A motor maintenance test platform and test method for aircraft

Abstract

The present invention discloses a motor maintenance test platform and a test method for aircraft, and relates to the technical field of aircraft generators. The present invention includes a platform, a test bench is fixedly installed on the top of the platform, a traction motor and a speed increaser are fixedly installed on the top of the test bench, a first coupling is arranged between the traction motor and the speed increaser, the output shaft of the traction motor is connected to the input shaft of the speed increaser through the first coupling, and the speed increaser is arranged on the side of the traction motor away from the traction motor with the aircraft generator to be tested and a transfer assembly. The present invention sets a transfer assembly so that the transfer assembly carries the aircraft generator to be tested to the height of the test bench, and then the staff continues to push the transfer trolley to move to the top of the transport plate, so that the aircraft generator to be tested is stably transported to the top of the test bench while being positioned, avoiding handling accidents and inaccurate placement problems, and facilitating subsequent docking with the speed increaser.

Description

Technical Field

[0001] The invention relates to the technical field of aircraft generators, and in particular to a motor maintenance test platform and a test method for aircraft. Background Art

[0002] The aircraft generator test platform is a key equipment for the aircraft power generation system test. It is used to simulate the generator speed, aircraft power load and other parameters during the ground test or maintenance of the aircraft generator. The current aircraft generator test platform is generally composed of a towing table, a simulated load, a measurement and control system, and an oil cooling system. It can realize the towing, loading, and data measurement functions, complete the performance index acceptance test and fault detection and positioning, and can reproduce, comprehensively analyze and troubleshoot faults occurring in the aircraft.

[0003] At present, when inspecting and repairing aircraft generators, the aircraft generator test platform uses a traction motor equipped with a speed increaser to drive the generator under test, and the input end of the generator and the output end of the speed increaser need to be connected through a coupling. Since aircraft generators are generally large in size and relatively heavy in weight, the generator under test needs to be moved to the test platform manually or with the help of a handling machine, and then driven and assembled with the speed increaser. The whole process is time-consuming and labor-intensive, and is prone to generator handling accidents and inaccurate placement problems. Therefore, an aircraft motor maintenance test platform and a test method are proposed. Summary of the invention

[0004] The purpose of the present invention is to solve the problem that the generator under test is currently transported manually or with the help of a transport machine to a test platform and then assembled with a speed increaser. The whole process is time-consuming and labor-intensive, and is prone to generator transportation accidents and inaccurate placement. The present invention provides an aircraft motor maintenance test platform and a test method.

[0005] In order to achieve the above-mentioned purpose, the present invention specifically adopts the following technical solutions:

[0006] An aircraft motor maintenance test platform and a test method, comprising a platform, a test bench is fixedly installed on the top of the platform, a traction motor and a speed increaser are fixedly installed on the top of the test bench, a first coupling is arranged between the traction motor and the speed increaser, an output shaft of the traction motor is connected to an input shaft of the speed increaser through the first coupling, and an aircraft generator to be tested and a transfer assembly are arranged on a side of the speed increaser away from the traction motor;

[0007] The transfer assembly is used to lift and transfer the aircraft generator to be tested. The transfer assembly includes a transfer trolley arranged on one side of the speed increaser, and the aircraft generator to be tested is arranged inside the transfer trolley. A flap is rotatably installed on the side of the transfer trolley close to the speed increaser, and a connecting hole is opened on one side of the flap. The input shaft of the aircraft generator to be tested is located inside the connecting hole. Locking pin groups are fixedly installed on both sides of the top of the transfer trolley. Two symmetrically arranged placement seats are slidably installed inside the transfer trolley. The aircraft generator to be tested is placed on top of the two placement seats. Horizontally arranged fastening electric push rods are fixedly installed on both sides of the transfer trolley. The telescopic ends of the fastening electric push rods are fixedly installed with fastening push plates, two fastening sliding holes are provided on both sides of the transfer trolley, and the same fastening rod is slidably installed inside the two fastening sliding holes at the same height, and the two ends of the fastening rod are respectively fixedly installed on the side walls of the two fastening push plates, and the four corners of the bottom of the transfer trolley are fixedly installed with traveling wheels, and the same lifting frame is arranged between the transfer trolley and the platform, and winches are fixedly installed at the four corners of the top of the lifting frame, and traction steel cables are wound inside the winches, and one end of the four traction steel cables passes through the top of the lifting frame and is fixedly installed with the same lifting seat, and a docking assembly is arranged on the top of the platform;

[0008] The docking assembly is used to assist the semi-automatic connection between the input shaft of the aircraft generator to be tested and the output shaft of the speed increaser, and the docking assembly includes two horizontally arranged travel guide rails fixedly installed on the top of the platform, and the top of the travel guide rails are driven to install a travel slide, and the top of the travel slide is fixedly installed with a support frame, and the same electric lifting platform is fixedly installed between the two support frames, and the top of the telescopic end of the electric lifting platform is fixedly installed with the same transport plate, and the interior of the lifting seat and the top of the transport plate are provided with two travel grooves, and the interior of the travel groove is provided with two wheel grooves adapted to the travel wheel, and the top of the test bench is fixedly installed with two guide rails. The slide rails are distributed on both sides of the transport plate, and guide sliders are slidably installed on the top of the guide slide rails. The same support frame is fixedly installed on the top of the two guide sliders, and a transposition guide rail is fixedly installed on the bottom of the support frame. A transposition slide is driven and installed on the top of the transposition guide rail. A transposition slide is fixedly installed on the top of the transposition slide. A transposition frame is slidably installed inside the support frame, and a plurality of evenly distributed mounting frames are fixedly installed on the top of the transposition frame. A second coupling is rotatably installed on the mounting frames. A connecting groove is opened on the side wall of the support frame, and the position of the connecting groove is consistent with the axial position of the output shaft of the speed increaser.

[0009] Furthermore, guide screw sleeves are fixedly installed on both sides of the transfer trolley, one end of the guide screw sleeves extends to the interior of the transfer trolley, and the interior of the guide screw sleeves is threaded with a pitch adjusting screw, one end of the two pitch adjusting screws are rotatably installed on the side walls of the two placement seats respectively, and the end of the pitch adjusting screw located outside the transfer trolley is fixedly installed with a pitch adjusting knob.

[0010] Furthermore, a first positioning slide frame is fixedly installed on the side of the bottom of the transfer trolley away from the speed increaser, a positioning plug plate is slidably installed inside the first positioning slide frame, and a second positioning slide frame compatible with the positioning plug plate is fixedly installed on the side of the transport plate away from the speed increaser.

[0011] Furthermore, four through-type jacks are fixedly installed inside the lifting frame, and the four through-type jacks are respectively located at the bottom of the four winches, and the traction steel rope located at the same place is inserted inside the through-type jacks.

[0012] Furthermore, a plurality of evenly distributed guide rollers are rotatably mounted on the top of the platform, the guide rollers are horizontally arranged and located between the two travel guide rails, the axes of the guide rollers are perpendicular to the travel guide rails, and the bottom of the electric lifting platform is in contact with the guide rollers.

[0013] Furthermore, an anti-pinch fixing baffle is fixedly installed on one side of the speed increasing box, a through hole is opened on the side wall of the anti-pinch fixing baffle, and the output shaft of the speed increasing box is located inside the through hole.

[0014] Furthermore, an anti-pinch flip plug plate is rotatably mounted on one side of the guide rail, a flip handle is fixedly mounted on the top of the anti-pinch flip plug plate, and a gear slot matching the anti-pinch flip plug plate is opened on the top of the guide rail.

[0015] A maintenance and testing method for an aircraft motor comprises the following steps:

[0016] S1. Installation of the generator: Place the aircraft generator to be tested into the transfer trolley, and use the fastening rod, flap and placement seat to clamp the aircraft generator to be tested at three points, and stably install the aircraft generator to be tested inside the transfer trolley;

[0017] S2. Transfer of the generator: Push the transfer trolley onto the lifting seat, and the hoist drives the lifting seat to the height of the test bench, and continue to push the transfer trolley to the top of the transport plate;

[0018] S3. Alignment of the generator: The electric lifting platform drives the transport plate to move up and down, so that the axis of the input shaft of the aircraft generator to be tested is consistent with the axis of the second coupling. The staff begins to manually adjust so that the output shafts of the second coupling and the speed increaser are aligned with the input shaft of the aircraft generator to be tested;

[0019] S4. Docking of the generator: Push the support frame as a whole to move toward the speed increaser, so that the second coupling is docked with the output shaft of the speed increaser, and the traveling slide drives the transport plate to move until the input shaft of the aircraft generator to be tested is inserted into the second coupling;

[0020] S5. Generator testing: gradually connect the load simulation system, measurement and control system, and lubricating oil cooling system to perform maintenance tests on the aircraft generator to be tested.

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

[0022] 1. The present invention provides a transfer assembly so that the transfer assembly carries the aircraft generator to be tested and moves to the height of the test bench. Then the staff continues to push the transfer trolley to move the transfer trolley to the top of the transport plate to realize the transportation of the aircraft generator to be tested. The aircraft generator to be tested is stably transported to the top of the test bench while being positioned, avoiding transportation accidents and inaccurate placement problems, and facilitating the subsequent docking with the speed increaser.

[0023] 2. The present invention sets a docking assembly so that the transport plate carries the transfer trolley to move automatically. The staff then manually adjusts the relative positions of the input shaft of the aircraft generator to be tested, the output shaft of the speed increaser and the second coupling so that the three are aligned. The docking assembly enables the semi-automatic docking of the aircraft generator to be tested, the second coupling and the speed increaser, which greatly reduces manual operations and reduces operational risks.

[0024] 3. The present invention provides a pitch-adjusting screw, so that before placing the aircraft generator to be tested on the transfer trolley, the pitch-adjusting knobs on both sides are rotated to drive the two placement seats to make reverse linear motion, and the distance between the two placement seats is adjusted, so that the placement seats can support aircraft generators to be tested of different specifications and sizes, so that the transfer trolley can handle common models of aircraft generators to be tested, thereby improving the versatility of the transfer trolley;

[0025] 4. The present invention sets a first positioning slide frame, so that after the transfer trolley is transported to the transport board, the first positioning slide frame is aligned with the second positioning slide frame, and then the staff slides the positioning plug plate in the first positioning slide frame to make the positioning plug plate snap into the second positioning slide frame, and further locks the transfer trolley to prevent the transfer trolley from being pushed by the reaction force and offset when the aircraft generator to be tested is docked with the second coupling and the speed increaser;

[0026] 5. The present invention provides a through-type jack so that during the lifting process of the lifting seat, the four traction cables can effectively prevent the lifting seat from shaking. At the same time, after the lifting seat is lifted to the height of the transport plate, the four through-type jacks on the top will lock the four traction cables respectively, so that the lifting seat is stably maintained at the current position, to prevent the lifting seat from shaking back and forth when the transfer trolley is pushed from the lifting seat to the transport plate, thereby affecting the transfer of the transfer trolley;

[0027] 6. The present invention provides guide rollers so that when the traveling slide drives the electric lifting platform and the transport plate to move, the electric lifting platform will move synchronously on multiple guide rollers, so that the multiple guide rollers support and lubricate the movement of the electric lifting platform, thereby preventing the transport plate carrying the transfer trolley and the aircraft generator to be tested from causing excessive burden on the traveling slide due to excessive load;

[0028] 7. The present invention provides an anti-pinch fixed baffle plate, so that when adjusting the positions of the input shaft of the aircraft generator to be tested, the second coupling and the output shaft of the speed increaser, the staff can put their hands in the gap between the anti-pinch fixed baffle plate and the speed increaser to adjust the output shaft of the speed increaser, so that the anti-pinch fixed baffle plate can protect the staff's hands to prevent the travel slide from losing control and causing the staff's hands to be pinched;

[0029] 8. The present invention provides an anti-pinch flip plate, so that during the process of aligning the aircraft generator to be tested, the second coupling and the speed increaser, the anti-pinch flip plate is first rotated to make the anti-pinch flip plate engage in the gear slot on the guide slide rail to block the guide slide block, so that the entire support frame is stuck on one side of the anti-pinch flip plate, which plays a role of emergency braking and further prevents the hands of staff from being clamped due to loss of control of the traveling slide. BRIEF DESCRIPTION OF THE DRAWINGS

[0030] Figure 1 It is a schematic diagram of the three-dimensional structure of the present invention;

[0031] Figure 2 It is a schematic diagram of the three-dimensional structure of the platform and the test platform of the present invention;

[0032] Figure 3 It is a schematic diagram of the three-dimensional structure of the traction motor and the speed increasing box of the present invention;

[0033] Figure 4 It is a schematic diagram of the three-dimensional structure of the traveling guide rail and the transport plate of the present invention;

[0034] Figure 5 It is a schematic diagram of the three-dimensional structure of the transfer vehicle of the present invention and the aircraft generator to be tested in cooperation with each other from a first-view perspective;

[0035] Figure 6 It is a schematic diagram of the third perspective structure of the transfer vehicle of the present invention and the aircraft generator to be tested;

[0036] Figure 7 It is a schematic diagram of the three-dimensional structure of the lifting frame of the present invention;

[0037] Figure 8 It is a schematic diagram of the three-dimensional structure of the supporting frame and the second coupling of the present invention;

[0038] Fig. 9 The present invention Figure 8 Schematic diagram of the structure at A in the middle;

[0039] Fig.10 It is a schematic diagram of a flow chart of a maintenance and testing method for an aircraft motor of the present invention;

[0040] Figure numerals: 1, platform; 2, test bench; 3, traction motor; 4, speed increaser; 5, first coupling; 6, transfer trolley; 7, aircraft generator to be tested; 8, flap; 801, connecting hole; 9, locking latch group; 10, placement seat; 11, fastening electric push rod; 12, fastening push plate; 13, fastening rod; 14, traveling wheel; 15, lifting frame; 16, winch; 17, traction steel rope; 18, lifting seat; 19, traveling guide rail; 20, traveling slide; 21, electric lifting platform; 22, Transport plate; 23. Travel groove; 24. Wheel groove; 25. Guide rail; 26. Guide slider; 27. Support frame; 2701. Connecting groove; 28. Transposition rail; 29. ​​Transposition frame; 30. Mounting frame; 31. Second coupling; 32. Pitch-adjusting screw; 33. Pitch-adjusting knob; 34. First positioning slide frame; 35. Positioning plug plate; 36. Second positioning slide frame; 37. Through-type jack; 38. Guide roller; 39. Anti-pinch fixed baffle; 40. Anti-pinch flip plug plate; 41. Flip handle. DETAILED DESCRIPTION

[0041] In order to make the purpose, technical solutions and advantages of the embodiments of the present invention clearer, the technical solutions in the embodiments of the present invention will be clearly and completely described below in conjunction with the drawings in the embodiments of the present invention. Obviously, the described embodiments are part of the embodiments of the present invention, not all of the embodiments. Generally, the components of the embodiments of the present invention described and shown in the drawings here can be arranged and designed in various different configurations.

[0042] Therefore, the following detailed description of the embodiments of the present invention provided in the accompanying drawings is not intended to limit the scope of the invention claimed for protection, but merely represents selected embodiments of the present invention. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0043] It should be noted that similar reference numerals and letters represent similar items in the following drawings, so once an item is defined in one drawing, it does not need to be further defined and explained in the subsequent drawings. In addition, the terms "first", "second", etc. are only used to distinguish the description and cannot be understood as indicating or implying relative importance.

[0044] In the description of the embodiments of the present invention, it should be noted that the terms "inside", "outside", "upper", etc. indicate orientations or positional relationships based on the orientations or positional relationships shown in the accompanying drawings, or are the orientations or positional relationships in which the inventive product is usually placed when used. They are only for the convenience of describing the present invention and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore cannot be understood as a limitation on the present invention.

[0045] like Figures 1 to 10 As shown, an aircraft motor maintenance test platform and test method include a platform 1, such as Figure 1 As shown, a test bench 2 is fixedly installed on the top of the platform 1. Figure 2 As shown, a traction motor 3 and a speed increasing box 4 are fixedly installed on the top of the test bench 2. Figure 3 As shown, a first coupling 5 is provided between the traction motor 3 and the speed increasing box 4, and the output shaft of the traction motor 3 is connected to the input shaft of the speed increasing box 4 by driving through the first coupling 5. Figure 1 As shown, the speed increasing box 4 is provided with the aircraft generator 7 to be tested and the transfer assembly on the side away from the traction motor 3. In this embodiment, the speed increasing box 4 and the aircraft generator 7 to be tested both have a self-locking function;

[0046] The transfer assembly is used to lift and transfer the aircraft generator 7 to be tested, such as Figure 1 As shown, the transfer assembly includes a transfer trolley 6 disposed on one side of the speed increasing box 4, and the aircraft generator 7 to be tested is disposed inside the transfer trolley 6. Figure 5 As shown, a flap 8 is rotatably mounted on one side of the transfer trolley 6 close to the speed increaser 4, a connecting hole 801 is provided on one side of the flap 8, the input shaft of the aircraft generator 7 to be tested is located inside the connecting hole 801, and a locking latch group 9 is fixedly mounted on both sides of the top of the transfer trolley 6. In this embodiment, the locking latch group 9 includes a sliding latch and a socket, the socket is mounted on both sides of the top of the transfer trolley 6, and the sliding latch is mounted on both sides of the top of the flap 8. Figure 6As shown, the transfer trolley 6 is internally slidably installed with two symmetrically arranged placement seats 10, and the aircraft generator 7 to be tested is placed on the top of the two placement seats 10. Both sides of the transfer trolley 6 are fixedly installed with horizontally arranged fastening electric push rods 11, and the telescopic ends of the fastening electric push rods 11 are fixedly installed with fastening push plates 12. Two fastening sliding holes are provided on both sides of the transfer trolley 6, and the same fastening rod 13 is slidably installed inside the two fastening sliding holes at the same height, and the two ends of the fastening rod 13 are respectively fixedly installed on the side walls of the two fastening push plates 12, and the four corners of the bottom of the transfer trolley 6 are fixedly installed with traveling wheels 14. Figure 1 As shown, a lifting frame 15 is provided between the transfer trolley 6 and the platform 1. Figure 7 As shown, winches 16 are fixedly installed at the four corners of the top of the lifting frame 15, and traction cables 17 are wound inside the winches 16. One end of the four traction cables 17 passes through the top of the lifting frame 15 and is fixedly installed with the same lifting seat 18. A docking assembly is provided on the top of the platform 1;

[0047] The docking assembly is used to assist the input shaft of the aircraft generator 7 to be tested to semi-automatically connect with the output shaft of the speed increaser 4. Figure 2 As shown, the docking assembly includes two horizontally arranged travel guide rails 19 fixedly mounted on the top of the platform 1, as shown in FIG. Figure 4 As shown, a traveling slide 20 is driven and installed on the top of the traveling guide rail 19, a support frame is fixedly installed on the top of the traveling slide 20, an electric lifting platform 21 is fixedly installed between the two support frames, and a transport plate 22 is fixedly installed on the top of the telescopic end of the electric lifting platform 21. In this embodiment, the test bench 2 is in a "U" shape and is horizontally installed on the top of the platform 1. The transport plate 22 is located between the two end surfaces of the test bench 2. Two traveling grooves 23 are provided inside the lifting seat 18 and on the top of the transport plate 22. Two wheel grooves 24 adapted to the traveling wheels 14 are provided inside the traveling grooves 23. Figure 8 , Fig. 9As shown, two guide rails 25 are fixedly installed on the top of the test bench 2, and the two guide rails 25 are distributed on both sides of the transport plate 22. Guide sliders 26 are slidably installed on the top of the guide rails 25. The same support frame 27 is fixedly installed on the top of the two guide sliders 26. A transposition guide rail 28 is fixedly installed on the bottom of the support frame 27. A transposition slide table is driven and installed on the top of the transposition guide rail 28. A transposition frame 29 is fixedly installed on the top of the transposition slide table. The transposition frame 29 is slidably installed inside the support frame 27. A plurality of evenly distributed mounting frames 30 are fixedly installed on the top of the transposition frame 29. Second couplings 31 are rotatably installed on the mounting frames 30. A connecting groove 2701 is opened on the side wall of the support frame 27. The position of the connecting groove 2701 is consistent with the axial position of the output shaft of the speed increaser 4.Specifically, when the aircraft motor maintenance test platform is in use, the aircraft generator 7 to be tested is first placed in the transfer trolley 6, so that the two placement seats 10 support the aircraft generator 7 to be tested, and then the flap 8 is rotated to buckle it on one side of the aircraft generator 7 to be tested, and the locking pin group 9 on the top is plugged in to fix the flap 8, and then the fastening electric push rods 11 on both sides of the transfer trolley 6 drive the two fastening rods 13 to move to the other side of the aircraft generator 7 to be tested through the fastening push plate 12, so that the fastening rods 13, the flap 8 and the placement seat 10 clamp the aircraft generator 7 to be tested at three points, so that the aircraft generator 7 to be tested is stably installed inside the transfer trolley 6, and then the staff pushes the transfer trolley 6 loaded with the aircraft generator 7 to be tested along the travel groove 23. The transfer trolley 6 is placed on the lifting seat 18 until the four traveling wheels 14 fall into the four wheel grooves 24 respectively, so that the bottom of the transfer trolley 6 contacts the top of the lifting seat 18, thereby stably placing the transfer trolley 6 on the lifting seat 18. At this time, the four winches 16 on the top of the lifting frame 15 simultaneously drive the four traction cables 17 to reel in, thereby driving the lifting seat 18 to lift, so that the transfer trolley 6 carries the aircraft generator 7 to be tested and moves to the height of the test bench 2. Then the staff continues to push the transfer trolley 6 to move the transfer trolley 6 to the top of the transport plate 22 to realize the transportation of the aircraft generator 7 to be tested, so that the aircraft generator 7 to be tested is stably transported to the top of the test bench 2 while maintaining its positioning, avoiding handling accidents and inaccurate placement, and facilitating subsequent connection with the speed increase box. 4, by setting a docking component, after the transfer cart 6 loaded with the aircraft generator 7 to be tested is transported to the top of the transport plate 22, the four traveling wheels 14 at the bottom of the transfer cart 6 will fall into the four wheel grooves 24 on the transport plate 22 again, and the bottom of the transfer cart 6 will contact the top of the transport plate 22, and then the electric lifting platform 21 drives the transport plate 22 to move up and down, so that the axis of the input shaft of the aircraft generator 7 to be tested is consistent with the axis of the second coupling 31, and the staff manually adjusts the relative positions of the input shaft of the aircraft generator 7 to be tested, the output shaft of the speed increaser 4 and the second coupling 31, so that the three are aligned, and then pushes the supporting frame 27 as a whole to move toward the speed increaser 4, so that the second coupling 31 is docked with the output shaft of the speed increaser 4, and the same When the second coupling 31 is positioned by the output shaft of the speed increasing box 4, the two traveling guide rails 19 drive the traveling slide 20 to start moving, thereby driving the electric lifting platform 21, the transport plate 22 and the top transfer trolley 6 to move toward the position of the support frame 27 through the support plate, until the input shaft of the aircraft generator 7 to be tested is inserted into the second coupling 31, and then driving the support frame 27 to move toward the speed increasing box 4 as a whole, so that the second coupling 31 is docked with the output shaft of the speed increasing box 4, completing the semi-automatic docking of the aircraft generator 7 to be tested, the second coupling 31 and the speed increasing box 4, greatly reducing manual operation and reducing operation risks, and then gradually connecting the load simulation system, the measurement and control system and the lubricating oil cooling system to the aircraft generator 7 to be tested for maintenance and testing. ;

[0048] like Figure 6 As shown, guide screw sleeves are fixedly installed on both sides of the transfer trolley 6, one end of the guide screw sleeves extends to the interior of the transfer trolley 6, and the interior of the guide screw sleeves is screwed with pitch-adjusting screws 32, one end of the two pitch-adjusting screws 32 is rotatably installed on the side walls of the two placement seats 10 respectively, and one end of the pitch-adjusting screw 32 located outside the transfer trolley 6 is fixedly installed with a pitch-adjusting knob 33. In this embodiment, a horizontal scale line can be set inside the transfer trolley 6 to facilitate accurate adjustment of the spacing between the two placement seats 10; specifically, by setting the pitch-adjusting screw 32, before the aircraft generator 7 to be tested is placed in the transfer trolley 6, the pitch-adjusting knobs 33 on both sides can be rotated, so that the pitch-adjusting screw 32, under the action of the guide screw sleeve, drives the two placement seats 10 to make reverse linear motion, adjusts the spacing between the two placement seats 10, and enables the placement seat 10 to support aircraft generators 7 to be tested of different specifications and sizes, so that the transfer trolley 6 can cope with common models of aircraft generators 7 to be tested, thereby improving the versatility of the transfer trolley 6.

[0049] like Figure 6 As shown, a first positioning slide frame 34 is fixedly installed on the side of the bottom of the transfer trolley 6 away from the speed increasing box 4, and a positioning plug plate 35 is slidably installed inside the first positioning slide frame 34, as shown in FIG. Figure 4 As shown, a second positioning slide frame 36 compatible with the positioning plug plate 35 is fixedly installed on the side of the transport plate 22 away from the speed increaser 4; specifically, by setting the first positioning slide frame 34, after the transfer trolley 6 is transported to the transport plate 22, the traveling wheel 14 at the bottom of the transfer trolley 6 will fall into the wheel groove 24, so that the transfer trolley 6 is in contact with the transport plate 22, which plays a role in preliminary positioning. At the same time, the first positioning slide frame 34 is aligned with the second positioning slide frame 36, and then the staff slides the positioning plug plate 35 in the first positioning slide frame 34 to make the positioning plug plate 35 stuck in the second positioning slide frame 36, and further locks the transfer trolley 6 to prevent the transfer trolley 6 from being pushed by the reaction force and offset when the aircraft generator 7 to be tested is docked with the second coupling 31 and the speed increaser 4.

[0050] like Figure 7As shown, four through-type jacks 37 are fixedly installed inside the lifting frame 15, and the four through-type jacks 37 are respectively located at the bottom of the four winches 16, and the traction cables 17 located at the same place are inserted inside the through-type jacks 37; specifically, by arranging the through-type jacks 37, when the winch 16 reels in the traction cables 17 to drive the lifting seat 18 to lift, the four traction cables 17 can effectively prevent the lifting seat 18 and the top transfer trolley 6 from shaking. At the same time, after the lifting seat 18 is lifted to the height of the transport plate 22, the four through-type jacks 37 on the top will lock the four traction cables 17 respectively, so that the lifting seat 18 is stably maintained at the current position to prevent the lifting seat 18 from shaking back and forth when the transfer trolley 6 is pushed from the lifting seat 18 to the transport plate 22, thereby affecting the transportation of the transfer trolley 6.

[0051] like Figure 2 As shown, a plurality of evenly distributed guide rollers 38 are rotatably installed on the top of the platform 1, and the guide rollers 38 are all horizontally arranged and located between the two travel guide rails 19, and the axes of the guide rollers 38 are perpendicular to the travel guide rails 19, and the bottom of the electric lifting platform 21 is in contact with the guide rollers 38; specifically, by arranging the guide rollers 38, the electric lifting platform 21 at the bottom of the transport plate 22 is located on the top of the plurality of guide rollers 38 and in contact with the guide rollers 38, and when the travel slide 20 drives the electric lifting platform 21 and the transport plate 22 to move, the electric lifting platform 21 will move synchronously on the plurality of guide rollers 38, so that the plurality of guide rollers 38 support and lubricate the movement of the electric lifting platform 21, thereby preventing the transport plate 22 carrying the transfer trolley 6 and the aircraft generator 7 to be tested from causing excessive burden on the travel slide 20 due to excessive load.

[0052] like Figure 3 As shown, an anti-pinch fixing baffle 39 is fixedly installed on one side of the speed increaser 4, and a through hole is opened on the side wall of the anti-pinch fixing baffle 39, and the output shaft of the speed increaser 4 is located inside the through hole; specifically, by setting the anti-pinch fixing baffle 39, when adjusting the positions of the input shaft of the aircraft generator 7 to be tested, the second coupling 31 and the output shaft of the speed increaser 4, the rotor of the aircraft generator 7 to be tested is first locked, and the second coupling 31 and the output shaft of the speed increaser 4 are rotated with the input shaft of the aircraft generator 7 to be tested as a reference, so that the second coupling 31 and the output shaft of the speed increaser 4 are locked. The output shafts of the device 31 and the speed increaser 4 are aligned with the input shaft of the aircraft generator 7 to be tested, and then the output shaft of the speed increaser 4 is locked, so that the aircraft generator 7 to be tested, the second coupling 31 and the speed increaser 4 can be stably aligned. At the same time, when adjusting the position of the output shaft of the speed increaser 4, the staff puts their hands in the gap between the anti-pinch fixed baffle 39 and the speed increaser 4, and adjusts the output shaft of the speed increaser 4 so that the anti-pinch fixed baffle 39 protects the staff's hands to prevent the travel slide 20 from getting out of control and causing the staff's hands to be pinched.

[0053] like Figure 8 As shown, an anti-pinch flip plug plate 40 is rotatably installed on one side of the guide slide rail 25, and a flip handle 41 is fixedly installed on the top of the anti-pinch flip plug plate 40, and a gear slot compatible with the anti-pinch flip plug plate 40 is opened on the top of the guide slide rail 25; specifically, by setting the anti-pinch flip plug plate 40, in the process of aligning the aircraft generator 7 to be tested, the second coupling 31 and the speed increaser 4, first hold the flip handle 41 to rotate the anti-pinch flip plug plate 40, so that the anti-pinch flip plug plate 40 is clamped in the gear slot on the guide slide rail 25, and the guide slider 26 is blocked, so that the support frame 27 is clamped on one side of the anti-pinch flip plug plate 40 as a whole, which plays a role of emergency braking, and further prevents the hands of the staff from being clamped due to the loss of control of the traveling slide 20.

[0054] like Fig.10 As shown, a maintenance test method for an aircraft motor includes the following steps:

[0055] S1. Installation of the generator: Place the aircraft generator 7 to be tested into the transfer cart 6, and use the fastening rod 13, the flap 8 and the placement seat 10 to perform three-point clamping on the aircraft generator 7 to be tested, so that the aircraft generator 7 to be tested is stably installed inside the transfer cart 6;

[0056] S2. Transfer of the generator: Push the transfer trolley 6 onto the lifting seat 18, the winch 16 drives the lifting seat 18 to lift to the height of the test bench 2, and continue to push the transfer trolley 6 to move to the top of the transport plate 22;

[0057] S3. Alignment of the generator: the electric lifting platform 21 drives the transport plate 22 to move up and down, so that the axis of the input shaft of the aircraft generator 7 to be tested is consistent with the axis of the second coupling 31, and the staff starts manual adjustment to make the output shaft of the second coupling 31 and the speed increaser 4 aligned with the input shaft of the aircraft generator 7 to be tested;

[0058] S4, docking of the generator: push the support frame 27 as a whole to move toward the speed increasing box 4, so that the second coupling 31 is docked with the output shaft of the speed increasing box 4, and the traveling slide 20 drives the transport plate 22 to move until the input shaft of the aircraft generator 7 to be tested is inserted into the second coupling 31;

[0059] S5. Generator testing: gradually connect the load simulation system, the measurement and control system, and the lubricating oil cooling system to perform maintenance testing on the aircraft generator 7 to be tested.

[0060] In summary: Installation of the generator: first rotate the pitch adjustment knobs 33 on both sides so that the pitch adjustment screw 32, under the action of the guide screw sleeve, drives the two placement seats 10 to make reverse linear motion, adjust the spacing between the two placement seats 10, and then put the aircraft generator 7 to be tested into the transfer cart 6, so that the two placement seats 10 support the aircraft generator 7 to be tested, and then rotate the flap 8 so that it is buckled on one side of the aircraft generator 7 to be tested, and plug the locking pin group 9 on the top to fix the flap 8, and then the fastening electric push rods 11 on both sides of the transfer cart 6 drive the two fastening rods 13 to move to the other side of the aircraft generator 7 to be tested through the fastening push plate 12, so that the fastening rod 13, the flap 8 and the placement seat 10 clamp the aircraft generator 7 to be tested at three points, so that the aircraft generator 7 to be tested is stably installed inside the transfer cart 6;

[0061] Transfer of generator: the staff pushes the transfer trolley 6 loaded with the aircraft generator 7 to be tested onto the lifting seat 18 along the travel groove 23 until the four travel wheels 14 fall into the four wheel grooves 24 respectively, so that the bottom of the transfer trolley 6 contacts the top of the lifting seat 18, thereby stably placing the transfer trolley 6 on the lifting seat 18. At this time, the four winches 16 on the top of the lifting frame 15 simultaneously drive the four traction cables 17 to reel up, thereby driving the lifting seat 18 to lift, so that the transfer trolley 6 carries the aircraft generator 7 to be tested and moves up to the height of the test bench 2. The four through-type jacks 37 on the top will lock the four traction cables 17 respectively, and then the staff continues to push the transfer trolley 6 to move the transfer trolley 6 to the top of the transport plate 22, so as to realize the transportation of the aircraft generator 7 to be tested, so that the aircraft generator 7 to be tested is stably transported to the top of the test bench 2 while being positioned, avoiding the problems of handling accidents and inaccurate placement;

[0062] Docking of the generator: After the transfer trolley 6 loaded with the aircraft generator 7 to be tested is transported to the top of the transport plate 22, the four traveling wheels 14 at the bottom of the transfer trolley 6 will fall into the four wheel grooves 24 on the transport plate 22 again, and the bottom of the transfer trolley 6 will contact the top of the transport plate 22. At the same time, the first positioning slide frame 34 and the second positioning slide frame 36 are aligned. The staff slides the positioning plug 35 in the first positioning slide frame 34 so that the positioning plug 35 is stuck in the second positioning slide frame 36, and the transfer trolley 6 is further locked. The electric lifting platform 21 then drives the transport plate 22 to move up and down, so that the axis of the input shaft of the aircraft generator 7 to be tested is consistent with the axis of the second coupling 31. The staff first holds the flip handle 41 to rotate the anti-pinch flip plug plate 40, so that the anti-pinch flip plug plate 40 is clamped in the gear slot on the guide slide rail 25, and the guide slide block 26 is blocked, so that the support frame 27 is clamped on one side of the anti-pinch flip plug plate 40 as a whole, which plays an emergency brake role, and then locks the rotor of the aircraft generator 7 to be tested. The input shaft of the generator 7 is taken as the reference, and then the hand is placed in the gap between the anti-pinch fixed baffle 39 and the speed increaser 4, the output shaft of the speed increaser 4 is adjusted, and then the second coupling 31 is rotated to make the second coupling 31 and the output shaft of the speed increaser 4 relative to the input shaft of the aircraft generator 7 to be tested, and then the output shaft of the speed increaser 4 is locked, and then the anti-pinch flip plug 40 is reset, and the support frame 27 is pushed as a whole to move toward the speed increaser 4, so that the second coupling 31 is connected to the output shaft of the speed increaser 4, and at the same time, the second coupling 31 is The output shaft of the speed increasing box 4 is positioned. At this time, the two traveling guide rails 19 drive the traveling slide 20 to start moving, thereby driving the electric lifting platform 21, the transport plate 22 and the top transfer trolley 6 to move toward the position of the support frame 27 through the support plate, until the input shaft of the aircraft generator 7 to be tested is inserted into the second coupling 31, so that the second coupling 31 is then connected with the output shaft of the speed increasing box 4, completing the semi-automatic connection of the aircraft generator 7 to be tested, the second coupling 31 and the speed increasing box 4, greatly reducing manual operations and reducing operational risks;

[0063] Generator testing: gradually connect the load simulation system, measurement and control system, and lubricating oil cooling system to perform maintenance tests on the aircraft generator 7 to be tested.

[0064] 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 to the above embodiments. The above embodiments and descriptions only describe the principles of the present invention. The present invention may be subject to various changes and improvements without departing from the spirit and scope of the present invention. These changes and improvements fall within the scope of the present invention. The scope of protection claimed by the present invention is defined by the attached claims and their equivalents.

Claims

1. An aircraft motor maintenance test platform, characterized in that: The invention comprises a platform (1), a test bench (2) is fixedly mounted on the top of the platform (1), a traction motor (3) and a speed increasing gearbox (4) are fixedly mounted on the top of the test bench (2), a first coupling (5) is arranged between the traction motor (3) and the speed increasing gearbox (4), an output shaft of the traction motor (3) and an input shaft of the speed increasing gearbox (4) are drivingly connected via the first coupling (5), and an aircraft generator (7) to be tested and a transfer assembly are arranged on a side of the speed increasing gearbox (4) away from the traction motor (3); The transfer assembly is used to lift and transfer the aircraft generator (7) to be tested. The transfer assembly comprises a transfer trolley (6) arranged on one side of the speed increasing box (4). The aircraft generator (7) to be tested is arranged inside the transfer trolley (6). A flap (8) is rotatably installed on a side of the transfer trolley (6) close to the speed increasing box (4). A connecting hole (801) is provided on one side of the flap (8). The input shaft of the aircraft generator (7) to be tested is located inside the connecting hole (801). Locking pin groups (9) are fixedly installed on both sides of the top of the transfer trolley (6). Two symmetrically arranged placement seats (10) are slidably installed inside the transfer trolley (6). The aircraft generator (7) to be tested is placed on top of the two placement seats (10). Horizontally arranged fastening electric push rods (11) are fixedly installed on both sides of the transfer trolley (6). The telescopic ends of the fastening electric push rod (11) are fixedly installed with fastening push plates (12), two fastening sliding holes are provided on both sides of the transfer trolley (6), and the same fastening rod (13) is slidably installed inside the two fastening sliding holes located at the same height, and the two ends of the fastening rod (13) are respectively fixedly installed on the side walls of the two fastening push plates (12), and the four corners at the bottom of the transfer trolley (6) are fixedly installed with traveling wheels (14), and the same lifting frame (15) is arranged between the transfer trolley (6) and the platform (1), and the four corners at the top of the lifting frame (15) are fixedly installed with winches (16), and the inside of the winches (16) is wound with traction steel cables (17), and one end of the four traction steel cables (17) passes through the top of the lifting frame (15) and is fixedly installed with the same lifting seat (18), and the top of the platform (1) is provided with a docking assembly; The docking assembly is used to assist the semi-automatic connection between the input shaft of the aircraft generator (7) to be tested and the output shaft of the speed increasing box (4), and the docking assembly comprises two horizontally arranged travel guide rails (19) fixedly mounted on the top of the platform (1), the top of each of the travel guide rails (19) being driven to be installed with a travel slide (20), the top of each of the travel slides (20) being fixedly mounted with a support frame, the same electric lift (21) being fixedly mounted between the two support frames, the top of the telescopic end of the electric lift (21) being fixedly mounted with a same transport plate (22), the interior of the lift seat (18) and the top of the transport plate (22) being provided with two travel grooves (23), the interior of each of the travel grooves (23) being provided with two wheel grooves (24) adapted to the travel wheels (14), the top of each of the test benches (2) being fixedly mounted with two guide rails (25), the two guide rails (25) being fixedly mounted with the two guide rails (25), and the two guide rails (25) being fixedly mounted with the two guide rails (25). The guide rails (25) are distributed on both sides of the transport plate (22); the tops of the guide rails (25) are slidably mounted with guide sliders (26); the tops of the two guide sliders (26) are fixedly mounted with a same support frame (27); the bottom of the support frame (27) is fixedly mounted with a transposition guide rail (28); the top of the transposition guide rail (28) is drivably mounted with a transposition slide; the top of the transposition slide is fixedly mounted with a transposition frame (29); the transposition frame (29) is slidably mounted inside the support frame (27); the top of the transposition frame (29) is fixedly mounted with a plurality of evenly distributed mounting frames (30); the mounting frames (30) are rotatably mounted with second couplings (31); a connecting groove (2701) is provided on the side wall of the support frame (27); the position of the connecting groove (2701) is consistent with the axial position of the output shaft of the speed increasing box (4).

2. The aircraft motor maintenance test platform according to claim 1, characterized in that: Guide screw sleeves are fixedly mounted on both sides of the transfer trolley (6), one end of each guide screw sleeve extends into the interior of the transfer trolley (6), and a pitch adjusting screw (32) is threadedly connected to the interior of each guide screw sleeve. One end of each of the two pitch adjusting screws (32) is rotatably mounted on the side walls of the two placement seats (10), and a pitch adjusting knob (33) is fixedly mounted on one end of each pitch adjusting screw (32) located outside the transfer trolley (6).

3. The aircraft motor maintenance and testing platform according to claim 1, characterized in that: A first positioning slide frame (34) is fixedly mounted on a side of the bottom of the transfer trolley (6) away from the speed increasing box (4), a positioning plug plate (35) is slidably mounted inside the first positioning slide frame (34), and a second positioning slide frame (36) adapted to the positioning plug plate (35) is fixedly mounted on a side of the transport plate (22) away from the speed increasing box (4).

4. The aircraft motor maintenance test platform according to claim 1, characterized in that: Four through-type jacks (37) are fixedly installed inside the lifting frame (15), and the four through-type jacks (37) are respectively located at the bottom of the four winches (16), and the traction steel rope (17) located at the same place is inserted inside the through-type jacks (37).

5. The aircraft motor maintenance test platform according to claim 1, characterized in that: A plurality of evenly distributed guide rollers (38) are rotatably mounted on the top of the platform (1); the guide rollers (38) are all horizontally arranged and located between the two travel guide rails (19); the axes of the guide rollers (38) are all perpendicular to the travel guide rails (19); and the bottom of the electric lifting platform (21) is in contact with the guide rollers (38).

6. The aircraft motor maintenance and testing platform according to claim 1, characterized in that: An anti-pinch fixing baffle (39) is fixedly mounted on one side of the speed increasing box (4), a through hole is provided on the side wall of the anti-pinch fixing baffle (39), and the output shaft of the speed increasing box (4) is located inside the through hole.

7. The aircraft motor maintenance and testing platform according to claim 1, characterized in that: An anti-pinch flip plug plate (40) is rotatably mounted on one side of the guide rail (25), a flip handle (41) is fixedly mounted on the top of the anti-pinch flip plug plate (40), and a gear slot adapted to the anti-pinch flip plug plate (40) is provided on the top of the guide rail (25).

8. A method for maintenance and testing of aircraft motors based on the test platform according to any one of claims 1 to 7, characterized in that: The steps include: S1. Generator installation: Place the aircraft generator (7) to be tested into the transfer trolley (6), and use the fastening rod (13), the flap (8) and the placement seat (10) to perform three-point clamping on the aircraft generator (7) to be tested, so that the aircraft generator (7) to be tested is stably installed inside the transfer trolley (6); S2. Transfer of the generator: Push the transfer trolley (6) onto the lifting seat (18), the winch (16) drives the lifting seat (18) to lift to the height of the test bench (2), and continue to push the transfer trolley (6) to move to the top of the transport plate (22); S3, alignment of the generator: the electric lifting platform (21) drives the transport plate (22) to move up and down, so that the axis of the input shaft of the aircraft generator (7) to be tested is consistent with the axis of the second coupling (31), and the staff begins to manually adjust so that the output shaft of the second coupling (31) and the speed increaser (4) are aligned with the input shaft of the aircraft generator (7) to be tested; S4, docking of the generator: pushing the support frame (27) as a whole to move toward the speed increasing box (4), so that the second coupling (31) is docked with the output shaft of the speed increasing box (4), and the traveling slide (20) drives the transport plate (22) to move until the input shaft of the aircraft generator (7) to be tested is inserted into the second coupling (31); S5. Generator testing: gradually connect the load simulation system, measurement and control system, and lubricating oil cooling system to perform maintenance testing on the aircraft generator (7) to be tested.

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