An aircraft wing disassembly device

Abstract

An aircraft wing dismounting device comprises a frame, a driving shaft and two groups of connecting assemblies for connecting wing rotating shafts, the two groups of connecting assemblies are arranged on one side of the driving shaft, the driving shaft is provided with transmission assemblies at both ends which move synchronously to approach or move away from each other, the two groups of transmission assemblies are connected with the two groups of connecting assemblies one by one, the height of the driving shaft and the transmission assemblies is less than the height of the connecting assemblies. In use, the driving shaft passes through the process hole on the side of the wing, the two groups of connecting assemblies are connected with the left and right wings respectively, the height of the driving shaft and the transmission assemblies is less than the height of the connecting assemblies, so as to avoid interference with the wing, since the transmission assemblies of the left and right wings are driven by the same driving shaft to realize synchronous movement, the left and right wings can be dismounted and assembled simultaneously, the two ends are action force and reaction force, the balance of dismounting force (mounting action force) is realized, the defects of the original knocking method such as time-consuming, laborious and damage to parts are overcome, the work efficiency is higher, and the dismounting precision is better.

Description

TECHNICAL FIELD

[0001] The present application relates to equipment for aircraft maintenance, in particular to an aircraft wing dismounting device. BACKGROUND

[0002] During the overhaul of an aircraft, the aircraft wing needs to be disassembled to perform non-destructive testing on the internal structures such as the wing shaft and bearing seat. In particular, some aircraft need to perform large load actions such as rolling, pitching, and rapid turning, which generate large alternating stresses on the aircraft wing, and therefore the aircraft wing needs to be disassembled periodically for non-destructive testing.

[0003] Since the aircraft wing is usually designed as a cantilever beam structure, the existing aircraft wing dismounting is performed by using a left wing locking device and a right wing locking device, and the traditional knocking method is used to disassemble the wing one by one. This dismounting method has several defects: 1) low work efficiency, the dismounting of the wing takes several days, which is not conducive to the rapid maintenance of the aircraft; 2) the knocking method of disassembly easily leads to the scrapping of parts due to over-dimensioning, which also reduces the production efficiency. SUMMARY

[0004] The technical problem to be solved by the present application is to overcome the shortcomings of the prior art and provide an aircraft wing dismounting device which has a simple structure, high automation, and is conducive to improving the dismounting efficiency and precision.

[0005] To solve the above technical problems, the present application adopts the following technical solutions:

[0006] An aircraft wing dismounting device comprises a rack, a driving shaft and two groups of connecting assemblies for connecting the wing shaft are arranged on the rack, the two groups of connecting assemblies are arranged on one side of the driving shaft, the driving shaft is provided with transmission assemblies at both ends which move synchronously to approach or move away from each other, the two groups of transmission assemblies are connected to the two groups of connecting assemblies one by one, and the height of the driving shaft and the transmission assemblies is less than the height of the connecting assemblies.

[0007] As a further improvement of the above technical solutions, the transmission assembly comprises a first sliding block, a second sliding block and a coaxial gear set, the first sliding block is connected to the driving shaft and is engaged with the lower gear of the coaxial gear set through a first rack, the height of the second sliding block is greater than that of the first sliding block and the second sliding block is engaged with the upper gear of the coaxial gear set through a second rack, the coaxial gear set is located between the first rack and the second rack, and the connecting assembly is arranged on the second sliding block.

[0008] As a further improvement of the above technical solutions, the rack is provided with a first sliding rail matched with the first sliding block and a second sliding rail matched with the second sliding block.

[0009] As a further improvement of the above technical solution: the first slider and the second slider are both provided with position detection components.

[0010] As a further improvement of the above technical solution: the rack comprises a box surrounded by multiple plates, and the first slider, the second slider and the coaxial gear set are arranged on the box.

[0011] As a further improvement of the above technical solution: two coaxial gear sets are arranged between the first rack and the second rack.

[0012] As a further improvement of the above technical solution: the connecting assembly comprises a mounting seat connected with the transmission assembly, the mounting seat is provided with a hoop and an inverted U-shaped bolt, and the inverted U-shaped bolt is located outside the hoop.

[0013] As a further improvement of the above technical solution: the drive shaft is provided with threaded segments at both ends, the pitch of the threaded segments is equal and the rotation directions are opposite, the transmission assembly comprises a nut arranged on the threaded segments, and a movement guide assembly is arranged between the nut and the rack.

[0014] As a further improvement of the above technical solution: the drive shaft is provided with a turbine reducer at one end, and a torque detection component is arranged between the turbine reducer and the drive shaft.

[0015] As a further improvement of the above technical solution: a torque limiting coupling is arranged between the torque detection component and the drive shaft.

[0016] Compared with the prior art, the aircraft wing dismounting device has the advantages that: when in use, the whole device is installed under the wing of the aircraft to be repaired, the drive shaft passes through the process hole on the side of the wing, two connecting assemblies are connected with the left wing and the right wing of the aircraft respectively, the height of the drive shaft and the transmission assembly is less than the height of the connecting assembly, so that interference with the wing is avoided, the transmission assemblies of the left and right wings are driven by the same drive shaft to realize synchronous movement, the left and right wings can be dismounted simultaneously (the left and right wings are far away from each other), assembled simultaneously (the left and right wings are close to each other), the two ends are action force and reaction force, the balance of the dismounting force (mounting action force) is realized, the defects of the original knocking method, such as time-consuming, laborious and damage to parts, are overcome, the work efficiency is improved, the dismounting precision is better, and the degree of automation is high. BRIEF DESCRIPTION OF DRAWINGS

[0017] Figure 1 is a perspective structural schematic view of the aircraft wing dismounting device.

[0018] Figure 2 is Figure 1 an enlarged view of A of

[0019] Figure 3 is a schematic diagram of the structure of the application in use.

[0020] Figure 4 is a schematic diagram of the structure of the application in use.

[0021] In the figure, the numbers represent: 1, frame; 11, first slide rail; 12, second slide rail; 13, box body; 2, drive shaft; 21, threaded section; 22, movement guide assembly; 23, turbine reducer; 24, hand wheel; 3, wing rotating shaft; 31, wing; 4, connecting assembly; 41, mounting seat; 42, hoop; 43, inverted U-shaped bolt; 5, transmission assembly; 51, first sliding block; 52, second sliding block; 53, lower gear; 54, upper gear; 55, first rack; 56, second rack; 57, position detection component; 58, nut; 59, connecting block; 61, torque detection component; 62, torque limiting coupling. DETAILED DESCRIPTION

[0022] In the description of the present application, it should be understood that the terms "length", "width", "upper", "lower", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer" and the like indicate the orientation or positional relationship based on the orientation or positional relationship shown in the drawings, and are only for the convenience of describing the present application and simplifying the description, and therefore cannot be understood as indicating or implying that the devices or elements referred to must have a particular orientation, be constructed and operated in a particular orientation, and therefore cannot be understood as limiting the present application.

[0023] In addition, the terms "first", "second" are only for descriptive purposes and cannot be understood as indicating or implying relative importance or implicitly indicating the number of the technical features referred to. Therefore, the features defined with "first", "second" can explicitly or implicitly include one or more of the features. In the description of the present application, the meaning of "multiple" is two or more, unless otherwise specifically limited.

[0024] In the present application, unless otherwise specifically defined and limited, the terms "assembly", "connection", "connection", "fixing" and the like should be understood broadly, for example, it can be fixed connection, or detachable connection, or integral; it can be mechanical connection, or electrical connection; it can be directly connected, or indirectly connected through intermediate medium; it can be the internal communication of two elements or the interaction relationship between two elements. For those skilled in the art, the specific meaning of the above terms in the present application can be understood according to the specific circumstances.

[0025] The present application will be further described in detail below in combination with the drawings and specific embodiments of the present application.

[0026] Figures 1 to 4An embodiment of the aircraft wing dismounting device is shown. The aircraft wing dismounting device comprises a frame 1, the frame 1 is provided with a driving shaft 2 and two groups of connecting assemblies 4 for connecting wing rotating shafts 3, the two groups of connecting assemblies 4 are arranged on one side of the driving shaft 2, the driving shaft 2 is provided with transmission assemblies 5 at both ends which synchronously move to approach or move away from each other, the two groups of transmission assemblies 5 are connected with the two groups of connecting assemblies 4 one by one, the height of the driving shaft 2 and the transmission assemblies 5 is less than the height of the connecting assemblies 4. Preferably, the frame 1 is a split structure and is arranged at both ends of the driving shaft 2, the split of the frame 1 is an L-shaped support and is arranged oppositely, a diagonal brace is connected between the vertical part and the horizontal part of the L-shaped support, a box body 13 at both ends is installed on the vertical part of the L-shaped support, a triangular support is arranged on the outside of the vertical part of one L-shaped support, a turbine speed reducer 23 and a torque detection component 61 are arranged on the triangular support, the overall structure is simple, reliable, high in strength, good in stability and high in carrying capacity.

[0027] The aircraft wing dismounting device is used, the whole device is first installed under the wings 31 of the aircraft to be repaired, the driving shaft 2 passes through the process hole on the side of the wings 31, the two groups of connecting assemblies 4 are connected with the left wing 31 and the right wing 31 of the aircraft respectively, the height of the driving shaft 2 and the transmission assemblies 5 is less than the height of the connecting assemblies 4, so as to avoid interference with the wings 31, the structure is simple and reasonable, the transmission assemblies 5 of the left and right wings 31 are synchronously moved by the same driving shaft 2, so that the left and right wings 31 can be simultaneously dismounted (the left and right wings 31 move away from each other), simultaneously assembled (the left and right wings 31 approach each other), the two ends are action force and reaction force, the balance of the dismounting force (mounting action force) is realized, the defects of the original knocking method, such as time-consuming, laborious and damage to parts, are overcome, the work efficiency is improved, the dismounting precision is better, and the degree of automation is high.

[0028] Further, in the embodiment, the transmission assembly 5 comprises a first sliding block 51, a second sliding block 52 and a coaxial gear set. The first sliding block 51 is connected with the driving shaft 2 and is engaged with a lower gear 53 of the coaxial gear set through a first rack 55. The height of the second sliding block 52 is greater than that of the first sliding block 51 and the second sliding block 52 is engaged with an upper gear 54 of the coaxial gear set through a second rack 56. The coaxial gear set is located between the first rack 55 and the second rack 56. The connecting assembly 4 is arranged on the second sliding block 52. Under the action of the driving shaft 2, the first sliding block 51 moves. The first sliding block 51 further drives the coaxial gear set to rotate through the lower gear 53. The upper gear 54 of the coaxial gear set drives the second sliding block 52 to move. The moving direction of the second sliding block 52 is opposite to that of the first sliding block 51. The connecting assembly 4 and the wing shaft 3 and the wing 31 move with the second sliding block 52. The gear and rack transmission has high transmission efficiency, accurate transmission ratio, reliable work and long service life. The two wings 31 can be disassembled and assembled at equal intervals and at equal speed and stably. Compared with the first sliding block 51 directly connected with the connecting assembly 4, since the moving direction of the second sliding block 52 is opposite to that of the first sliding block 51, the stroke can be amplified (when the specifications of the upper gear 54 and the lower gear 53 are the same, the moving speed of the second sliding block 52 is equal to that of the first sliding block 51, so the stroke is amplified by two times). The time required for disassembling and assembling the wing 31 can be further shortened and the production efficiency can be improved.

[0029] As a preferred embodiment, the rack 1 is provided with a first sliding rail 11 matched with the first sliding block 51 and a second sliding rail 12 matched with the second sliding block 52. The first sliding rail 11 and the second sliding rail 12 provide a guiding effect for the movement of the first sliding block 51 and the second sliding block 52 and reduce the moving resistance, so that the first sliding block 51 and the second sliding block 52 move more stably and smoothly and have higher motion accuracy.

[0030] As a preferred embodiment, the first sliding block 51 and the second sliding block 52 are both provided with a position detection component 57 (such as a position sensor or a travel switch light). The position detection component 57 limits the limit position of the first sliding block 51 and the second sliding block 52, further improves the reliability of the device and avoids damage.

[0031] Further, in the embodiment, the rack 1 comprises a box body 13 enclosed by a plurality of plate members. The first sliding block 51, the second sliding block 52 and the coaxial gear set are arranged on the box body 13. The box body 13 enclosed by the plurality of plate members has high strength, good rigidity and strong carrying capacity, so as to bear the weight of the wing 31 and facilitate the installation of the first sliding rail 11, the second sliding rail 12 and the coaxial gear set. Preferably, except the upper surface of the box body 13 for installing the first sliding block 51, the second sliding block 52 and the coaxial gear set, the other surfaces are hollow structures, which is beneficial to reduce the self-weight.

[0032] As a preferred embodiment, two coaxial gear sets are arranged between the first rack 55 and the second rack 56. The two coaxial gear sets are arranged to better transmit power between the first rack 55 and the second rack 56, prevent the first rack 55 and the second rack 56 from deflecting when a single point is stressed, and have a simple and effective structure.

[0033] Further, in the embodiment, the connecting assembly 4 includes a mounting seat 41 connected with the transmission assembly 5, the mounting seat 41 is provided with a hoop 42 and a reverse U-shaped bolt 43, and the reverse U-shaped bolt 43 is located outside the hoop 42 (i.e., the hoop 42 is located between the reverse U-shaped bolts 43 at both ends). The reverse U-shaped bolt 43 and the hoop 42 cooperate to effectively fix the wing 31 to the mounting seat 41, avoid shaking and deviation of the wing 31 during disassembly and assembly, and have a simple and reliable structure and convenient disassembly and assembly.

[0034] Further, in the embodiment, the driving shaft 2 is provided with threaded segments 21 at both ends, the pitches of the threaded segments 21 are equal, and the directions of rotation are opposite. The transmission assembly 5 includes nuts 58 arranged on the threaded segments 21, and a moving guide assembly 22 (such as a slide rail and a slide block, or a guide column and a guide sleeve, etc.) is arranged between the nuts 58 and the rack 1. Since the pitches of the threaded segments 21 at both ends are equal and the directions of rotation are opposite, when the driving shaft 2 is rotated, the nuts 58 at both ends can approach or move away from each other at equal speeds, and the left and right wings 31 move equal distances to realize simultaneous disassembly and synchronous assembly of the left and right wings 31. The driving shaft 2 at both ends is a force and a counterforce, which balances the disassembly force (assembly force). The moving guide assembly 22 provides a guide function for the nuts 58 to ensure high movement accuracy of the nuts 58 and avoid rotation. The threaded engagement has high transmission efficiency, accurate transmission ratio, reliable work, and long service life, and can realize equal distance, equal speed, and stable disassembly and assembly at both ends. Preferably, the nut 58 has a square structure, and the upper surface and one side surface are fixedly connected with the first slide block 51 through a connecting block 59, which has good reliability and facilitates transmission of driving force.

[0035] Further, in the embodiment, the driving shaft 2 is provided with a turbine reducer 23 at one end, and a torque detection component 61 is arranged between the turbine reducer 23 and the driving shaft 2. Preferably, the torque detection component 61 is provided with a display screen or externally connected with a display, a display panel or the like, so as to facilitate the operator to monitor the torque value in real time, and the hand wheel 24 is stopped in time when the torque reaches the warning value. The turbine reducer 23 is used to realize speed reduction and torque increase, so that the connecting assembly 4 and the wing 31 can obtain sufficient translation driving force, and the disassembly and assembly of the wing 31 are facilitated. The torque detection component 61 is used to detect the torque of the output shaft of the turbine reducer 23 in real time, so as to play a protection role and avoid damage of the wing 31 due to excessive force. Preferably, the hand wheel 24 is arranged on the input shaft of the turbine reducer 23, so as to facilitate manual driving of the input shaft of the turbine reducer 23. The manual driving of the turbine reducer 23 simplifies the structure of the device, adapts to the needs of field repair in time, avoids the influence of high-voltage electricity and high-pressure oil pumps on the electronic equipment of the aircraft, and avoids damage of the expensive aircraft due to the failure of the motor or the hydraulic source motor, so that the structure is more reliable in operation, high in working stability and good in practicability.

[0036] Further, in the embodiment, a torque limiting coupling 62 is arranged between the torque detection component 61 and the driving shaft 2. The torque limiting coupling 62 is used to limit the torque within a certain range, and the two parts of the torque limiting coupling 62 are separated from each other when the torque exceeds the set value, so that the torque cannot be continuously transmitted, and a protection role is played to avoid damage of the wing 31 due to excessive force.

[0037] Preferably, threaded fasteners are used to connect the parts of the device, the reliability is good, the device can be quickly assembled into a shape during use, and the problem of high-voltage power supply in the field is solved.

[0038] Although the present application has been disclosed with reference to the preferred embodiments, it is not intended to limit the present application. Any person skilled in the art can make many possible changes and modifications to the technical solutions disclosed above, or modify equivalent embodiments with equivalent changes, without departing from the scope of the technical solutions of the present application. Therefore, any simple modification, equivalent change and modification made to the above embodiments according to the technical essence of the present application shall fall within the scope of protection of the technical solutions of the present application.

Claims

1. An aircraft wing dismounting device comprising a frame (1), characterized in that: The rack (1) is provided with a driving shaft (2) and two groups of connecting assemblies (4) for connecting wing rotating shafts (3), the driving shaft (2) is used for penetrating from the wing (31) side process hole, two groups of the connecting assemblies (4) are arranged on one side of the driving shaft (2), the driving shaft (2) is provided with synchronous moving transmission assemblies (5) at both ends, the two groups of transmission assemblies (5) are connected with the two groups of connecting assemblies (4) one by one, the height of the driving shaft (2) and the transmission assembly (5) is less than the height of the connecting assembly (4), so as to avoid interference with the wing (31), the transmission assembly (5) comprises a first sliding block (51), a second sliding block (52) and a coaxial gear set, the first sliding block (51) is connected with the driving shaft (2) and is engaged with the lower gear (53) of the coaxial gear set through the first rack (55), the height of the second sliding block (52) is greater than that of the first sliding block (51) and is engaged with the upper gear (54) of the coaxial gear set through the second rack (56), the coaxial gear set is located between the first rack (55) and the second rack (56), the connecting assembly (4) is arranged on the second sliding block (52), the connecting assembly (4) comprises a mounting seat (41) connected with the transmission assembly (5), the mounting seat (41) is provided with a hoop (42) and a reverse U-shaped bolt (43), the reverse U-shaped bolt (43) is located outside the hoop (42), the driving shaft (2) is provided with threaded sections (21) at both ends, the pitches of the threaded sections (21) are equal and the rotation directions are opposite, the transmission assembly (5) comprises a nut (58) arranged on the threaded section (21), and a moving guide assembly (22) is arranged between the nut (58) and the rack (1).

2. An aircraft wing de-rigging apparatus as claimed in claim 1, wherein: The rack (1) is provided with a first sliding rail (11) matched with the first sliding block (51) and a second sliding rail (12) matched with the second sliding block (52).

3. The aircraft wing deinstallation device of claim 1, wherein: The first sliding block (51) and the second sliding block (52) are both provided with position detection components (57) at both ends.

4. The aircraft wing deinstallation device of claim 1, wherein: The rack (1) comprises a box body (13) enclosed by a plurality of plate pieces, and the first sliding block (51), the second sliding block (52) and the coaxial gear set are arranged on the box body (13).

5. The aircraft wing deinstallation device of claim 1, wherein: Two groups of the coaxial gear sets are arranged between the first rack (55) and the second rack (56).

6. An aircraft wing de-rigging apparatus as claimed in any one of claims 1 to 5, wherein: One end of the driving shaft (2) is provided with a turbine reducer (23), and a torque detection component (61) is arranged between the turbine reducer (23) and the driving shaft (2).

7. The aircraft wing deinstallation device of claim 6, wherein: A torque limiting coupling (62) is arranged between the torque detection component (61) and the driving shaft (2).

Images