Coordinated assembly method for special-shaped wings

Abstract

The invention discloses a coordinated assembly method for special-shaped wings. The coordinated assembly method comprises the following steps that S1, the wings are divided into winglets, main wings and ailerons; s2, the aileron is assembled; s3, a winglet is assembled through a winglet wing frame; s4, the main wings are assembled in a vertical mode; s5, the main wing, the winglet and the aileron are horizontally assembled through the butt joint platform, and then the wing is formed; and S6, through cooperation of the drill jig and the allowance lug pieces, the wing and the central wing are assisted to be accurately assembled. The wing is divided into the winglet, the main wing and the aileron which are assembled respectively, the main wing is vertically assembled, then the winglet, the main wing and the aileron are horizontally assembled to form the wing, and then the wing is accurately matched with the central wing. The problems of high fixture precision guarantee difficulty, inconvenience in hoisting and large inner and outer wing butt joint coordination hole making error in wing vertical assembly are effectively solved.

Description

TECHNICAL FIELD

[0001] The present application relates to the field of aircraft assembly, in particular to a method for coordinated assembly of a special-shaped wing. BACKGROUND

[0002] The wing part of a certain carrier has a single wing span of about 5m and a wing length of about 9m, and is mainly composed of ribs, beams, partitions, skins and joints. The side wall of the wing is connected to the middle fuselage, and the tail is connected to the aileron. According to the wing mechanism and the assembly method, the wing can be divided into three parts, i.e. the main wing 1, the aileron 2 and the wing tip winglet 3, for assembly on three jigs respectively. The wing structure is shown in Figure 1 The main wing 1 is connected to the wing tip winglet 3 at the No. 9 rib 6, and the inner and outer wings are connected through the inner and outer wing connecting joints 8. The main wing structure is shown in Figure 2 According to the assembly idea of the aircraft wing, the main wing and the wing tip winglet of the wing are assembled on the vertical jig. During the assembly process of the main wing, the leading edge 4 is upward or the trailing edge beam 5 is upward. First, the ribs, beams and joints are positioned using the jig, the metal structure is combined, and the skin is riveted. Then, the wing tip winglet is combined under the jig and connected to the main wing on the vertical jig. After the assembly is completed, the wing side is lifted out of the jig, and then the wing is turned to a horizontal state and placed on the connecting platform for subsequent assembly and connecting work.

[0003] According to the existing wing structure, the wing is placed on the jig in a state where the leading edge is upward or downward, and the side of the wing is lifted out of the jig after assembly. However, there are the following problems: 1. Difficulty in ensuring high precision of the jig The wing has a single wing span of about 5m and a wing length of about 9m. When placed in a state where the leading edge 4 is upward or downward, the height of the product and tooling will reach 10m. At this time, the No. 1 rib 7 is on the side, and a 9m vertical column needs to be set on the side to set the joint positioning seat to ensure the position and coaxiality of the joint. However, it is difficult to ensure the precision of the 9m positioning seat. According to the size of the wing structure, the No. 1 rib can be placed on the lower side for assembly, which can solve the problem of high jig.

[0004] 2. Difficulty in lifting the wing tip winglet from the side Although the method of assembling the No. 1 rib on the lower side can solve the problem of difficulty in ensuring the high precision of the jig, the wing tip winglet is on the upper side at this time. Therefore, a wing tip winglet connecting device needs to be set on the upper side of the jig, and the wing tip winglet is perpendicular to the wing surface. After the wing tip winglet is assembled, it is difficult to lift the wing out of the jig from the side. The wing surface lifting tool interferes with the wing tip winglet, and the wing surface connecting lifting tool cannot be used.

[0005] 3. Difficulty in coordinated hole making for inner and outer wing connection The inner and outer wings are butt-jointed and the bushing is installed, the inner diameter of the bushing is large, the diameter reaches Phi 45, Phi 50, in order to ensure the butt-joint quality, the bushing is left with a machining allowance, the hole is expanded after butt-joint, meanwhile, due to the large expansion of the hole, the bushing rotates in the expansion process, and it is difficult to ensure the reliable butt-joint connection. In view of the problems that the wing vertical assembly side face is lifted out and turned over for butt-joint, the type frame precision is difficult to ensure, the lifting is inconvenient and the inner and outer wings are difficult to butt-joint and coordinate, an assembly mode needs to be explored to solve the problems of type frame precision, lifting inconvenience and inner and outer wing butt-joint and coordination, so as to ensure the wing assembly and butt-joint requirements. SUMMARY

[0006] The present application discloses a special-shaped wing coordinated assembly method, the wing is divided into wing tip winglet, main wing and aileron for assembly, the main wing is assembled vertically, then the wing tip winglet, main wing and aileron are horizontally assembled to form a wing, and then the wing is precisely matched with the central wing, effectively solving the problems of difficulty in ensuring type frame precision, inconvenience in lifting and large error in inner and outer wing butt-joint and coordination.

[0007] The present application is realized by the following technical solutions: The present application provides a special-shaped wing coordinated assembly method, comprising the following steps: S1, dividing the wing into wing tip winglet, main wing and aileron; S2, assembling the aileron; S3, assembling the wing tip winglet through the wing tip winglet type frame; S4, assembling the main wing through the vertical mode; S5, horizontally assembling the main wing, wing tip winglet and aileron through the butt-joint platform to form a wing; S6, precisely assembling the wing and the central wing through the drill jig and the excess ear piece.

[0008] As a further scheme, the wing tip winglet type frame comprises a main frame and a clamping plate installed above the main frame, the clamping plate comprises an upper part and a lower part fixedly connected to the upper part, the upper part is fixedly connected to the top of the main frame, the lower part is fixedly connected to the bottom of the main frame, the upper part is formed by sequentially connecting a plurality of rhombic frames with the same height, the lower part is formed by connecting a plurality of rectangular frames with the same height, a plurality of skin positioning plates for conveniently checking the structure size are detachably installed on the frame of the clamping plate, and a plurality of positioning pin fixing units for connecting with process holes on the beams and ribs are also arranged.

[0009] As a further scheme, nine rib process pieces are arranged on the lower part, and the nine rib process pieces have the same structure as the ninth rib of the main wing.

[0010] As a further scheme, the lower part 922 can also detachably install a plurality of external joints 94.

[0011] As a further scheme, the assembly method of the wing tip winglet in S3 is: first, the beam and rib of the wing tip winglet are positioned by using the clamping plate, the skin of the wing tip winglet is positioned, the skin near the outer side of the No. 9 rib is drilled and then disassembled, and the assembly is temporarily not riveted, and after the assembly is completed, the No. 9 rib connecting piece is disassembled.

[0012] As a further scheme, the method of S4 is: when the main wing is hoisted to the main wing jig, the No. 1 rib is placed on the upper side, the detachable inner and outer wing butt joint positioning tool is installed on the upper side of the main wing jig, and the inner and outer wing butt joint positioning tool is used as the assembly reference to position: first, the leading edge is assembled on one side of the main wing, a plurality of inner and outer wing butt joints are installed above the No. 1 rib, and then the skin is assembled, and the main wing assembly is completed.

[0013] As a further scheme, the inner and outer wing butt joint positioning tool includes a cross beam and a positioning seat installed above the cross beam, a plurality of joint positioning tabs, and two detachable locks, wherein the cross beam is a force bearing structure, the positioning seat is used to position the relative position of the main wing jig and the inner and outer wing butt joint positioning tool, and the joint positioning tab is used to position the inner and outer wing butt joint; the two detachable locks are symmetrically installed on the two sides of the cross beam and are used to lock the cross beam and the main wing jig.

[0014] As a further scheme, the butt joint platform includes a main wing bracket for supporting the main wing, an aileron bracket for supporting the aileron, and a wing tip winglet bracket for supporting the wing tip winglet.

[0015] As a further scheme, the main wing bracket is a rectangular frame structure, and a plurality of main wing interfaces for positioning the position of the main wing are arranged on the main wing bracket, and a main wing positioning column is fixedly installed on each main wing interface.

[0016] As a further scheme, the aileron bracket is a lifting bracket.

[0017] As a further scheme, the wing tip winglet bracket includes a fixed frame and a storage rack slidably connected above the fixed frame, and the storage rack is used to place the wing tip winglet.

[0018] As a further scheme, the fixed frame is a symmetrical frame structure and is slidably connected with the storage rack through a sliding rail.

[0019] As a further scheme, a plurality of wing tip winglet external joint interfaces for positioning the relative position of the wing tip winglet and the wing tip winglet bracket are further arranged on the storage rack.

[0020] As a further scheme, the specific method of S5 is: S51, according to the actual situation, arranging the positions of the main wing bracket, the aileron bracket and the wing tip winglet bracket, respectively hoisting the main wing to the main wing bracket and positioning and placing, hoisting the aileron to the aileron bracket and positioning and placing, and hoisting the wing tip winglet to the storage rack and positioning and placing; S52, move the storage rack to the main wing bracket through the slide rail until the winglet insertion main wing No. 9 rib assembly is completed, at this time the winglet transition structure outer skin is not assembled; S53, adjust the height of the aileron using the aileron bracket, connect the aileron and the main wing to form a wing.

[0021] As a further scheme, the drill jig includes a drill jig body, the drill jig body is a U-shaped groove structure, a stop card for clamping a joint bushing is installed in the groove of the drill jig body, the stop card is a U-shaped groove, bushings are symmetrically installed on the inner wall of the stop card, and a drill sleeve and a positioning pin are fixedly installed on the outer wall of one side of the drill jig body.

[0022] As a further scheme, the method of S6 is: setting a surplus ear on the central wing joint, using an automatic feed drill and a drill jig to cooperate, and expanding a hinge hole at the wing and the central wing joint.

[0023] The characteristics and benefits of the present application are: (1) The present application divides the wing into a winglet, a main wing and an aileron, which are precisely assembled respectively, wherein the main wing is assembled vertically, then the winglet, the main wing and the aileron are horizontally and efficiently assembled into a wing through a docking platform, and then precisely matched with the central wing through an auxiliary tooling, effectively solving the problems of difficulty in ensuring the precision of the jig, inconvenience in lifting and large error in coordinated hole making of the inner and outer wings in vertical assembly of the wing.

[0024] (2) The present application efficiently and precisely assembles the winglet through the winglet jig, greatly improves the assembly efficiency, and the jig has strong universality and wider application range.

[0025] (3) The present application changes the assembly method of the main wing from horizontal to vertical, reduces the space occupation area, and reduces the assembly difficulty, greatly improving the work efficiency.

[0026] (4) The docking platform of the present application, wherein the winglet can move from the winglet bracket to the main wing bracket, the aileron bracket can drive the aileron to adjust the height and be flush with the main wing, greatly improving the horizontal assembly efficiency, replacing the lifting assembly mode through a simple moving mode, and improving the assembly precision of the wing.

[0027] (5) The present application sets surplus ears on the central wing joint and cooperates with the drill jig, which can effectively ensure the expansion of the hinge hole after the inner and outer wings are docked, and solve the problem of large error in coordinated hole making of the inner and outer wings. BRIEF DESCRIPTION OF DRAWINGS

[0028] In order to more clearly illustrate the technical solutions in the embodiments of the present application, the following will briefly introduce the drawings needed to be used in the embodiments or prior art description. Obviously, the drawings in the following description are only some embodiments of the present application, and for those skilled in the art, other drawings can also be obtained from these drawings without any creative effort.

[0029] Figure 1 Schematic diagram of a wing to be assembled according to the present application; Figure 2 Schematic diagram of a main wing to be assembled according to the present application; Figure 3 Schematic diagram of a winglet to be assembled according to the present application; Figure 4 Schematic diagram of a winglet jig according to an embodiment of the present application; Figure 5 Schematic diagram of an external joint according to an embodiment of the present application; Figure 6 Schematic diagram of an inner-outer wing butt joint positioning tool according to an embodiment of the present application; Figure 7 Schematic diagram of a butt joint platform according to an embodiment of the present application; Figure 8 Schematic diagram of a surplus tab according to an embodiment of the present application; Figure 9 Schematic diagram of a drilling jig according to an embodiment of the present application; Figure 10 Flowchart of an assembly method according to an embodiment of the present application.

[0030] Explanation of reference signs: 1 - main wing; 2 - aileron; 3 - winglet; 4 - leading edge; 5 - trailing edge beam; 6 - 9th rib; 7 - 1st rib; 8 - inner-outer wing butt joint; 9 - winglet jig; 91 - main frame; 92 - clamping plate; 921 - upper part; 922 - lower part; 93 - 9th rib connecting piece; 94 - external joint; 10 - inner-outer wing butt joint positioning tool; 101 - cross beam; 102 - positioning seat; 103 - joint positioning tab; 104 - detachable lock; 11 - main wing bracket; 111 - main wing positioning column; 12 - aileron bracket; 13 - winglet bracket; 131 - fixing frame; 132 - storage rack; 133 - sliding rail; 14 - surplus tab; 15 - drilling jig; 151 - drilling jig body; 152 - stop clamping piece; 153 - bushing; 154 - drill sleeve; 155 - positioning pin; A - butt joint platform. DETAILED DESCRIPTION

[0031] In order to facilitate the understanding of the present application, the following will give a more comprehensive description of the present application, and embodiments of the present application are given, but the scope of the present application is not limited thereby.

[0032] In the description of the present application, it needs to be understood that the terms "center", "longitudinal", "transverse", "upper", "lower", "front", "rear", "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, which is only for the convenience of describing the present application and simplifying the description, and does not indicate or imply 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 a limitation on the present application. In addition, the terms "first", "second" and the like are only for descriptive purposes and cannot be understood as indicating or implying relative importance or implicitly indicating the number of technical features indicated. Therefore, the features defined with "first", "second" and the like can be explicitly or implicitly included one or more. In the description of the present application, unless otherwise specified, the meaning of "a plurality of" is two or more.

[0033] In the description of the present application, it needs to be understood that unless otherwise explicitly specified and limited, the terms "mounting", "connection", "connection" should be understood broadly, for example, it can be fixed connection, or detachable connection, or integral connection; it can be mechanical connection, or electrical connection; it can be directly connected, or indirectly connected through intermediate medium, or the communication inside two elements. For those skilled in the art, the specific meaning of the above terms in the present application can be understood through specific circumstances.

[0034] Noun explanation: Wing tip winglet: a small wing-shaped structure installed at the end of the wing.

[0035] As Figures 3 to 10 shown, a special-shaped wing coordinated assembly method comprises the following steps: S1, the wing is divided into wing tip winglet 3, main wing 1 and aileron 2, S2, assembling aileron 2 Install beams and ribs on the metal skeleton of aileron 2, and rivet the composite skin and joint coordination hole under the premise of ensuring assembly accuracy after the installation of composite beams and ribs.

[0036] S3, assembling wing tip winglet 3 through wing tip winglet bracket 9 As Figure 6 and 7As shown, the winglet mounting frame 9 comprises a main frame 91, a clamping plate 92, a 9-rib connecting piece 93 and an external joint 94. The main frame 91 is a rectangular frame structure installed on the ground for maintaining the overall shape and size of the structure. The clamping plate 92 comprises an upper part 921 and a lower part 922 fixedly connected thereto. The upper part 921 is fixedly connected to the top of the main frame 91, and the lower part 922 is fixedly connected to the bottom of the main frame 91. The upper part 921 is formed by sequentially connecting a plurality of rhombic frames with the same height, and the lower part 922 is formed by connecting a plurality of rectangular frames with the same height, A plurality of skin positioning plates for checking the shape and size of the structure and a plurality of positioning pin fixing units for connecting with the process holes on the beams and ribs are arranged on the frame of the clamping plate 92. These skin positioning plates and positioning pin fixing holes are arranged to ensure the positioning accuracy of the winglet. The skin positioning plates and the positioning pin fixing units are detachably installed (threaded connection or clamping or pin hole connection) with the frame of the clamping plate, which facilitates adaptive adjustment according to different winglet structures. This greatly increases the versatility of the winglet mounting frame 9. The specific number, shape and position of the skin positioning plates and the positioning pin fixing units are related to the structure of the winglet to be assembled. Since the skin positioning plates and the positioning pin fixing units are detachably installed with the frame of the clamping plate, their position, shape and number can be adaptively adjusted. The shape can be adjusted by replacing different structures.

[0037] To ensure the docking accuracy of the winglet 3 and the main wing 1, a coordinated positioning reference needs to be arranged in the winglet 3 and the main wing 1. Therefore, a 9-rib process piece is arranged on the lower part 922. The 9-rib process piece has the same structure as the No. 9 rib 93 of the main wing 1 to ensure the consistency of the docking shape surface of the winglet and the main wing. To ensure the docking accuracy of the winglet 3 and the main wing 1, the lower part 922 can also detachably install (threaded connection or clamping or pin hole connection) a plurality of external joints 94. The specific structure of the external joint 94 can be adjusted according to the docking part, as long as the connection method is detachable.

[0038] In one embodiment, the upper end of the external joint 94 is arc-shaped and provided with a bolt or a pin shaft connected with the winglet 3. The profile is consistent with the skin shape of the winglet 3.

[0039] The assembly process of the winglet 3 is as follows: First, the beams and ribs of the winglet 3 are positioned by the clamping plate 92, and then the winglet skin is positioned. The skin near the outer side of the No. 9 rib 6 is drilled and then disassembled without riveting assembly. The assembly positions of the beams on the winglet 3 are ensured by the 9-rib connecting piece 93. After the assembly is completed, the 9-rib connecting piece 93 is removed.

[0040] S4, vertically assemble the main wing 1 The main wing 1 comprises trailing edge beams 5, ribs 6, 7 and inner-outer wing butt joints 8. For the purpose of convenient assembly and hoisting of the main wing 1, the main wing is vertically assembled, the ribs 6, 7 are self-structured frames of the main wing 1, and therefore, when the main wing 1 is hoisted to the main wing jig, the ribs 7 are placed on the upper side, the inner-outer wing butt joint positioning tool 10 is detachably installed on the upper side of the main wing jig, and the inner-outer wing butt joint positioning tool 10 is used as an assembly reference for positioning. The positioning process is as follows: the leading edge 4 is assembled on one side of the main wing 1, the inner-outer wing butt joints 8 are installed on the upper side of the ribs 7, and then the skin is assembled, thereby completing the assembly of the main wing.

[0041] The inner-outer wing butt joint positioning tool 10 comprises a cross beam 101, a positioning seat 102 installed on the upper side of the cross beam 101, a plurality of joint positioning lugs 103 and two detachable locks 104. The cross beam 101 is a force-bearing structure, the positioning seat is used for positioning the relative position of the main wing jig and the inner-outer wing butt joint positioning tool 10, the joint positioning lugs 103 are used for positioning the inner-outer wing butt joints 8 and ensuring the coaxiality and position accuracy of the inner-outer wing butt joints 8, and the two detachable locks 104 are symmetrically installed on the two sides of the cross beam 101 and used for locking the cross beam 101 and the main wing jig. When the detachable locks 104 are pressed, they are in the locked state. During product assembly, the detachable locks are in the locked state, and after assembly is completed, the locks are opened, the inner-outer wing butt joint positioning tool 10 is removed, the main wing 1 is hoisted out, and the main wing is turned horizontal through overturning and hanging.

[0042] S5, the main wing 1, the winglet 3 and the aileron 2 are horizontally assembled through the butt joint platform A to form the wing.

[0043] The butt joint platform A comprises a main wing bracket 11 for supporting the main wing 1, an aileron bracket 12 for supporting the aileron 2 and a winglet bracket 13 for supporting the winglet 3. The specific placement positions of the main wing bracket 11, the aileron bracket 12 and the winglet bracket 13 can be adjusted according to the actual assembly direction and space condition, thereby improving the use direction and flexibility of the butt joint platform A and enhancing the versatility.

[0044] In some embodiments, the main wing bracket 11 is a rectangular frame structure, a plurality of main wing interfaces for positioning the position of the main wing 1 are arranged on the main wing bracket 11, and a main wing positioning column 111 is fixedly installed on each main wing interface. When the main wing 1 is positioned, the main wing 1 and the main wing interface are connected through the main wing positioning column 111, and the main wing positioning accuracy is ensured. In some embodiments, the aileron bracket 12 is a liftable structure.

[0045] In some embodiments, the wing tip winglet bracket 13 comprises a fixed frame 131 and a storage rack 132 slidably connected above the fixed frame 131, and the storage rack 132 is used to place the wing tip winglet 3. The storage rack 132 and the fixed frame 131 are slidably connected, which facilitates the hoisting of the wing tip winglet 3 to the storage rack 132 and then sliding the wing tip winglet 3 to the main wing bracket 11 to assemble with the main wing 1.

[0046] In one embodiment, the fixed frame 131 is a symmetrical frame structure, and is movably connected with the storage rack 132 through a sliding rail 133.

[0047] In one embodiment, the storage rack 132 is further provided with a plurality of wing tip winglet external joint interfaces for positioning the relative position of the wing tip winglet 3 and the wing tip winglet bracket 13. The wing tip winglet external joint interfaces can effectively ensure the positioning accuracy of the wing tip winglet 3. The position and number of the wing tip winglet external joint interfaces can be adapted to different types of wing tip winglets, and have stronger universality.

[0048] The docking process of the main wing, the wing tip winglet and the docking aileron on the docking platform A is as follows: according to the actual situation, the positions of the main wing bracket 11, the aileron bracket 12 and the wing tip winglet bracket 13 are arranged, then the main wing 1 is hoisted to the main wing bracket 11 and positioned and placed, the aileron 2 is hoisted to the aileron bracket 12 and positioned and placed, and the wing tip winglet 3 is hoisted to the storage rack 132 and positioned and placed. The storage rack 132 is moved to the main wing bracket 11 through the sliding rail 133 until the wing tip winglet 3 is inserted into the No. 9 rib 6 of the main wing 1 to complete the assembly, at this time the transition structure outer skin of the wing tip winglet 3 is not assembled, leaving an operation space for connecting the wing tip winglet 3 and the main wing 1, then the height of the aileron 2 is adjusted by the aileron bracket 12, and the aileron 2 and the main wing 1 are connected to form a wing.

[0049] S6, through the cooperation of the drill jig and the excess ear piece, the wing and the central wing are precisely assembled.

[0050] The wings are left and right wings, and the inner and outer wings are connected by joints and docking on both sides of the central wing. Due to the large overall structure of the wings and the central wing, there is a positioning error in the joint of the wings and the central wing. In order to ensure the docking of the inner and outer wings, a 3mm excess is left in the joint sleeve of the inner and outer wings in the part state, and the hinge hole is expanded after docking to ensure the docking accuracy.

[0051] The expansion of the hinge hole is carried out by using an automatic feed drill. Since the automatic feed drill has no positioning reference, an excess ear piece 14 is arranged on the central wing joint and a drill jig structure is designed to assist the positioning of the automatic feed drill, thereby ensuring the docking accuracy.

[0052] The drill jig 15 comprises a drill jig body 151, a stop card 152, a bushing 153, a drill sleeve 154 and a positioning pin 155. The drill jig body 151 is a U-shaped groove structure. The stop card 152 is fixedly installed in the groove of the drill jig body 151. The stop card 152 is a U-shaped groove. The bushing 153 is symmetrically installed on the inner wall of the stop card 152. The drill sleeve 154 and the positioning pin 155 are fixedly installed on the outer wall of one side of the drill jig body 151. The positioning pin 155 is fixedly connected with the excess ear piece 14 of the central wing joint, so that the drill jig is fixedly connected with the central wing joint. The drill sleeve 154 is used for clamping an automatic feeding drill and has a drill hole guiding function. The stop card 152 is used for clamping the joint bushing 153.

[0053] In one embodiment, in order to prevent the rotation of the bushing during the reaming process, in addition to increasing the interference amount of the bushing and the joint assembly, the bushing 153 is made into a tooth shape. In order to match the shape of the bushing 153, a tooth shape matched with the bushing 153 is arranged on the stop card 152. During the drilling process, the stop card is clamped in the tooth shape of the bushing 153, so as to ensure the reaming quality after the outer wing is butt-jointed.

[0054] The application solves the problems of large precision error of the jig, inconvenient hoisting and large error of coordinated hole making of the inner and outer wings during butt joint, and ensures the wing assembly and butt joint requirements.

[0055] It should be noted that the above only describes the preferred embodiments of the application and is not intended to limit the application. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the application shall be included in the protection scope of the application.

Claims

1. A method of coordinated assembly of a contoured wing, characterized by: The method comprises the following steps: S1, dividing the wing into winglet, main wing and aileron; S2, assembling the aileron; S3, assembling the winglet through the winglet bracket; S4, assembling the main wing through the vertical mode; S5, assembling the main wing, winglet and aileron through the horizontal assembly platform to form the wing; S6, assisting the accurate assembly of the wing and central wing through the cooperation of the drill jig and the excess ear piece.

2. The method of claim 1, wherein: The winglet bracket comprises a main frame and a clamping plate installed above the main frame, the clamping plate comprises an upper part and a lower part fixedly connected to the upper part, the upper part is fixedly connected to the top of the main frame, the lower part is fixedly connected to the bottom of the main frame, the upper part is formed by sequentially connecting a plurality of rhombic frames with the same height, the lower part is formed by connecting a plurality of rectangular frames with the same height, a plurality of skin positioning plates for facilitating the inspection of the structure and size are detachably installed on the frame of the clamping plate, and a plurality of positioning pin fixing units for connecting with the process holes on the beams and ribs are further arranged. Preferably, nine rib process pieces are arranged on the lower part, and the nine rib process pieces have the same structure as the ninth rib of the main wing. Preferably, the lower part 922 is further detachably installed with a plurality of external joints 94.

3. A method of conforming fit of a complex wing as claimed in claim 2, wherein: In S3, the assembly method of the winglet is as follows: first, the beams and ribs of the winglet are positioned by using the clamping plate, then the skin of the winglet is positioned, the skin near the outer side of the ninth rib is drilled and then detached, and the assembly is temporarily not riveted, and after the assembly is completed, the ninth rib connecting piece is removed.

4. The method of claim 1, wherein: In S4, when the main wing is hoisted to the main wing bracket, the first rib is arranged on the upper side, the inner and outer wing butt joint positioning tool is detachably installed on the upper side of the main wing bracket, and the assembly is positioned by taking the inner and outer wing butt joint positioning tool as the assembly reference: first, the leading edge is assembled on one side of the main wing, then a plurality of inner and outer wing butt joint connecting pieces are installed on the upper side of the first rib, and then the skin is assembled, and the assembly of the main wing is completed.

5. A method of conforming fit of a complex wing as claimed in claim 4, wherein: The inner and outer wing butt joint positioning tool comprises a horizontal beam, a positioning seat installed on the upper side of the horizontal beam, a plurality of joint positioning ear pieces and two detachable locks, wherein the horizontal beam is a force bearing structure, the positioning seat is used for positioning the relative position of the main wing bracket and the inner and outer wing butt joint positioning tool, and the joint positioning ear pieces are used for positioning the inner and outer wing butt joint; the two detachable locks are symmetrically installed on the two sides of the horizontal beam and are used for locking the horizontal beam and the main wing bracket.

6. The method of claim 1, wherein: The assembly platform comprises a main wing bracket for supporting the main wing, an aileron bracket for supporting the aileron and a winglet bracket for supporting the winglet. Preferably, the main wing bracket is a rectangular frame structure, a plurality of main wing interfaces for positioning the position of the main wing are arranged on the main wing bracket, and a main wing positioning column is fixedly installed on each main wing interface. Preferably, the aileron bracket is a lifting bracket.

7. The method of claim 1, wherein: The winglet bracket comprises a fixed frame and a storage frame slidably connected to the upper side of the fixed frame, and the storage frame is used for placing the winglet. Preferably, the fixed frame is a symmetrical frame structure and is slidably connected to the storage frame through a sliding rail. Preferably, a plurality of winglet external joint interfaces for positioning the relative position of the winglet and the winglet bracket are further arranged on the storage frame.

8. The method of claim 7, wherein: The specific method of S5 is as follows: S51, according to the actual situation, the positions of the main wing bracket, the aileron bracket and the winglet bracket are arranged, the main wing is hoisted to the main wing bracket and positioned, the aileron is hoisted to the aileron bracket and positioned, and the winglet is hoisted to the bracket and positioned; S52, the bracket is moved to the main wing bracket through the slide rail until the winglet is inserted into the No. 9 rib of the main wing, and the assembly of the winglet transition structure outer skin is not completed; S53, the height of the aileron is adjusted again by using the aileron bracket, and the aileron is connected with the main wing to form a wing.

9. The method of claim 1, wherein: The drill jig comprises a drill jig body, the drill jig body is a U-shaped groove structure, a stop card for clamping a joint bushing is mounted in the groove of the drill jig body, the stop card is a U-shaped groove, bushings are symmetrically mounted on the inner wall of the stop card, and a drill sleeve and a positioning pin are fixedly mounted on the outer wall of one side of the drill jig body.

10. The method of claim 9, wherein: The method of S6 is to set a surplus ear on the central wing joint, use an automatic feeding drill and a drill jig to cooperate, and expand the hinge hole at the joint of the wing and the central wing.

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