Quick dismounting and mounting device and method for universal joint ring of aero-engine

Abstract

The invention discloses a quick dismounting and mounting device for a universal joint ring of an aero-engine, and particularly relates to the technical field of mechanical control devices, the quick dismounting and mounting device comprises a quick dismounting and mounting device body, a quick dismounting assembly, an elastic assembly, a connection reset assembly and a limiting assembly; the quick dismounting and mounting device body comprises a workbench used for containing the aero-engine universal joint ring and a hammer used for knocking the aero-engine universal joint ring. A clamp is arranged on the workbench; the hammer head is connected with the workbench through a quick release assembly; the quick release assembly comprises a support frame, a servo motor, a rotating disc, a moving plate, a connecting plate, a damper, a fixed plate and a return spring A; according to the device, the structural design is reasonable, through driving of the servo motor and under the action of the connection reset assembly, the hammer head can continuously knock the aero-engine universal joint ring, the disassembly and assembly efficiency is high, the aero-engine universal joint ring can be rapidly disassembled and assembled, and the automation degree is high.

Description

Technical Field

[0001] The present invention relates to the technical field of mechanical control devices, and more specifically, to a device and method for quickly disassembling and assembling a universal joint ring of an aeroengine. Background Art

[0002] An aeroengine universal joint ring refers to a mechanical device mainly used to achieve power transmission between different axes. It allows two shafts to rotate freely within a certain angle range while maintaining continuous power transmission. The core principle of the universal joint ring is to use a ball socket joint or a cross shaft joint so that the two shafts can work properly under variable angles.

[0003] For example, a universal joint disassembly and assembly device with a positioning structure provided by the Chinese utility model patent with the publication number CN221211518U includes an operation table. A support seat is installed at the top of the operation table, and an L-shaped support frame is installed at the top of the operation table on one side of the support seat. A hammer is penetrated through the top of the L-shaped support frame, and a guide cylinder is sleeved outside the hammer. The top of the guide cylinder is connected to the top inside the L-shaped support frame, and a plurality of balls are evenly installed inside the guide cylinder. By the cooperation of an adjusting plate, adjusting holes, roller shafts, a movable plate, etc., the present invention is conducive to the left and right limit fixation of the universal joint by two clamping plates, and with the cooperation of a limit plate, the up and down fixation of the universal joint is further carried out, so that the whole universal joint can ensure a stable position during the disassembly and assembly process, and reduces the continuous support of the artificial hand on the universal joint.

[0004] During the use of the aeroengine universal joint ring, a disassembly and assembly device is needed for its installation or disassembly. However, during the use of the existing disassembly and assembly device, it is still necessary to manually hammer the pressing plate so that the hammering force is distributed on the cross shaft through the hammer, with a low degree of automation. While reducing the disassembly and assembly efficiency of the aeroengine universal joint ring, it will also affect the use effect of the disassembly and assembly device. Summary of the Invention

[0005] In order to overcome the above-mentioned defects of the prior art, the present invention provides a device for quickly disassembling and assembling an aeroengine universal joint ring. The technical problem to be solved by the present invention is that during the use of the existing disassembly and assembly device, it is still necessary to manually hammer the pressing plate so that the hammering force is distributed on the cross shaft through the hammer, with a low degree of automation. While reducing the disassembly and assembly efficiency of the aeroengine universal joint ring, it will also affect the use effect of the disassembly and assembly device.

[0006] To achieve the above object, the present invention provides the following technical solution: a quick disassembly and assembly device for an aero-engine universal joint ring, comprising a quick disassembly and assembly device body, a quick disassembly component, an elastic component, a connection and reset component, and a limiting component; the quick disassembly and assembly device body includes a workbench for placing the aero-engine universal joint ring and a hammer head for knocking the aero-engine universal joint ring; a clamp is arranged on the workbench; the hammer head is connected to the workbench through the quick disassembly component; the quick disassembly component includes a support frame, a servo motor, a rotating disk, a moving plate, a connecting plate, a damper, a fixing plate, and a return spring A; the support frame is fixedly arranged on the workbench; the servo motor is fixedly arranged on the support frame through a motor seat; the rotating disk is fixedly connected to the output end of the servo motor; the moving plate is connected to the rotating disk through the elastic component; the connecting plate is fixedly arranged on the bottom surface of the moving plate, and the connecting plate is connected to the support frame through the connection and reset component; the damper is fixedly arranged on the side of the connecting plate away from the moving plate; the fixing plate is fixedly connected to the end of the damper away from the connecting plate, and the fixing plate is connected to the hammer head through the limiting component; the return spring A is sleeved on the damper, and both ends of the return spring A are fixedly connected to the connecting plate and the fixing plate respectively.

[0007] As a further solution of the present invention: the elastic component includes an abutting groove, an abutting block, a return spring B, and a movable groove; an abutting groove is formed on the side of the rotating disk away from the servo motor; the abutting block slidably penetrates through the abutting groove; both ends of the return spring B are fixedly connected to the inner wall of the abutting groove and the abutting block respectively; a movable groove is formed on the side of the moving plate close to the rotating disk, and the abutting block is slidably matched with the movable groove.

[0008] As a further solution of the present invention: the abutting block is of a frustum structure, the size of the abutting block on the side close to the return spring B is larger than the size of the abutting block on the side away from the return spring B, and the circumferential surface of the abutting block contacts the inner wall of the abutting groove.

[0009] As a further solution of the present invention: the movable groove is of an isosceles trapezoid structure, and the opening direction of the movable groove is arranged towards the rotating disk.

[0010] As a further solution of the present invention: the connection and reset component includes a sliding groove, a sliding block, a reset spring, a guiding groove, and a guiding block; a sliding groove is formed on the side of the support frame close to the connecting plate; the sliding block slidably penetrates through the sliding groove and is fixedly connected to the connecting plate; both ends of the reset spring are fixedly connected to the inner wall of the sliding groove and the sliding block respectively; at least one guiding groove is formed in the sliding groove; the guiding block slidably penetrates through the guiding groove and is fixedly connected to the sliding block; the elastic strength of the reset spring is less than the elastic strength of the return spring B.

[0011] As a further solution of the present invention: the sliding block is of a Y-shaped structure, and the size of the sliding block on the side close to the connecting plate is larger than the size of the sliding block on the side far from the connecting plate.

[0012] As a further solution of the present invention: the limiting component includes a limiting groove, a limiting block, a receiving groove, a positioning block, a positioning groove, a return spring C, a wedge-shaped groove, a screw and a sphere; a limiting groove is opened on the fixing plate close to the hammer head side; the limiting block slides through the limiting groove and is fixedly connected to the hammer head; at least one receiving groove is opened in the limiting groove; the positioning block slides through the receiving groove and extends into the limiting groove; at least one positioning groove is opened on the limiting block, and the positioning block is inserted and matched with the positioning groove; the two ends of the return spring C are respectively fixedly connected to the inner wall of the receiving groove and the positioning block; a wedge-shaped groove is opened on the top surface of the positioning block; the screw is screwed on the fixing plate; the sphere is fixedly connected to the end of the screw.

[0013] As a further solution of the present invention: the limiting block is of a T-shaped structure with a larger upper part and a smaller lower part.

[0014] As a further solution of the present invention: the wedge-shaped groove is provided with an inclined surface, the spherical surface of the sphere slides with the inclined surface, and the diameter size of the sphere is larger than the diameter size of the screw.

[0015] In addition, the present invention also relates to a method for a quick disassembly and assembly device of an aero-engine universal joint ring, including the following steps:

[0016] Step 1: Through the limiting component, the hammer head can be replaced according to the size of the aero-engine universal joint ring, and a hammer head with a suitable size can be selected.

[0017] Step 2: Through the fixture on the workbench, the position of the aero-engine universal joint ring can be fixed on the workbench.

[0018] Step 3: Start the servo motor to make the rotating disk rotate, and through the elastic force component, the hammer head can be driven to rise to a certain height so that the hammer head can strike the cross shaft on the aero-engine universal joint ring.

[0019] Step 4: Under the action of the connection reset component, through a single rotation of the rotating disk, the hammer head can continuously strike the cross shaft.

[0020] The beneficial effects of the present invention are as follows:

[0021] 1. The present invention is provided with a quick-release component and a connection reset component. Through the fixture on the workbench, the universal joint ring of the aero-engine is fixed on the workbench, and the cross shaft on the universal joint ring of the aero-engine is positioned directly below the hammer head. Then, the servo motor is started, and the output shaft of the servo motor drives the rotating disk to rotate, causing the moving plate to drive the connecting plate, damper, fixed plate, and return spring A to move upward through the elastic component. The sliding block slides upward in the sliding groove, the guiding block slides upward in the guiding groove, and the reset spring is stretched under force until the top surface of the sliding block contacts the inner top wall of the sliding groove. At this time, under the action of the elastic component, the reset spring is no longer under force and begins to contract, causing the sliding block to slide downward in the sliding groove, the guiding block to slide downward in the guiding groove, and the moving plate to drive the connecting plate, damper, fixed plate, and return spring A to move downward, enabling the hammer head to contact the cross shaft on the universal joint ring of the aero-engine and strike the cross shaft. During the striking process, the damper can provide resistance and buffering effects to adapt to the striking position of the cross shaft, and the return spring A can return the damper to its original position. Moreover, under the elastic force of the reset spring, the hammer head continuously strikes the cross shaft. Compared with the prior art, the structure of the present invention is reasonably designed. Driven by the servo motor and under the action of the connection reset component, the hammer head can continuously strike the universal joint ring of the aero-engine, with relatively high disassembly and assembly efficiency, so as to achieve rapid disassembly and assembly of the universal joint ring of the aero-engine, and moreover, the degree of automation is relatively high.

[0022] 2. The present invention is provided with an elastic component. When the rotating disk rotates, the abutting block presses against the inner wall of the movable groove. Since the elastic strength of the reset spring is less than that of the return spring B, the moving plate drives the connecting plate, damper, fixed plate, and return spring A to move upward, causing the abutting block to slide in the movable groove until the top surface of the sliding block contacts the inner top wall of the sliding groove. At this time, the circumferential surface of the abutting block presses against the inner wall of the movable groove, causing the abutting block to slide in the abutting groove, and the return spring B is compressed under force until the abutting block no longer contacts the moving plate. At this time, under the elastic force of the reset spring, the hammer head continuously strikes the cross shaft. When the abutting block no longer contacts the moving plate, under the elastic force of the return spring B, the abutting block slides back to its original position. Moreover, during the rotation of the rotating disk, the abutting block contacts the top surface of the moving plate, enabling the abutting block to gradually eliminate the elastic force of the reset spring until the bottom surface of the sliding block contacts the inner bottom wall of the sliding groove. At this time, the circumferential surface of the abutting block presses against the moving plate, causing the abutting block to slide in the abutting groove, and the return spring B is compressed under force until the abutting block rotates to the lowest end. At this time, under the elastic force of the return spring B, the abutting block contacts the inner wall of the movable groove.

[0023] 3. In the present invention, by providing a limit component, according to the size of the universal joint ring of the aero-engine to be disassembled and assembled as needed, rotate the screw rod so that the screw rod is threadedly connected to the fixed plate, causing the spherical surface of the sphere to press against the inclined surface of the wedge-shaped groove, enabling the positioning block to slide within the receiving groove and the positioning groove, causing the return spring C to contract under force until the spherical surface of the sphere contacts the inner bottom wall of the wedge-shaped groove. At this time, the positioning block moves out of the positioning groove. Then, move the hammer head so that the limiting block slides within the limiting groove until the limiting block moves out of the limiting groove. Then, select a hammer head of a suitable size, insert the limiting block into the limiting groove, and make the side surface of the limiting block contact the inner side wall of the limiting groove. Subsequently, rotate the screw rod in the reverse direction so that the screw rod is threadedly connected to the fixed plate. Under the elastic force of the return spring C, the positioning block will slide reversely within the receiving groove and the positioning groove until the side surface of the sphere contacts the inner top wall of the receiving groove. At this time, the positioning block is inserted into the positioning groove. BRIEF DESCRIPTION OF THE DRAWINGS

[0024] Figure 1 is a schematic diagram of the overall structure of the present invention;

[0025] Figure 2 is a sectional view of the overall structure of the present invention;

[0026] Figure 3 is a sectional view of the support frame structure of the present invention;

[0027] Figure 4 is a sectional view of the moving plate structure of the present invention;

[0028] Figure 5 is a sectional view of a partial structure disassembly of the present invention;

[0029] Figure 6 is a sectional view of the limit component disassembly of the present invention;

[0030] Figure 7 is of the present invention Figure 2 enlarged schematic view at A;

[0031] Figure 8 is of the present invention Figure 2 enlarged schematic view at B.

[0032] In the figure:

[0033] 1. Quick disassembly and assembly device body; 2. Quick disassembly component; 3. Elastic component; 4. Connection and reset component; 5. Limit component; 101. Workbench; 102. Hammer head; 201. Support frame; 202. Servo motor; 203. Rotating disk; 204. Moving plate; 205. Connecting plate; 206. Damper; 207. Fixed plate; 208. Return spring A; 301. Contact groove; 302. Contact block; 303. Return spring B; 304. Activity groove; 401. Sliding groove; 402. Sliding block; 403. Reset spring; 404. Guide groove; 405. Guide block; 501. Limit groove; 502. Limit block; 503. Accommodation groove; 504. Positioning block; 505. Positioning groove; 506. Return spring C; 507. Wedge groove; 508. Screw; 509. Sphere. Detailed implementation manners

[0034] Next, the technical solutions in the embodiments of the present invention will be clearly and completely described in conjunction with the accompanying drawings in the embodiments of the present invention. Obviously, the described embodiments are only a part of the embodiments of the present invention, rather than all the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those of ordinary skill in the art without creative efforts shall fall within the protection scope of the present invention.

[0035] As Figures 1 to 8 shown, the present invention provides a quick disassembly and assembly device for an aero-engine universal joint ring, including a quick disassembly and assembly device body 1, a quick disassembly component 2, an elastic component 3, a connection and reset component 4, and a limit component 5; the quick disassembly and assembly device body 1 includes a workbench 101 for placing the aero-engine universal joint ring and a hammer head 102 for knocking the aero-engine universal joint ring; a fixture is arranged on the workbench 101; the hammer head 102 is connected to the workbench 101 through the quick disassembly component 2;

[0036] The quick disassembly component 2 includes a support frame 201, a servo motor 202, a rotating disk 203, a moving plate 204, a connecting plate 205, a damper 206, a fixed plate 207, and a return spring A 208; the support frame 201 is fixedly arranged on the workbench 101; the servo motor 202 is fixedly arranged on the support frame 201 through a motor base; the rotating disk 203 is fixedly connected to the output end of the servo motor 202; the moving plate 204 is connected to the rotating disk 203 through the elastic component 3; the connecting plate 205 is fixedly arranged on the bottom surface of the moving plate 204, and the connecting plate 205 is connected to the support frame 201 through the connection and reset component 4; the damper 206 is fixedly arranged on the side of the connecting plate 205 away from the moving plate 204; the fixed plate 207 is fixedly connected to the end of the damper 206 away from the connecting plate 205, and the fixed plate 207 is connected to the hammer head 102 through the limit component 5; the return spring A 208 is sleeved on the damper 206, and both ends of the return spring A 208 are fixedly connected to the connecting plate 205 and the fixed plate 207 respectively;

[0037] The connecting and resetting component 4 includes a sliding groove 401, a sliding block 402, a reset spring 403, a guiding groove 404 and a guiding block 405; a sliding groove 401 is formed on one side of the support frame 201 close to the connecting plate 205; the sliding block 402 is slidably disposed in the sliding groove 401 and fixedly connected to the connecting plate 205; both ends of the reset spring 403 are fixedly connected to the inner wall of the sliding groove 401 and the sliding block 402 respectively; two guiding grooves 404 are symmetrically formed on both sides of the inner wall of the sliding groove 401; the guiding block 405 is slidably disposed in the guiding groove 404 and fixedly connected to the sliding block 402; the elastic strength of the reset spring 403 is less than that of the return spring B 303; the sliding block 402 is of a Y-shaped structure, and the size of the sliding block 402 on the side close to the connecting plate 205 is larger than the size of the sliding block 402 on the side far from the connecting plate 205, so as to conveniently increase the contact area between the sliding block 402 and the connecting plate 205 and improve the connection strength between the sliding block 402 and the connecting plate 205.

[0038] In the present invention, by providing the quick-release component 2 and the connecting and resetting component 4, the universal joint ring of the aero-engine is fixed on the workbench 101 through the fixture on the workbench 101, and the cross shaft on the universal joint ring of the aero-engine is positioned directly below the hammer head 102. Then, the servo motor 202 is started, so that the output shaft of the servo motor 202 drives the rotating disc 203 to rotate, and the moving plate 204 drives the connecting plate 205, the damper 206, the fixing plate 207 and the return spring A 208 to move upward through the elastic component 3, so that the sliding block 402 slides upward in the sliding groove 401, the guiding block 405 slides upward in the guiding groove 404, and the reset spring 403 is stretched under force until the top surface of the sliding block 402 contacts the inner top wall of the sliding groove 401. At this time, under the action of the elastic component 3, the reset spring 403 is no longer under force and begins to contract, so that the sliding block 402 slides downward in the sliding groove 401, the guiding block 405 slides downward in the guiding groove 404, the moving plate 204 drives the connecting plate 205, the damper 206, the fixing plate 207 and the return spring A 208 to move downward, so that the hammer head 102 can contact the cross shaft on the universal joint ring of the aero-engine and strike the cross shaft. During the striking process, the damper 206 can provide resistance and buffering effect to adapt to the striking position of the cross shaft, and the return spring A 208 can make the damper 206 return to its original position. Moreover, under the elastic force of the reset spring 403, the hammer head 102 continuously strikes the cross shaft. Compared with the prior art, the structure of the present invention is reasonably designed. Driven by the servo motor 202 and under the action of the connecting and resetting component 4, the hammer head 102 can continuously strike the universal joint ring of the aero-engine, with relatively high disassembly and assembly efficiency, so as to realize the rapid disassembly and assembly of the universal joint ring of the aero-engine, and moreover, the degree of automation is relatively high.

[0039] As a preferred embodiment, the elastic component 3 includes an abutting groove 301, an abutting block 302, a return spring B 303 and a movable groove 304; an abutting groove 301 is formed on the side of the rotating disk 203 away from the servo motor 202; the abutting block 302 is slidably disposed in the abutting groove 301; both ends of the return spring B 303 are fixedly connected to the inner wall of the abutting groove 301 and the abutting block 302 respectively; a movable groove 304 is formed on the side of the moving plate 204 close to the rotating disk 203, and the abutting block 302 is slidably engaged with the movable groove 304; the abutting block 302 has a frustum-shaped structure, the size of the abutting block 302 on the side close to the return spring B 303 is larger than the size of the abutting block 302 on the side away from the return spring B 303, and the circumferential surface of the abutting block 302 is in contact with the inner wall of the abutting groove 301; the movable groove 304 has an isosceles trapezoid structure, and the opening direction of the movable groove 304 is set towards the rotating disk 203 to facilitate the adaptation of the movable groove 304 to the abutting block 302.

[0040] In the present invention, by providing the elastic component 3, when the rotating disk 203 rotates, the abutting block 302 will squeeze the inner wall of the movable groove 304. Since the elastic strength of the return spring 403 is less than the elastic strength of the return spring B 303, the moving plate 204 will drive the connecting plate 205, the damper 206, the fixing plate 207 and the return spring A 208 to move upward, causing the abutting block 302 to slide in the movable groove 304 until the top surface of the sliding block 402 contacts the inner top wall of the sliding groove 401. At this time, the circumferential surface of the abutting block 302 will squeeze the inner wall of the movable groove 304, causing the abutting block 302 to slide in the abutting groove 301, causing the return spring B 303 to contract under force until the abutting block 302 no longer contacts the moving plate 204. At this time, under the elastic force of the return spring 403, the hammer head 102 will continuously strike the cross shaft. When the abutting block 302 no longer contacts the moving plate 204, under the elastic force of the return spring B 303, the abutting block 302 will slide to its original position. And during the rotation of the rotating disk 203, the abutting block 302 will contact the top surface of the moving plate 204, enabling the abutting block 302 to gradually eliminate the elastic force of the return spring 403 until the bottom surface of the sliding block 402 contacts the inner bottom wall of the sliding groove 401. At this time, the circumferential surface of the abutting block 302 will squeeze the moving plate 204, causing the abutting block 302 to slide in the abutting groove 301, causing the return spring B 303 to contract under force until the abutting block 302 rotates to the lowest end. At this time, under the elastic force of the return spring B 303, the abutting block 302 will contact the inner wall of the movable groove 304.

[0041] As a preferred embodiment, the limiting component 5 includes a limiting groove 501, a limiting block 502, a receiving groove 503, a positioning block 504, a positioning groove 505, a return spring C 506, a wedge-shaped groove 507, a screw 508 and a sphere 509; a limiting groove 501 is formed on one side of the fixing plate 207 close to the hammer head 102; the limiting block 502 is slidably inserted into the limiting groove 501 and fixedly connected to the hammer head 102; a receiving groove 503 is formed in the limiting groove 501; the positioning block 504 is slidably inserted into the receiving groove 503 and extends into the limiting groove 501; a positioning groove 505 is formed on the limiting block 502, and the positioning block 504 is inserted and matched with the positioning groove 505; both ends of the return spring C 506 are fixedly connected to the inner wall of the receiving groove 503 and the positioning block 504 respectively; a wedge-shaped groove 507 is formed on the top surface of the positioning block 504; the screw 508 is screwed on the fixing plate 207; the sphere 509 is fixedly connected to the end of the screw 508; the limiting block 502 has a T-shaped structure with a larger upper part and a smaller lower part to facilitate the limitation of the position of the limiting block 502; an inclined surface is provided on the wedge-shaped groove 507, the spherical surface of the sphere 509 is slidably matched with the inclined surface, and the diameter of the sphere 509 is larger than the diameter of the screw 508; when the top surface of the sliding block 402 contacts the inner top wall of the sliding groove 401, the abutting block 302 is not at the highest end.

[0042] In the present invention, by providing the limiting component 5, according to the size of the universal joint ring of the aero-engine to be disassembled and assembled, the screw 508 is rotated to thread the screw 508 with the fixing plate 207, so that the spherical surface of the sphere 509 presses the inclined surface of the wedge-shaped groove 507, causing the positioning block 504 to slide in the receiving groove 503 and the positioning groove 505, and the return spring C 506 is forced to contract until the spherical surface of the sphere 509 contacts the inner bottom wall of the wedge-shaped groove 507. At this time, the positioning block 504 moves out of the positioning groove 505. Then, the hammer head 102 is moved so that the limiting block 502 slides in the limiting groove 501 until the limiting block 502 moves out of the limiting groove 501. Then, a hammer head 102 with a suitable size is selected, the limiting block 502 is inserted into the limiting groove 501, and the side surface of the limiting block 502 contacts the inner side wall of the limiting groove 501. Subsequently, the screw 508 is rotated in the reverse direction to thread the screw 508 with the fixing plate 207. Under the elastic force of the return spring C 506, the positioning block 504 slides reversely in the receiving groove 503 and the positioning groove 505 until the side surface of the sphere 509 contacts the inner top wall of the receiving groove 503. At this time, the positioning block 504 is inserted into the positioning groove 505.

[0043] In addition, the present invention also relates to a method for a quick disassembly and assembly device of a universal joint ring of an aero-engine, including the following steps:

[0044] Step 1: Through the limiting component 5, the hammer head 102 can be replaced according to the size of the universal joint ring of the aero-engine, and a hammer head 102 with a suitable size can be selected.

[0045] Step 2: The position of the universal joint ring of the aero-engine can be fixed on the workbench 101 through the fixture on the workbench 101;

[0046] Step 3: Start the servo motor 202 to rotate the rotating disk 203, and drive the hammer head 102 to rise to a certain height through the elastic component 3, so that the hammer head 102 can strike the cross shaft on the universal joint ring of the aero-engine;

[0047] Step 4: Under the action of the connecting and resetting component 4, the hammer head 102 can continuously strike the cross shaft through the single-circle rotation of the rotating disk 203.

[0048] Working principle of the present invention: When in use, first, according to the size of the universal joint ring of the aero-engine to be disassembled and assembled, rotate the screw rod 508 to make the screw rod 508 threadedly connected with the fixed plate 207, so that the spherical surface of the sphere 509 presses against the inclined surface of the wedge-shaped groove 507, causing the positioning block 504 to slide in the receiving groove 503 and the positioning groove 505, making the return spring C506 contract under force until the spherical surface of the sphere 509 contacts the inner bottom wall of the wedge-shaped groove 507. At this time, the positioning block 504 moves out of the positioning groove 505. Then, move the hammer head 102 to make the limiting block 502 slide in the limiting groove 501 until the limiting block 502 moves out of the limiting groove 501. Then, select a hammer head 102 with a suitable size, insert the limiting block 502 into the limiting groove 501 and make the side surface of the limiting block 502 contact the inner side wall of the limiting groove 501. Subsequently, rotate the screw rod 508 in the reverse direction to make the screw rod 508 threadedly connected with the fixed plate 207. Under the elastic force of the return spring C506, the positioning block 504 will slide reversely in the receiving groove 503 and the positioning groove 505 until the side surface of the sphere 509 contacts the inner top wall of the receiving groove 503. At this time, the positioning block 504 is inserted into the positioning groove 505;Next, fix the aero-engine universal joint ring on the workbench 101 through the fixture on the workbench 101, and make the cross shaft on the aero-engine universal joint ring directly below the hammer head 102. Then, start the servo motor 202, so that the output shaft of the servo motor 202 drives the rotating disk 203 to rotate, causing the abutting block 302 to squeeze the inner wall of the movable slot 304. Since the elastic strength of the return spring 403 is less than that of the return spring B 303, the moving plate 204 will drive the connecting plate 205, the damper 206, the fixing plate 207 and the return spring A 208 to move upward, causing the abutting block 302 to slide in the movable slot 304, causing the sliding block 402 to slide upward in the sliding slot 401, causing the guiding block 405 to slide upward in the guiding slot 404, and causing the return spring 403 to be stretched until the top surface of the sliding block 402 contacts the inner top wall of the sliding slot 401. At this time, the circumferential surface of the abutting block 302 will squeeze the inner wall of the movable slot 304, causing the abutting block 302 to slide in the abutting slot 301, causing the return spring B 303 to be compressed until the abutting block 302 no longer contacts the moving plate 204. At this time, the return spring 403 is no longer stressed and begins to contract, causing the sliding block 402 to slide downward in the sliding slot 401, causing the guiding block 405 to slide downward in the guiding slot 404, causing the moving plate 204 to drive the connecting plate 205, the damper 206, the fixing plate 207 and the return spring A 208 to move downward, so that the hammer head 102 can contact the cross shaft on the aero-engine universal joint ring and strike the cross shaft. During the striking process, the damper 206 can provide resistance and buffering effect to adapt to the striking position of the cross shaft, and the return spring A 208 can make the damper 206 return to its original position. And under the elastic force of the return spring 403, the hammer head 102 will continuously strike the cross shaft. When the abutting block 302 no longer contacts the moving plate 204, under the elastic force of the return spring B 303, the abutting block 302 will slide back to its original position. And during the rotation of the rotating disk 203, the abutting block 302 will contact the top surface of the moving plate 204, enabling the abutting block 302 to gradually eliminate the elastic force of the return spring 403 until the bottom surface of the sliding block 402 contacts the inner bottom wall of the sliding slot 401. At this time, the circumferential surface of the abutting block 302 will squeeze the moving plate 204, causing the abutting block 302 to slide in the abutting slot 301, causing the return spring B 303 to be compressed until the abutting block 302 rotates to the lowest end. At this time, under the elastic force of the return spring B 303, the abutting block 302 will contact the inner wall of the movable slot 304, causing the abutting block 302 to squeeze the inner wall of the movable slot 304, causing the moving plate 204 to drive the connecting plate 205, the damper 206, the fixing plate 207 and the return spring A 208 to move upward, and so on until after the disassembly and assembly of the aero-engine universal joint ring is completed, control the servo motor 202 so that the output shaft of the servo motor 202 no longer rotates, and then the disassembled and assembled aero-engine universal joint ring can be removed from the workbench 101.;

[0049] The following points should be noted: First, in the description of this application, it should be noted that unless otherwise specified and defined, the terms "installed", "connected", and "linked" should be understood in a broad sense. It can be a mechanical connection or an electrical connection, or it can be the communication inside two components. It can be directly connected. The terms "upper", "lower", "left", "right", etc. are only used to represent relative positional relationships. When the absolute position of the object being described changes, the relative positional relationship may change;

[0050] Second, in the attached drawings of the disclosed embodiments of the present invention, only the structures related to the disclosed embodiments of the present invention are involved. For other structures, reference can be made to the general design. Without conflict, the same embodiment and different embodiments of the present invention can be combined with each other;

[0051] The above is only a preferred specific implementation manner of the present invention, but the protection scope of the present invention is not limited thereto. Any person skilled in the art within the technical scope disclosed by the present invention, according to the technical solution of the present invention and its inventive concept, makes equivalent substitutions or changes, and should be covered by the protection scope of the present invention.

Claims

1. Quick disassembly and assembly device for a universal joint ring of an aeroengine, characterized in that, It includes the main body (1) of the quick disassembly device, the quick release component (2), the elastic component (3), the connection reset component (4) and the limit component (5); the main body (1) of the quick disassembly device includes a workbench (101) for placing the universal joint ring of the aero-engine and a hammer head (102) for knocking the universal joint ring of the aero-engine; a fixture is arranged on the workbench (101); the hammer head (102) is connected to the workbench (101) through the quick release component (2); the quick release component (2) includes a support frame (201), a servo motor (202), a rotating disc (203), a moving plate (204), a connecting plate (205), a damper (206), a fixing plate (207) and a return spring A (208); the support frame (201) is fixedly arranged on the workbench (101); the servo motor (202) is fixedly arranged on the support frame (201) through a motor base; the rotating disc (203) is fixedly connected to the output end of the servo motor (202); the moving plate (204) is connected to the rotating disc (203) through the elastic component (3); the connecting plate (205) is fixedly arranged on the bottom surface of the moving plate (204), and the connecting plate (205) is connected to the support frame (201) through the connection reset component (4); the damper (206) is fixedly arranged on the side of the connecting plate (205) away from the moving plate (204); the fixing plate (207) is fixedly connected to the end of the damper (206) away from the connecting plate (205), and the fixing plate (207) is connected to the hammer head (102) through the limit component (5); the return spring A (208) is sleeved on the damper (206), and both ends of the return spring A (208) are fixedly connected to the connecting plate (205) and the fixing plate (207) respectively.

2. The quick disassembly and assembly device for the universal joint ring of an aeroengine according to claim 1, characterized in that The elastic component (3) includes a butting groove (301), a butting block (302), a return spring B (303) and a movable groove (304); a butting groove (301) is formed on the side of the rotating disc (203) away from the servo motor (202); the butting block (302) slidably penetrates through the butting groove (301); both ends of the return spring B (303) are fixedly connected to the inner wall of the butting groove (301) and the butting block (302) respectively; a movable groove (304) is formed on the side of the moving plate (204) close to the rotating disc (203), and the butting block (302) is slidably matched with the movable groove (304).

3. The quick disassembling and assembling device for the universal joint ring of an aero-engine according to claim 2, characterized in that, The butting block (302) is of a frustum structure, the size of the side of the butting block (302) close to the return spring B (303) is larger than the size of the side of the butting block (302) away from the return spring B (303), and the circumferential surface of the butting block (302) is in contact with the inner wall of the butting groove (301).

4. The quick disassembling and assembling device for the universal joint ring of an aeroengine according to claim 2, wherein The movable groove (304) is of an isosceles trapezoid structure, and the opening direction of the movable groove (304) is set towards the rotating disc (203).

5. The quick disassembly and assembly device for the universal joint ring of an aeroengine according to claim 1, wherein The connection and reset component (4) includes a sliding groove (401), a sliding block (402), a reset spring (403), a guiding groove (404) and a guiding block (405); a sliding groove (401) is formed on one side of the support frame (201) close to the connecting plate (205); the sliding block (402) is slidably inserted into the sliding groove (401) and fixedly connected to the connecting plate (205); both ends of the reset spring (403) are fixedly connected to the inner wall of the sliding groove (401) and the sliding block (402) respectively; at least one guiding groove (404) is formed in the sliding groove (401); the guiding block (405) is slidably inserted into the guiding groove (404) and fixedly connected to the sliding block (402); the elastic strength of the reset spring (403) is less than the elastic strength of the return spring B (303).

6. The quick disassembly and assembly device for the universal joint ring of an aero-engine according to claim 5, characterized in that, The sliding block (402) is of a Y-shaped structure, and the dimension of the sliding block (402) on the side close to the connecting plate (205) is larger than the dimension of the sliding block (402) on the side far from the connecting plate (205).

7. The quick disassembling and assembling device for the universal joint ring of an aeroengine according to claim 1, characterized in that The limiting component (5) includes a limiting groove (501), a limiting block (502), a receiving groove (503), a positioning block (504), a positioning groove (505), a return spring C (506), a wedge-shaped groove (507), a screw (508) and a sphere (509); a limiting groove (501) is formed on one side of the fixing plate (207) close to the hammer head (102); the limiting block (502) is slidably inserted into the limiting groove (501) and fixedly connected to the hammer head (102); at least one receiving groove (503) is formed in the limiting groove (501); the positioning block (504) is slidably inserted into the receiving groove (503) and extends into the limiting groove (501); at least one positioning groove (505) is formed on the limiting block (502), and the positioning block (504) is inserted and matched with the positioning groove (505); both ends of the return spring C (506) are fixedly connected to the inner wall of the receiving groove (503) and the positioning block (504) respectively; a wedge-shaped groove (507) is formed on the top surface of the positioning block (504); the screw (508) is screwed on the fixing plate (207); the sphere (509) is fixedly connected to the end of the screw (508).

8. The quick disassembling and assembling device for the universal joint ring of an aeroengine according to claim 7, characterized in that, The limiting block (502) is of a T-shaped structure with a larger upper part and a smaller lower part.

9. The quick disassembling and assembling device for the universal joint ring of an aeroengine according to claim 7, characterized in that, The wedge-shaped groove (507) is provided with an inclined surface, the spherical surface of the sphere (509) is slidably matched with the inclined surface, and the diameter dimension of the sphere (509) is larger than the diameter dimension of the screw (508).

10. A method for a quick disassembly and assembly device of an aero-engine universal joint ring, applicable to the quick disassembly and assembly device of an aero-engine universal joint ring according to any one of claims 1-9, characterized in that: It includes the following steps: Step 1: Through the limiting component (5), the hammer head (102) can be replaced according to the size of the aero-engine universal joint ring, and a hammer head (102) with a suitable size can be selected; Step 2: Through the fixture on the workbench (101), the position of the aero-engine universal joint ring can be fixed on the workbench (101); Step 3: Start the servo motor (202) to rotate the rotating disc (203), and drive the hammer head (102) to rise to a certain height through the elastic component (3), so that the hammer head (102) can strike the cross shaft on the universal joint ring of the aeroengine; Step 4: Under the action of the connection and reset component (4), the hammer head (102) can continuously strike the cross shaft by a single rotation of the rotating disc (203).

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