Auxiliary measuring equipment for aircraft maintenance and detection

Abstract

The invention discloses auxiliary measuring equipment for aircraft maintenance and detection, and particularly relates to the technical field of aircraft maintenance and detection, the auxiliary measuring equipment comprises a measuring table, the upper part of the measuring table is provided with a moving assembly I, the upper end of the measuring table is fixedly connected with a fixed seat I, and the lower end of the measuring table is fixedly connected with a fixed seat II; a first measuring assembly is arranged on the front side of the first moving assembly, a second moving assembly is arranged on the front side of the first moving assembly, a second measuring assembly is arranged on the upper side of the second moving assembly, and an intermittent assembly is arranged on the left side of the first fixing base. According to the invention, through cooperation of the structures, limiting and fixing of the hub and measurement of the diameters of the inner and outer rims of the hub can be synchronously completed, the hub is intermittently rotated through the intermittent assembly, and the inner and outer diameter measurement values of the rims at different angles are compared, so that the measurement accuracy is improved. The problems such as small deformation of the aircraft hub or size change caused by friction in wartime are checked, and smooth development of each flight task is guaranteed.

Description

Technical Field

[0001] The present invention relates to the technical field of aircraft maintenance and inspection, and particularly to an auxiliary measuring device for aircraft maintenance and inspection. Background Art

[0002] In the modern war environment, as an important air combat force, aircraft face unprecedented challenges of high-intensity use and complex and harsh working conditions. During wartime, aircraft need to frequently perform various combat missions, including emergency takeoff, high-speed cruise, intense air combat maneuvers, short-distance landing, etc. Their wheels are subjected to huge mechanical stress, thermal stress, as well as the impacts of foreign objects and the erosion of the battlefield environment. Traditional measuring tools and methods have limitations when detecting and measuring wartime aircraft wheels. Caliper, micrometer, etc. are cumbersome to operate and have low efficiency. They can only perform simple or partial measurements, and it is difficult to detect potential hidden dangers caused by uneven stress, internal cracks, etc. They cannot meet the high-frequency turnover of wartime aircraft and the large number of wheel detection requirements, and cannot provide data support for precise maintenance and condition assessment. Therefore, there is an urgent need to develop special measuring devices to ensure the combat effectiveness and flight safety of wartime aircraft.

[0003] Chinese Patent Publication No. CN211668473U discloses an automatic roundness detection device for aircraft wheels, including a machine body. One side of the machine body is provided with a workbench. A second chute is opened on one side of the workbench. A second slider is arranged in the second chute. The second slider is fixedly connected with the machine body. A clamping block is fixedly connected to one side of the second slider. A rubber pad is fixedly connected to the other side of the workbench. A cylindrical block is fixedly connected to one side of the rubber pad. A motor box is arranged on one side of the cylindrical block. A motor is arranged in the motor box. The rotating shaft of the motor passes through the motor box and is arranged outside the motor box. The rotating shaft of the motor is fixedly connected with a connecting rod. First detection device and second detection device are symmetrically arranged at both ends of the connecting rod. Through the coordinated use of the machine body, workbench, cylindrical block, motor box, motor, connecting rod, first detection device and second detection device, it can realize replacing manual measurement of the roundness of aircraft wheels;

[0004] However, the above device cannot synchronously measure the inner and outer diameters of the wheel rim and the rim size of the wheel during use, and cannot judge the size deviation of the inner and outer diameters of the wheel at different angles. Summary of the Invention

[0005] The main purpose of the present invention is to provide an auxiliary measuring device for aircraft maintenance and inspection, which can effectively solve the problems that it is impossible to synchronously measure the inner and outer diameters of the wheel rim and the rim size of the wheel, and it is impossible to judge the size deviation of the inner and outer diameters of the wheel at different angles.

[0006] To achieve the above purpose, the technical solution adopted by the present invention is as follows:

[0007] An auxiliary measuring device for aircraft maintenance inspection, including a measuring table, on the upper part of the measuring table is provided with a first moving component, on the upper end of the measuring table is fixedly connected with a first fixing seat, on the lower end of the measuring table is fixedly connected with a second fixing seat, on the front side of the first moving component is provided with a first measuring component, on the front side of the first moving component is provided with a second moving component, on the upper side of the second moving component is provided with a second measuring component, and on the left side of the first fixing seat is provided with an intermittent component.

[0008] Preferably, the first moving component includes a hydraulic device fixedly installed at the lower end of the first fixing seat, the output end of the hydraulic device is fixedly connected with a third fixing seat, on both sides of the upper end of the measuring table are fixedly connected with support blocks, on the front side of the adjacent surfaces of the two support blocks is jointly fixedly connected with a first limiting rod, and on the rear side of the adjacent surfaces of the two support blocks is jointly fixedly connected with a second limiting rod.

[0009] Preferably, on the rear side of the third fixing seat are symmetrically fixedly connected with connecting frames, the lower ends of the two connecting frames are both slidably connected with sliding plates, on the outer surfaces of the two sliding plates are symmetrically provided with L-shaped grooves, the inner surfaces of the two L-shaped grooves are slidably connected with the outer surfaces of the two connecting frames, the lower ends of the two sliding plates are both fixedly connected with sliding seats, the inner surface of the left sliding seat is slidably connected with the first limiting rod, and the inner surface of the right sliding seat is slidably connected with the second limiting rod.

[0010] Preferably, the first measuring component includes adjusting seats fixedly connected to the upper ends of the two sliding seats, on the front side of the two adjusting seats are both provided with sliding grooves, the inner surfaces of the two adjusting seats are both rotatably connected with bidirectional threaded rods, on the upper sides of the outer surfaces of the two bidirectional threaded rods are both threadedly connected with first threaded sleeves, the front ends of the two first threaded sleeves are both fixedly connected with first connecting rods, the outer surfaces of the first connecting rods are slidably connected with the sliding grooves, on the mutually approaching surfaces of the two first connecting rods are both fixedly connected with first springs, at the mutually approaching ends of the two first springs are both installed first measuring devices, the lower ends of the two first measuring devices are both fixedly connected with connecting blocks, and at the mutually approaching ends of the two connecting blocks are both installed second measuring devices.

[0011] Preferably, on the lower sides of the outer surfaces of the two bidirectional threaded rods are both threadedly connected with second threaded sleeves, the outer surfaces of the second threaded sleeves are slidably connected with the sliding grooves, the front ends of the two second threaded sleeves are both fixedly connected with second connecting rods, at the mutually approaching ends of the two second connecting rods are both fixedly connected with second springs, and at the mutually approaching ends of the two second springs are both fixedly connected with clamping blocks.

[0012] Preferably, the second moving component includes first racks fixedly connected to the front sides of the two sliding seats, the outer surfaces of the two first racks are both meshed with first gears, and the lower ends of the two first gears are jointly rotatably connected with the measuring table.

[0013] Preferably, a third limiting rod is fixedly connected to the front side of each of the two sliding seats. Both ends of the two third limiting rods are fixedly connected to the connecting frame. The outer surfaces of the two third limiting rods are both slidably connected with an L-shaped sliding frame. A second rack is fixedly connected to the rear side of each of the two L-shaped sliding frames. The outer surfaces of the two second racks are both meshed and connected with two first gears.

[0014] Preferably, the second measuring assembly includes a third spring fixedly connected to the upper ends of the two L-shaped sliding frames. The upper ends of the two third springs are both fixedly connected with an L-shaped movable frame. A plurality of pulleys are rotatably connected to the upper ends of the two L-shaped movable frames. A fourth spring is fixedly connected to each of the two sides of the two L-shaped movable frames away from each other. A third measuring device is installed at each end of the two fourth springs away from each other.

[0015] Preferably, the intermittent assembly includes a first fixing block fixedly connected to the left side of the first fixing seat. A third rack is fixedly connected to the left end of the left connecting frame. A second fixing block is fixedly connected to the lower end of the first fixing block. A second gear is rotatably connected to the front end of the second fixing block. A one-way rotating shaft is rotatably connected to the inner surface of the second gear. A connecting shaft is fixedly connected to the front side of the one-way rotating shaft. A bevel gear transmission group is fixedly connected to the front end of the connecting shaft. A rotating shaft is fixedly connected to the inner surface of the bevel gear transmission group.

[0016] Preferably, the upper end of the rotating shaft is rotatably connected to the first fixing block. The lower end of the rotating shaft is fixedly connected with an intermittent mechanism. The lower end of the intermittent mechanism is rotatably connected to the second fixing seat. The upper end of the intermittent mechanism is fixedly connected with a support shaft. The upper end of the support shaft is fixedly connected with a rotating base. The lower end of the rotating base is rotatably connected to the measuring table.

[0017] Compared with the prior art, the present invention has the following beneficial effects:

[0018] 1. Through the cooperation of the structures among the first moving assembly, the first measuring assembly, the second moving assembly and the second measuring assembly, the present invention can synchronously complete the limiting and fixing of the hub and the measurement of the diameters of the inner and outer rims of the hub, and intermittently rotate the hub through the intermittent assembly to compare the measured values of the inner and outer diameters of the rim at different angles, so as to detect various damages to the hub caused by the high-intensity use of the wartime aircraft, such as minor deformations, dimensional changes caused by friction, etc., as well as local deformations caused by uneven stress, and avoid serious accidents endangering flight safety such as landing gear failure caused by the damage to the structural integrity of the hub in subsequent flights, thus ensuring the smooth progress of each flight mission.

[0019] 2. Through the cooperation of the first moving component and the first measuring component, when the first moving component descends, it drives the first measuring component to move synchronously towards the middle, ensuring that the two measuring devices on both sides move completely synchronously in the horizontal direction. The clamping block limits the hub first to prevent unnecessary shaking or displacement of the hub during the measurement. Subsequently, the first measuring device and the second measuring device simultaneously measure the rim and the wheel rim of the hub, improving the measurement accuracy and efficiency while ensuring the measurement accuracy.

[0020] 3. Through the cooperation of the structures among the first moving component, the first measuring component, the second moving component, and the second measuring component, when the first measuring device and the second measuring device perform a moving measurement on the outer diameters of the rim and the wheel rim, the fourth spring can move in the opposite direction to the first measuring device and the second measuring device to measure the inner diameter of the wheel rim inside the hub, thereby obtaining the inner and outer diameter data of the wheel rim at the same moment and under the same working conditions, simplifying the overall structure and operation process of the equipment, completing a comprehensive inspection of the hub in a short time, quickly judging whether the hub meets the conditions for the aircraft to continue combat, shortening the aircraft's ground time, and enabling the aircraft to quickly return to the combat sequence.

[0021] 4. Through the cooperation of the first moving component and the intermittent component, when the one-way rotating shaft rotates, the intermittent mechanism drives the hub on the rotating base to rotate at fixed angular intervals, providing stable conditions for subsequent repeated measurements, realizing multi-angle measurement, and avoiding problems such as size deviation, wear, and deformation at different angles of the aircraft hub after high-intensity use that are not detected in time, thus preventing serious failures during flight combat and ensuring the smooth progress of each flight mission. BRIEF DESCRIPTION OF THE DRAWINGS

[0022] Figure 1 is a schematic diagram of the overall structure of the present invention;

[0023] Figure 2 is a schematic diagram of the structure of another state of the overall of the present invention;

[0024] Figure 3 is a schematic diagram of the structure of the moving component of the present invention;

[0025] Figure 4 is a partial schematic diagram of the structure of the first measuring component of the present invention;

[0026] Figure 5 is a schematic diagram of the structure of the first measuring component of the present invention;

[0027] Figure 6 is a schematic diagram of the structure of the second moving component of the present invention;

[0028] Figure 7 of the present invention Figure 6Schematic diagram of the enlarged structure at position A in

[0029] Figure 8 Schematic diagram of the second measurement component of the present invention;

[0030] Figure 9 Schematic diagram of the intermittent component of the present invention;

[0031] Figure 10 Partial schematic diagram of the intermittent component of the present invention.

[0032] In the figure: 1. Measuring table; 11. First fixed seat; 12. Second fixed seat; 2. First moving component; 21. Hydraulic device; 22. Third fixed seat; 23. Connecting frame; 231. Support block; 24. First limiting rod; 241. Second limiting rod; 25. Sliding seat; 26. Sliding plate; 27. L-shaped groove; 3. First measurement component; 31. Adjusting seat; 32. Sliding groove; 33. Bidirectional threaded rod; 34. First threaded sleeve; 35. First connecting rod; 36. First spring; 37. First measuring device; 371. Connecting block; 372. Second measuring device; 38. Second threaded sleeve; 39. Second connecting rod; 310. Second spring; 311. Clamping block; 4. Second moving component; 41. First rack; 42. First gear; 43. Third limiting rod; 44. L-shaped sliding frame; 441. Second rack; 5. Second measurement component; 51. Third spring; 52. L-shaped movable frame; 521. Pulley; 53. Fourth spring; 54. Third measuring device; 6. Intermittent component; 61. First fixed block; 62. Third rack; 63. Second fixed block; 64. Second gear; 65. Unidirectional rotating shaft; 66. Connecting shaft; 67. Bevel gear transmission group; 68. Rotating shaft; 69. Intermittent mechanism; 610. Support shaft; 611. Rotating base. Detailed implementation manners

[0033] In order to make the technical means, creative features, achieved purposes and effects of the present invention easy to understand, the present invention will be further described below in conjunction with specific implementation manners.

[0034] Example 1, as Figure 1 And Figure 2As shown in the figure, an auxiliary measuring device for aircraft maintenance and inspection includes a measuring table 1. A first moving component 2 is arranged on the upper part of the measuring table 1. A first fixed seat 11 is fixedly connected to the upper end of the measuring table 1, and a second fixed seat 12 is fixedly connected to the lower end of the measuring table 1. A first measuring component 3 is arranged on the front side of the first moving component 2. Through the cooperation of the first moving component 2, the limiting of the hub and the measurement of the diameters of the external rim and flange are realized simultaneously. A second moving component 4 is arranged on the front side of the first moving component 2. While the first moving component 2 is moving, it can drive the second measuring component 5 and the first moving component 2 to move in the opposite direction through the second moving component 4, so that the second measuring component 5 synchronously measures the internal diameter of the rim, improving the measurement efficiency. A second measuring component 5 is arranged on the upper side of the second moving component 4, which can measure the internal diameter of the rim of the hub. An intermittent component 6 is arranged on the left side of the first fixed seat 11, which can drive the whole hub to rotate 90 degrees when the first moving component 2 rises, ensuring that the hub can rotate at fixed angular intervals, detecting the dimensional conditions at various angles, helping to discover problems such as tiny deformations of the hub, dimensional changes caused by friction, and local deformations caused by uneven stress, and checking various damages to the hub caused by the high-intensity use of the aircraft during wartime, greatly improving the comprehensiveness and accuracy of the detection, and realizing multi-angle measurement.

[0035] Therefore, through the cooperation of the structures among the first moving component 2, the first measuring component 3, the second moving component 4 and the second measuring component 5 in this solution, it can synchronously complete the limiting and fixing of the hub and the measurement of the diameters of the inner and outer rims of the hub, and make the hub rotate intermittently through the intermittent component 6, comparing the measured values of the inner and outer diameters of the rim at different angles, checking various damages to the hub caused by the high-intensity use of the aircraft during wartime, such as tiny deformations, dimensional changes caused by friction, and local deformations caused by uneven stress, avoiding serious accidents endangering flight safety such as landing gear failure caused by the damaged structural integrity of the hub in subsequent flights, and ensuring the smooth progress of each flight mission.

[0036] Embodiment 2. On the basis of Embodiment 1, this embodiment is to achieve the effect of synchronously measuring and clamping the outside of the hub.

[0037] Refer to Figure 1 、 Figure 2 、 Figure 3 、 Figure 4 and Figure 5 , the first moving component 2 includes a hydraulic device 21 fixedly installed at the lower end of the first fixed seat 11. The output end of the hydraulic device 21 is fixedly connected to a third fixed seat 22. Support blocks 231 are fixedly connected to both sides of the upper end of the measuring table 1. A first limiting rod 24 is fixedly connected to the front side of the adjacent surfaces of the two support blocks 231, and a second limiting rod 241 is fixedly connected to the rear side of the adjacent surfaces of the two support blocks 231.

[0038] On the rear side of the third fixed seat 22, connecting frames 23 are symmetrically and fixedly connected. At the lower ends of the two connecting frames 23, sliding plates 26 are slidably connected. On the outer surfaces of the two sliding plates 26, L-shaped grooves 27 are symmetrically formed. The inner surfaces of the two L-shaped grooves 27 are slidably connected to the outer surfaces of the two connecting frames 23. At the lower ends of the two sliding plates 26, sliding seats 25 are fixedly connected. The inner surface of the left sliding seat 25 is slidably connected to the first limiting rod 24, and the inner surface of the right sliding seat 25 is slidably connected to the second limiting rod 241.

[0039] Specifically, the first limiting rod 24 and the second limiting rod 241 are arranged staggeredly front and back. The two sliding seats 25, sliding plates 26 and other structures connected to the first limiting rod 24 and the second limiting rod 241 are also symmetrically arranged with a front-back stagger, which can prevent the two sliding plates 26 from colliding when moving towards the middle synchronously. Also, due to the front-back difference, the lengths of the two connecting frames 23 are different. The length of the right connecting frame 23 in the front-back direction is greater than the length of the left connecting frame 23.

[0040] Furthermore, the angle of the L-shaped groove 27 is an obtuse angle, and the two L-shaped grooves 27 are also symmetrically arranged. When the connecting frame 23 follows the third fixed seat 22 and descends, the lower end of the connecting frame 23 will slide on the inner surface of the L-shaped groove 27, thereby driving the two sliding plates 26 to move towards the middle together.

[0041] Furthermore, place the hub on the surface of the measuring table 1, start the hydraulic device 21 to drive the third fixed seat 22 to descend. During the descent of the third fixed seat 22, the connecting frame 23 is driven to slide in the L-shaped groove 27. When the connecting frame 23 is located at the vertical part of the L-shaped groove 27, the sliding plate 26 remains stationary. When the connecting frame 23 moves on the inclined part of the L-shaped groove 27, the two sliding plates 26 will move towards the middle simultaneously, thereby driving the two sliding seats 25 to slide on the first limiting rod 24 and the second limiting rod 241 respectively.

[0042] Refer to Figure 4 And Figure 5 , the first measuring assembly 3 includes adjusting seats 31 fixedly connected to the upper ends of the two sliding seats 25. On the front sides of the two adjusting seats 31, sliding grooves 32 are formed. The inner surfaces of the two adjusting seats 31 are rotatably connected with bidirectional threaded rods 33. On the upper sides of the outer surfaces of the two bidirectional threaded rods 33, thread sleeves 34 are threadedly connected. At the front ends of the two thread sleeves 34, connecting rods 35 are fixedly connected. The outer surface of the connecting rod 35 is slidably connected to the sliding groove 32. On the closer sides of the two connecting rods 35, first springs 36 are fixedly connected. At the mutually approaching ends of the two first springs 36, first measuring devices 37 are installed. At the lower ends of the two first measuring devices 37, connecting blocks 371 are fixedly connected. At the mutually approaching ends of the two connecting blocks 371, second measuring devices 372 are installed.

[0043] Further, the thread directions on the upper and lower sides of the adjusting seat 31 are opposite. By rotating the round block on the adjusting seat 31, the bidirectional threaded rod 33 rotates, so that the first threaded sleeve 34 and the second threaded sleeve 38 can move synchronously in opposite directions, facilitating the measurement and clamping of hubs of different sizes. The two first measuring devices 37 and the second measuring device 372 respectively move towards the middle following the sliding seat 25 and the sliding plate 26, so that the first measuring device 37 and the second measuring device 372 are attached to the wheel rims and wheel flanges on both sides of the hub, and the diameters of the outer wheel rims and wheel flanges of the hub are measured.

[0044] Further, the first measuring device 37 and the second measuring device 372 in the above are inductive micrometers in the prior art. The inductive micrometer itself uses the mature electromagnetic induction principle to achieve high-precision measurement. The inductive sensor inside it consists of key components such as a coil and a movable iron core. When the iron core, that is, the measuring head part, and the movable element connected to it generate displacement due to contact with an object, the magnetic flux in the coil will change, and then the inductance will change. Then, it is accurately captured by the built-in dedicated measurement circuit. This circuit uses advanced analog signal processing technology to amplify, filter, and linearly calibrate the electrical signals caused by weak inductive changes, ensuring that the finally output electrical signal can accurately reflect the displacement of the measuring head. Finally, the displacement is converted into the corresponding dimension value and displayed. The measurement accuracy can reach the micron or even sub-micron level, meeting the dimensional measurement requirements of precision components such as hubs.

[0045] The working process is as follows:

[0046] Let the initial distance between the two inductive micrometers be D O , after contacting the hub, the displacement of one side of the measuring head is X 1 , and the other side is X 2 , the calculation of the hub diameter D is based on the formula D = D 0 - (X 1 + X 2 ). The two inductive micrometers will respectively measure and output the values of X 1 and X 2 , and then transmit them to the external data processing system, and finally calculate the hub diameter.

[0047] Refer to Figure 5 , on the lower sides of the outer surfaces of the two bidirectional threaded rods 33, second threaded sleeves 38 are all threadedly connected. The outer surface of the second threaded sleeve 38 is slidably connected to the sliding groove 32. The outer surface of the second threaded sleeve 38 is slidably connected to the sliding groove 32. At the front ends of the two second threaded sleeves 38, second connecting rods 39 are fixedly connected. At the mutually approaching ends of the two second connecting rods 39, second springs 310 are fixedly connected. At the mutually approaching ends of the two second springs 310, clamping blocks 311 are fixedly connected.

[0048] Further, during the process of measuring or limiting the hub, the presence of the first measuring device 37 and the second spring 310 can play a buffering role, and telescopic rods are provided inside both of them, which can keep themselves stable during buffering and avoid damaging the inductive micrometer or the hub during the measurement or clamping process.

[0049] Furthermore, the entire adjusting seat 31 moves towards the middle together with the sliding seat 25 and the sliding plate 26, thereby driving the first connecting rod 35, the first spring 36, the first measuring device 37, the connecting block 371, the second measuring device 372, the second connecting rod 39, the second spring 310 and the clamping block 311 to move towards the middle together. Among them, the clamping block 311 will first touch the hub to limit the hub. Subsequently, the two first measuring devices 37 abut against the wheel rim, and the second measuring device 372 abuts against the wheel web, simultaneously measuring the outer diameters of the wheel rim and the wheel web of the hub. When facing hubs of different sizes, the two-way threaded rod 33 can be rotated by rotating the round block at the upper end of the adjusting seat 31, thereby driving the first connecting rod 35 and the second connecting rod 39 to move away from or close to each other to adjust the distance, facilitating dealing with hubs of different sizes.

[0050] Therefore, through the cooperation of the first moving component 2 and the first measuring component 3, when the first moving component 2 descends, it drives the first measuring component 3 to move towards the middle synchronously, ensuring that the horizontal movements of the two first measuring devices 37 and the second measuring device 372 are completely synchronous. The clamping block 311 limits the hub first to prevent unnecessary shaking or displacement of the hub during the measurement process. Subsequently, the first measuring device 37 and the second measuring device 372 simultaneously measure the wheel rim and the wheel web of the hub, ensuring measurement accuracy while also improving the measurement efficiency.

[0051] Embodiment 3, on the basis of Embodiments 1 and 2, to achieve the effect of simultaneously measuring the inner and outer diameters of the wheel web.

[0052] Refer to Figure 6 、 Figure 7 and Figure 8 , the second moving component 4 includes a first rack 41 fixedly connected to the front sides of both sliding seats 25. The outer surfaces of the two first racks 41 are both meshed with a first gear 42. The lower ends of the two first gears 42 are jointly rotatably connected to the measuring table 1.

[0053] Refer to Figure 7 , the front sides of both sliding seats 25 are fixedly connected with third limiting rods 43. Both ends of the two third limiting rods 43 are fixedly connected to the connecting frame 23. The outer surfaces of the two third limiting rods 43 are both slidably connected with L-shaped sliding frames 44. The rear sides of the two L-shaped sliding frames 44 are both fixedly connected with second racks 441. The outer surfaces of the two second racks 441 are both meshed with the two first gears 42.

[0054] Specifically, one of the two limiting rods 43 is located on the front side of the first limiting rod 24, and the other is located on the front side of the second limiting rod 241. The two limiting rods 43 can limit the two L-shaped sliding frames 44 to slide back and forth stably, while the first gear 42 can make the sliding seat 25 move in the direction opposite to that of the L-shaped sliding frame 44.

[0055] Refer to Figure 8 , the second measuring assembly 5 includes third springs 51 fixedly connected to the upper ends of the two L-shaped sliding frames 44. The upper ends of the two third springs 51 are fixedly connected with L-shaped movable frames 52. A plurality of pulleys 521 are rotatably connected to the upper ends of the two L-shaped movable frames 52. A plurality of pulleys 521 are rotatably connected to the upper ends of the two L-shaped movable frames 52. Fourth springs 53 are fixedly connected to the opposite sides of the two L-shaped movable frames 52 away from each other. Measuring devices 54 are installed at the opposite ends of the two fourth springs 53 away from each other.

[0056] Furthermore, a telescopic rod is arranged inside the third spring 51 to facilitate the third spring 51 to remain stable when being squeezed. The pulley 521 can reduce the friction between the L-shaped movable frame 52 and the third fixed seat 22, facilitating the movement of the L-shaped movable frame 52 in the pressed state. The measuring device 54 described above has the same structure and measuring principle as the first measuring device 37 and the second measuring device 372 in the second embodiment, so it will not be repeated here.

[0057] Furthermore, when the hydraulic device 21 drives the third fixed seat 22 to descend, through the structure in the above embodiment, the two sliding seats 25 move. When the sliding seats 25 move, the first rack 41 will respectively engage with the first gear 42, thereby driving the second rack 441 and the L-shaped sliding frame 44 to move in the direction opposite to that of the sliding seat 25, that is, move towards both sides. During this process, the third fixed seat 22 will squeeze the L-shaped movable frame 52, causing the L-shaped movable frame 52 to open towards both sides during the descent. When the lower end of the connecting frame 23 moves to the lowermost end of the vertical part of the L-shaped groove 27, the measuring device 54 is basically parallel to the upper end of the hub. Then, when the lower end of the connecting frame 23 moves to the inclined surface of the L-shaped groove 27, during this process, the measuring device 54 will open towards both sides when descending. When the lower end of the connecting frame 23 moves to the lowermost end of the inclined surface of the L-shaped groove 27, the measuring device 54 will contact the inner surface of the rim, thereby measuring the value of the inner diameter of the rim, and thus completing the comprehensive detection of the hub in a short time and quickly judging whether the hub meets the conditions for the aircraft to continue combat.

[0058] Therefore, through the cooperation of the structures between the first moving component 2, the first measuring component 3, the second moving component 4 and the second measuring component 5, when the first measuring device 37 and the second measuring device 372 perform a moving measurement on the outer diameters of the wheel flange and the wheel rim, the fourth spring 53 can move in the opposite direction to the first measuring device 37 and the second measuring device 372 to measure the inner diameter of the wheel rim inside the hub. Thus, the inner and outer diameter data of the wheel rim are obtained at the same moment and under the same working conditions, simplifying the overall structure and operation process of the equipment, completing a comprehensive inspection of the hub in a short time, quickly judging whether the hub meets the conditions for the aircraft to continue fighting, shortening the aircraft's ground time, and enabling the aircraft to quickly return to the combat sequence.

[0059] Embodiment 4: On the basis of Embodiments 1, 2, and 3, this embodiment is to achieve the effect of multi-angle detection of the hub.

[0060] Refer to Figure 9 and Figure 10 , the intermittent component 6 includes a first fixing block 61 fixedly connected to the left side of the first fixing seat 11, a third rack 62 fixedly connected to the left end of the left connecting frame 23, a second fixing block 63 fixedly connected to the lower end of the first fixing block 61, a second gear 64 rotatably connected to the front end of the second fixing block 63, a one-way rotating shaft 65 rotatably connected to the inner surface of the second gear 64, a connecting shaft 66 fixedly connected to the front side of the one-way rotating shaft 65, a bevel gear transmission group 67 fixedly connected to the front end of the connecting shaft 66, and a rotating shaft 68 fixedly connected to the inner surface of the bevel gear transmission group 67.

[0061] Specifically, the bevel gear transmission group 67 is composed of two meshing bevel gears. The second gear 64 and the one-way rotating shaft 65 are both conventional designs in the prior art and are composed of an outer ring, an inner ring, rollers, and a spring. Its working principle is as follows:

[0062] Outer ring: Usually fixed to the housing or connected to other components to form a cylindrical structure;

[0063] Inner ring: The structure of the inner ring is relatively special. It has a sloped circle, and this slope enables the one-way rotating shaft 65 to achieve one-way rotation and locking functions;

[0064] Rollers: The rollers are always in contact with the inner and outer rings, and their working surfaces are also slopes:

[0065] Spring: The spring is in contact with the rollers, used to maintain the position of the rollers, and provide a restoring force when needed;

[0066] Therefore, the second gear 64 and the one-way rotating shaft 65 are conventional settings in the prior art, and this solution will not be elaborated in detail.

[0067] Furthermore, when the connecting frame 23 descends, the rack three 62 will mesh with the gear two 64, and the gear two 64 will rotate clockwise. At this time, the one-way shaft 65 will not rotate, so that the bevel gear transmission group 67 and the rotating shaft 68 will not rotate. When the connecting frame 23 rises, the rack three 62 and the gear two 64 will mesh, and the gear two 64 will rotate counterclockwise. At this time, the one-way shaft 65 starts to rotate, driving the bevel gear transmission group 67 and the rotating shaft 68 to rotate.

[0068] The upper end of the rotating shaft 68 is rotatably connected to the fixed block 61, the lower end of the rotating shaft 68 is fixedly connected to the intermittent mechanism 69, the lower end of the intermittent mechanism 69 is rotatably connected to the fixed seat 2 12, the upper end of the intermittent mechanism 69 is fixedly connected to the support shaft 610, the upper end of the support shaft 610 is fixedly connected to the rotating base 611, and the lower end of the rotating base 611 is rotatably connected to the measuring table 1.

[0069] Furthermore, the intermittent mechanism 69 is a conventional design in the prior art, and is composed of a disc with radial grooves, an active dial and a round pin. When the active dial rotates continuously, the round pin on it enters the radial groove of the disc, driving the disc to rotate a certain angle. As the active dial continues to rotate, the round pin will be separated from the radial groove. At this time, due to its own structural characteristics and the external stop arc limitation, the disc stops rotating and remains stationary until the round pin on the active dial enters the next radial groove again, and the disc repeatedly rotates a certain angle, and so on, to achieve the effect of intermittent rotation.

[0070] Furthermore, when the hydraulic device 21 drives the fixing seat three 22 and the connecting frame 23 to rise, the structures in the second embodiment and the third embodiment will move in opposite directions, and the structures such as the measuring device one 37, the measuring device two 372 and the clamping block 311 will be separated from the surface of the hub. When they rise to a certain extent, the rack three 62 and the gear two 64 will mesh. At this time, the one-way rotating shaft 65 drives the bevel gear transmission group 67 and the rotating shaft 68 to rotate, so that the active dial in the intermittent mechanism 69 rotates, driving the round pin to enter the radial groove of the disc, driving the disc to rotate a certain angle, so that the support shaft 610 and the rotating base 611 drive the hub to rotate ninety degrees, and then the hydraulic device 21 and the fixing seat three 22 are controlled to descend again, and repeated measurements at different angles are performed.

[0071] Therefore, in this solution, through the cooperation between the moving component 2 and the intermittent component 6, when the one-way rotating shaft 65 rotates, the intermittent mechanism 69 will drive the hub on the rotating base 611 to rotate at a fixed angle interval, providing stable conditions for subsequent repeated measurements, realizing multi-angle measurement, and avoiding the problem of dimensional deviation, wear, deformation and other problems of the aircraft hub at different angles after high-intensity use without being discovered in time, thereby causing serious malfunctions during flight combat, ensuring the smooth implementation of each flight mission.

[0072] It should be specifically noted that the specific installation methods of the hydraulic device 21, the first measuring device 37, the second measuring device 372 and the third measuring device 54, the connection methods of the circuits, and the control methods adopted in the present invention are all conventional designs, and the present invention will not elaborate in detail.

[0073] The foregoing has shown and described the basic principles, main features and advantages of the present invention. Those skilled in the art should understand that the present invention is not limited by the above embodiments, and what is described in the above embodiments and the specification is only to illustrate the principle of the present invention. Without departing from the spirit and scope of the present invention, the present invention will also have various changes and improvements, and these changes and improvements all fall within the scope of the present invention claimed. The scope of protection claimed by the present invention is defined by the appended claims and their equivalents.

Claims

1. An auxiliary measuring device for aircraft maintenance and inspection, comprising a measuring table (1), characterized in that: A moving component (2) is arranged on the upper part of the measuring platform (1); a fixing seat (1) is fixedly connected to the upper end of the measuring platform (1); a fixing seat (12) is fixedly connected to the lower end of the measuring platform (1); a measuring component (3) is arranged on the front side of the moving component (2); a moving component (4) is arranged on the front side of the moving component (2); a measuring component (5) is arranged on the upper side of the moving component (4); and an intermittent component (6) is arranged on the left side of the fixing seat (11).

2. The auxiliary measurement equipment for aircraft maintenance and inspection according to claim 1, characterized in that: The moving assembly (2) comprises a hydraulic device (21) fixedly mounted on the lower end of the fixed seat (11); the output end of the hydraulic device (21) is fixedly connected to the fixed seat (22); both sides of the upper end of the measuring platform (1) are fixedly connected to support blocks (231); the front sides of the adjacent sides of the two support blocks (231) are fixedly connected to the limiting rod (24); and the rear sides of the adjacent sides of the two support blocks (231) are fixedly connected to the limiting rod (241).

3. The auxiliary measurement equipment for aircraft maintenance and inspection according to claim 2, characterized in that: The rear side of the fixed seat three (22) is symmetrically fixedly connected with a connecting frame (23), the lower ends of the two connecting frames (23) are slidably connected with sliding plates (26), the outer surfaces of the two sliding plates (26) are symmetrically provided with L-shaped grooves (27), the inner surfaces of the two L-shaped grooves (27) are slidably connected to the outer surfaces of the two connecting frames (23), the lower ends of the two sliding plates (26) are fixedly connected with a sliding seat (25), the inner surface of the left sliding seat (25) is slidably connected to the limiting rod one (24), and the inner surface of the right sliding seat (25) is slidably connected to the limiting rod two (241).

4. The auxiliary measurement equipment for aircraft maintenance and inspection according to claim 3, characterized in that: The measuring assembly (3) comprises an adjusting seat (31) fixedly connected to the upper ends of the two sliding seats (25), the front sides of the two adjusting seats (31) are provided with sliding grooves (32), the inner surfaces of the two adjusting seats (31) are rotatably connected with bidirectional threaded rods (33), the upper sides of the outer surfaces of the two bidirectional threaded rods (33) are threadedly connected with threaded sleeves (34), the front ends of the two threaded sleeves (34) are fixedly connected with connecting rods (35), the outer surfaces of the connecting rods (35) are slidably connected with the sliding grooves (32), the adjacent sides of the two connecting rods (35) are fixedly connected with springs (36), the adjacent ends of the two springs (36) are installed with measuring devices (37), the lower ends of the two measuring devices (37) are fixedly connected with connecting blocks (371), and the adjacent ends of the two connecting blocks (371) are installed with measuring devices (372).

5. The auxiliary measurement equipment for aircraft maintenance and inspection according to claim 4, characterized in that: The lower sides of the outer surfaces of the two bidirectional threaded rods (33) are both threadedly connected with threaded sleeves (38), the outer surfaces of the threaded sleeves (38) are slidably connected to the sliding groove (32), the front ends of the two threaded sleeves (38) are both fixedly connected with connecting rods (39), the ends of the two connecting rods (39) close to each other are both fixedly connected with springs (310), and the ends of the two springs (310) close to each other are both fixedly connected with clamping blocks (311).

6. The auxiliary measurement equipment for aircraft maintenance and inspection according to claim 3, characterized in that: The moving assembly 2 (4) comprises a rack 1 (41) fixedly connected to the front sides of the two sliding seats (25), the outer surfaces of the two racks 1 (41) are meshedly connected with a gear 1 (42), and the lower ends of the two gears 1 (42) are rotatably connected to the measuring platform (1).

7. The auxiliary measurement equipment for aircraft maintenance and inspection according to claim 6, characterized in that: The front sides of the two sliding seats (25) are fixedly connected to the limiting rod three (43), the two ends of the two limiting rods three (43) are fixedly connected to the connecting frame (23), the outer surfaces of the two limiting rods three (43) are slidably connected to the L-shaped sliding frame (44), the rear sides of the two L-shaped sliding frames (44) are fixedly connected to the rack two (441), and the outer surfaces of the two rack twos (441) are meshingly connected to the two gear ones (42).

8. The auxiliary measurement equipment for aircraft maintenance and inspection according to claim 7, characterized in that: The measuring assembly 2 (5) comprises a spring 3 (51) fixedly connected to the upper ends of the two L-shaped sliding frames (44); the upper ends of the two springs 3 (51) are fixedly connected to an L-shaped movable frame (52); the upper ends of the two L-shaped movable frames (52) are rotatably connected to a plurality of pulleys (521); the sides of the two L-shaped movable frames (52) away from each other are fixedly connected to a spring 4 (53); and the ends of the two springs 4 (53) away from each other are installed with a measuring device 3 (54).

9. The auxiliary measurement equipment for aircraft maintenance and inspection according to claim 3, characterized in that: The intermittent component (6) comprises a fixed block 1 (61) fixedly connected to the left side of the fixed seat 1 (11); the left end of the left connecting frame (23) is fixedly connected to a rack 3 (62); the lower end of the fixed block 1 (61) is fixedly connected to a fixed block 2 (63); the front end of the fixed block 2 (63) is rotatably connected to a gear 2 (64); the inner surface of the gear 2 (64) is rotatably connected to a one-way rotating shaft (65); the front side of the one-way rotating shaft (65) is fixedly connected to a connecting shaft (66); the front end of the connecting shaft (66) is fixedly connected to a bevel gear transmission group (67); the inner surface of the bevel gear transmission group (67) is fixedly connected to a rotating shaft (68).

10. The auxiliary measurement equipment for aircraft maintenance and inspection according to claim 9, characterized in that: The upper end of the rotating shaft (68) is rotatably connected to the fixed block 1 (61), the lower end of the rotating shaft (68) is fixedly connected to an intermittent mechanism (69), the lower end of the intermittent mechanism (69) is rotatably connected to the fixed seat 2 (12), the upper end of the intermittent mechanism (69) is fixedly connected to a support shaft (610), the upper end of the support shaft (610) is fixedly connected to a rotating base (611), and the lower end of the rotating base (611) is rotatably connected to the measuring platform (1).

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