A method and system for improving aircraft wing assembly efficiency

Abstract

The application relates to the field of airplane assembly, in particular to an assembly system for improving airplane wing assembly efficiency, which comprises left-end mobile support frames and right-end mobile support frames for supporting wings on both sides of a fuselage, the left-end mobile support frames and the right-end mobile support frames both comprise main frame bodies, lifting boxes are installed on the two sides of the top of the main frame bodies, support plates are installed on the movable ends of the lifting boxes, the support plates on the left-end mobile support frames and the right-end mobile support frames are used for supporting wings, a group of fuselage contact pulleys are installed on the opposite side walls of the left-end mobile support frames and the right-end mobile support frames, each group comprises two fuselage contact pulleys with the same height; the mobile support frames can be connected, the left-end mobile support frames and the right-end mobile support frames can be connected while the unilateral wing installation is facilitated, then the wings on both sides of the fuselage can be simultaneously installed, and the assembly efficiency is improved.

Description

Technical Field

[0001] The present invention relates to the technical field of aircraft assembly, and in particular to a method and system for improving aircraft wing assembly efficiency. Background Art

[0002] Application number CN201820992658.9 discloses an auxiliary tool for assembling an aircraft wing, comprising a support body, a lifting device movably mounted on the support body and connected to the wing, and a jack mounted on the support body and used to lift the lifting device. The auxiliary tool disclosed in this application, through the coordination of the lifting device and the jack, facilitates the assembly of the wing onto the aircraft fuselage. It features a simple structure, ease of use, low cost, and ease of maintenance, thereby improving the efficiency of wing-to-fuselage assembly.

[0003] Currently, aircraft wing assembly uses separate mounting frames to install the aircraft wings on both sides. Since the mounting frames are separate, only one wing can be installed, resulting in low installation efficiency. At the same time, after the wing on one side is installed, the weight of the fuselage is unbalanced, requiring the fuselage to be fixed and have strong stability to resist the roll force. To this end, the present invention provides a method and system for improving the efficiency of aircraft wing assembly. Summary of the Invention

[0004] In view of the above problems existing in the prior art, the present invention provides a method and system for improving the assembly efficiency of aircraft wings.

[0005] The basic scheme of the present invention is: an assembly system for improving the assembly efficiency of aircraft wings, comprising a left-end movable support bracket and a right-end movable support bracket located on both sides of the fuselage for supporting the wings, the left-end movable support bracket and the right-end movable support bracket both comprising a main frame, lifting boxes are installed on both sides of the top of the main frame, and supporting plates are installed on the movable ends of the lifting boxes, and the supporting plates on the left-end movable support bracket and the right-end movable support bracket on both sides are used for supporting the wings, and a group of fuselage contact pulleys are installed on the opposite side walls of the left-end movable support bracket and the right-end movable support bracket, each group includes two fuselage contact pulleys of the same height, and the axes of the fuselage contact pulleys have a certain angle with the horizontal line, and connecting structures for connection are installed on the opposite side walls of the left-end movable support bracket and the right-end movable support bracket.

[0006] Preferably, the connecting structure includes an outer sleeve, an inner sleeve, a connecting part, an arc-shaped connecting piece and a connecting rod. The outer sleeve and the connecting rod are installed oppositely at the bottom of the left-end movable support bracket and the right-end movable support bracket. The end of the connecting rod is installed with an arc-shaped connecting piece with a notch. The inner side of the outer sleeve is inserted with an inner sleeve that moves along its axis, and the end of the inner sleeve is a connecting part that cooperates with the arc-shaped connecting piece.

[0007] Preferably, the outer side of the inner sleeve is provided with axially arranged springs, the first end of the spring is fixedly connected with the inner sleeve, and the other end of the spring is fixedly connected with the inner wall of the outer sleeve.

[0008] Preferably, a cut is arranged on the bottom end of the connecting part in the opposite inclined direction of the connecting point of the inner sleeve, and the connecting part is connected with the connecting part through the cut to realize the mounting and dismounting of the connecting part and the arc-shaped connecting piece.

[0009] Preferably, a slide is arranged on the left end moving support frame and the right end moving support frame, and a mechanical arm structure moving along the slide is arranged on the slide, and the mechanical arm structure is used for assembling the wing.

[0010] Preferably, a slide is arranged on the left end moving support frame and the right end moving support frame, and a mechanical arm structure moving along the slide is arranged on the slide, and the mechanical arm structure is used for assembling the wing.

[0011] Preferably, the angle between the axis of the fuselage contact pulley and the horizontal line is 30-60 degrees.

[0012] Preferably, a slide is arranged on the left end moving support frame and the right end moving support frame, and a mechanical arm structure moving along the slide is arranged on the slide, and the mechanical arm structure is used for assembling the wing.

[0013] Preferably, a slide is arranged on the left end moving support frame and the right end moving support frame, and a mechanical arm structure moving along the slide is arranged on the slide, and the mechanical arm structure is used for assembling the wing.

[0014] A. The wing is hoisted to the supporting plate on the left end moving support frame and the right end moving support frame, the wing is supported through the supporting plate, and the connecting end of the wing is directed towards the fuselage;

[0015] B. The left end moving support frame and the right end moving support frame are moved to the nose of the fuselage, the left end moving support frame and the right end moving support frame are rotated, the cut of the connecting part on the left end moving support frame and the right end moving support frame corresponds to the notch of the arc-shaped connecting piece, the connecting part enters the inner side of the arc-shaped connecting piece, the left end moving support frame and the right end moving support frame are rotated to be parallel to each other, and the fuselage contact pulleys on the left end moving support frame and the right end moving support frame are attached to the surface of the fuselage;

[0016] C. The arc-shaped curve of the nose is used to push the left end moving support frame and the right end moving support frame to move towards the tail, during which the width of the fuselage is continuously increased to compress the spring and move the inner sleeve to the outside, the total width of the left end moving support frame and the right end moving support frame is increased, and the left end moving support frame and the right end moving support frame are moved to the wing installation position;

[0017] D. The mechanical arm structure moves along the slide to assemble the wing parts, and after the assembly of the single-side wing is completed, the mechanical arm structure is used to synchronously install and fix the two-side wings to the fuselage.

[0018] The working principle and advantages of the present application are as follows:

[0019] The left end moving support bracket and the right end moving support bracket can be connected, which facilitates the installation of the single side wing, and the connection of the left end moving support bracket and the right end moving support bracket is realized, thereby facilitating the synchronous installation of the wings on both sides of the fuselage, improving the assembly efficiency, and the structure is simple, and the application is suitable for wide promotion.

[0020] When the connection structure is connected, the connection part is matched with the arc-shaped connecting piece, and the fuselage contact pulley contacts the side wall of the corresponding position of the fuselage, so that both sides are three-point fixed, the convenience of connection is ensured, the installation of the wing is facilitated, and the practicability is further improved.

[0021] By additionally arranging the elastic member, different widths of fuselages can be conveniently adapted, and the fuselages of different widths are correspondingly matched, thereby facilitating the installation in the later period. DETAILED DESCRIPTION

[0022] Fig. 1 It is a structural schematic diagram of the application;

[0023] Fig. 2 It is an enlarged structural schematic diagram of the A part of the application;

[0024] Fig. 3 It is an enlarged structural schematic diagram of the B part of the application;

[0025] Fig. 4 It is a structural diagram of the outer sleeve tube of the application;

[0026] Fig. 5 It is a structural diagram of the outer sleeve tube of the application;

[0027] The reference signs involved in the drawings are: 1, left end moving support bracket; 101, support plate; 102, lifting box; 103, main frame body; 104, pulley; 105, slide; 106, sliding block; 2, right end moving support bracket; 3, connection structure; 301, outer sleeve tube; 302, inner tube sleeve; 3021, spring; 303, connection part; 3031, notch; 304, arc-shaped connecting piece; 305, connecting rod; 4, mechanical arm structure; 5, fuselage contact pulley. DETAILED DESCRIPTION

[0028] The following will be further described in detail through specific embodiments:

[0029] As Figs. 1 to 5As shown, an assembly system for improving the assembly efficiency of an aircraft wing, characterized in that: a left end moving support frame 1 and a right end moving support frame 2 are arranged on both sides of the fuselage to support the wing, the left end moving support frame 1 and the right end moving support frame 2 each include a main frame body 103, a slide 105 is installed on the left end moving support frame 1 and the right end moving support frame 2, a mechanical arm structure 4 is installed on the slide 105 to move along the slide 105, the mechanical arm structure 4 is used for assembling the wing, and a pulley 104 is installed at the bottom of the main frame body 103 to facilitate movement.

[0030] A lifting box 102 is installed on both sides of the top of the main frame body 103, a support plate 101 is installed on the movable end of the lifting box 102, the support plate 101 on the left end moving support frame 1 and the right end moving support frame 2 is used for supporting the wing, a group of fuselage contact pulleys 5 are installed on the opposite side walls of the left end moving support frame 1 and the right end moving support frame 2, each group includes two fuselage contact pulleys 5 of the same height, the axis of the fuselage contact pulley 5 has a certain angle with the horizontal line, and the opposite side walls of the left end moving support frame 1 and the right end moving support frame 2 are provided with a connecting structure 3 for connection, the left end moving support frame 1 and the right end moving support frame 2 are connected, which can realize the convenient single-wing installation, and the connection of the left end moving support frame 1 and the right end moving support frame 2 can realize the synchronous installation of the wings on both sides of the fuselage, improve the assembly efficiency, and the structure is simple, suitable for wide promotion.

[0031] The connecting structure 3 includes an outer sleeve 301, an inner sleeve 302, a connecting part 303, an arc-shaped connecting piece 304, and a connecting rod 305, the outer sleeve 301 and the connecting rod 305 are oppositely installed at the bottom of the left end moving support frame 1 and the right end moving support frame 2, the end of the connecting rod 305 is provided with the arc-shaped connecting piece 304 with a notch, the inner side of the outer sleeve 301 is provided with the inner sleeve 302 moving along the axis thereof, the end of the inner sleeve 302 is provided with the connecting part 303 matched with the arc-shaped connecting piece 304, and a notch 3031 is formed in the axial direction at the opposite inclined position of the connecting point of the bottom end of the connecting part 303 and the inner sleeve 302, and the connecting part 303 is connected with the arc-shaped connecting piece 304 by rotating through the notch 3031.

[0032] Specifically, the outer side of the inner sleeve 302 is provided with axially arranged springs 3021, one end of the spring 3021 is fixedly connected with the inner sleeve 302, and the other end of the spring 3021 is fixedly connected with the inner wall of the outer sleeve 301.

[0033] Specifically, a sliding block 106 moving along the slide 105 is installed on the slide 105, and the mechanical arm structure 4 is installed on the sliding block 106.

[0034] Specifically, the angle between the axis of the fuselage contact pulley 5 and the horizontal line is 45 degrees.

[0035] The embodiment also provides an assembly method for improving the assembly efficiency of an aircraft wing, comprising the following steps:

[0036] S1. Hoisting the wing to the supporting plate 101 of the left end moving support frame 1 and the right end moving support frame 2, supporting the wing through the supporting plate 101, and connecting the end of the wing to the fuselage;

[0037] S2. Moving the left end moving support frame 1 and the right end moving support frame 2 to the nose of the fuselage, rotating the left end moving support frame 1 and the right end moving support frame 2 so that the cutout 3031 of the connecting part 303 of the left end moving support frame 1 and the right end moving support frame 2 corresponds to the notch of the arc-shaped connecting piece 304, realizing that the connecting part 303 enters the inner side of the arc-shaped connecting piece 304, and rotating the left end moving support frame 1 and the right end moving support frame 2 to make them parallel to each other, and the fuselage contact pulley 5 on the left end moving support frame 1 and the right end moving support frame 2 is attached to the surface of the fuselage;

[0038] S3. Pushing the left end moving support frame 1 and the right end moving support frame 2 to the tail of the fuselage by using the arc-shaped curve of the nose, during which the spring 3021 is compressed and the inner tube sleeve 302 moves outward as the width of the fuselage increases, increasing the total width of the left end moving support frame 1 and the right end moving support frame 2, until moving to the wing installation position;

[0039] S4. The mechanical arm structure 4 moves along the slide 105 to assemble the components between the wings, and after the single-side wing assembly is completed, the mechanical arm structure 4 is used to synchronize the installation and fixation of the two-side wings to the fuselage.

[0040] When installing, the wing is hoisted to the supporting plate 101 on the left end moving support frame 1 and the right end moving support frame 2, the wing is supported through the supporting plate 101, and the connecting end of the wing is directed to the fuselage, the left end moving support frame 1 and the right end moving support frame 2 are moved to the nose of the fuselage, the left end moving support frame 1 and the right end moving support frame 2 are rotated so that the cutout 3031 of the connecting part 303 on the left end moving support frame 1 and the right end moving support frame 2 corresponds to the notch of the arc-shaped connecting piece 304, the connecting part 303 enters the inside of the arc-shaped connecting piece 304 is realized, and the left end moving support frame 1 and the right end moving support frame 2 are rotated to be parallel to each other, and the fuselage contact pulley 5 on the left end moving support frame 1 and the right end moving support frame 2 is attached to the surface of the fuselage, the left end moving support frame 1 and the right end moving support frame 2 are pushed to the tail by the arc-shaped curve of the nose, because of the streamline design of the fuselage, the left end moving support frame 1 and the right end moving support frame 2 on both sides are contacted by the mechanical arm structure 4 and the connecting part (303) in five-point mode, which can ensure that the left end moving support frame 1 and the right end moving support frame 2 are nearly perpendicular to the surface of the fuselage during movement, and the left end moving support frame 1 and the right end moving support frame 2 do not need to be pulled in the opposite direction by manpower, thereby easily attaching to the fuselage on both sides, during which the width of the fuselage is continuously increased to compress the spring 3021 and move the inner tube sleeve 302 outward, increase the total width of the left end moving support frame 1 and the right end moving support frame 2, and move to the wing installation position, the mechanical arm structure 4 moves along the slide 105 to assemble the wing components, and after the single-side wing is assembled, the two-side wings are fixed and installed on the fuselage by the mechanical arm structure 4.

[0041] The above is only an embodiment of the present application, and the specific structure and characteristics of the scheme are not described in detail, and the ordinary technical personnel in the art knows all the ordinary technical knowledge in the technical field of the application before the application date or the priority date, can know all the prior art in the field, and has the ability to apply conventional experimental means before that date, and the ordinary technical personnel in the art can improve and implement the scheme under the guidance of the application, and some typical known structures or known methods should not be an obstacle for the ordinary technical personnel to implement the application. It should be pointed out that, for those skilled in the art, without departing from the structure of the present application, a number of modifications and improvements can be made, which should be considered as the protection scope of the present application, which will not affect the effect and practicality of the patent.

Claims

1. An assembly system for improving aircraft wing assembly efficiency, characterized by: The invention comprises a left-end movable support bracket (1) and a right-end movable support bracket (2) located on both sides of the fuselage for supporting the wings, wherein the left-end movable support bracket (1) and the right-end movable support bracket (2) both comprise a main frame (103), and lifting boxes (102) are installed on both sides of the top of the main frame (103), and a supporting plate (101) is installed on the movable end of the lifting box (102), and the supporting plates (101) on the left-end movable support bracket (1) and the right-end movable support bracket (2) are both used for supporting the wings. A group of fuselage contact pulleys (5) are installed on the opposite side walls of the left end movable support bracket (1) and the right end movable support bracket (2), each group includes two fuselage contact pulleys (5) of the same height, and there is a certain angle between the axis of the fuselage contact pulley (5) and the horizontal line, and a connecting structure (3) for connection is installed on the opposite side walls of the left end movable support bracket (1) and the right end movable support bracket (2), so as to realize the connection between the left end movable support bracket (1) and the right end movable support bracket (2).

2. The assembly system for improving aircraft wing assembly efficiency according to claim 1, characterized in that: The connecting structure (3) comprises an outer sleeve (301), an inner sleeve (302), a connecting portion (303), an arc-shaped connecting piece (304) and a connecting rod (305). The outer sleeve (301) and the connecting rod (305) are mounted opposite each other at the bottom of the left-end movable support bracket (1) and the right-end movable support bracket (2). The end of the connecting rod (305) is mounted with an arc-shaped connecting piece (304) having a notch. The inner sleeve (302) that moves along its axis is inserted into the inner side of the outer sleeve (301). The end of the inner sleeve (302) is connected to the connecting portion (303) that matches the arc-shaped connecting piece (304).

3. The assembly system for improving aircraft wing assembly efficiency according to claim 2, characterized in that: An axially arranged spring (3021) is installed on the outer side of the inner tube sleeve (302), a first end of the spring (3021) is fixedly connected to the inner tube sleeve (302), and the other end of the spring (3021) is fixedly connected to the inner wall of the outer tube sleeve (301).

4. The assembly system for improving aircraft wing assembly efficiency according to claim 3, characterized in that: A notch (3031) is provided in the axial direction at a position opposite to the connection point of the bottom end of the connecting portion (303) and the inner sleeve (302). The rotating connecting portion (303) cooperates with the connecting portion (303) through the notch (3031) to realize the installation and removal of the connecting portion (303) and the arc-shaped connecting member (304).

5. The assembly system for improving aircraft wing assembly efficiency according to claim 4, characterized in that: A slideway (105) is installed on both the left-end movable support bracket (1) and the right-end movable support bracket (2). A mechanical arm structure (4) that moves along the slideway (105) is installed on the slideway (105). The mechanical arm structure (4) is used to assemble the wing.

6. The assembly system for improving aircraft wing assembly efficiency according to claim 5, characterized in that: A slider (106) is installed on the slideway (105) and moves along the slideway (105), and a mechanical arm structure (4) is installed on the slider (106).

7. The assembly system for improving aircraft wing assembly efficiency according to claim 6, characterized in that: The angle between the axis of the fuselage contact pulley (5) and the horizontal line is 30-60 degrees.

8. The assembly system for improving aircraft wing assembly efficiency according to claim 7, characterized in that: The bottom of the main frame (103) is equipped with pulleys (104) for easy movement.

9. An assembly method using the assembly system for improving aircraft wing assembly efficiency according to claim 8, characterized in that: The steps include: A. Hoist the wing onto the support plates (101) on the left-end movable support bracket (1) and the right-end movable support bracket (2), support the wing via the support plates (101), and orient the connecting end of the wing toward the fuselage; B. Move the left movable support bracket (1) and the right movable support bracket (2) to the nose of the fuselage, rotate the left movable support bracket (1) and the right movable support bracket (2) so that the cutout (3031) of the connecting portion (303) on the left movable support bracket (1) and the right movable support bracket (2) corresponds to the notch of the arc-shaped connecting member (304), so that the connecting portion (303) enters the inner side of the arc-shaped connecting member (304), and rotate the left movable support bracket (1) and the right movable support bracket (2) so that the two are parallel to each other, and the fuselage contact pulleys (5) on the left movable support bracket (1) and the right movable support bracket (2) are in contact with the fuselage surface; C. Using the arc curve of the nose to push the left end movable support bracket (1) and the right end movable support bracket (2) toward the tail of the aircraft, during which the width of the fuselage increases continuously, thereby compressing the spring (3021) and the inner tube sleeve (302) moving outward, thereby increasing the total width of the left end movable support bracket (1) and the right end movable support bracket (2), until they move to the wing installation position; D. The mechanical arm structure (4) moves along the slideway (105) to assemble the wing components first. After the assembly of one wing is completed, the mechanical arm structure (4) is used to synchronously install and fix the wings on both sides to the fuselage.

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