An automated assembly system for aircraft engines

Abstract

The present invention discloses an automated assembly system for aircraft engines. A transfer unit is installed at both ends of the system base unit of the present invention. The transfer unit and the lateral rectangular track unit and the horizontal rectangular track unit in the system base unit form a 90° circular track switching system, which breaks through the traditional production line layout and can significantly reduce the floor space. Multiple flexible assembly rack devices are hung on the lateral rectangular track unit, and can be synchronized and moved in a rhythmic and pulsating manner according to the assembly production scheduling instructions of batch production machines, with a high degree of automation. The system can also adapt to the fixed-station production of new scientific research machines. The system can adapt to changes in the number of assembly stations by increasing or decreasing the number of flexible assembly rack devices, and the system has certain scalability. The system can adapt to the co-production of aircraft engines of multiple models and small batches through the special flip unit C-shaped frame of the quick-change flexible assembly rack device, reflecting the characteristics of flexible production and manufacturing.

Description

Technical Field

[0001] The invention belongs to the technical field of aviation engine automatic assembly and relates to an assembly system, in particular to an aviation engine automatic assembly system. Background Art

[0002] Aircraft engine assembly is one of the most critical steps in the engine manufacturing process. Its product structure is complex, the working environment is harsh, and the manufacturing process involves a large number of parts and complex coordination. The level of assembly technology and quality directly affect the engine's operating characteristics, directly determining the engine's reliability, lifespan, and key performance parameters. The assembly process consists of thousands or even tens of thousands of parts, starting with part manufacturing and unit component assembly, and then through final assembly and test runs to complete the delivery of the engine. This process requires repeated posture adjustments of the engine assembly object, typically undergoing multiple cycles of disassembly, measurement, repair, and testing to ensure key assembly accuracy indicators. As a result, assembly efficiency is low, and the first-time delivery pass rate is not high, seriously restricting the comprehensive requirements of modern aircraft manufacturers for engines with short cycle times, high reliability, and long life.

[0003] At present, the level of domestic aviation engine assembly technology lags significantly behind that of related industries such as automobiles and aircraft, which have introduced a large number of digital and intelligent production lines and equipment. Especially in terms of assembly technology, traditional manufacturing methods such as simple mechanical welding assembly frames, manual measurement and visual observation are still the mainstream. Summary of the Invention

[0004] In order to improve the overall level of high-end equipment for my country's aviation engine production and make up for the shortcomings of manufacturing process equipment, it is urgent to independently innovate and develop new technologies, new methods and new equipment suitable for the characteristics of my country's engine development process. The purpose of this invention is to provide an automated assembly system that meets the requirements of efficient, multi-model, small-batch flexible manufacturing of domestic aviation engines. It is based on the characteristics of domestic aviation engine assembly process to realize the automation and digital assembly of final assembly according to the beat. It has the characteristics of high precision, high efficiency and good safety, and reduces the labor intensity of operators. It is the development trend of aviation engine assembly technology from traditional fixed assembly mode to flexible and automated assembly technology, and has broad application prospects in the field of digital and intelligent assembly of aerospace engines.

[0005] The technical solutions of the present invention are as follows:

[0006] The present invention comprises a lifting unit, a flexible assembly device, a system base unit and a transfer unit;

[0007] A lifting unit is arranged above the system base unit, and a flexible assembly device is arranged on the side of the system base unit. The flexible assembly device is connected to the system base unit. Corresponding transfer units are also installed at both ends of the system base unit. The lifting unit is arranged above multiple flexible assembly devices and transfer units; the lifting unit lifts the aircraft engine to the corresponding flexible assembly device and then fixes it in the flexible assembly device. Each flexible assembly device is transferred in the system base unit through the transfer unit.

[0008] The system base unit includes a mounting base, a lateral rectangular track unit, a horizontal rectangular track unit and an assembly rack recovery operation ladder;

[0009] A plurality of mounting bases are fixedly installed on the ground at intervals along a straight line to form a mounting base, a lifting unit is fixedly installed on the mounting base, corresponding transfer units are respectively installed on the mounting bases at both ends of the mounting base, horizontal rectangular rail units are fixedly installed on the plurality of mounting bases between the two transfer units, and lateral rectangular rail units are also fixedly installed on the sides of the plurality of mounting bases between the two transfer units, the lateral rectangular rail units and the horizontal rectangular rail units are parallel and arranged at intervals, an assembly rack recovery operation ladder is provided on the side of the horizontal rectangular rail unit away from the lateral rectangular rail unit, a flexible assembly device is arranged on the lateral rectangular rail unit and / or the horizontal rectangular rail unit, the flexible assembly device on the lateral rectangular rail unit is transferred to the horizontal rectangular rail unit through the corresponding transfer unit, and the flexible assembly device on the horizontal rectangular rail unit is transferred to the lateral rectangular rail unit through the corresponding transfer unit.

[0010] The transfer unit includes an electric push rod drive device, a transfer unit track, a slewing support seat and a slewing support bearing;

[0011] The slewing support seat is installed on the end side of the system base unit through a slewing support bearing. The transfer unit track is fixedly installed on the side of the slewing support seat. The flexible assembly device on the system base unit can be moved to the transfer unit track. An electric push rod drive device is fixedly installed on the end of the system base unit. The output shaft of the electric push rod drive device is fixedly connected to the slewing support seat under the transfer unit track. The axial direction of the output shaft of the electric push rod drive device is arranged perpendicular to the track sliding direction of the transfer unit track; the drive of the electric push rod drive device drives the slewing support seat to rotate, thereby driving the transfer unit track to rotate, and transferring the flexible assembly device to the system base unit.

[0012] The lifting unit includes a lifting rail support column, a lifting rail and an electric hoist assembly. One end of the multiple lifting rail support columns is fixedly installed on the system base unit, and the other end of the multiple lifting rail support columns extends upward and is curved. The other end of the multiple lifting rail support columns is fixedly installed with a lifting rail, and an electric hoist assembly is arranged in the lifting rail, and the electric hoist assembly slides along the lifting rail.

[0013] The flexible assembly device includes a lifting unit column, a turning unit reducer, a turning unit C-shaped frame, an engine main mounting section, an engine front adjustable support rod, a lifting unit slide, an operation button box, an HMI control panel, a rotating unit slide, a roller assembly, a turning unit worm gear drive mechanism, a rotating unit reducer, a rotating unit worm gear drive mechanism, a lifting unit worm gear servo drive mechanism and a lifting guide rail;

[0014] The rotating unit skateboard is embedded in the system base unit through a roller assembly, and a rotating unit reducer is fixedly installed on the end face of the rotating unit skateboard, and the rotating unit worm gear drive mechanism is connected to the rotating unit reducer, and the rotating unit reducer is fixedly connected to the lifting unit column. The driving of the rotating unit worm gear drive mechanism drives the rotating unit reducer to rotate, and then drives the lifting unit column to rotate; a lifting guide rail is installed in the lifting unit column, and the lifting unit worm gear servo drive mechanism is arranged at one end of the lifting unit column and connected to one end of the lifting guide rail, and the lifting unit skateboard is sleeved in the lifting guide rail, and a flipping unit reducer is fixedly installed on the end face of the lifting unit skateboard, and the flipping unit worm gear drive mechanism is connected to the flipping unit reducer, and the flipping unit reducer is connected to the flipping unit C-shaped frame. The driving of the flipping unit worm gear drive mechanism drives the flipping unit reducer to rotate, and then drives the flipping unit C-shaped frame and the aircraft engine to flip; the aircraft engine is fixedly installed in the flip unit C-shaped frame through the engine main mounting section and the engine front adjustable support rod.

[0015] The aircraft engine is fixedly mounted in the C-shaped frame of the flip unit through the engine main mounting section and the engine front adjustable support rod, specifically:

[0016] There are raised blocks on both sides of the middle part of the aircraft engine, and mounting raised blocks are also provided on the sides of the flip unit C-shaped frame. The raised blocks of the aircraft engine and the mounting raised blocks corresponding to the flip unit C-shaped frame are fixedly connected through the main mounting section of the engine. One end of the adjustable strut in front of the engine is connected to the end of the aircraft engine, and the other end of the adjustable strut in front of the engine is connected to the C-shaped frame of the flip unit.

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

[0018] 1) The system base unit of the present invention is equipped with corresponding transfer units on both ends to form a 90° circular track switching system. Compared with the traditional production line layout, the 90° circular track switching system of the present invention significantly reduces the occupied space;

[0019] 2) The flexible assembly rack device of the present invention is mounted on a side rectangular track unit, and can be synchronized with the production scheduling instructions of the batch production machine to produce in a pulsating manner according to the beat, with a high degree of automation. It can also adapt to the fixed-station production of new scientific research machines.

[0020] 3) The present invention can increase the number of flexible assembly rack devices, can adapt to changes in the number of assembly stations, and the system has certain scalability;

[0021] 4) The present invention utilizes a dedicated C-shaped flip unit in a quick-change flexible assembly rack device to accommodate the co-production of multiple models and small batches of aircraft engines, embodying the characteristics of flexible production.

[0022] 5) The flexible assembly rack device is normally assembled by hanging on the side rectangular track unit, and has good operation convenience;

[0023] 6) The present invention is provided with an integrated lifting unit to assist in the lifting and docking assembly of large components during the assembly of engine components, thereby reducing labor intensity and avoiding the risk of product collision. BRIEF DESCRIPTION OF THE DRAWINGS

[0024] Figure 1 This is the axial view (front view) of the aircraft engine automated assembly system;

[0025] Figure 2 This is the axial view of the aircraft engine automated assembly system (back);

[0026] Figure 3 This is an axial view of the base unit of the aircraft engine automated assembly system;

[0027] Figure 4 This is the main view of the aircraft engine automated assembly system;

[0028] Figure 5 This is the right view of the aircraft engine automated assembly system;

[0029] Figure 6 This is the axial view A of the flexible assembly device of the aircraft engine automated assembly system;

[0030] Figure 7 This is the axis view B of the flexible assembly device of the aircraft engine automated assembly system;

[0031] Figure 8 This is the axial view A of the first transfer unit of the aircraft engine automated assembly system;

[0032] Figure 9 This is the axis view B of the first transfer unit of the aircraft engine automated assembly system;

[0033] In the figure: lifting track support column 1, lifting track 2, mounting base 3, electric hoist assembly 4, first transfer unit 5, flexible assembly device 6, safety fence 7, aircraft engine 8, second transfer unit 12, assembly rack recovery operation ladder 13, lateral rectangular track unit 14, horizontal rectangular track unit 15, lifting unit column 17, lifting unit accordion cover 18, flip unit reducer 19, flip unit C-shaped frame 20, engine main mounting section 21, engine front adjustable support rod 22, lifting unit slide plate 23, operation button box 24, HMI control panel 25, rotation unit slide plate 26, roller assembly 27, flip unit worm gear drive mechanism 28, rotation unit reducer 29, rotation unit worm gear drive mechanism 30, lifting unit worm gear servo drive mechanism 31, electric push rod drive device 33, transfer unit track 34, slewing support seat 35, slewing support bearing 36, adjustable shim assembly 37, positioning pin 38, lifting guide rail 39. DETAILED DESCRIPTION

[0034] The present invention will be further described in detail below with reference to the accompanying drawings and specific embodiments:

[0035] like Figure 1 、 Figure 2 、 Figure 3 and Figure 4 As shown, the present invention includes a lifting unit, a flexible assembly device 6, a system base unit, and a transfer unit; a lifting unit is provided above the system base unit, and the flexible assembly device 6 is provided on the side of the system base unit. The flexible assembly device 6 is connected to the system base unit. Corresponding transfer units are also installed at both ends of the system base unit. The lifting unit is provided above multiple flexible assembly devices 6 and the transfer unit; the lifting unit lifts the aircraft engine to the corresponding flexible assembly device and then fixes it in the flexible assembly device 6. Each flexible assembly device 6 is transferred within the system base unit via the transfer unit. In a specific implementation, the flexible assembly devices 6 on the lateral rectangular track unit 14 are provided in five numbers, i.e., five assembly stations. Normal assembly is performed laterally, with good operability. The assembly at each station can be performed in a fixed-station production or in a pulsed production according to a beat.

[0036] The system base unit includes a mounting base 3, a safety fence 7, an adjustable shim assembly 37, a lateral rectangular track unit 14, a horizontal rectangular track unit 15 and an assembly rack recovery operation ladder 13;

[0037] Multiple mounting bases 3 are fixedly mounted on the ground at equal intervals along a straight line through corresponding adjustable pad assemblies 37 to form a mounting base, a lifting unit is fixedly mounted on the mounting base, and the mounting bases 3 at both ends of the mounting base are respectively mounted with electric push rod drive devices 33 and slewing support bearings 36 of corresponding transfer units, the transfer units at both ends are symmetrically arranged, a horizontal rectangular track unit 15 is fixedly mounted on the multiple mounting bases 3 between the two transfer units, and a lateral rectangular track unit 14 is also fixedly mounted on the side of the multiple mounting bases 3 between the two transfer units, the lateral rectangular track unit 14 and the horizontal rectangular track unit 15 are arranged in parallel and at intervals, the track direction of the lateral rectangular track unit 14 is to the side of the mounting base 3, and the track direction of the horizontal rectangular track unit 15 is to the top of the mounting base 3, forming a 90° layout. An assembly rack recovery operation ladder 13 is provided on the side of the horizontal rectangular track unit 15 away from the lateral rectangular track unit 14. A safety fence 7 is also installed on the assembly rack recovery operation ladder 13 for operators. Operators perform actual operations on the assembly rack recovery operation ladder 13. Flexible assembly devices 6 are arranged on the lateral rectangular track unit 14 and / or the horizontal rectangular track unit 15. Flexible assembly devices 6 are moved on the tracks manually or automatically. The two transfer units are designated as the first transfer unit 5 and the second transfer unit 12. The transfer unit track 34 of the first transfer unit 5 is connected to the lateral rectangular track unit 14 and / or the horizontal rectangular track unit 15, and the second transfer unit 12 is connected to the lateral rectangular track unit 14 and / or the horizontal rectangular track unit 15. The flexible assembly device on the lateral rectangular track unit 14 is transferred to the horizontal rectangular track unit 15 through the corresponding transfer unit, and the flexible assembly device on the horizontal rectangular track unit 15 is transferred to the lateral rectangular track unit 14 through the corresponding transfer unit, that is, the flexible assembly device installed with the engine is transferred from one end of the lateral rectangular track unit 14 to one end of the horizontal rectangular track unit 15. After the flexible assembly device unloads the engine from the horizontal rectangular track unit 15, it is transferred from the other end of the horizontal rectangular track unit 15 to the other end of the lateral rectangular track unit 14, thus forming a 90° circular track switching system.

[0038] like Figure 8 and Figure 9 As shown, the transfer unit includes an electric push rod drive device 33, a transfer unit track 34, a slewing support seat 35 and a slewing support bearing 36;

[0039] The slewing support seat 35 is installed on the mounting base 3 at the end of the system base unit close to the side of the lateral rectangular track unit 14 through a slewing support bearing 36. The slewing support bearing 36 is fixedly installed on the end mounting base 3. The slewing support seat 35 is coaxially connected to the inner ring of the slewing support bearing 36. The side of the slewing support seat 35 is fixedly installed with a transfer unit track 34. The transfer unit track 34 is located at the end of the lateral rectangular track unit 14. The transfer unit track 34 and the lateral rectangular track unit 14 are in a straight line and the tracks of the two are in the same direction. The flexible assembly device 6 on the lateral rectangular track unit 14 of the system base unit can be moved to the transfer unit track 34. An electric push rod drive device 33 is fixedly installed on the current mounting base 3 at the end of the system base unit. The output shaft of the electric push rod drive device 33 is fixedly connected to the slewing support seat 35 under the transfer unit track 34. The axial direction of the output shaft of the electric push rod drive device 33 is aligned with the transfer unit track 34. The sliding direction of the track is arranged vertically in space; the electric push rod drive device 33 drives the slewing support seat 35 to rotate on the slewing support bearing 36 (that is, to perform a flipping action), and then drives the transfer unit track 34 to rotate, so that the transfer unit track 34 is set at the end of the horizontal rectangular track unit 15, the transfer unit track 34 and the horizontal rectangular track unit 15 are in a straight line and the tracks of the two are in the same direction, and finally the flexible assembly device 6 is transferred to the horizontal rectangular track unit 15 of the system base unit to achieve precise switching and docking of the tracks.

[0040] like Figure 5 As shown, the lifting unit includes a lifting rail support column 1, a lifting rail 2 and an electric hoist assembly 4. One ends of multiple lifting rail support columns 1 are respectively fixedly mounted on multiple mounting bases 3 of the system base unit, that is, multiple lifting rail support columns 1 are arranged at intervals in a straight line, and the other ends of multiple lifting rail support columns 1 extend upward and are curved. The other ends of multiple lifting rail support columns 1 are fixedly mounted with a lifting rail 2, and the track direction of the lifting rail 2 is downward of the mounting base 3. Directly below the lifting rail 2 is a flexible assembly device on the lateral rectangular rail unit 14. An electric hoist assembly 4 is arranged in the lifting rail 2, and the electric hoist assembly 4 slides along the lifting rail 2 for lifting and installation of engine components or the entire machine.

[0041] like Figure 6 and Figure 7As shown, the flexible assembly device 6 includes a lifting unit column 17, a lifting unit accordion cover 18, a flip unit reducer 19, a flip unit C-shaped frame 20, an engine main mounting section 21, an engine front adjustable support rod 22, a lifting unit slide 23, an operation button box 24, an HMI control panel 25, a rotation unit slide 26, a roller assembly 27, a positioning pin 38, a flip unit worm gear drive mechanism 28, a rotation unit reducer 29, a rotation unit worm gear drive mechanism 30, a lifting unit worm gear servo drive mechanism 31 and a lifting guide rail 39;

[0042] The rotating unit slide 26 is embedded in the lateral rectangular track unit 14 or the horizontal rectangular track unit 15 of the system base unit via a roller assembly 27. Multiple positioning holes are defined within the lateral rectangular track unit 14 and the horizontal rectangular track unit 15. Positioning pins 38 are fixedly mounted on the rotating unit slide 26. Manually sliding the rotating unit slide 26 allows the positioning pins 38 to engage with the corresponding positioning holes to position the flexible assembly device 6 within the track. In a specific implementation, the positioning pins on the rotating unit slide 26 are replaced with pneumatic cylinders. A servo motor drive unit is fixedly mounted on the side of the rotating unit slide 26. The servo motor drive unit and the pneumatic cylinder control the drive. The servo motor drive unit engages with the track, and the pneumatic cylinder engages with the positioning holes, allowing the rotating unit slide 26 to automatically slide and position itself on the track.A rotating unit reducer 29 is fixedly installed on the end surface of the rotating unit slide 26 away from the roller assembly 27, and a rotating unit worm gear drive mechanism 30 is installed on the rotating unit reducer 29. The rotating unit worm gear drive mechanism 30 is connected to the rotating unit reducer 29 through a coupling, and the rotating unit reducer 29 is fixedly connected to the lifting unit column 17. The drive of the rotating unit worm gear drive mechanism 30 drives the rotating unit reducer 29 to rotate, thereby driving the lifting unit column 17 to rotate; a lifting guide rail 39 is installed in the lifting unit column 17, and a lifting unit worm gear servo drive mechanism 31 is arranged at one end of the lifting unit column 17 and connected to one end of the lifting guide rail 39. The lifting unit slide 23 is sleeved in the lifting guide rail 39 and is connected through threads. The sides of the lifting unit columns 17 on the upper and lower sides of the lifting unit slide 23 are equipped with lifting unit accordion covers 18. The lifting unit accordion covers 18 on both sides are connected, and the lifting unit slide plate 23 is lifted and lowered along the lifting guide rails 39, and the lifting unit accordion cover 18 is also folded accordingly to ensure that the lifting unit column 17 is closed. The end surface of the lifting unit slide plate 23 is fixedly installed with a flip unit reducer 19, and the flip unit worm gear drive mechanism 28 is installed on the flip unit reducer 19. The flip unit worm gear drive mechanism 28 is connected to the flip unit reducer 19 through a coupling, and the flip unit reducer 19 is connected to the flip unit C-shaped frame 20. The flip unit worm gear drive mechanism 28 drives the flip unit reducer 19 to rotate, and then drives the flip unit C-shaped frame 20 and the aircraft engine 8 to flip; the aircraft engine 8 is connected to the main engine mounting section 21 The front adjustable strut 22 of the engine is fixedly mounted in the C-shaped frame 20 of the flip unit, that is, the aircraft engine 8 is clamped by the C-shaped frame 20 of the flip unit. Specifically, protrusions are provided on both sides of the middle of the aircraft engine 8, and mounting protrusions are also provided on the sides of the C-shaped frame 20 of the flip unit. The protrusions of the aircraft engine 8 and the mounting protrusions corresponding to the C-shaped frame 20 of the flip unit are fixedly connected through the main mounting section 21 of the engine. One end of the front adjustable strut 22 of the engine is connected to the end of the aircraft engine 8, and the other end of the front adjustable strut 22 of the engine is connected to the C-shaped frame 20 of the flip unit. In a specific implementation, by replacing the main mounting section (21) and the front adjustable strut (22) of the engine with different sizes, it is possible to assemble different types of engines on the flexible assembly device 6.

Claims

1. An automated assembly system for aircraft engines, characterized in that: The invention comprises a lifting unit, a flexible assembly device (6), a system base unit and a transfer unit; the lifting unit is arranged above the system base unit, the flexible assembly device (6) is arranged on the side of the system base unit, the flexible assembly device (6) is connected to the system base unit, and corresponding transfer units are respectively installed at both ends of the system base unit, and the lifting unit is arranged above the plurality of flexible assembly devices (6) and the transfer unit; the lifting unit lifts the aircraft engine to the corresponding flexible assembly device and then fixes it in the flexible assembly device (6), and each flexible assembly device (6) is transferred in the system base unit through the transfer unit; The system base unit comprises a mounting base (3), a lateral rectangular track unit (14), a horizontal rectangular track unit (15) and an assembly rack recovery operation ladder (13); a plurality of mounting bases (3) are fixedly mounted on the ground at intervals along a straight line to form a mounting seat, a lifting unit is fixedly mounted on the mounting seat, corresponding transfer units are respectively mounted on the mounting bases (3) at both ends of the mounting seat, a horizontal rectangular track unit (15) is fixedly mounted on the plurality of mounting bases (3) between the two transfer units, a lateral rectangular track unit (14) is also fixedly mounted on the side of the plurality of mounting bases (3) between the two transfer units, the lateral rectangular track unit (14) and the horizontal rectangular track unit (15) are arranged in parallel and at intervals, i.e., a 90° direction layout is formed, and the horizontal rectangular track unit (15) is away from one side of the lateral rectangular track unit (14). An assembly rack recovery operation ladder (13) is provided, and a flexible assembly device (6) is arranged on the lateral rectangular track unit (14) and / or the horizontal rectangular track unit (15). The flexible assembly device on the lateral rectangular track unit (14) is transferred to the horizontal rectangular track unit (15) through a corresponding transfer unit, and the flexible assembly device on the horizontal rectangular track unit (15) is transferred to the lateral rectangular track unit (14) through a corresponding transfer unit, that is, the flexible assembly device installed with the engine is transferred from one end of the lateral rectangular track unit (14) to one end of the horizontal rectangular track unit (15), and the flexible assembly device is transferred from the other end of the horizontal rectangular track unit (15) to the other end of the lateral rectangular track unit (14) after unloading the engine from the horizontal rectangular track unit (15), thereby forming a 90° circular track switching system; The transfer unit comprises an electric push rod drive device (33), a transfer unit track (34), a slewing support seat (35) and a slewing support bearing (36); the slewing support seat (35) is installed on the end side of the system base unit through the slewing support bearing (36); the side of the slewing support seat (35) is fixedly installed with the transfer unit track (34); the flexible assembly device (6) on the system base unit can be moved to the transfer unit track (34); the end of the system base unit is fixedly installed with an electric push rod drive device (33); the output shaft of the electric push rod drive device (33) is fixedly connected to the slewing support seat (35) under the transfer unit track (34); the axial direction of the output shaft of the electric push rod drive device (33) is arranged perpendicular to the track sliding direction of the transfer unit track (34); the drive of the electric push rod drive device (33) drives the slewing support seat (35) to rotate, that is, to perform a 90° flipping action, thereby driving the transfer unit track (34) to rotate, and transferring the flexible assembly device (6) to the system base unit.

2. The aircraft engine automated assembly system according to claim 1, characterized in that: The hoisting unit comprises a hoisting rail support column (1), a hoisting rail (2) and an electric hoist assembly (4), wherein one end of the plurality of hoisting rail support columns (1) is fixedly mounted on the system base unit, the other end of the plurality of hoisting rail support columns (1) extends upward and is curved, the other end of the plurality of hoisting rail support columns (1) is fixedly mounted with the hoisting rail (2), the hoisting rail (2) is provided with an electric hoist assembly (4), and the electric hoist assembly (4) slides along the hoisting rail (2).

3. The aircraft engine automated assembly system according to claim 1, characterized in that: The flexible assembly device (6) includes a lifting unit column (17), a turning unit reducer (19), a turning unit C-shaped frame (20), an engine main mounting section (21), an engine front adjustable support rod (22), a lifting unit slide (23), an operation button box (24), an HMI control panel (25), a rotating unit slide (26), a roller assembly (27), a turning unit worm gear drive mechanism (28), a rotating unit reducer (29), a rotating unit worm gear drive mechanism (30), a lifting unit worm gear servo drive mechanism (31) and a lifting guide rail (39); The rotating unit slide plate (26) is embedded in the system base unit through the roller assembly (27). The end surface of the rotating unit slide plate (26) is fixedly installed with a rotating unit reducer (29). The rotating unit worm gear drive mechanism (30) is connected to the rotating unit reducer (29). The rotating unit reducer (29) is fixedly connected to the lifting unit column (17). The driving of the rotating unit worm gear drive mechanism (30) drives the rotating unit reducer (29) to rotate, thereby driving the lifting unit column (17) to rotate; a lifting guide rail (39) is installed in the lifting unit column (17), and the lifting unit worm gear servo drive mechanism (31) is arranged at one end of the lifting unit column (17) and is connected to the lifting guide rail ( 39), the lifting unit slide plate (23) is sleeved in the lifting guide rail (39), a flip unit reducer (19) is fixedly mounted on the end surface of the lifting unit slide plate (23), a flip unit worm gear drive mechanism (28) is connected to the flip unit reducer (19), and the flip unit reducer (19) is connected to the flip unit C-shaped frame (20), and the flip unit worm gear drive mechanism (28) drives the flip unit reducer (19) to rotate, thereby driving the flip unit C-shaped frame (20) and the aircraft engine (8) to flip; the aircraft engine (8) is fixedly mounted in the flip unit C-shaped frame (20) through the engine main mounting section (21) and the engine front adjustable support rod (22).

4. The aircraft engine automated assembly system according to claim 3, characterized in that: The aero engine (8) is fixedly mounted in the flip unit C-shaped frame (20) via the engine main mounting section (21) and the engine front adjustable strut (22), specifically: The aircraft engine (8) is provided with raised blocks on both sides of the middle portion, and the side of the flip unit C-shaped frame (20) is also provided with mounting raised blocks. The raised blocks of the aircraft engine (8) and the corresponding mounting raised blocks of the flip unit C-shaped frame (20) are fixedly connected via an engine main mounting section (21). One end of an engine front adjustable strut (22) is connected to an end portion of the aircraft engine (8), and the other end of the engine front adjustable strut (22) is connected to the flip unit C-shaped frame (20).

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