Device for erecting and overturning aircraft

Abstract

The invention provides a device for erecting and overturning an aircraft. The device comprises a gantry type lifting arm, a hanging assembly, an erecting driving and adjusting assembly and an erecting telescopic assembly. The hanging assembly is connected to the gantry type lifting arm and used for hanging and lifting the gantry type lifting arm. The erecting driving adjusting assembly is used for being connected to a corresponding connecting point of the aircraft body and driving the aircraft body to rotate in the Z direction so as to adjust the erecting posture of the aircraft body. One end of the erecting telescopic assembly is connected to the erecting drive adjusting assembly, and the other end of the erecting telescopic assembly is connected to the gantry type suspension arm and used for buffering the impact of the dead weight of the device on the aircraft body. According to the device for erecting and overturning the aircraft, the erecting posture of the aircraft can be adjusted, and the weight and the gravity center of the aircraft can be measured.

Description

Technical Field

[0001] The present invention relates to the technical field of aircraft erection and flipping equipment, and more specifically, to a device for erection and flipping of an aircraft. Background Art

[0002] The vertical flipping of aircraft is mostly done manually, with the aircraft fixed by a specific tooling such as a vertical frame, and then acting on the lifting point of the tooling by means of a crane, and the relative position and relative height of the hook are adjusted to make the aircraft vertical flipping. This manual operation method is relatively cumbersome, it is difficult to achieve high-precision vertical flipping, it is relatively time-consuming, and data measurement is impossible. Summary of the invention

[0003] 1. Technical issues to be resolved

[0004] The technical problem to be solved by the present invention is that the existing aircraft uprighting and flipping device has the problems of complicated operation method and inability to perform data measurement.

[0005] (II) Technical solution

[0006] To achieve the above object, the technical solution adopted by the present invention is:

[0007] The present invention provides a device for erecting and flipping an aircraft, comprising a gantry crane arm, a hanging assembly, an erection drive adjustment assembly and an erection telescopic assembly; the hanging assembly is connected to the gantry crane arm and is used to suspend and lift the gantry crane arm; the erection drive adjustment assembly is used to be connected to a corresponding connection point of an aircraft body and drive the aircraft body to rotate along the Z direction to adjust the erection posture of the aircraft body; one end of the erection telescopic assembly is connected to the erection drive adjustment assembly, and the other end of the erection telescopic assembly is connected to the gantry crane arm, and is used to buffer the impact of the device's own weight on the aircraft body.

[0008] Preferably, the hanging assembly includes a hanging point assembly, a sling frame, a weighing sensor, an X-direction fine-adjustment assembly and a Y-direction fine-adjustment assembly, the Y-direction fine-adjustment assembly is arranged in the sling frame, the X-direction fine-adjustment assembly is arranged on the Y-direction fine-adjustment assembly, the gantry boom is arranged on the X-direction fine-adjustment assembly, the X-direction fine-adjustment assembly is used to drive the gantry boom to move along the X-direction, the Y-direction fine-adjustment assembly is used to drive the gantry boom to move along the Y-direction, the hanging point assembly is connected to the end of the sling frame away from the gantry boom, the hanging point assembly is used to be connected to the hook of the lifting device, and the weighing sensor is arranged between the sling frame and the hanging point assembly.

[0009] Preferably, the Y-axis fine-tuning assembly includes a Y-axis support seat, a Y-axis drive motor and a Y-axis screw rod, the Y-axis drive motor is installed and connected to the hanger frame, the Y-axis support seat is slidably connected to the hanger frame, the Y-axis screw rod is threadedly connected to the Y-axis support seat, and the end of the Y-axis screw rod is connected to the output end of the Y-axis drive motor.

[0010] Preferably, the X-axis fine-tuning assembly includes an X-axis support seat, an X-axis drive motor and an X-axis screw rod, the X-axis support seat is slidably connected to the Y-axis support seat, the X-axis screw rod is threadedly connected to the X-axis support seat, the end of the X-axis screw rod is connected to the output end of the X-axis drive motor, and the gantry boom is provided on the X-axis support seat.

[0011] Preferably, the erection drive adjustment assembly includes an active end frame, a passive end frame, a driving assembly, an active end connecting plate, a driven shaft, a driven end connecting plate, an encoder and a locking pin. The active end frame and the driven end frame are arranged opposite to each other and are respectively connected to opposite sides of the erection telescopic assembly. The active end frame is provided with the driving assembly, the output end of the driving assembly is connected to the active end connecting plate, the encoder is rotatably connected to the passive end frame, one end of the driven shaft is connected to the output end of the encoder, and the other end of the driven shaft is connected to the driven end connecting plate. The active end connecting plate and the driven end connecting plate are respectively used to connect to corresponding connecting points of the aircraft body, and the locking pin is used to lock the driven end connecting plate and the driven end frame.

[0012] Preferably, the erection drive adjustment assembly further includes a spline adjustment assembly, and the spline adjustment assembly includes a moving section and a guide section, the guide section is arranged along the Z direction, and the moving section is slidably connected to the guide section.

[0013] Preferably, the driving assembly includes a motor, a worm gear reducer and a planetary reducer, the motor, the worm gear reducer and the planetary reducer are all connected to the active end frame, the output end of the motor is connected to the input end of the worm gear reducer, the output end of the worm gear reducer is connected to the input end of the planetary reducer, and the output end of the planetary reducer is connected to the active end connecting plate.

[0014] Preferably, the erecting telescopic assembly includes a first telescopic assembly and a second telescopic assembly with the same structure, the first telescopic assembly and the second telescopic assembly are arranged opposite to each other and are respectively connected to opposite sides of the gantry boom, the first telescopic assembly includes a mounting frame, a spring telescopic shaft, a compression spring and an anti-rotation shaft, the mounting frame is connected to the gantry boom, the spring telescopic shaft is arranged along the Z direction and is slidably connected to the mounting frame, one end of the compression spring is connected to the lower end of the spring telescopic shaft, and the other end of the compression spring is connected to the mounting frame, the anti-rotation shaft connects the mounting frame and the gantry boom, and the anti-rotation shaft is used to prevent the spring telescopic shaft from rotating in the circumferential direction.

[0015] Preferably, the gantry boom comprises a main crossbeam, a first boom, a second boom and an electric control cabinet, the main crossbeam is arranged along the X direction, the main crossbeam is connected to the hanging assembly, one end of the main crossbeam is connected to the first boom, the other end of the main crossbeam is connected to the second boom, the first boom and the second boom are both arranged along the Z direction, and the electric control cabinet is arranged on the first boom or the second boom.

[0016] Preferably, it also includes a crane, a movable track is provided in the production workshop, the crane is slidably connected to the movable track, and the hanging assembly is connected to the crane.

[0017] (III) Beneficial effects

[0018] The above technical solution of the present invention has at least the following advantages:

[0019] 1. In the present invention, a suspension assembly and a gantry-type crane arm are provided to realize the erection and hanging of the aircraft body, an erection drive adjustment assembly is provided to realize the driving of the aircraft body to flip, and then realize the adjustment of the erection posture of the aircraft body, and an erection telescopic assembly is provided to buffer the impact of the deadweight of the device on the aircraft body, prevent the device from damaging the aircraft body during the erection and flipping process, and ensure the stability of the entire erection and flipping process. The present invention simplifies the operation method of erecting and flipping the aircraft, has high flipping accuracy, and saves operation time.

[0020] 2. In the present invention, an X-axis fine-tuning assembly and a Y-axis fine-tuning assembly are provided, which can realize the position adjustment of the aircraft body in the X-axis direction and the Y-axis direction, and then the center of gravity axis of the aircraft body can be adjusted to coincide with the erection and flipping axis of the device, ensuring that there is no eccentricity during the erection and flipping of the aircraft, and evenly applying the load to the entire device, making the erection and flipping smoother.

[0021] 3. In the present invention, a weighing sensor is provided, which can be combined with a corresponding control program to measure the weight and center of gravity position of the aircraft body, and provide data support for the test of the aircraft. BRIEF DESCRIPTION OF THE DRAWINGS

[0022] In order to more clearly illustrate the technical solutions in the embodiments of the present invention, the drawings required for use in the embodiments will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying creative work.

[0023] Figure 1 It is a schematic diagram of the structure of a device for uprighting and flipping an aircraft provided by an embodiment of the present invention.

[0024] Figure 2 It is a schematic structural diagram of a gantry boom provided in an embodiment of the present invention.

[0025] Figure 3 It is a schematic diagram of the structure of a hanging assembly provided in an embodiment of the present invention.

[0026] Figure 4 It is a structural schematic diagram of an erection drive adjustment assembly provided in an embodiment of the present invention.

[0027] Figure 5 It is a structural schematic diagram of an erecting and telescopic assembly provided in an embodiment of the present invention.

[0028] The reference numerals in the figures are:

[0029] 1. Gantry boom; 2. Suspension assembly; 3. Erecting drive adjustment assembly; 4. Erecting telescopic assembly; 11. Main crossbeam; 12. First boom; 13. Second boom; 14. Electric control cabinet; 21. Suspension point assembly; 22. Spreader frame; 23. Weighing sensor; 24. X-axis fine-tuning assembly; 25. Y-axis fine-tuning assembly; 241. X-axis support seat; 242. X-axis drive motor; 243. X-axis lead screw; 251. Y-axis support seat; 252. Y-axis drive motor; 253. Y-axis Screw rod; 31, active end frame; 32, driven end frame; 33, driving assembly; 34, active end connecting plate; 35, follower shaft; 36, driven end connecting plate; 37, encoder; 38, locking pin shaft; 39, spline adjustment assembly; 331, motor; 332, worm gear reducer; 333, planetary reducer; 41, first telescopic assembly; 42, second telescopic assembly; 411, mounting frame; 412, spring telescopic shaft; 413, compression spring; 414, anti-rotation shaft. DETAILED DESCRIPTION

[0030] In order to make the technical problems, technical solutions and beneficial effects to be solved by the present invention more clearly understood, the present invention is further described in detail below in conjunction with the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are only used to explain the present invention and are not used to limit the present invention.

[0031] It should be noted that when an element is referred to as being "fixed to" or "disposed on" another element, it may be directly located on the other element or indirectly located on the other element. When an element is referred to as being "connected to" another element, it may be directly connected to the other element or indirectly connected to the other element.

[0032] It should be understood that the terms "length", "width", "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside" and "outside" etc., indicating directions or positional relationships, are based on the directions or positional relationships shown in the accompanying drawings and are only for the convenience of describing the present invention, and do not indicate that a device or element must have a specific direction, be constructed and operated in a specific direction, and therefore should not be understood as a limitation on the present invention.

[0033] In addition, the terms "first" and "second" are used for descriptive purposes only and cannot be understood as indicating relative importance or indicating the number of technical features. In the description of the present invention, the meaning of "multiple" is two or more, unless otherwise clearly and specifically defined. The specific implementation of the present invention is described in more detail below in conjunction with specific embodiments:

[0034] like Figure 1 , Figure 2 and Figure 3 As shown, an embodiment of the present invention provides a device for erecting and flipping an aircraft, comprising a gantry crane 1, a hanging assembly 2, an erection drive adjustment assembly 3 and an erection telescopic assembly 4; the hanging assembly 2 is connected to the gantry crane 1, and is used to suspend and lift the gantry crane 1; the erection drive adjustment assembly 3 is used to connect to the corresponding connection point of the aircraft body, and drive the aircraft body to rotate along the Z direction to adjust the erection posture of the aircraft body; one end of the erection telescopic assembly 4 is connected to the erection drive adjustment assembly 3, and the other end of the erection telescopic assembly 4 is connected to the gantry crane 1, and is used to buffer the impact of the device's own weight on the aircraft body.

[0035] In one embodiment, the hanging assembly 2 includes a hanging point assembly 21, a sling frame 22, a weighing sensor 23, an X-direction fine-tuning assembly 24 and a Y-direction fine-tuning assembly 25. The Y-direction fine-tuning assembly 25 is provided in the sling frame 22, the X-direction fine-tuning assembly 24 is provided on the Y-direction fine-tuning assembly 25, the X-direction fine-tuning assembly 24 is provided on the gantry boom 1, the X-direction fine-tuning assembly 24 is used to drive the gantry boom 1 to move along the X direction, the Y-direction fine-tuning assembly 25 is used to drive the gantry boom 1 to move along the Y direction, the hanging point assembly 21 is connected to the end of the sling frame 22 away from the gantry boom 1, the hanging point assembly 21 is used to be connected to the hook of the lifting device, and the weighing sensor 23 is provided between the sling frame 22 and the hanging point assembly 21. Specifically, the X-direction fine-tuning assembly 24 can achieve fine-tuning of the position of the gantry boom 1 in the X-axis direction, and the Y-direction fine-tuning assembly 25 can achieve fine-tuning of the position of the gantry boom 1 in the Y-axis direction. Through the fine-tuning of the above positions, the axis of the aircraft passing through the center of gravity can be adjusted to be parallel to the vertical axis. If there is an angular deviation between the axis of the aircraft passing through the center of gravity and the vertical axis, the aircraft will generate a torque on the heavier side during the flipping process, and the torque will affect the flipping of the aircraft. In this embodiment, the X-direction fine-tuning assembly 24 and the Y-direction fine-tuning assembly 25 can achieve fine-tuning of the position of the aircraft in the X-axis direction and the Y-axis direction. In addition, when performing the vertical flip test of the aircraft, a corresponding test device will be set up below the aircraft. During the test, it is necessary to control the connection position on the aircraft body to match the corresponding connection structure on the test device. The position of the aircraft body in the X-axis direction and the Y-axis direction can be fine-tuned through the X-direction fine-tuning component 24 and the Y-direction fine-tuning component 25, thereby facilitating the position matching of the connection position on the aircraft body with the corresponding connection structure on the test device below. More specifically, the weighing sensor 23 is a pressure sensor, which converts the traditional tension into the pressure between the two components, and can accurately measure the weight and center of gravity of the aircraft body.

[0036] In one embodiment, the Y-axis fine-tuning assembly 25 includes a Y-axis support seat 251, a Y-axis driving motor 252 and a Y-axis screw rod 253. The Y-axis driving motor 252 is installed and connected to the sling frame 22, the Y-axis support seat 251 is slidably connected to the sling frame 22, the Y-axis screw rod 253 is threadedly connected to the Y-axis support seat 251, and the end of the Y-axis screw rod 253 is connected to the output end of the Y-axis driving motor 252. Specifically, the Y-axis driving motor 252 can rotate forward or reverse. When it rotates forward, it can drive the Y-axis support seat 251 to move in a specific direction. When it reverses, it can drive the Y-axis support seat 251 to move in the opposite direction of the specific direction. By driving the Y-axis screw rod 253 forward or reversely by the Y-axis driving motor 252, the Y-axis support seat 251 can be driven to move in the Y-axis direction, thereby realizing the fine adjustment of the position of the gantry boom 1 on the Y-axis.

[0037] In one embodiment, the X-axis fine-tuning assembly 24 includes an X-axis support seat 241, an X-axis drive motor 242 and an X-axis screw rod 243. The X-axis support seat 241 is slidably connected to the Y-axis support seat 251, the X-axis screw rod 243 is threadedly connected to the X-axis support seat 241, and the end of the X-axis screw rod 243 is connected to the output end of the X-axis drive motor 242. The gantry boom 1 is provided on the X-axis support seat 241. Specifically, the X-axis drive motor 242 can rotate forward or reverse. When it rotates forward, it can drive the X-axis support seat 241 to move in a specific direction. When it reverses, it can drive the X-axis support seat 241 to move in the opposite direction of the specific direction. By driving the X-axis drive motor 242 to drive the X-axis screw rod 243 forward or reverse, the X-axis support seat 241 can be driven to move in the X-axis direction, thereby achieving fine adjustment of the position of the gantry boom 1 on the X-axis.

[0038] In one embodiment, the erection drive adjustment assembly 3 includes an active end frame 31, a passive end frame 32, a drive assembly 33, an active end connecting plate 34, a follower shaft 35, a driven end connecting plate 36, an encoder 37 and a locking pin 38. The active end frame 31 and the driven end frame 32 are arranged opposite to each other and are respectively connected to the opposite sides of the erection telescopic assembly 4. The active end frame 31 is provided with a drive assembly 33, the output end of the drive assembly 33 is connected to the active end connecting plate 31, the driven end frame 32 is rotatably connected with an encoder 37, one end of the follower shaft 35 is connected to the output end of the encoder 37, and the other end of the follower shaft 35 is connected to the driven end connecting plate 36. The active end connecting plate 31 and the driven end connecting plate 36 are respectively used to connect with the corresponding connection points of the aircraft body, and the locking pin 38 is used to lock the driven end connecting plate 36 and the driven end frame 32. Specifically, the drive assembly 33 is used as a power source output to drive the aircraft body to flip. In order to adapt to the rotation of the drive assembly 33, a follower shaft 35 that can follow the movement is set on the driven end frame 32, so that the stable flipping of the aircraft body can be achieved. The active end connecting plate 34 is installed on the inner side of the active end frame 31, and the driven end connecting plate 36 is installed on the inner side of the driven end frame 32. The active end connecting plate 34 is connected to the drive assembly 33, and the driven end connecting plate 36 is connected to the follower shaft 35. The active end connecting plate 34 and the driven end connecting plate 36 can be connected to the aircraft or its tooling. Different connection hole positions can adapt to equipment with different centers of gravity. The vertical flip axis of the active end connecting plate 34 and the driven end connecting plate 36 coincides with the vertical flip axis of the aircraft after installation, ensuring that there is no eccentricity during the vertical flipping of the aircraft, and evenly applying load to the entire device to make the vertical flipping smoother. The locking pin 38 is installed on the driven end frame 32, and the device can be locked at a specific position; the encoder 37 is installed on the outside of the driven end frame 32 and is connected to the follower shaft 35, which can provide accurate feedback on the vertical flip angle to facilitate related compensation.

[0039] In one embodiment, the erection drive adjustment assembly 3 further includes a spline adjustment assembly 39, which includes a moving section and a guide section, the guide section is arranged along the Z direction, and the moving section is slidably connected to the guide section. The spline adjustment assembly 39 can be adjusted in distance to a certain extent to adapt to the matching connection between different aircraft or tooling and the test device below it.

[0040] In one embodiment, the driving assembly 33 includes a motor 331, a worm gear reducer 332 and a planetary reducer 333. The motor 331, the worm gear reducer 332 and the planetary reducer 333 are all connected to the driving end frame 31. The output end of the motor 331 is connected to the input end of the worm gear reducer 332. The output end of the worm gear reducer 332 is connected to the input end of the planetary reducer 333. The output end of the planetary reducer 333 is connected to the driving end connecting plate 34. Specifically, the planetary reducer 333 is installed on the outer side of the driving end frame 31 on one side, the worm gear reducer 332 is installed on the planetary reducer 333, and the motor 331 is installed on the worm gear reducer 332. The driving form of the motor 331, the worm gear reducer 332 and the planetary reducer 333 is adopted to meet the use requirements of low speed and high torque. In addition, the worm gear reducer 332 has a self-locking characteristic, which can ensure that the aircraft is fixed at any vertical position of the rotation.

[0041] In one embodiment, the erecting telescopic assembly 4 includes a first telescopic assembly 41 and a second telescopic assembly 42 with the same structure. The first telescopic assembly 41 and the second telescopic assembly 42 are arranged opposite to each other and are respectively connected to the opposite sides of the gantry boom 1. The first telescopic assembly 41 includes a mounting frame 411, a spring telescopic shaft 412, a compression spring 413 and an anti-rotation shaft 414. The mounting frame 411 is connected to the gantry boom 1, the spring telescopic shaft 412 is arranged along the Z direction and is slidably connected to the mounting frame 411, one end of the compression spring 413 is connected to the lower end of the spring telescopic shaft 412, and the other end of the compression spring 413 is connected to the mounting frame 411, the anti-rotation shaft 414 connects the mounting frame 411 and the gantry boom 1, and the anti-rotation shaft 414 is used to prevent the spring telescopic shaft 412 from rotating in the circumferential direction. Specifically, the spring telescopic shaft 412 can realize position adjustment in the vertical direction (Z-axis direction); the compression spring 413 is installed between the spring telescopic shaft 412 and the mounting frame 411, and plays a buffering role during the lifting and lowering of the aircraft, ensuring that the weight of the device will not be fully loaded onto the aircraft; the anti-rotation shaft 414 is respectively connected to both sides of the mounting frame 411 to prevent the spring telescopic shaft 412 from rotating during movement.

[0042] In one embodiment, the gantry boom 1 includes a main crossbeam 11, a first boom 12, a second boom 13 and an electric control cabinet 14. The main crossbeam 11 is arranged along the X direction, the main crossbeam 11 is connected to the suspension assembly 2, one end of the main crossbeam 11 is connected to the first boom 12, the other end of the main crossbeam 11 is connected to the second boom 13, the first boom 12 and the second boom 13 are both arranged along the Z direction, and the electric control cabinet 14 is arranged on the first boom 12 or the second boom 13. Specifically, the first boom 12 and the second boom 13 are respectively installed at the lower parts of the two ends of the main crossbeam 11 to bear the main pulling force of the device; the electric control cabinet 14 is installed in the middle of one side of the first boom 12 or the second boom 13, and is equipped with a series of electric control components, which can be connected to the operating table to facilitate the user to operate the device for vertically flipping the aircraft through the operating table.

[0043] In one embodiment, a crane is also included, a mobile track is provided in the production workshop, the crane is slidably connected to the mobile track, and the hanging assembly 2 is connected to the crane. By driving the crane to move, the aircraft can be transported in the production workshop.

[0044] The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention. Any modifications, equivalent substitutions and improvements made within the spirit and principles of the present invention should be included in the protection scope of the present invention.

Claims

1. A device for vertically flipping an aircraft, characterized in that: include: Gantry type crane; A hanging assembly, connected to the gantry boom, for hanging and lifting the gantry boom; The erection drive adjustment assembly is used to be connected to the corresponding connection point of the aircraft body and drive the aircraft body to rotate along the Z direction to adjust the erection posture of the aircraft body; An erecting and telescopic assembly, one end of which is connected to the erecting drive adjustment assembly, and the other end of which is connected to the gantry boom, is used to buffer the impact of the deadweight of the device on the aircraft body.

2. The device for vertically flipping an aircraft according to claim 1, characterized in that: The hanging assembly includes a hanging point assembly, a sling frame, a weighing sensor, an X-direction fine-tuning assembly and a Y-direction fine-tuning assembly. The Y-direction fine-tuning assembly is arranged in the sling frame, the X-direction fine-tuning assembly is arranged on the Y-direction fine-tuning assembly, the gantry boom is arranged on the X-direction fine-tuning assembly, the X-direction fine-tuning assembly is used to drive the gantry boom to move along the X-direction, the Y-direction fine-tuning assembly is used to drive the gantry boom to move along the Y-direction, the hanging point assembly is connected to the end of the sling frame away from the gantry boom, the hanging point assembly is used to be connected to the hook of the lifting device, and the weighing sensor is arranged between the sling frame and the hanging point assembly.

3. The device for vertically flipping an aircraft according to claim 1, characterized in that: The Y-axis fine-tuning assembly includes a Y-axis support seat, a Y-axis drive motor and a Y-axis lead screw. The Y-axis drive motor is installed and connected to the hanger frame, the Y-axis support seat is slidably connected to the hanger frame, the Y-axis lead screw is threadedly connected to the Y-axis support seat, and the end of the Y-axis lead screw is connected to the output end of the Y-axis drive motor.

4. The device for vertically flipping an aircraft as claimed in claim 3, characterized in that: The X-axis fine-tuning assembly includes an X-axis support seat, an X-axis drive motor and an X-axis lead screw. The X-axis support seat is slidably connected to the Y-axis support seat, the X-axis lead screw is threadedly connected to the X-axis support seat, the end of the X-axis lead screw is connected to the output end of the X-axis drive motor, and the gantry boom is provided on the X-axis support seat.

5. The device for vertically flipping an aircraft according to claim 1, characterized in that: The erection drive adjustment assembly includes an active end frame, a passive end frame, a driving assembly, an active end connecting plate, a driven shaft, a driven end connecting plate, an encoder and a locking pin. The active end frame and the driven end frame are arranged opposite to each other and are respectively connected to opposite sides of the erection telescopic assembly. The active end frame is provided with the driving assembly, the output end of the driving assembly is connected to the active end connecting plate, the encoder is rotatably connected to the passive end frame, one end of the driven shaft is connected to the output end of the encoder, and the other end of the driven shaft is connected to the passive end connecting plate. The active end connecting plate and the passive end connecting plate are respectively used to connect with corresponding connecting points of the aircraft body, and the locking pin is used to lock the passive end connecting plate and the passive end frame.

6. The device for vertically flipping an aircraft according to claim 5, characterized in that: The erection drive adjustment assembly also includes a spline adjustment assembly, and the spline adjustment assembly includes a moving section and a guide section. The guide section is arranged along the Z direction, and the moving section is slidably connected to the guide section.

7. The device for vertically flipping an aircraft according to claim 5, characterized in that: The driving assembly includes a motor, a worm gear reducer and a planetary reducer. The motor, the worm gear reducer and the planetary reducer are all connected to the active end frame, the output end of the motor is connected to the input end of the worm gear reducer, the output end of the worm gear reducer is connected to the input end of the planetary reducer, and the output end of the planetary reducer is connected to the active end connecting plate.

8. The device for vertically flipping an aircraft according to claim 1, characterized in that: The erecting telescopic assembly includes a first telescopic assembly and a second telescopic assembly with the same structure. The first telescopic assembly and the second telescopic assembly are arranged opposite to each other and are respectively connected to opposite sides of the gantry boom. The first telescopic assembly includes a mounting frame, a spring telescopic shaft, a compression spring and an anti-rotation shaft. The mounting frame is connected to the gantry boom, the spring telescopic shaft is arranged along the Z direction and is slidably connected to the mounting frame, one end of the compression spring is connected to the lower end of the spring telescopic shaft, and the other end of the compression spring is connected to the mounting frame. The anti-rotation shaft connects the mounting frame and the gantry boom, and the anti-rotation shaft is used to prevent the spring telescopic shaft from rotating in the circumferential direction.

9. The device for vertically flipping an aircraft according to claim 1, characterized in that: The gantry boom includes a main crossbeam, a first boom, a second boom and an electric control cabinet. The main crossbeam is arranged along the X direction, the main crossbeam is connected to the hanging assembly, one end of the main crossbeam is connected to the first boom, the other end of the main crossbeam is connected to the second boom, the first boom and the second boom are both arranged along the Z direction, and the electric control cabinet is arranged on the first boom or the second boom.

10. The device for vertically flipping an aircraft according to claim 1, characterized in that: It also includes a crane, a movable track is provided in the production workshop, the crane is slidably connected to the movable track, and the hanging assembly is connected to the crane.

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