Flaw detector for aircraft hub maintenance

Abstract

The utility model discloses a flaw detector for aircraft hub maintenance, and relates to the technical field of aircraft hub maintenance. The flaw detector for aircraft hub maintenance comprises a workbench, a positioning mechanism and a cleaning mechanism, the positioning mechanism is arranged at the top of the workbench and comprises a hollow support, a threaded rod, an internal threaded block, a lifting plate and a pressing plate, and the outer wall of the threaded rod is in threaded connection with the interior of the internal threaded block; the outer wall of the internal thread block is slidably connected with the inner wall of the hollow support, a lifting plate is fixedly mounted on one side of the internal thread block, and the bottom of the lifting plate is rotatably connected with the top of a pressing plate through a rotating shaft; the cleaning mechanism is arranged at the top of the workbench and comprises a fixing plate and an electric push rod, and the fixing plate is fixedly installed at the top of the workbench. When the aircraft hub is clamped and fixed, a to-be-detected area on the surface of the hub is prevented from being shielded, so that the dark damage of the hub is fully detected as much as possible, the accuracy of a detection result is improved, and the flaw detection effect of the device is ensured.

Description

TECHNICAL FIELD

[0001] The utility model relates to aircraft hub maintenance technical field especially relates to a flaw detector for aircraft hub maintenance. BACKGROUND

[0002] Chinese patent document CN218727156U discloses a flaw detection mechanism for hub quality detection, including the casing, the bottom surface both sides of casing are equipped with connecting column, and the bottom of connecting column is equipped with bottom plate, the utility model discloses, the hub to be detected is placed on the bearing box, and the bidirectional screw rod is driven to rotate through the first motor, and the moving block is limited through the limiting block and the limiting groove, so that the moving block can move on the bidirectional screw rod, the fixed block on the top surface of moving block moves in the adjusting groove on the bearing box while moving, through the use of spring, can effectively make the clamping plate on the side of fixed block move, when the protective pad on the side surface of clamping plate abuts against the inner wall of hub, can clamp and limit hub, it is convenient to improve the stability of hub when detecting flaw, wherein through the use of protective pad, it can effectively reduce the risk of damage to the inner wall of hub caused by clamping impact force, and it is convenient to protect the hub, thereby facilitating the subsequent processing of the hub

[0003] The flaw detection mechanism for hub quality detection described above causes a lot of occlusion on the surface of the hub when in use, which may lead to missed detection of hidden damage in the occluded area of the hub, reduces the accuracy of the detection result, and affects the flaw detection effect of the device. UTILITY MODEL CONTENTS

[0004] The utility model discloses a flaw detection mechanism for aircraft hub maintenance, which can solve the problem of the flaw detection mechanism for hub quality detection described above, that is, the clamping plate causes a lot of occlusion on the surface of the hub when in use, which may lead to missed detection of hidden damage in the occluded area of the hub, reduces the accuracy of the detection result, and affects the flaw detection effect of the device

[0005] To achieve the above-mentioned purpose, the utility model provides the following technical scheme: a flaw detection mechanism for aircraft hub maintenance, including workbench, positioning mechanism and cleaning mechanism, positioning mechanism sets up at the top of workbench, and positioning mechanism includes hollow support, screw rod, internal thread block, lifting plate and pressing plate, the outer wall of screw rod is connected with the internal thread of internal thread block, the outer wall of internal thread block is connected with the inner wall of hollow support and slides, the one side of internal thread block is fixedly installed with lifting plate, and the bottom of lifting plate is rotatably connected with the top of pressing plate through the pivot; cleaning mechanism sets up at the top of workbench, and cleaning mechanism includes fixed plate and electric push rod, and the top of workbench is fixedly installed with fixed plate, and the one side of fixed plate is fixedly installed with electric push rod.

[0006] Preferably, the positioning mechanism further comprises a clutch motor, a rotating rod and a circular supporting plate, the top of the workbench is fixedly connected with the bottom of the hollow support, the inner top and the inner bottom of the hollow support are rotationally connected with the two ends of the threaded rod respectively, the top of the hollow support is fixedly installed with the clutch motor, the output shaft of the clutch motor is fixedly connected with one end of the threaded rod, the top of the workbench is rotationally connected with one end of the rotating rod, the other end of the rotating rod is fixedly connected with the bottom of the circular supporting plate, the aircraft hub is clamped and fixed, the surface of the hub to be detected is avoided from being shielded, the hidden damage of the hub is detected as much as possible, the accuracy of the detection result is improved, and the flaw detection effect of the device is ensured.

[0007] Preferably, the cleaning mechanism further comprises a sponge brush, the free end of the electric push rod passes through the fixed plate and is clampedly connected with one side of the sponge brush, dust and stains on the surface of the hub are automatically removed before detection, the workload of the staff during cleaning is reduced, the device can be applied to aircraft hubs of various sizes, and the availability and practicality of the device are improved.

[0008] Preferably, the bottom of the workbench is fixedly installed with a speed reducer, and the output shaft of the speed reducer is fixedly connected with one end of the rotating rod.

[0009] Preferably, the top of the circular supporting plate and the bottom of the pressing plate are both provided with anti-skid rubber pads.

[0010] Preferably, the top of the workbench is fixedly installed with a flaw detection assembly.

[0011] Preferably, the bottom of the workbench is fixedly installed with a plurality of groups of support rods distributed in a rectangular manner.

[0012] Compared with the prior art, the utility model has the beneficial effects that:

[0013] (1), the aircraft hub maintenance flaw detector, through the cooperation of the hollow support, the clutch motor, the threaded rod, the internal threaded block, the lifting plate, the pressing plate, the rotating rod and the circular supporting plate, the aircraft hub is clamped and fixed, the surface of the hub to be detected is avoided from being shielded, the hidden damage of the hub is detected as much as possible, the accuracy of the detection result is improved, and the flaw detection effect of the device is ensured.

[0014] (2), the aircraft hub maintenance flaw detector, through the cooperation of the fixed plate, the electric push rod and the sponge brush, dust and stains on the surface of the hub are automatically removed before detection, the workload of the staff during cleaning is reduced, the device can be applied to aircraft hubs of various sizes, and the availability and practicality of the device are improved. BRIEF DESCRIPTION OF DRAWINGS

[0015] The utility model is further illustrated in connection with the drawings and embodiments as follows:

[0016] Fig. 1 is a perspective view of the utility model;

[0017] Fig. 2 is a perspective view of the utility model from below;

[0018] Fig. 3 is a perspective view of the utility model from below.

[0019] The drawings show: 1, workbench; 2, positioning mechanism; 201, hollow support; 202, brake motor; 203, threaded rod; 204, internal threaded block; 205, lifting plate; 206, pressing plate; 207, rotating rod; 208, circular supporting plate; 3, cleaning mechanism; 301, fixed plate; 302, electric push rod; 303, sponge brush; 4, speed reducer motor; 5, flaw detection assembly; 6, supporting rod. DETAILED DESCRIPTION

[0020] This part will describe the specific embodiments of the utility model in detail, and the preferred embodiments of the utility model are shown in the drawings, and the drawings are used to supplement the description of the text part in the form of graphics, so that people can intuitively and visually understand each technical feature and the overall technical scheme of the utility model, but it cannot be understood as a limitation on the protection scope of the utility model.

[0021] Please refer to Figs. 1-3 The utility model provides a kind of technical scheme: a flaw detector for aircraft hub maintenance, including workbench 1, positioning mechanism 2 and cleaning mechanism 3, positioning mechanism 2 is set to the top of workbench 1, and positioning mechanism 2 includes hollow support 201, threaded rod 203, internal threaded block 204, lifting plate 205 and pressing plate 206, the outer wall of threaded rod 203 is connected with the internal thread of internal threaded block 204, the outer wall of internal threaded block 204 is slidably connected with the inner wall of hollow support 201, one side of internal threaded block 204 is fixedly installed with lifting plate 205, and the bottom of lifting plate 205 is rotatably connected with the top of pressing plate 206 by rotating shaft;Cleaning mechanism 3 is set to the top of workbench 1, and cleaning mechanism 3 includes fixed plate 301 and electric push rod 302, and the top of workbench 1 is fixedly installed with fixed plate 301, and one side of fixed plate 301 is fixedly installed with electric push rod 302;The bottom of workbench 1 is fixedly installed with speed reducer motor 4, and the output shaft of speed reducer motor 4 is fixedly connected with one end of rotating rod 207;The top of circular supporting plate 208 and the bottom of pressing plate 206 are provided with antiskid rubber pad;The top of workbench 1 is fixedly installed with flaw detection assembly 5;The bottom of workbench 1 is fixedly installed with multiple groups of rectangularly distributed supporting rods 6.

[0022] Secondly, the positioning mechanism 2 further includes a clutch motor 202, a rotating rod 207 and a circular supporting plate 208, the top of the workbench 1 is fixedly connected with the bottom of the hollow support 201, the inner top and the inner bottom of the hollow support 201 are rotationally connected with both ends of the threaded rod 203 respectively, the top of the hollow support 201 is fixedly installed with the clutch motor 202, the output shaft of the clutch motor 202 is fixedly connected with one end of the threaded rod 203, the top of the workbench 1 is rotationally connected with one end of the rotating rod 207, the other end of the rotating rod 207 is fixedly connected with the bottom of the circular supporting plate 208, the aircraft hub is clamped and fixed, at the same time, the surface of the hub to be detected is avoided from being shielded, the hidden damage of the hub is detected as much as possible, the accuracy of the detection result is improved, and the flaw detection effect of the device is ensured.

[0023] Further, the cleaning mechanism 3 further includes a sponge brush 303, the free end of the electric push rod 302 passes through the fixed plate 301 and is clampedly connected with one side of the sponge brush 303, dust and stains on the surface of the hub are automatically wiped off before detection, the workload of the staff during cleaning is reduced, the device can be applied to aircraft hubs of various sizes, and the availability and practicality of the device are improved.

[0024] Working principle: when the device is used, the aircraft hub to be detected is placed at the center position of the circular supporting plate 208, the clutch motor 202 is started to drive the threaded rod 203 to rotate, under the limiting of the hollow support 201, the inner threaded block 204 slides downward in the hollow support 201, the lifting plate 205 is driven to slide downward to one end, and then the pressing plate 206 is driven to press on the top of the aircraft hub, the aircraft hub is clamped and fixed in cooperation with the circular supporting plate 208, the rotating rod 207 is driven to rotate by starting the speed reducer 4, the circular supporting plate 208 is driven to rotate and the hub is continuously rotated, the sponge brush 303 is driven to move and adhere to the surface of the rotating hub by starting the electric push rod 302 to extend, and then the outer wall of the hub is continuously detected by starting the flaw detection assembly 5.

[0025] The above embodiment of the utility model is described in detail in combination with the drawings, but the utility model is not limited to the above embodiment, and various changes can be made within the knowledge range of ordinary skilled persons in the technical field without departing from the purpose of the utility model.

Claims

1. An aircraft wheel hub servicing flaw detector, characterized by, Include: Workbench (1); Positioning mechanism (2) is arranged on the top of the workbench (1), the positioning mechanism (2) includes hollow support (201), threaded rod (203), internal thread block (204), lifting plate (205) and pressing plate (206), the outer wall of the threaded rod (203) is connected with the internal thread of the internal thread block (204), the outer wall of the internal thread block (204) is connected with the inner wall of the hollow support (201) in sliding mode, the lifting plate (205) is fixedly installed on one side of the internal thread block (204), and the bottom of the lifting plate (205) is rotatably connected with the top of the pressing plate (206) through a rotating shaft; Cleaning mechanism (3) is arranged on the top of the workbench (1), the cleaning mechanism (3) includes fixed plate (301) and electric push rod (302), the top of the workbench (1) is fixedly installed with the fixed plate (301), and the electric push rod (302) is fixedly installed on one side of the fixed plate (301).

2. An aircraft wheel hub servicing flaw detector according to claim 1, wherein: The positioning mechanism (2) further includes a brake motor (202), a rotating rod (207) and a circular supporting plate (208), the top of the workbench (1) is fixedly connected with the bottom of the hollow support (201), the inner top and the inner bottom of the hollow support (201) are rotatably connected with both ends of the threaded rod (203), the brake motor (202) is fixedly installed on the top of the hollow support (201), the output shaft of the brake motor (202) is fixedly connected with one end of the threaded rod (203), the top of the workbench (1) is rotatably connected with one end of the rotating rod (207), and the other end of the rotating rod (207) is fixedly connected with the bottom of the circular supporting plate (208).

3. An aircraft wheel hub servicing flaw detector according to claim 2, wherein: The cleaning mechanism (3) further includes a sponge brush (303), the free end of the electric push rod (302) passes through the fixed plate (301) and is connected with one side of the sponge brush (303) in clamping mode.

4. An aircraft wheel hub servicing flaw detector according to claim 3, wherein: The bottom of the workbench (1) is fixedly installed with a speed reducer (4), and the output shaft of the speed reducer (4) is fixedly connected with one end of the rotating rod (207).

5. An aircraft wheel hub servicing flaw detector according to claim 4, wherein: The top of the circular supporting plate (208) and the bottom of the pressing plate (206) are provided with antiskid rubber pads.

6. An aircraft wheel hub servicing flaw detector according to claim 5, wherein: The top of the workbench (1) is fixedly installed with a flaw detection assembly (5).

7. An aircraft wheel hub servicing flaw detector according to claim 6, wherein: The bottom of the workbench (1) is fixedly installed with a plurality of groups of rectangularly distributed supporting rods (6).

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