An aircraft engine assembly platform

Abstract

The present invention discloses an aircraft engine assembly platform, which includes an AGV. The AGV body is provided with a first vertical frame and a second vertical frame. The first vertical frame is slidably provided with a first sliding seat, which is connected to a first turntable via a first slewing bearing. The first turntable is fixed with a first upper support plate and a first lower support plate, and a first C-shaped ring is slidably provided between the first upper support plate and the first lower support plate. The second vertical frame is slidably provided with a second sliding seat, which is connected to a second turntable via a second slewing bearing. The second turntable is fixed with a second upper support plate and a second lower support plate, and a second C-shaped ring is slidably provided between the second upper support plate and the second lower support plate. The first C-shaped ring and the second C-shaped ring form a circular closed loop for clamping the aircraft engine. The circular closed loop can rotate around its own axis under the drive of a third drive device. The purpose is to provide a movable and highly secure aircraft engine assembly platform.

Description

Technical Field

[0001] The present invention relates to the field of aviation engine assembly, in particular to a platform for aviation engine assembly. Background Art

[0002] During the final assembly of aircraft engines, the engine structure is complex and the number of parts is large. In particular, the installation locations of external pipes and joints are distributed in the circumferential direction of the engine and have poor accessibility. During the final assembly of the engine, it is often necessary to repeatedly flip the engine up and down and in the circumferential direction to meet the assembly ergonomic requirements and facilitate engine assembly and dimensional measurement operations. Existing aircraft engine assembly platforms, such as the Chinese utility model patent application number 201420167053.8, issued on August 20, 2014, and entitled "A Multi-Degree-of-Freedom Aircraft Engine Assembly Platform," disclose an assembly platform comprising a lifting device, a pitch drive device, a C-ring drive device, a C-ring device, and a control module. The lifting device is fixedly connected to a foundation, the pitch drive device is slidably connected to the lifting device and has a vertical connection surface, the C-ring drive device is rotatably connected to the vertical connection surface and has a drive gear, the C-ring device has a C-ring meshing with the drive gear, and the C-ring rotates about a rotation centerline when the drive gear rotates. The control module is electrically connected to the lifting device, the pitch drive device, and the C-ring drive device, respectively. As can be seen, the assembly platform is fixedly connected to the foundation and cannot be moved, which does not meet practical needs. Furthermore, the aircraft engine is clamped by only a single C-ring, which is not very safe. Summary of the Invention

[0003] The technical problem to be solved by the present invention is to provide a movable and highly safe aviation engine assembly platform.

[0004] The aircraft engine assembly platform of the present invention includes an AGV, wherein a first vertical frame and a second vertical frame arranged relatively to each other are provided on the body of the AGV, a first sliding seat is provided on the first vertical frame for sliding along the vertical direction, the first sliding seat is connected to a first driving device, the first driving device can drive the first sliding seat to slide along the first vertical frame, the first sliding seat is connected to one side of the first turntable through a first slewing bearing, a first upper support plate and a first lower support plate are fixed on the other side of the first turntable, a first C-shaped ring is provided for sliding between the first upper support plate and the first lower support plate, a second sliding seat is provided on the second vertical frame for sliding along the vertical direction, the second sliding seat is connected to the second driving device, and the second driving device can drive the second sliding seat The cam is connected to the second support plate by a second slewing bearing, and the cam is connected to the second support plate by a second slewing bearing. The cam is connected to the second support plate by a second slewing bearing. The cam is connected to the second support plate by a second slewing bearing. The cam is connected to the second support plate by a second slewing bearing. The cam is connected to the second support plate by a second slewing bearing.

[0005] The aircraft engine assembly platform of the present invention, wherein the first vertical frame is fixedly provided with a first slide rail arranged in a vertical direction, the first sliding seat is slidably installed on the first slide rail through a first slider, the first driving device includes a first motor, a first reducer and a first lifting screw, the first lifting screw is rotatably installed on the first vertical frame along the vertical direction, the first motor and the first reducer are arranged on the first vertical frame, the output shaft of the first motor is connected to the input shaft of the first reducer, the output shaft of the first reducer is connected to the lower end of the first lifting screw, and the first sliding seat is threadedly connected to the first lifting screw.

[0006] The aircraft engine assembly platform of the present invention, wherein the second vertical frame is fixedly provided with a second slide rail arranged in the vertical direction, the second sliding seat is slidably installed on the second slide rail through a second slider, the second driving device includes a second motor, a second reducer and a second lifting screw, the second lifting screw is rotatably installed on the second vertical frame along the vertical direction, the second motor and the second reducer are arranged on the second vertical frame, the output shaft of the second motor is connected to the input shaft of the second reducer, the output shaft of the second reducer is connected to the lower end of the second lifting screw, and the second sliding seat is threadedly connected to the second lifting screw.

[0007] The aircraft engine assembly platform of the present invention, wherein the first slewing bearing includes a first outer ring, a first inner ring, a support base, a third motor and a worm, the first inner ring is fixedly arranged on the support base, the first outer ring is rotatably installed on the outside of the first inner ring, the third motor is fixedly arranged on the support base, the output shaft of the third motor is fixedly connected to the worm, the outer peripheral surface of the first outer ring is provided with circumferentially arranged external teeth, the worm is engaged with the external teeth, the support base is fixedly connected to the first sliding seat, and the first outer ring is fixedly connected to one side of the first turntable.

[0008] The aircraft engine assembly platform of the present invention, wherein the second slewing bearing includes a second outer ring and a second inner ring, the second inner ring is rotatably installed in the second outer ring, the second inner ring is fixedly connected to the second sliding seat, and the second outer ring is fixedly connected to one side of the second turntable.

[0009] The aerospace engine assembly platform of the present invention, wherein the upper surface of the first C-shaped ring is fixedly provided with a first upper arc slide rail, the first upper arc slide rail is arranged along the circumference of the first C-shaped ring, the lower surface of the first upper support plate is fixedly provided with a first upper arc slide block, the first upper arc slide block is slidably installed on the first upper arc slide rail, the lower surface of the first C-shaped ring is fixedly provided with a first lower arc slide rail, the first lower arc slide rail is arranged along the circumference of the first C-shaped ring, the upper surface of the first lower support plate is fixedly provided with a first lower arc slide block, the first lower arc slide block is slidably installed on the first lower arc slide rail, the upper surface of the second C-shaped ring is fixedly provided with a second upper arc slide rail, the second upper arc slide rail is arranged along the circumference of the second C-shaped ring, the lower surface of the second upper support plate is fixedly provided with a second upper arc slide block, the second upper arc slide block is slidably installed on the second upper arc slide rail, The first gear and the second gear are connected with each other to form a circle, and the first gear and the second gear are connected with each other to form a circle.

[0010] The aircraft engine assembly platform of the present invention, wherein the first C-shaped ring and the second C-shaped ring are both provided with radially arranged through holes, and a clamping member is installed in the through hole, and the clamping member includes a clamping seat, a clamping screw and a clamping block, and the clamping seat is U-shaped, and the clamping seat includes a base plate fixed in the through hole, and two relatively arranged side plates are fixed on the base plate, and a clamping screw is rotatably installed between the two side plates, and the arrangement direction of the clamping screw is the same as the through hole, and the clamping block is threadedly connected to the clamping screw between the two side plates, and a clamping slide rail with the same arrangement direction as the clamping screw is provided on the base plate, and a clamping slider is fixed at the lower end of the clamping block, and the clamping slider is slidably installed on the clamping slide rail, and a clamping plate is fixed at the upper end of the clamping block, and the height of the clamping plate is higher than the two side plates.

[0011] The aviation engine assembly platform of the present invention is characterized in that the clamping screw is fixedly connected with a hand wheel, and the hand wheel is located outside the clamping seat.

[0012] The aircraft engine assembly platform of the present invention, wherein the body of the AGV is fixedly provided with a third slide rail, the bottom of the first vertical frame is fixedly provided with a third slider, the third slider is slidably installed on the third slide rail, the second vertical frame is fixedly provided on the body of the AGV, when the first vertical frame slides along the third slide rail through the third slider, the first vertical frame moves closer to or away from the second vertical frame, the body of the AGV is fixedly provided with a linear rack, the arrangement direction of the linear rack is the same as that of the third slide rail, the first vertical frame is fixedly provided with a fifth motor, the output shaft of the fifth motor is fixedly connected to a second gear, and the second gear is engaged with the linear rack.

[0013] In the aircraft engine assembly platform of the present invention, the specific manner in which the second gear and the linear rack are engaged is: a third gear is provided between the second gear and the linear rack, the third gear is rotatably mounted on the first vertical frame, and the third gear is engaged with the second gear and the linear rack respectively.

[0014] The difference between the aircraft engine assembly platform of the present invention and the prior art is that when the aircraft engine assembly platform of the present invention is used, the entire assembly platform can be moved to a suitable position by an AGV, and then the aircraft engine can be clamped in the circular closed loop formed by the first C-ring and the second C-ring by a clamping member. Then, according to actual requirements, the first driving device and the second driving device can simultaneously drive the first sliding seat and the second sliding seat to rise or fall, thereby driving the aircraft engine to rise or fall. After the aircraft engine rises or falls to a suitable height, the first rotary support and the second rotary support can also be used to simultaneously rotate the first turntable and the second turntable, so that the aircraft engine rotates in a vertical plane. After the aircraft engine rotates to a suitable position, the third driving device can also be used to drive the circular closed loop to rotate around its own axis, that is, the aircraft engine rotates around its own axis, thereby facilitating the assembly of the aircraft engine. It can be seen that since the present invention clamps the aircraft engine by the first C-ring and the second C-ring arranged relatively, it is safer, and since the present invention uses the AGV as the bearing base, it can be easily moved.

[0015] The present invention will be further described below with reference to the accompanying drawings. BRIEF DESCRIPTION OF THE DRAWINGS

[0016] Figure 1 This is a front view of the aircraft engine assembly platform of the present invention;

[0017] Figure 2 A top view of the aircraft engine assembly platform of the present invention;

[0018] Figure 3 The three-dimensional structure of the aircraft engine assembly platform of the present invention Figure 1 ;

[0019] Figure 4 The three-dimensional structure of the aircraft engine assembly platform of the present invention Figure 2 ;

[0020] Figure 5 The three-dimensional structure of the aircraft engine assembly platform of the present invention Figure 3 ;

[0021] Figure 6 The three-dimensional structure of the aircraft engine assembly platform of the present invention Figure 4 ;

[0022] Figure 7 The three-dimensional structure of the aircraft engine assembly platform of the present invention Figure 5 ;

[0023] Figure 8 The three-dimensional structure of the aircraft engine assembly platform of the present invention Figure 6 (Hide the second C-ring);

[0024] Figure 9 for Figure 8 A partial enlarged view of point A in the middle. DETAILED DESCRIPTION

[0025] like Figure 1 As shown, combined with Figure 2-9 As shown, the aircraft engine assembly platform of the present invention includes an AGV, wherein a first vertical frame 1 and a second vertical frame 22 are arranged opposite to each other on the body 3 of the AGV, a first sliding seat 2 is provided on the first vertical frame 1 for sliding along the vertical direction, the first sliding seat 2 is connected to a first driving device, the first driving device can drive the first sliding seat 2 to slide along the first vertical frame 1, the first sliding seat 2 is connected to one side of the first turntable 33 through a first slewing bearing 9, a first upper support plate 32 and a first lower support plate 10 are fixed on the other side of the first turntable 33, a first C-shaped ring 13 is slidably provided between the first upper support plate 32 and the first lower support plate 10, a second sliding seat 20 is provided on the second vertical frame 22 for sliding along the vertical direction, the second sliding seat 20 is connected to a second driving device, the second driving device can drive the second sliding seat 20 to slide along the second vertical frame 22, the second sliding seat 20 is connected to a second slewing bearing 19 It is connected to one side of the second turntable 23, and a second upper support plate 25 and a second lower support plate 18 are fixed on the other side of the second turntable 23, and a second C-shaped ring 14 is slidably provided between the second upper support plate 25 and the second lower support plate 18, and the first C-shaped ring 13 and the second C-shaped ring 14 form a circular closed ring for clamping the aircraft engine 29 (in actual use, the first C-shaped ring 13 and the second C-shaped ring 14 can be fixed by fasteners such as bolts to form a stable circular closed ring), and the first C-shaped ring 13 and the second C-shaped ring 14 are both provided with a clamping member 15 for clamping the aircraft engine 29, and the circular closed ring can rotate around its own axis under the drive of the third driving device. When the circular closed ring rotates around its own axis, the first C-shaped ring 13 slides relative to the first upper support plate 32 and the first lower support plate 10, and the second C-shaped ring 14 slides relative to the second upper support plate 25 and the second lower support plate 18.

[0026] When the aircraft engine assembly platform of the present invention is in use, the entire assembly platform can first be moved to a suitable position by an AGV. Then, the aircraft engine 29 is clamped in the circular closed loop formed by the first C-shaped ring 13 and the second C-shaped ring 14 by the clamping member 15. Then, according to actual requirements, the first and second driving devices can simultaneously drive the first and second sliding seats 20 to rise or fall, thereby driving the aircraft engine 29 to rise or fall. After the aircraft engine 29 is raised or lowered to a suitable height, the first and second slewing bearings 9 and 19 can also simultaneously rotate the first and second turntables 33 and 23, thereby rotating the aircraft engine 29 in a vertical plane. After the aircraft engine 29 is rotated to a suitable position, the third driving device can also drive the circular closed loop to rotate around its own axis, that is, the aircraft engine 29 rotates around its own axis, thereby facilitating the assembly of the aircraft engine 29. As can be seen, since the present invention clamps the aircraft engine 29 by the relatively arranged first and second C-shaped rings 13 and 14, it is safer. Moreover, since the present invention uses the AGV as the support base, it can be easily moved.

[0027] like Figure 3 As shown, the aircraft engine assembly platform of the present invention, wherein the first vertical frame 1 is fixedly provided with a first slide rail 46 arranged in the vertical direction, the first sliding seat 2 is slidably installed on the first slide rail 46 through the first slider 41, the first driving device includes a first motor 4, a first reducer 42 and a first lifting screw 47, the first lifting screw 47 is rotatably installed on the first vertical frame 1 along the vertical direction, the first motor 4 and the first reducer 42 are arranged on the first vertical frame 1, the output shaft of the first motor 4 is connected to the input shaft of the first reducer 42, the output shaft of the first reducer 42 is connected to the lower end of the first lifting screw 47, and the first sliding seat 2 is threadedly connected to the first lifting screw 47.

[0028] The first vertical frame 1 includes a first top plate 37 and a first bottom plate 40, and a first vertical side plate 38 fixedly connected between the first top plate 37 and the first bottom plate 40. A first support plate 39 is provided between the first top plate 37 and the first bottom plate 40, and the first support plate 39 is fixedly connected to the first vertical side plate 38. The first slide rail 46 is fixedly mounted on the first vertical side plate 38 in the vertical direction. The upper and lower ends of the first lifting screw 47 are rotatably mounted on the first top plate 37 and the first support plate 39 respectively via bearings. The first motor 4 and the first reducer 42 are fixedly mounted on the lower surface of the first support plate 39. Of course, the first motor 4 and the first reducer 42 can also be fixedly mounted on the first bottom plate 40. A first nut is fixedly mounted inside the first sliding seat 2, and the first sliding seat 2 is threadedly connected to the first lifting screw 47 via the first nut.

[0029] When the first motor 4 drives the first lifting screw 47 to rotate through the first reducer 42, since the first sliding seat 2 is slidably mounted on the first slide rail 46 through the first slider 41, the first sliding seat 2 will not rotate with the first lifting screw 47, but will only slide up and down along the first slide rail 46.

[0030] like Figure 4 As shown, the aircraft engine assembly platform of the present invention is fixedly provided with a second slide rail 51 arranged in the vertical direction on the second vertical frame 22, the second sliding seat 20 is slidably installed on the second slide rail 51 through the second slider 49, the second driving device includes a second motor 8, a second reducer 48 and a second lifting screw 50, the second lifting screw 50 is rotatably installed on the second vertical frame 22 in the vertical direction, the second motor 8 and the second reducer 48 are provided on the second vertical frame 22, the output shaft of the second motor 8 is connected to the input shaft of the second reducer 48, the output shaft of the second reducer 48 is connected to the lower end of the second lifting screw 50, and the second sliding seat 20 is threadedly connected to the second lifting screw 50.

[0031] The second vertical frame 22 has the same structure as the first vertical frame 1. The second slide rail 51, second lifting screw 50, second motor 8, and second reducer 48 are mounted on the second vertical frame 22 in the same manner as the first slide rail 46, first lifting screw 47, first motor 4, and first reducer 42 are mounted on the first vertical frame 1. The second sliding seat 20 is also threadedly connected to the second lifting screw 50 via a second nut fixed therein. When the second motor 8 drives the second lifting screw 50 to rotate via the second reducer 48, the second sliding seat 20 slides up and down along the second slide rail 51.

[0032] like Figure 1 As shown, combined with Figure 2-7 As shown, the aircraft engine assembly platform of the present invention, wherein the first slewing bearing 9 includes a first outer ring, a first inner ring, a supporting base, a third motor 34 and a worm, the first inner ring is fixedly arranged on the supporting base, the first outer ring is rotatably installed on the outside of the first inner ring, the third motor 34 is fixedly arranged on the supporting base, the output shaft of the third motor 34 is fixedly connected to the worm, the outer peripheral surface of the first outer ring is provided with circumferentially arranged external teeth, the worm is engaged with the external teeth, the supporting base is fixedly connected to the first sliding seat 2, and the first outer ring is fixedly connected to one side of the first turntable 33.

[0033] The aircraft engine assembly platform of the present invention, wherein the second slewing bearing 19 includes a second outer ring and a second inner ring, the second inner ring is rotatably installed in the second outer ring, the second inner ring is fixedly connected to the second sliding seat 20, and the second outer ring is fixedly connected to one side of the second turntable 23.

[0034] The second slewing bearing 19 is a prior art, which is a large bearing. Its specific structure and working principle will not be described in detail here.

[0035] The first slewing bearing 9 is of prior art. When the third motor 34 drives the worm to rotate, the worm engages with the outer teeth of the first outer ring. Therefore, under the drive of the worm, the first outer ring rotates relative to the first inner ring and the support base.

[0036] When the third motor 34 drives the first outer ring to rotate relative to the first inner ring and the support base, since the support base is fixedly connected to the first sliding seat 2 and the first outer ring is fixedly connected to the first turntable 33, the first turntable 33 rotates relative to the first sliding seat 2. Since the first C-shaped ring 13 on the first turntable 33 and the second C-shaped ring 14 on the second turntable 23 jointly clamp the aircraft engine 29, the first turntable 33 can drive the second turntable 23 to rotate through the first C-shaped ring 13 and the second C-shaped ring 14, that is, the second turntable 23 rotates relative to the second sliding seat 20 (because the second inner ring and the second outer ring of the second slewing bearing 19 are fixedly connected to the second sliding seat 20 and the second turntable 23, respectively, the second turntable 23 can rotate relative to the second sliding seat 20), thereby enabling the aircraft engine 29 to rotate in a vertical plane.

[0037] like Figure 1 As shown, combined with Figure 2-7As shown, the aircraft engine assembly platform of the present invention, wherein the upper surface of the first C-shaped ring 13 is fixedly provided with a first upper arc-shaped slide rail 30, and the first upper arc-shaped slide rail 30 is arranged along the circumference of the first C-shaped ring 13, and the lower surface of the first upper support plate 32 is fixedly provided with a first upper arc-shaped slider 31, and the first upper arc-shaped slider 31 is slidably installed on the first upper arc-shaped slide rail 30, the lower surface of the first C-shaped ring 13 is fixedly provided with a first lower arc-shaped slide rail 12, and the first lower arc-shaped slide rail 12 is arranged along the circumference of the first C-shaped ring 13, the upper surface of the first lower support plate 10 is fixedly provided with a first lower arc-shaped slider 11, and the first lower arc-shaped slider 11 is slidably installed on the first lower arc-shaped slide rail 12, the upper surface of the second C-shaped ring 14 is fixedly provided with a second upper arc-shaped slide rail 27, and the second upper arc-shaped slide rail 27 is arranged along the circumference of the second C-shaped ring 14, the lower surface of the second upper support plate 25 is fixedly provided with a second upper arc-shaped slider 26, and the second upper arc-shaped slider 26 is slidably installed on the second upper arc-shaped slide rail 27, A second lower arc-shaped slide rail 16 is fixedly provided on the lower surface of the second C-shaped ring 14, and the second lower arc-shaped slide rail 16 is arranged along the circumference of the second C-shaped ring 14. A second lower arc-shaped slider 17 is fixedly provided on the upper surface of the second lower support plate 18, and the second lower arc-shaped slider 17 is slidably mounted on the second lower arc-shaped slide rail 16. The cross-sections of the first upper arc-shaped slide rail 30 and the second upper arc-shaped slide rail 27 are the same. The first upper arc-shaped slide rail 30 and the second upper arc-shaped slide rail 27 form an upper circular slide rail. The first lower arc-shaped slide rail The rail 12 and the second lower arc-shaped slide rail 16 have the same cross-section. The first lower arc-shaped slide rail 12 and the second lower arc-shaped slide rail 16 form a lower circular slide rail. The third driving device includes a fourth motor 24, a first gear 21 and a circular rack 28. The circular rack 28 is fixedly arranged on the outer peripheral side of the circular closed ring along the circumferential direction. The fourth motor 24 is fixedly arranged on the second upper support plate 25. The first gear 21 is fixedly connected to the output shaft of the fourth motor 24, and the first gear 21 is engaged with the circular rack 28.

[0038] A first arc-shaped rack arranged circumferentially is fixedly provided on the outer peripheral side surface of the first C-shaped ring 13, and a second arc-shaped rack arranged circumferentially is fixedly provided on the outer peripheral side surface of the second C-shaped ring 14. The cross-sections of the first arc-shaped rack and the second arc-shaped rack are the same, and the first arc-shaped rack and the second arc-shaped rack form a circular rack 28. When the fourth motor 24 drives the first gear 21 to rotate, since the first gear 21 is engaged with the circular rack 28, and the upper circular slide is slidably installed with the first upper arc-shaped slider 31 and the second upper arc-shaped slider 26, and the lower circular slide is slidably installed with the first lower arc-shaped slider 11 and the second lower arc-shaped slider 17, the first gear 21 can drive the circular rack 28 to rotate, that is, drive the circular closed ring formed by the first C-shaped ring 13 and the second C-shaped ring 14 to rotate around its own axis (at the same time, the aircraft engine 29 clamped inside the circular closed ring also rotates around its own axis). At this time, the upper circular slide slides relative to the first upper arc-shaped slider 31 and the second upper arc-shaped slider 26, and the lower circular slide slides relative to the first lower arc-shaped slider 11 and the second lower arc-shaped slider 17. That is to say, the first C-shaped ring 13 slides relative to the first upper support plate 32 and the first lower support plate 10, and the second C-shaped ring 14 slides relative to the second upper support plate 25 and the second lower support plate 18.

[0039] like Figure 8 、 9 As shown, combined with Figure 1-7 As shown, the aircraft engine assembly platform of the present invention, wherein the first C-shaped ring 13 and the second C-shaped ring 14 are both provided with radially arranged through holes, and a clamping member 15 is installed in the through hole, and the clamping member 15 includes a clamping seat 56, a clamping screw 59 and a clamping block 52, and the clamping seat 56 is U-shaped, and the clamping seat 56 includes a bottom plate 54 fixed in the through hole, and two oppositely arranged side plates 58 are fixed on the bottom plate 54, and a clamping screw 59 is rotatably installed between the two side plates 58, and the arrangement direction of the clamping screw 59 is the same as that of the through hole, and the two side plates 58 are arranged in the same direction. The clamping block 52 is threadedly connected to the clamping screw 59 in the middle, and the base plate 54 is provided with a clamping slide rail 55 with the same arrangement direction as the clamping screw 59. The lower end of the clamping block 52 is fixed with a clamping slider 53, and the clamping slider 53 is slidably installed on the clamping slide rail 55. The upper end of the clamping block 52 is fixed with a clamping plate 36, and the height of the clamping plate 36 is higher than the two side plates 58, that is, the clamping plate 36 is located above the two side plates 58, so that the two side plates 58 will not hinder the clamping block 52 from sliding with the clamping plate 36 to clamp or release the aircraft engine 29.

[0040] In the aircraft engine assembly platform of the present invention, a hand wheel 57 is fixedly connected to the clamping screw 59 , and the hand wheel 57 is located outside the clamping seat 56 .

[0041] The clamping screw 59 is rotatably mounted between the two side plates 58 via bearings. When the clamping screw 59 is rotated by the hand wheel 57, the clamping block 52, which is slidably mounted on the clamping rail 55 via the clamping slider 53, does not rotate with the clamping screw 59 but can only slide along the clamping rail 55. Consequently, the clamping block 52, along with the clamping plate 36, slides radially inward along the first C-shaped ring 13 / second C-shaped ring 14 to clamp the aircraft engine 29, or slides outward to release the aircraft engine 29. When the clamping block 52, along with the clamping plate 36, slides radially inward along the first C-shaped ring 13 / second C-shaped ring 14, it slides radially toward the center of the circular closed loop formed by the first C-shaped ring 13 and the second C-shaped ring 14. Conversely, when the clamping block 52, along with the clamping plate 36, slides radially away from the center of the circular closed loop to release the aircraft engine 29, it slides radially away from the center of the circular closed loop.

[0042] To facilitate clamping aircraft engine 29, several clamping lugs 35 are provided along the circumference of aircraft engine 29. When a clamping plate 36 approaches aircraft engine 29 to clamp it, the clamping plate 36 contacts the clamping lugs 35. Through holes are provided in both the clamping plate 36 and the clamping lugs 35, allowing fasteners such as bolts or pins to be inserted through the through holes in the clamping plate 36 and the clamping lugs 35 to secure the two. After assembling aircraft engine 29, aircraft engine 29 can be released by simply removing the fasteners and moving the clamping plate 36 away from the aircraft engine 29.

[0043] like Figure 3 As shown, the aircraft engine assembly platform of the present invention, wherein the third slide rail 7 is fixedly provided on the body 3 of the AGV, the third slider 43 is fixedly provided at the bottom of the first vertical frame 1, the third slider 43 is slidably installed on the third slide rail 7, the second vertical frame 22 is fixedly provided on the body 3 of the AGV, when the first vertical frame 1 slides along the third slide rail 7 through the third slider 43, the first vertical frame 1 moves closer to or away from the second vertical frame 22, a linear rack 44 is fixedly provided on the body 3 of the AGV, the arrangement direction of the linear rack 44 is the same as that of the third slide rail 7, a fifth motor 45 is fixedly provided on the first vertical frame 1, the output shaft of the fifth motor 45 is fixedly connected to the second gear 5, and the second gear 5 is engaged with the linear rack 44.

[0044] In the aircraft engine assembly platform of the present invention, the specific manner in which the second gear 5 is engaged with the linear rack 44 is as follows: a third gear 6 is provided between the second gear 5 and the linear rack 44, the third gear 6 is rotatably mounted on the first vertical frame 1, and the third gear 6 is engaged with the second gear 5 and the linear rack 44 respectively.

[0045] The fifth motor 45 is fixedly mounted on the first base plate 40 of the first vertical frame 1. The third gear 6 is also rotatably mounted on the first base plate 40 of the first vertical frame 1. Specifically, the third gear 6 is fixedly connected to a shaft, which is in turn rotatably mounted on the first base plate 40 via a bearing. When the fifth motor 45 drives the second gear 5 to rotate, the third gear 6, which is meshed with the second gear 5, also rotates. Since the third gear 6 meshes with the linear rack 44, the third gear 6 causes the entire first vertical frame 1 to slide along the third slide rail 7 via the third slider 43, thereby moving the first vertical frame 1 toward or away from the second vertical frame 22.

[0046] like Figure 1 As shown, combined with Figure 2-9 As shown, when the aircraft engine assembly platform of the present invention is in use, the entire assembly platform can first be moved to a suitable position by the AGV, and then the distance between the first vertical frame 1 and the second vertical frame 22 is increased by the fifth motor 45, and then the aircraft engine 29 is placed between the first C-shaped ring 13 and the second C-shaped ring 14, and then the distance between the first vertical frame 1 and the second vertical frame 22 is reduced by the fifth motor 45 until the first C-shaped ring 13 and the second C-shaped ring 14 are in contact, and the two C-shaped rings are fixed by fasteners to form a circular closed loop, and then the hand wheel 57 is rotated to make the clamping block 52 slide with the clamping plate 36 toward the center of the circular closed loop until the clamping plate 36 contacts the clamping lug 35 on the aircraft engine 29, and then the clamping plate 36 is fixed to the clamping lug 35 by fasteners, thereby clamping the aircraft engine 29 in the circular closed loop. Then, according to actual requirements, the first motor 4 and the second motor 8 are used to simultaneously drive the first sliding seat 2 and the second sliding seat 20 to rise or fall, thereby driving the aircraft engine 29 to rise or fall. After the aircraft engine 29 rises or falls to an appropriate height, the third motor 34 is used to drive the first slewing support 9 and the second slewing support 19, causing the first turntable 33 and the second turntable 23 to rotate simultaneously, thereby causing the aircraft engine 29 to rotate in a vertical plane. After the aircraft engine 29 rotates to an appropriate position, the fourth motor 24 is used to drive the circular closed structure to rotate around its own axis, that is, the aircraft engine 29 rotates around its own axis, thereby facilitating the assembly of the aircraft engine 29. It can be seen that since the present invention clamps the aircraft engine 29 through the relatively arranged first C-ring 13 and the second C-ring 14, it is safer. Since the present invention uses the AGV as the support base, it can be easily moved.

[0047] After completing the assembly of the aircraft engine 29, it is only necessary to use the lifting equipment to lift the engine 29, then remove the fasteners between the clamping lug 35 and the clamping plate 36, then turn the hand wheel 57 to move the clamping plate 36 away from the engine 29, then remove the fasteners between the first C-shaped ring 13 and the second C-shaped ring 14, and then use the fifth motor 45 to increase the distance between the first vertical frame 1 and the second vertical frame 22, and finally use the lifting equipment to lift the engine 29 away.

[0048] It should be noted that the directions or positional relationships indicated by terms such as "center", "up", "down", "front", "back", "left", "right", and "middle" are based on the directions or positional relationships shown in the accompanying drawings. 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 direction, be constructed and operated in a specific direction. Therefore, they should not be understood as limiting the present invention.

[0049] In the description of the present invention, it should be noted that, unless otherwise expressly specified or limited, the terms "connected" and "connection" should be understood in a broad sense. For example, they can refer to fixed connection, detachable connection, or integral connection; mechanical connection, electrical connection; direct connection, or indirect connection through an intermediary. Those skilled in the art will understand the specific meanings of the above terms in the present invention based on the specific circumstances.

[0050] The embodiments described above are merely descriptions of preferred implementations of the present invention and are not intended to limit the scope of the present invention. Without departing from the spirit of the present invention, various modifications and improvements made to the technical solutions of the present invention by ordinary technicians in this field should fall within the scope of protection determined by the claims of the present invention.

Claims

1. An aircraft engine assembly platform, characterized by: The AGV includes an AGV body, wherein a first vertical frame and a second vertical frame are arranged relatively to each other, a first sliding seat is provided on the first vertical frame to slide in a vertical direction, the first sliding seat is connected to a first driving device, the first driving device can drive the first sliding seat to slide along the first vertical frame, the first sliding seat is connected to one side of the first turntable through a first slewing bearing, a first upper support plate and a first lower support plate are fixedly provided on the other side of the first turntable, a first C-shaped ring is provided for sliding between the first upper support plate and the first lower support plate, a second sliding seat is provided on the second vertical frame to slide in a vertical direction, the second sliding seat is connected to the second driving device, and the second driving device can drive the second sliding seat to slide along the second vertical frame The second sliding seat is connected to one side of the second turntable through a second slewing bearing, and a second upper support plate and a second lower support plate are fixed on the other side of the second turntable. A second C-shaped ring is slidably provided between the second upper support plate and the second lower support plate, and the first C-shaped ring and the second C-shaped ring form a circular closed ring for clamping the aircraft engine. The first C-shaped ring and the second C-shaped ring are both provided with clamping parts for clamping the aircraft engine. The circular closed ring can rotate around its own axis under the drive of the third driving device. When the circular closed ring rotates around its own axis, the first C-shaped ring slides relative to the first upper support plate and the first lower support plate, and the second C-shaped ring slides relative to the second upper support plate and the second lower support plate. The upper surface of the first C-shaped ring is fixed with a first upper arc slide rail, and the first upper arc slide rail is arranged along the circumference of the first C-shaped ring. The lower surface of the first upper support plate is fixed with a first upper arc slide block, and the first upper arc slide block is slidably installed on the first upper arc slide rail, and the lower surface of the first C-shaped ring is fixed with a first lower arc slide rail, and the first lower arc slide rail is arranged along the circumference of the first C-shaped ring. The upper surface of the first lower support plate is fixed with a first lower arc slide block, and the first lower arc slide block is slidably installed on the first lower arc slide rail, and the upper surface of the second C-shaped ring is fixed with a second upper arc slide rail, and the second upper arc slide rail is arranged along the circumference of the second C-shaped ring. The lower surface of the second upper support plate is fixed with a second upper arc slide block, and the second upper arc slide block is slidably installed on the second upper arc slide rail. The first gear is fixedly provided on the second supporting plate, and the second gear is fixedly provided on the second supporting plate, and the first gear is engaged with the first gear and the second gear is engaged with the first gear.

2. The aircraft engine assembly platform according to claim 1, characterized in that: The first vertical frame is fixed with a first slide rail arranged in a vertical direction, and the first sliding seat is slidably installed on the first slide rail through a first slider. The first driving device includes a first motor, a first reducer and a first lifting screw. The first lifting screw is rotatably installed on the first vertical frame along the vertical direction. The first motor and the first reducer are arranged on the first vertical frame, the output shaft of the first motor is connected to the input shaft of the first reducer, the output shaft of the first reducer is connected to the lower end of the first lifting screw, and the first sliding seat is threadedly connected to the first lifting screw.

3. The aircraft engine assembly platform according to claim 2, characterized in that: The second vertical frame is fixed with a second slide rail arranged in the vertical direction, and the second sliding seat is slidably installed on the second slide rail through the second slider. The second driving device includes a second motor, a second reducer and a second lifting screw. The second lifting screw is rotatably installed on the second vertical frame along the vertical direction. The second motor and the second reducer are arranged on the second vertical frame, the output shaft of the second motor is connected to the input shaft of the second reducer, the output shaft of the second reducer is connected to the lower end of the second lifting screw, and the second sliding seat is threadedly connected to the second lifting screw.

4. The aircraft engine assembly platform according to claim 3, characterized in that: The first slewing bearing includes a first outer ring, a first inner ring, a supporting base, a third motor and a worm. The first inner ring is fixedly mounted on the supporting base, the first outer ring is rotatably mounted on the outside of the first inner ring, the third motor is fixedly mounted on the supporting base, the worm is fixedly connected to the output shaft of the third motor, the outer peripheral surface of the first outer ring is provided with circumferentially arranged external teeth, the worm is engaged with the external teeth, the supporting base is fixedly connected to the first sliding seat, and the first outer ring is fixedly connected to one side of the first turntable.

5. The aircraft engine assembly platform according to claim 4, characterized in that: The second slewing bearing includes a second outer ring and a second inner ring. The second inner ring is rotatably mounted in the second outer ring. The second inner ring is fixedly connected to the second sliding seat. The second outer ring is fixedly connected to one side of the second turntable.

6. The aircraft engine assembly platform according to claim 5, characterized in that: The first C-shaped ring and the second C-shaped ring are both provided with radially arranged through holes, and a clamping member is installed in the through hole, and the clamping member includes a clamping seat, a clamping screw and a clamping block. The clamping seat is U-shaped, and the clamping seat includes a base plate fixed in the through hole, and two relatively arranged side plates are fixed on the bottom plate. A clamping screw is rotatably installed between the two side plates, and the arrangement direction of the clamping screw is the same as the through hole. The clamping block is threadedly connected to the clamping screw between the two side plates, and a clamping slide rail with the same arrangement direction as the clamping screw is provided on the bottom plate. A clamping slider is fixed to the lower end of the clamping block, and the clamping slider is slidably installed on the clamping slide rail. A clamping plate is fixed to the upper end of the clamping block, and the height of the clamping plate is higher than the two side plates.

7. The aircraft engine assembly platform according to claim 6, characterized in that: A hand wheel is fixedly connected to the clamping screw, and the hand wheel is located outside the clamping seat.

8. The aircraft engine assembly platform according to claim 7, characterized in that: A third slide rail is fixedly provided on the body of the AGV, a third slider is fixedly provided at the bottom of the first vertical frame, the third slider is slidably mounted on the third slide rail, and the second vertical frame is fixedly provided on the body of the AGV. When the first vertical frame slides along the third slide rail through the third slider, the first vertical frame moves closer to or away from the second vertical frame. A linear rack is fixedly provided on the body of the AGV, and the arrangement direction of the linear rack is the same as that of the third slide rail. A fifth motor is fixedly provided on the first vertical frame, and a second gear is fixedly connected to the output shaft of the fifth motor, and the second gear is meshed with the linear rack.

9. The aircraft engine assembly platform according to claim 8, characterized in that: The specific manner in which the second gear is engaged with the linear rack is as follows: a third gear is provided between the second gear and the linear rack, the third gear is rotatably mounted on the first vertical frame, and the third gear is engaged with the second gear and the linear rack respectively.

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