of rotating disc (9), large gear ring and gear (12) are mutually engaged, second sliding frame (13) is slidably connected in the upper and lower front and rear of guide disc (10).

4. The roundness detecting device for an aero bearing bushing part according to claim 3, wherein Rotating disc (9) is opened with multiple sliding grooves, and second sliding frame (13) is slidably matched with rotating disc (9) through the sliding grooves.

5. A roundness detection device for aircraft bushing parts according to claim 1, characterized in that, It further includes clamping buffer assembly, and the clamping buffer assembly includes clamping frame (14) and telescopic spring (15), and the one of second sliding frame (13) is slidably connected with clamping frame (14) and is connected with telescopic spring (15) between adjacent second sliding frame (13).

6. The roundness detecting device for an aero bearing bushing part according to claim 5, wherein Clamping frame (14) is arc structure.

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