Stator and rotor separation device and separation method of aviation direct-current generator

Abstract

The invention relates to the technical field of aviation direct-current generator maintenance, in particular to an aviation direct-current generator stator and rotor separating device and a separating method thereof.The separating device comprises a rack and a fixing plate arranged on the rack, a first separating mechanism is arranged on the right side of the fixing plate, and a second separating mechanism is arranged on the left side of the fixing plate; the first separation mechanism and the second separation mechanism are matched to implement separation of a stator and a rotor, the bottom of the first separation mechanism is connected with an axial adjusting mechanism, and the second separation mechanism and the bottom of the axial adjusting mechanism are correspondingly connected with a radial adjusting mechanism. According to the invention, stator and rotor separation of aviation direct-current generators with different models and diameters can be realized, the separation process is safe and reliable, damage to the aviation direct-current generator caused by knocking separation is avoided, and the separation process is efficient and environment-friendly; the device has the advantages of simple mechanism, low cost, wide range, convenient operation and the like, and is suitable for various types of aviation direct-current generators.

Description

Technical Field

[0001] The present invention relates to the technical field of maintenance of aviation DC generators, and specifically to a stator-rotor separation device for an aviation DC generator and a separation method thereof. Background Technique

[0002] When a certain type of aviation DC generator is being repaired, it is necessary to separate its stator assembly and permanent magnet rotor. Since one end of the shaft of the permanent magnet rotor and the stator assembly bearing are in interference fit, and there is a strong attraction between the permanent magnet rotor and the stator assembly, it is difficult to separate the permanent magnet rotor from the stator assembly. At the same time, due to the different diameters of the stator assemblies and rotor assemblies of different models of aviation DC generators, it is difficult for a separation device with fixed dimensions to separate different models of DC generators.

[0003] Chinese Patent CN217087711U discloses a disassembly and assembly tooling for the stator and rotor of a DC generator. Through the mechanical transmission composed of a crank, a chain, a worm and a worm gear, and a cylindrical cam, as well as positioning and fixing, the up and down movement of the rotor can be realized, and the separation and assembly of the stator and rotor can be realized. Practice has proved that when the interference amount between the rotor shaft and the stator assembly bearing is large, the separation efficiency is low, and at the same time, this device cannot adapt to the separation of the stator assemblies and rotor assemblies of different model diameters of DC generators.

[0004] To solve such problems and improve efficiency at the same time, a stator-rotor separation device for an aviation DC generator and a separation method thereof are designed to solve the problem that it is difficult to separate the permanent magnet rotor and the stator assembly of different models of aviation DC generators. Summary of the Invention

[0005] To solve the above technical problems, the present invention proposes a stator-rotor separation device for an aviation DC generator and a separation method thereof.

[0006] The technical problems to be solved by the present invention are realized by adopting the following technical solutions:

[0007] A stator-rotor separation device for an aviation DC generator includes a bench, a fixing plate arranged on the bench. A first separation mechanism is arranged on the right side of the fixing plate, a second separation mechanism is arranged on the left side of the fixing plate. The first separation mechanism and the second separation mechanism cooperate to implement stator-rotor separation. The bottom of the first separation mechanism is connected with an axial adjustment mechanism, and the second separation mechanism and the bottom of the axial adjustment mechanism are correspondingly connected with a radial adjustment mechanism.

[0008] As a further improvement of the present invention, a telescopic rod is connected to the bottom of the fixing plate, and the telescopic rod is fixedly installed on the bench.

[0009] As a further improvement of the present invention, the radial adjustment mechanism includes a lining plate arranged below the tabletop of the bench, a first hydraulic cylinder, a second hydraulic cylinder, and a third hydraulic cylinder correspondingly arranged on the lining plate. The first hydraulic cylinder is connected with a square guide rail, the square guide rail is connected with the second detachment mechanism, and the second hydraulic cylinder and the third hydraulic cylinder are connected with the axial adjustment mechanism.

[0010] As a further improvement of the present invention, the axial adjustment mechanism includes a support plate located on the right side of the fixed plate, a guide rail and a cylinder arranged on the support plate, and a drag plate slidably mounted on the guide rail. The cylinder is connected with a cylinder piston rod, the cylinder piston rod is connected with the drag plate, and the first detachment mechanism is arranged on the drag plate.

[0011] As a further improvement of the present invention, the first detachment mechanism includes a right motor and a first tail attachment assembly arranged on the drag plate, a first lead screw arranged on the first tail attachment assembly, a first sleeve connected with the first lead screw, and a first Morse No. 2 taper center connected with the first sleeve. The right motor is connected with the first lead screw through a first belt.

[0012] As a further improvement of the present invention, the second detachment mechanism includes a left motor and a second tail attachment assembly connected with the square guide rail, a second lead screw arranged on the second tail attachment assembly, a second sleeve connected with the second lead screw, and a second Morse No. 2 taper center connected with the second sleeve. The left motor is connected with the second lead screw through a second belt.

[0013] An aviation DC generator stator-rotor detachment method, which applies the above-mentioned aviation DC generator stator-rotor detachment device, includes the following steps:

[0014] The first step: The operator starts the cylinder to drag the drag plate through the cylinder piston rod, and pulls the first detachment mechanism to the right by a certain distance.

[0015] The second step: Fix the stator assembly with the rotor assembly on a certain type of aviation DC generator in the fixed plate.

[0016] The third step: Start the first hydraulic cylinder, the second hydraulic cylinder, and the third hydraulic cylinder, and adjust the height of the first Morse No. 2 taper center in the first detachment mechanism and the height of the second Morse No. 2 taper center in the second detachment mechanism, so that the first Morse No. 2 taper center and the second Morse No. 2 taper center are on the same axis as the rotor assembly.

[0017] The fourth step: Start the cylinder again to drag the drag plate to reset through the cylinder piston rod, so that the first Morse No. 2 taper center in the first detachment mechanism and the second Morse No. 2 taper center in the second detachment mechanism clamp the rotating shaft on the rotor assembly from the left and right sides.

[0018] Step 5: After the operator sets the movement displacement, start the left motor and the right motor to run, and stop until the rotor assembly is completely separated from the stator assembly;

[0019] Step 6: The operator holds the rotor assembly, starts the cylinder, and drags the drag plate through the cylinder piston rod, so that the No. 2 Morse taper tip in the first separation mechanism exits from the contact with the rotating shaft of the rotor assembly, and removes the separated rotor assembly and stator assembly.

[0020] As a further improvement of the present invention, the specific process of Step 5 is as follows: The left motor in the second separation mechanism drives the second belt through counterclockwise rotation, drives the second lead screw through the second belt, and the rotational movement of the second lead screw drives the second sleeve to push the No. 2 Morse taper tip to push the rotor assembly to move; at the same time, the right motor in the first separation mechanism drives the first belt through counterclockwise rotation, drives the first lead screw through the first belt, and the rotational movement of the first lead screw drives the first sleeve to push the No. 1 Morse taper tip to hold the rotor assembly and move to the right together until the rotor assembly is completely separated from the stator assembly.

[0021] The beneficial effects of the present invention are:

[0022] The present invention provides a device and method for separating the stator and rotor of an aviation DC generator, which can realize the separation of the stator and rotor of aviation DC generators with different diameters, and the separation process is safe and reliable, avoiding the damage to the aviation DC generator caused by knocking separation, making the separation process efficient and environmentally friendly; it has the advantages of simple structure, low cost, adapting to many types and wide ranges of aviation DC generators, and convenient operation. Description of the Drawings

[0023] The following further describes the present invention with reference to the drawings and embodiments:

[0024] Figure 1 It is the front view structural schematic diagram of the present invention;

[0025] Figure 2 It is the top view structural schematic diagram of the present invention.

[0026] In the figure: 1. Bench; 2. Liner; 3. First hydraulic cylinder; 4. Square guide rail; 5. Second hydraulic cylinder; 6. Third hydraulic cylinder; 7. Cylinder; 8. First belt; 9. First lead screw; 10. First tail attachment assembly; 11. First sleeve; 12. No. 2 Morse taper tip; 13. Rotor assembly; 14. Stator assembly; 15. No. 2 Morse taper tip; 16. Second sleeve; 17. Second tail attachment assembly; 18. Second lead screw; 19. Second belt; 20. Left motor; 21. Fixed plate; 22. Telescopic rod; 23. Right motor; 24. Cylinder piston rod; 25. Support plate; 26. Guide rail; 27. Drag plate. Detailed Embodiments

[0027] In order to make the technical means, creative features, achieved purposes and effects realized by the present invention easy to understand, the present invention will be further described below in conjunction with the accompanying drawings and embodiments.

[0028] As shown in Figures 1 to 2 FIG. 1, an aero DC generator stator-rotor separating device includes a bench 1 and a fixing plate 21 arranged on the bench 1. The fixing plate 21 is used for fixedly installing a stator assembly 14. A telescopic rod 22 is connected to the bottom of the fixing plate 21. The telescopic rod 22 is fixedly installed on the bench 1. The telescopic rod 22 can adjust the height of the fixing plate 21 so as to adapt to aero DC generators with different radial dimensions.

[0029] A first separating mechanism is arranged on the right side of the fixing plate 21, and a second separating mechanism is arranged on the left side of the fixing plate 21. The first separating mechanism and the second separating mechanism cooperate to implement stator-rotor separation. The bottom of the first separating mechanism is connected with an axial adjusting mechanism. The axial adjusting mechanism can adjust the distance between the first separating mechanism and the fixing plate 21 and the distance between the first separating mechanism and the second separating mechanism, so as to adapt to aero DC generators with different rotor circumferential dimensions. The bottom of the second separating mechanism and the axial adjusting mechanism are correspondingly connected with a radial adjusting mechanism. The radial adjusting mechanism can adjust the height of the separating mechanism to adapt to aero DC generators with different radial dimensions.

[0030] As a further improvement of this embodiment, the radial adjusting mechanism includes a lining plate 2 arranged under the tabletop of the bench 1, a first hydraulic cylinder 3, a second hydraulic cylinder 5 and a third hydraulic cylinder 6 correspondingly arranged on the lining plate 2. The first hydraulic cylinder 3 is connected with a square guide rail 4. The square guide rail 4 is connected with the second separating mechanism. The second hydraulic cylinder 5 and the third hydraulic cylinder 6 are connected with the axial adjusting mechanism.

[0031] As a further improvement of this embodiment, the axial adjusting mechanism includes a supporting plate 25 on the right side of the fixing plate 21, a guide rail 26 and a cylinder 7 arranged on the supporting plate 25, and a drag plate 27 slidably installed on the guide rail 26. The cylinder 7 is connected with a cylinder piston rod 24. The cylinder piston rod 24 is connected with the drag plate 27. The first separating mechanism is arranged on the drag plate 27.

[0032] As a further improvement of this embodiment, the first detachment mechanism includes a right motor 23 and a first tail attachment assembly 10 provided on the carriage 27, a first lead screw 9 provided on the first tail attachment assembly 10, a first sleeve 11 connected to the first lead screw 9, and a first Morse No. 2 taper center 12 connected to the first sleeve 11. The right motor 23 is connected to the first lead screw 9 through a first belt 8.

[0033] As a further improvement of this embodiment, the second detachment mechanism includes a left motor 20 and a second tail attachment assembly 17 connected to the square guide rail 4, a second lead screw 18 provided on the second tail attachment assembly 17, a second sleeve 16 connected to the second lead screw 18, and a second Morse No. 2 taper center 15 connected to the second sleeve 16. The left motor 20 is connected to the second lead screw 18 through a second belt 19.

[0034] An aviation DC generator stator-rotor detachment method, which applies the above-mentioned aviation DC generator stator-rotor detachment device, includes the following steps:

[0035] First step: The operator starts the cylinder 7 and drags the carriage 27 through the cylinder piston rod 24, pulling the first detachment mechanism to the right by a certain distance.

[0036] Second step: Fix the stator assembly 14 with the rotor assembly 13 on a certain type of aviation DC generator in the fixing plate 21.

[0037] Third step: Start the first hydraulic cylinder 3, the second hydraulic cylinder 5, and the third hydraulic cylinder 6, and adjust the height of the first Morse No. 2 taper center 12 in the first detachment mechanism and the height of the second Morse No. 2 taper center 15 in the second detachment mechanism, so that the first Morse No. 2 taper center 12 and the second Morse No. 2 taper center 15 are on the same axis as the rotor assembly 13.

[0038] Fourth step: Start the cylinder 7 again and drag the carriage 27 to reset through the cylinder piston rod 24, so that the first Morse No. 2 taper center 12 in the first detachment mechanism cooperates with the second Morse No. 2 taper center 15 in the second detachment mechanism to clamp the rotating shaft on the rotor assembly 13 from both left and right sides.

[0039] Fifth step: After the operator sets the movement displacement, start the left motor 20 and the right motor 23 to start running, and stop until the rotor assembly 13 is completely detached from the stator assembly 14.

[0040] Specifically: The left motor 20 in the second detachment mechanism drives the second belt 19 through counterclockwise rotation, drives the second lead screw 18 through the second belt 19, and the rotational movement of the second lead screw 18 drives the second sleeve 16 to push the second Morse No. 2 taper center 15 to push the rotor assembly 13 to move; at the same time, the right motor 23 in the first detachment mechanism drives the first belt 8 through counterclockwise rotation, drives the first lead screw 9 through the first belt 8, and the rotational movement of the first lead screw 9 drives the first sleeve 11 to push the first Morse No. 2 taper center 12 to hold the rotor assembly 13 and move to the right together until the rotor assembly 13 is completely detached from the stator assembly 14.

[0041] Sixth step: The operator holds the rotor assembly 13 and starts the cylinder 7 to drag the drag plate 27 through the cylinder piston rod 24, so that the first Morse No. 2 taper center 12 in the first detachment mechanism withdraws from the contact with the rotating shaft of the rotor assembly 13, and the detached rotor assembly 13 and stator assembly 14 are taken off.

[0042] The above shows and describes 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. What is described in the above embodiments and the specification is only the principle of the present invention. Without departing from the spirit and scope of the present invention, the present invention will 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 aircraft DC generator stator and rotor separation device, characterized in that: The invention comprises a stand (1) and a fixed plate (21) arranged on the stand (1); a first disengagement mechanism is arranged on the right side of the fixed plate (21); a second disengagement mechanism is arranged on the left side of the fixed plate (21); the first disengagement mechanism cooperates with the second disengagement mechanism to implement stator-rotor disengagement; an axial adjustment mechanism is connected to the bottom of the first disengagement mechanism; and a radial adjustment mechanism is connected to the bottom of the second disengagement mechanism and the axial adjustment mechanism.

2. The stator and rotor separation device of an aviation DC generator according to claim 1, characterized in that: The bottom of the fixed plate (21) is connected to a telescopic rod (22), and the telescopic rod (22) is fixedly mounted on the stand (1).

3. The stator and rotor separation device of an aviation DC generator according to claim 1, characterized in that: The radial adjustment mechanism comprises a lining plate (2) arranged below the table surface of the platform (1), a first hydraulic cylinder (3), a second hydraulic cylinder (5) and a third hydraulic cylinder (6) arranged correspondingly on the lining plate (2), the first hydraulic cylinder (3) is connected to a square guide rail (4), the square guide rail (4) is connected to the second disengagement mechanism, and the second hydraulic cylinder (5) and the third hydraulic cylinder (6) are connected to the axial adjustment mechanism.

4. The stator and rotor separation device of an aviation DC generator according to claim 3, characterized in that: The axial adjustment mechanism comprises a support plate (25) located on the right side of the fixed plate (21), a guide rail (26) and a cylinder (7) arranged on the support plate (25), and a drag plate (27) slidably mounted on the guide rail (26); the cylinder (7) is connected to a cylinder piston rod (24), the cylinder piston rod (24) is connected to the drag plate (27), and the first disengagement mechanism is arranged on the drag plate (27).

5. The stator and rotor separation device of an aviation DC generator according to claim 4, characterized in that: The first disengagement mechanism comprises a right motor (23) and a first tail attachment (10) arranged on the carriage (27), a first lead screw (9) arranged on the first tail attachment (10), a first sleeve (11) connected to the first lead screw (9), and a first Morse No. 2 cone tip (12) connected to the first sleeve (11); the right motor (23) is connected to the first lead screw (9) via a first belt (8).

6. The stator and rotor separation device of an aviation DC generator according to claim 3, characterized in that: The second disengagement mechanism comprises a left motor (20) connected to the square guide rail (4) and a second tail attachment (17), a second lead screw (18) arranged on the second tail attachment (17), a second sleeve (16) connected to the second lead screw (18), and a second Morse No. 2 cone tip (15) connected to the second sleeve (16); the left motor (20) and the second lead screw (18) are connected via a second belt (19).

7. A method for separating the stator and rotor of an aviation DC generator, characterized in that: An aircraft DC generator stator and rotor separation device according to any one of claims 1 to 6 comprises the following steps: Step 1: The operator starts the cylinder (7) and drags the drag plate (27) through the cylinder piston rod (24), thereby pulling the first disengagement mechanism to the right by a certain distance; Step 2: fix the stator assembly (14) with the rotor assembly (13) on a certain type of aviation DC generator in a fixing plate (21); Step 3: Start the first hydraulic cylinder (3), the second hydraulic cylinder (5), and the third hydraulic cylinder (6), and adjust the height of the first Morse No. 2 cone tip (12) in the first disengagement mechanism and the height of the second Morse No. 2 cone tip (15) in the second disengagement mechanism, so that the first Morse No. 2 cone tip (12), the second Morse No. 2 cone tip (15) and the rotor assembly (13) are located on the same axis; Step 4: Start the cylinder (7) again and use the cylinder piston rod (24) to drag the drag plate (27) to reset, so that the first Morse No. 2 cone tip (12) in the first disengagement mechanism cooperates with the second Morse No. 2 cone tip (15) in the second disengagement mechanism to clamp the rotating shaft on the rotor assembly (13) from the left and right sides; Step 5: After the operator sets the movement displacement, the left motor (20) and the right motor (23) are started to run until the rotor assembly (13) is completely separated from the stator assembly (14); Step 6: The operator holds the rotor assembly (13) and starts the cylinder (7) to drag the drag plate (27) through the cylinder piston rod (24), so that the first Morse No. 2 cone tip (12) in the first disengagement mechanism withdraws from the contact with the rotating shaft of the rotor assembly (13), and removes the disengaged rotor assembly (13) and stator assembly (14).

8. The method for separating the stator and rotor of an aviation DC generator according to claim 7, characterized in that: The specific process of the fifth step is as follows: the left motor (20) in the second disengagement mechanism drives the second belt (19) by rotating counterclockwise, and drives the second lead screw (18) by the second belt (19), and the rotational movement of the second lead screw (18) drives the second sleeve (16) to push the second Modulus No. 2 cone top (15) to push the rotor assembly (13) to move; at the same time, the right motor (23) in the first disengagement mechanism drives the first belt (8) by rotating counterclockwise, and drives the first lead screw (9) by the first belt (8), and the rotational movement of the first lead screw (9) drives the first sleeve (11) to push the first Modulus No. 2 cone top (12) to press against the rotor assembly (13) and move to the right together, until the rotor assembly (13) is completely separated from the stator assembly (14).

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