Aircraft wing combined dismounting device

Abstract

The application discloses an aircraft wing combined dismounting device, which comprises a lifting adjusting base and a U-shaped support arranged on the lifting adjusting base, a driving shaft assembly is arranged on the lower side of the U-shaped support, connecting assemblies for connecting wing rotating shafts are arranged at the two ends of the upper side of the U-shaped support, transmission assemblies are arranged at the two ends of the driving shaft assembly, two groups of the transmission assemblies are connected with two groups of the connecting assemblies one by one and drive the two groups of the connecting assemblies to move synchronously to approach or move away from each other. The application has the advantages of simple structure, high automation degree, and the like, and is favorable for improving the dismounting efficiency and precision.

Description

TECHNICAL FIELD

[0001] The present application relates to aircraft maintenance equipment, in particular to a combined 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 thus 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 and right wing locking device and a traditional knocking method to disassemble 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 out of tolerance, 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 a combined 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] A combined aircraft wing dismounting device, comprising a lifting and adjusting base and a U-shaped support provided on the lifting and adjusting base, a driving shaft assembly is provided on the lower side of the U-shaped support, connecting assemblies for connecting the wing shafts are provided at the two ends of the upper side of the U-shaped support, a transmission assembly is provided at the two ends of the driving shaft assembly, and two sets of transmission assemblies are connected one by one with two sets of connecting assemblies and drive the two sets of connecting assemblies to move synchronously to approach or move away from each other.

[0007] As a further improvement of the above technical solution: the transmission assembly comprises a first bevel gear provided on the driving shaft assembly, a transmission shaft, a worm gear, a gear, and a sliding block provided on the U-shaped support, the second bevel gear is provided on the lower end of the transmission shaft and meshes with the first bevel gear, the worm gear is provided on the upper end of the transmission shaft and meshes with the worm gear, the gear is coaxially arranged with the worm gear, the sliding block is provided with a rack that meshes with the gear, and the connecting assembly is provided on the sliding block.

[0008] As a further improvement of the above technical solution: a sliding rail that cooperates with the sliding block is provided on the U-shaped support.

[0009] As a further improvement of the above technical solution: the sliding rail is provided on both sides of the rack.

[0010] As a further improvement of the above technical solution: the sliding block is provided with a position detection component at both ends.

[0011] As a further improvement of the above technical solution: the lower concave part of the U-shaped support is provided with a flexible anti-collision strip.

[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 a reverse U-shaped bolt, and the reverse U-shaped bolt is located outside the hoop.

[0013] As a further improvement of the above technical solution: the lifting adjusting base comprises a base and a lifting seat located above the base, lifting adjusting assemblies are arranged between both ends of the base and the lifting seat, and supporting legs are hingedly connected to both sides of the base.

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

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

[0016] Compared with the prior art, the advantages of the present application are as follows: the aircraft wing combined dismounting device disclosed by the present application is used by first pushing the entire device from under the radar cover of the aircraft head into the lower end of the wing of the aircraft to be repaired, penetrating the aircraft head at the middle lower concave position of the U-shaped support, adjusting the height of both ends of the U-shaped support by the lifting adjusting base, coordinating the height of the connecting assembly with the wing of the aircraft, connecting the left wing and the right wing of the aircraft by the two connecting assemblies respectively, and since the connecting assemblies of the left and right wings are driven to move synchronously by the driving shaft assembly, the left and right wings can be simultaneously dismounted (moving away from each other), simultaneously assembled (moving close to each other), the two ends are mutually acting force and reaction force, the balance of the dismounting force (installation acting force) is achieved, 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 combined dismounting device of the present application in a use state.

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

[0019] Figure 3 is a perspective structural schematic view of the U-shaped support in the present application.

[0020] Figure 4 isFigure 3 Enlarged view of B in FIG.

[0021] Figure 5 is a front structural schematic view of the transmission assembly in the application.

[0022] Figure 6 is a partial enlarged view of the transmission assembly in the application.

[0023] Figure 7 is a three-dimensional structural schematic view of the outrigger in the application.

[0024] The various reference signs in the drawings represent:

[0025] 11, lifting adjusting base; 111, base; 112, lifting seat; 113, lifting adjusting assembly; 114, outrigger; 115, adjusting hand wheel; 12, U-shaped support; 13, sliding rail; 14, flexible anti-collision strip; 2, driving shaft assembly; 21, worm reducer; 22, driving hand wheel; 3, wing rotating shaft; 31, wing; 4, connecting assembly; 41, mounting seat; 42, clamp; 43, inverted U-shaped bolt; 5, transmission assembly; 51, first bevel gear; 52, transmission shaft; 53, worm gear; 54, gear; 55, sliding block; 56, second bevel gear; 57, worm; 58, rack; 59, position detection component; 61, torque detection component; 62, torque limiting coupling. DETAILED DESCRIPTION

[0026] 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 shown in the drawings 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 device or element 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.

[0027] In addition, the terms "first", "second" are only for description purpose, and cannot be understood as indicating or implying relative importance or implicitly indicating the number of the technical features indicated. 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.

[0028] In this application, unless specifically defined otherwise, the terms "assembly", "connection", "joining", "fixing" and the like are to be construed broadly in accordance with ordinary meanings of the terms, for example, can be fixed connection, can be detachable connection, or integral; can be mechanical connection, or electrical connection; can be direct connection, or indirect connection through intermediate medium; can be internal connection of two elements, or interaction relationship between two elements. For those skilled in the art, the specific meanings of the above terms in this application can be understood according to specific circumstances.

[0029] The application will be further described in detail below in combination with the accompanying drawings and specific embodiments.

[0030] Figures 1 to 7 An embodiment of the aircraft wing combined dismounting device of the application is shown. The aircraft wing combined dismounting device of the embodiment comprises a lifting adjusting base 11 and a U-shaped support 12 arranged on the lifting adjusting base 11. The U-shaped support 12 is provided with a driving shaft assembly 2 at the lower side. The U-shaped support 12 is provided with a connecting assembly 4 for connecting a wing rotating shaft 3 at the upper side of two ends. The driving shaft assembly 2 is provided with a transmission assembly 5 at two ends. Two sets of transmission assemblies 5 are connected with two sets of connecting assemblies 4 one by one and drive the two sets of connecting assemblies 4 to move synchronously to approach or move away from each other.

[0031] In use, the whole device is first pushed from under the radar cover of the aircraft head to be installed at the lower end of the wing 31 of the aircraft to be repaired. The U-shaped support 12 is inserted into the aircraft head at the concave position in the middle. The lifting adjusting base 11 adjusts the height of the two ends of the U-shaped support 12 to make the connecting assembly 4 height coordinated with the wing 31 of the aircraft. The two sets of connecting assemblies 4 are connected with the left wing 31 and the right wing 31 of the aircraft respectively. Since the connecting assemblies 4 of the left and right wings 31 are driven by the driving shaft assembly 2 to move synchronously, the left and right wings 31 can be disassembled (moved away from each other) and assembled (moved close to each other) simultaneously. The two ends are the action force and the reaction force, which balances the dismounting force (installation action force), overcomes the defects of the original knocking method, such as time-consuming, laborious, and damage to parts, and improves the working efficiency, the dismounting precision, and the automation degree.

[0032] Further, in the embodiment, the transmission assembly 5 comprises a first bevel gear 51 arranged on the drive shaft assembly 2, a transmission shaft 52, a worm gear 53, a gear 54 and a sliding block 55 arranged on the U-shaped support 12, the lower end of the transmission shaft 52 is provided with a second bevel gear 56 engaged with the first bevel gear 51, the upper end of the transmission shaft 52 is provided with a worm 57 engaged with the worm gear 53, the gear 54 is coaxially arranged with the worm gear 53, the sliding block 55 is provided with a rack 58 engaged with the gear 54, and the connecting assembly 4 is arranged on the sliding block 55. In operation, the drive shaft assembly 2 drives the first bevel gear 51 to rotate, the first bevel gear 51 drives the transmission shaft 52 to rotate through the second bevel gear 56, the worm 57 at the upper end of the transmission shaft 52 drives the worm gear 53 to rotate, the gear 54 rotates synchronously with the worm gear 53, and in turn drives the rack 58 to move, so that the sliding block 55, the connecting assembly 4 and the wing 31 connected with the connecting assembly 4 move as a whole with the rack 58, thereby achieving the disassembly and assembly of the wing 31. The transmission assembly 5 composed of the bevel gear pair, the worm gear pair and the gear-rack pair has high transmission efficiency, accurate transmission ratio, reliable operation and long service life, and can achieve equidistance, equal speed and stable disassembly and assembly of the wings 31 at both ends.

[0033] Further, in the embodiment, the U-shaped support 12 is provided with a sliding rail 13 matched with the sliding block 55. The sliding rail 13 provides a guiding effect for the movement of the sliding block 55 and reduces the moving resistance, so that the sliding block 55 moves more smoothly and has higher movement precision.

[0034] As a preferred embodiment, the sliding rail 13 is arranged on both sides of the rack 58, which has good symmetry and is beneficial to keep the overall force of the sliding block 55 balanced.

[0035] Further, in the embodiment, the sliding block 55 is provided with a position detection component 59 (such as a position sensor, a travel switch, etc.) at both ends. The position detection component 59 limits the limit position of the sliding block 55, further improving the reliability of the device and avoiding damage.

[0036] Further, in the embodiment, the lower recess of the U-shaped support 12 is provided with a flexible anti-collision strip 14 (such as a hollow rubber strip, a plastic strip, etc.). The flexible anti-collision strip 14 is arranged at the position where the U-shaped support 12 may contact the airplane, which is beneficial to avoid scratching the airplane.

[0037] Further, in the embodiment, 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, 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 on the mounting seat 41, avoid the wing 31 from shaking or deviating during disassembly and assembly, and have simple structure, high reliability and convenient disassembly and assembly.

[0038] Further, in the embodiment, the lifting adjusting base 11 comprises a base 111 and a lifting seat 112 above the base 111, and lifting adjusting assemblies 113 are arranged between the two ends of the base 111 and the lifting seat 112, and supporting legs 114 are hinged to the two sides of the base 111. The height of the two ends of the lifting seat 112 can be adjusted by the lifting adjusting assemblies 113 at the two ends, so as to adjust the height of the two ends of the U-shaped support 12, so that the center of the U-shaped support 12 coincides with the center axis of the airplane, and the connecting assemblies 4 at the two ends are accurately connected with the left and right wing rotating shafts 3. Preferably, the lifting adjusting assemblies 113 adopt a threaded structure, and the lifting of the lifting seat 112 is realized by rotating an adjusting hand wheel 115. In operation, the supporting legs 114 are opened to increase the contact area of the base 111 with the ground and improve the stability of the base 111; after disassembly or assembly is completed, the supporting legs 114 are folded to reduce the occupied space, and the structure is simple and reasonable.

[0039] Further, in the embodiment, the driving shaft assembly 2 is provided with a worm reducer 21 at one end, and a torque detection component 61 is arranged between the worm reducer 21 and the driving shaft assembly 2. Preferably, the torque detection component 61 is provided with a display screen or is 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 driving hand wheel 22 is stopped in time when the torque reaches an alarm value. The worm reducer 21 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, which is beneficial to the disassembly and assembly of the wing 31; the torque detection component 61 detects the torque of the output shaft of the worm reducer 21 in real time, which plays a protection role and avoids damage to the wing 31 due to excessive force. Preferably, the driving hand wheel 22 can be arranged on the input shaft of the worm reducer 21, so as to facilitate manual rotation of the input shaft of the worm reducer 21. Manual driving of the worm reducer 21 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 airplane, and also avoids damage to the expensive airplane due to faults of the motor or the hydraulic source motor, so that the structure is more reliable in operation, has high working stability and good practicability.

[0040] Further, in the embodiment, a torque limiting coupling 62 is arranged between the torque detection component 61 and the worm reducer 21. The torque limiting coupling 62 is used to limit the torque within a certain range, and when the torque exceeds a set value, the two parts of the torque limiting coupling 62 are separated from each other, so that the torque cannot be continuously transmitted, which plays a protection role and avoids damage to the wing 31 due to excessive force.

[0041] Preferably, threaded fasteners are used to connect the parts of the device, which has good reliability, is convenient for disassembly and transportation, can be quickly assembled when used, and solves the problem of high-voltage power supply in the field.

[0042] Although the present application has been described in connection with the preferred embodiment thereof with reference to the drawings, it is not to be limited to the details described therein but can be modified in various ways which will be apparent to one of ordinary skill in the art without departing from the scope of the present application as defined by the appended claims.

Claims

1. An aircraft wing joint disassembly device, characterized by: The application relates to a combined dismounting device for airplane wings, which comprises a lifting adjusting base (11) and a U-shaped support (12) arranged on the lifting adjusting base (11), a driving shaft assembly (2) is arranged on the lower side of the U-shaped support (12), connecting assemblies (4) for connecting wing rotating shafts (3) are arranged at the two ends of the upper side of the U-shaped support (12), driving shaft assemblies (2) are arranged at the two ends of the driving shaft assembly (2), the driving shaft assembly (2) and the two ends of the driving shaft assembly (2) are in U-shaped structure, so that the whole airplane wing combined dismounting device can be pushed from the lower side of the radar cover of the airplane head, two groups of the driving shaft assemblies (2) and the two groups of the connecting assemblies (4) are connected one by one and drive the two groups of the connecting assemblies (4) to move synchronously to approach or move away from each other, the driving shaft assembly (2) comprises a first bevel gear (51) arranged on the driving shaft assembly (2), a transmission shaft (52), a worm gear (53), a gear (54) and a sliding block (55) arranged on the U-shaped support (12), the lower end of the transmission shaft (52) is provided with a second bevel gear (56) meshing with the first bevel gear (51), the upper end of the transmission shaft (52) is provided with a worm (57) meshing with the worm gear (53), the gear (54) is coaxially arranged with the worm gear (53), the sliding block (55) is provided with a rack (58) meshing with the gear (54), the connecting assembly (4) is arranged on the sliding block (55), the connecting assembly (4) comprises a mounting seat (41) connected with the driving shaft 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 lifting adjusting base (11) comprises a base (111) and a lifting seat (112) located above the base (111), lifting adjusting assemblies (113) are arranged between the two ends of the base (111) and the lifting seat (112), and supporting legs (114) are hingedly arranged on the two sides of the base (111).

2. The aircraft wing de- / assembling device according to claim 1, characterized in that A sliding rail (13) is arranged on the U-shaped support (12) and matched with the sliding block (55).

3. The aircraft wing de- / assembling device according to claim 2, characterized in that The sliding rail (13) is arranged on the two sides of the rack (58).

4. The aircraft wing de- / assembling device according to claim 1, characterized in that Position detection components (59) are arranged at the two ends of the sliding block (55).

5. The aircraft wing de- / assembling device according to claim 1, characterized in that Flexible anti-collision strips (14) are arranged in the concave part of the U-shaped support (12).

6. The aircraft wing de- / assembling device according to any one of claims 1 to 5, characterized in that: A worm reducer (21) is arranged at one end of the driving shaft assembly (2), and a torque detection component (61) is arranged between the worm reducer (21) and the driving shaft assembly (2).

7. The aircraft wing de- / assembling device according to claim 6, characterized in that A torque limiting shaft coupling (62) is arranged between the torque detection component (61) and the worm reducer (21).

Images