Wing assembling method and wing assembling device

Abstract

The invention discloses a wing assembling method and a wing assembling device, the wing assembling method is used for assembling a wing, the wing comprises a central wing and two outer wings respectively arranged at two ends of the central wing, the wing assembling method comprises the following steps: assembling the central wing on a central wing assembling fixture, and respectively assembling the two outer wings on two outer wing assembling fixtures; the two outer wing assembling jig frames assembled with the outer wings are hoisted to the two ends of the central wing assembling jig frame assembled with the central wing correspondingly, and the two outer wing assembling jig frames are correspondingly connected with the two ends of the central wing assembling jig frame correspondingly; and the two outer wings are correspondingly connected with the two ends of the central wing respectively. The central wing and the two outer wings are respectively assembled on different assembly fixtures, so that the central wing and the two outer wings can be synchronously assembled, the assembly time of the wings is saved, and the assembly efficiency is improved; secondary installation and positioning of the assembled outer wing are avoided, tools do not need to be replaced for the central wing or the outer wing, the assembling steps are simplified, the assembling efficiency is improved, and the assembling precision is improved.

Description

Technical Field

[0001] This invention relates to the field of wing assembly technology, and more specifically, to a wing assembly method and wing assembly apparatus. Background Technology

[0002] The carbon fiber wings consist of a center wing and two outer wings. The center wing and outer wings each include an upper skin, a lower skin, a spars, and ribs, and are connected by a connecting bracket.

[0003] In related technologies, the middle wing and outer wing are assembled on a tooling. During assembly, the middle wing and outer wing must be assembled in sequence, which results in low assembly efficiency.

[0004] Therefore, how to improve the assembly efficiency of wings is a problem that urgently needs to be solved by those skilled in the art. Summary of the Invention

[0005] In view of this, the purpose of the present invention is to provide a wing assembly method to improve the assembly efficiency of the wing.

[0006] Another object of the present invention is to provide a wing assembly apparatus for implementing the above-described wing assembly method, so as to improve the assembly efficiency of the wing.

[0007] To achieve the above objectives, the present invention provides the following technical solution:

[0008] A wing assembly method is provided for assembling an aircraft wing, the wing comprising a central wing and two outer wings respectively disposed at both ends of the central wing, the wing assembly method comprising:

[0009] The central wing is assembled on the central wing assembly frame, and the two outer wings are assembled on the two outer wing assembly frames respectively.

[0010] The two outer wing assembly frames assembled with the outer wings are respectively hoisted to the two ends of the central wing assembly frame assembled with the central wing, and the two outer wing assembly frames are respectively connected to the two ends of the central wing assembly frame.

[0011] The two outer wings are respectively connected to the two ends of the central wing.

[0012] Optionally, the central wing assembly frame is provided with a docking seat, the outer wing assembly frame is provided with a docking end joint, one of the docking seat and the docking end joint is provided with a sliding groove, and the other is provided with a boss that slides with the sliding groove. The docking seat is provided with a first pin hole and a first fixing hole, and the docking end joint is provided with a second pin hole and a second fixing hole.

[0013] Connecting the two outer wing assembly frames to the two ends of the central wing assembly frame respectively, including:

[0014] The outer wing assembly frame is installed to the position where it docks with the central wing assembly frame by sliding fit between the boss and the slide groove, so that the first pin hole is aligned with the second pin hole and the first fixing hole is aligned with the second fixing hole.

[0015] Insert the docking positioning pin into the first pin hole and the second pin hole;

[0016] Connect the fasteners to the first fixing hole and the second fixing hole respectively.

[0017] Optionally, the central wing includes a lower skin of the central wing, a central wing frame, a first connecting seat, a lower skin of the flap, a second connecting seat, a flap frame, an upper skin of the flap, and an upper skin of the central wing.

[0018] Assemble the central wing on the central wing assembly jig, including:

[0019] Position the lower skin of the central wing onto the central wing assembly frame;

[0020] The central wing frame is mounted onto the lower skin of the central wing;

[0021] One end of the first connecting seat is connected to the central wing frame, and the first connecting seat is used to connect the outer wing;

[0022] Position the lower flap skin onto the central wing assembly frame;

[0023] Connect the second connecting seat to the central wing frame;

[0024] Install the flap frame onto the lower flap skin and connect the flap frame to the second connecting seat;

[0025] The upper skin of the central wing is installed onto the central wing frame, and the upper skin of the flap is installed onto the flap frame.

[0026] Optionally, the central wing frame includes wing spars and wing ribs;

[0027] Mounting the central wing frame onto the central wing underskin includes:

[0028] Along the width direction of the central wing assembly frame, the wing ribs and wing spars are installed sequentially onto the lower skin of the central wing, following the pattern of first installing the wing ribs, then installing the wing spars, and repeating the alternating installation of the wing ribs and wing spars.

[0029] Optionally, the wing rib and the wing spars are sequentially mounted onto the central wing underside skin, including:

[0030] Along the width direction of the central wing assembly frame, the wing ribs and wing spars are pre-installed onto the lower skin of the central wing in a manner that involves first installing the wing ribs, then installing the wing spars, and repeating the alternating installation of the wing ribs and wing spars.

[0031] The positions of each of the ribs and spars are marked respectively;

[0032] Remove each of the aforementioned ribs and each of the aforementioned spars;

[0033] The bonding locations of each of the ribs and spars are sanded and glued.

[0034] Along the width direction of the central wing assembly frame, the wing ribs are installed first, followed by the wing spars, and the wing ribs and wing spars are installed alternately and repeatedly, and the wing ribs and wing spars are fixed to the lower skin of the central wing according to the marked positions.

[0035] Optionally, the central wing assembly frame is provided with a first positioning seat, a second positioning seat and a first positioning block. The first positioning seat is provided with a first positioning hole, and the first positioning block can be adjusted to be connected to the second positioning seat along the height direction of the central wing assembly frame.

[0036] The wing ribs and wing spars are sequentially installed onto the lower skin of the central wing, including:

[0037] Place the wing sparb onto the central wing underskin, align the process hole of the wing sparb with the first positioning hole, and insert the positioning pin into the process hole and the first positioning hole to complete the positioning of the wing sparb.

[0038] The rib is placed on the lower skin of the central wing, so that the end of the rib away from the lower skin of the central wing is in contact with one side of the first positioning block, thus completing the positioning of the rib along the length direction of the central wing assembly frame.

[0039] Optionally, the central wing assembly frame is provided with a lower contour support plate, a second positioning block, and a third positioning block;

[0040] Positioning the lower central wing skin onto the central wing assembly frame includes:

[0041] Place the central wing underside skin onto the lower contour support plate;

[0042] The end of the central wing underskin in the width direction is fastened to the second positioning block;

[0043] The end of the central wing lower skin that faces the flap lower skin along its length is fastened to the third positioning block.

[0044] Optionally, the method of assembling the outer wing on the outer wing assembly frame is the same as the method of assembling the central wing on the central wing assembly frame.

[0045] Optionally, connecting the two outer wings to the two ends of the central wing respectively includes:

[0046] Connect the third connecting seat of the outer wing to the first connecting seat.

[0047] A wing assembly apparatus is used to assemble a wing using any of the above-described wing assembly methods. The wing includes a central wing and two outer wings respectively disposed at both ends of the central wing. The wing assembly apparatus includes:

[0048] A central wing assembly frame is used to assemble the central wing, and docking seats are respectively provided at both ends of the central wing assembly frame;

[0049] Two outer wing assembly frames are used to assemble the two outer wings respectively. The outer wing assembly frames are provided with docking end joints, which are used to detachably connect with the docking seat.

[0050] Optionally, one of the docking seat and the docking end joint is provided with a sliding groove, and the other is provided with a boss that slides with the sliding groove. The docking seat is provided with a first pin hole and a first fixing hole, and the docking end joint is provided with a second pin hole and a second fixing hole. The first pin hole is used to connect with the second pin hole through a docking positioning pin, and the first fixing hole is used to connect with the second fixing hole through a fastener.

[0051] Optionally, the central wing includes a wing spars, and the central wing assembly is provided with a first positioning seat. The first positioning seat is provided with a first positioning hole, which is used to align with the process hole of the wing spars and connect through a positioning pin.

[0052] Optionally, the central wing includes a wing rib, and the central wing assembly frame is provided with a second positioning seat and a first positioning block. The first positioning block is adjustablely connected to the second positioning seat along the height direction of the central wing assembly frame, and the first positioning block is used to limit the wing rib along the length direction of the central wing assembly frame.

[0053] Optionally, the central wing assembly frame is provided with:

[0054] The lower contour support plate is used to provide matching support for the lower skin of the central wing;

[0055] The second positioning block is used to clamp the end of the central wing lower skin in the width direction;

[0056] The third positioning block is used to clamp the end of the central wing lower skin along its length and facing the flap lower skin.

[0057] Optionally, the positioning structure of the outer wing assembly frame for positioning the outer wing is the same as the positioning structure of the central wing assembly frame for positioning the central wing.

[0058] The wing assembly method provided by this invention has at least the following beneficial effects:

[0059] Assemble the center wing and the two outer wings separately on different assembly jigs, allowing for simultaneous assembly of the center wing and the two outer wings. This saves assembly time and improves efficiency. After the center wing and the two outer wings are assembled, the outer wing assembly jig with the outer wings attached is hoisted to a docking position with the center wing assembly jig, allowing direct docking. Then, the outer wings on the outer wing assembly jig are connected to the center wing. This connection method avoids disassembling the assembled outer wings and their assembly jigs, and then reinstalling the assembled outer wings onto the center wing assembly jig. In other words, this solution avoids secondary installation and positioning of the assembled outer wings, eliminates the need to change tooling for the center wing or the outer wings, simplifies the assembly process, further improves efficiency, and enhances assembly accuracy.

[0060] The wing assembly apparatus provided by the present invention is used to implement the above-mentioned wing assembly method and has at least the beneficial effects of the above-mentioned wing assembly method. Attached Figure Description

[0061] To more clearly illustrate the technical solutions in the embodiments of the present invention or related technologies, the drawings used in the description of the embodiments or related technologies will be briefly introduced below. Obviously, the drawings described below are only embodiments of the present invention. For those skilled in the art, other drawings can be obtained based on the provided drawings without creative effort.

[0062] Figure 1 A flowchart illustrating the wing assembly method provided in a specific embodiment of the present invention;

[0063] Figure 2 A flowchart showing how to connect the two outer wing assembly frames to the two ends of the central wing assembly frame;

[0064] Figure 3 A flowchart illustrating the assembly of the center wing on the center wing assembly jig;

[0065] Figure 4This is a schematic diagram of the structure of the wing assembly device provided in a specific embodiment of the present invention;

[0066] Figure 5 This is a structural schematic diagram of the central wing assembly frame;

[0067] Figure 6 This is a structural schematic diagram of the outer wing assembly frame;

[0068] Figure 7 A structural diagram showing the connection point between the outer wing assembly frame and the central wing assembly frame;

[0069] Figure 8 This is a partial structural diagram of the central wing assembly frame.

[0070] Figure label:

[0071] 1-Central wing assembly frame; 11-Dating seat; 111-Slide groove; 12-First positioning seat; 13-Second positioning seat; 14-First positioning block; 15-Lower contour support plate; 2-Outer wing assembly frame; 21-Dating end connector; 211-Boss; 3-Dating positioning pin; 4-Fastener. Detailed Implementation

[0072] The technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0073] The core of this invention is to provide a wing assembly method to improve wing assembly efficiency. Another core aspect of this invention is to provide a wing assembly apparatus for implementing the aforementioned wing assembly method, thereby improving wing assembly efficiency.

[0074] Please refer to Figure 1 This invention provides a wing assembly method for assembling an aircraft wing, the wing including a central wing and two outer wings respectively disposed at both ends of the central wing, the wing assembly method including S1 to S3:

[0075] S1: Assemble the central wing onto the central wing mounting frame 1 (e.g.) Figure 4 As shown), assemble the two outer wings on the two outer wing assembly frames 2 respectively (as shown). Figure 4 As shown) assembled on the assembly;

[0076] S2: Hoist the two outer wing assembly frames 2 with the outer wings assembled to the two ends of the central wing assembly frame 1 with the central wing assembled, and connect the two outer wing assembly frames 2 to the two ends of the central wing assembly frame 1 respectively.

[0077] S3: Connect the two outer wings to the corresponding ends of the central wing.

[0078] In other words, in this embodiment of the invention, the central wing and the two outer wings are assembled on different assembly frames, allowing the assembly of the central wing and the two outer wings to be carried out simultaneously, thereby saving wing assembly time and improving assembly efficiency. Simultaneously, after the central wing and the two outer wings are assembled separately, the outer wing assembly frame 2 with the outer wings is hoisted as a whole to a position where it docks with the central wing assembly frame 1, allowing the outer wing assembly frame 2 to directly dock with the central wing assembly frame 1 with the central wing assembled on it. Based on this, the outer wings on the outer wing assembly frame 2 are then connected to the central wing. This connection method avoids disassembling the assembled outer wings and outer wing assembly frame 2, and then installing the assembled outer wings onto the central wing assembly frame 1. In other words, this solution avoids secondary installation and positioning of the assembled outer wings, eliminates the need to change tooling for the central wing or outer wings, simplifies the assembly steps, further improves assembly efficiency, and is conducive to improving assembly accuracy.

[0079] To facilitate the connection between the outer wing assembly frame 2 and the central wing assembly frame 1, such as Figure 5 , Figure 6 and Figure 7 As shown, in some embodiments, the central wing assembly frame 1 is provided with a docking seat 11, and the outer wing assembly frame 2 is provided with a docking end connector 21. One of the docking seat 11 and the docking end connector 21 is provided with a sliding groove 111, and the other is provided with a boss 211 that slides with the sliding groove 111. The docking seat 11 is provided with a first pin hole and a first fixing hole, and the docking end connector 21 is provided with a second pin hole and a second fixing hole.

[0080] Please refer to Figure 2 Connect the two outer wing assembly frames 2 to the two ends of the central wing assembly frame 1 respectively, including steps S21-S23:

[0081] S21: Install the outer wing assembly frame 2 into the position where it is connected to the central wing assembly frame 1 by sliding fit between the boss 211 and the slide groove 111, so that the first pin hole is aligned with the second pin hole and the first fixing hole is aligned with the second fixing hole.

[0082] S22: Insert the docking positioning pin 3 into the first pin hole and the second pin hole;

[0083] S23: Connect the fastener 4 to the first fixing hole and the second fixing hole respectively.

[0084] In other words, when the outer wing assembly frame 2 with the outer wing is hoisted to the position where it docks with the central wing assembly frame 1, the boss 211 slides into the slide groove 111, allowing the outer wing assembly frame 2 to slide into place along the direction defined by the slide groove 111. At this point, the first pin hole aligns with the second pin hole, and the first fixing hole aligns with the second fixing hole. Then, the docking positioning pin 3 is inserted into the first and second pin holes, positioning the outer wing assembly frame 2 and the central wing assembly frame 1 relative to each other. Finally, the fasteners 4 are connected to the first and second fixing holes respectively, thus fixing the outer wing assembly frame 2 and the central wing assembly frame 1. This solution enables rapid docking of the outer wing assembly frame 2 and the central wing assembly frame 1 without the need for additional auxiliary docking devices.

[0085] It should be noted that this embodiment does not limit the length direction of the slide groove 111. Exemplarily, the length direction of the slide groove 111 is the width direction of the central wing assembly frame 1 or the outer wing assembly frame 2. That is, the outer wing assembly frame 2 and the central wing assembly frame 1 are aligned by the sliding of the boss 211 along the width direction of the central wing assembly frame 1 or the outer wing assembly frame 2. Furthermore, this embodiment does not limit the number of the first fixing holes and the second fixing holes. Exemplarily, there are four first fixing holes and four second fixing holes, each distributed in a quadrilateral shape. Each first fixing hole corresponds to one second fixing hole, and the first fixing hole and the corresponding second fixing hole are connected by a locking bolt. Additionally, exemplarily, the docking positioning pin 3 is a cylindrical conical guide structure, facilitating quick insertion into the first pin hole and the second pin hole during docking for initial positioning.

[0086] Furthermore, the above embodiments do not limit the specific method of assembling the central wing on the central wing assembly frame 1, as long as the central wing is assembled on the central wing assembly frame 1.

[0087] Please refer to Figure 3 In some embodiments, the central wing includes a central wing lower skin, a central wing frame, a first connecting seat, a flap lower skin, a second connecting seat, a flap frame, a flap upper skin, and a central wing upper skin.

[0088] Assemble the center wing on the center wing assembly jig 1, including steps S11-S17:

[0089] S11: Position the lower skin of the central wing onto the central wing assembly frame 1;

[0090] S12: Install the central wing frame onto the lower skin of the central wing;

[0091] S13: Connect one end of the first connecting seat to the central wing frame. The first connecting seat is used to connect the outer wing.

[0092] S14: Position the lower flap skin onto the central wing assembly frame 1;

[0093] S15: Connect the second connecting seat to the central wing frame;

[0094] S16: Install the flap frame onto the lower flap skin and connect the flap frame to the second connecting seat;

[0095] S17: Install the upper skin of the center wing onto the center wing frame, and install the upper skin of the flaps onto the flap frame.

[0096] In other words, when assembling the central wing on the central wing assembly jig 1, the lower skin of the central wing is installed first, followed by the central wing frame, then the first connecting seat, and subsequently the lower flap skin, second connecting seat, and flap frame. Finally, the upper central wing skin and upper flap skin are installed. This design, after the central wing frame is installed, uses the central wing frame as a reference to install the first and second connecting seats, and then installs the flap frame, etc., which facilitates the positioning of each structural component.

[0097] Furthermore, in some embodiments, the central wing frame includes spars and ribs;

[0098] Installing the central wing frame onto the lower skin of the central wing includes:

[0099] Along the width direction of the central wing assembly frame 1, install the wing ribs first, then the wing spars, and repeat the alternating installation of the wing ribs and wing spars in sequence onto the lower skin of the central wing.

[0100] In other words, the central wing frame includes multiple spars and multiple ribs. In this embodiment, the wing is assembled in the order of the first rib, the first spar, the second rib, the second spar, the third rib, the third spar, and so on, until the last spar and the last rib. In this way, the spars can be used to limit the width of the ribs, and the ribs can be used to limit the width of the spars, which helps to ensure the accurate and reliable positioning of the central wing frame.

[0101] It should be noted that this embodiment does not limit the specific number of wing spars and wing ribs. For example, the central wing frame includes three wing spars, that is, the wing adopts a three-spar design. The three wing spars are spaced apart along the width direction of the wing. In addition, the central wing frame includes 11 wing ribs. The 11 wing ribs are divided into four rows along the width direction of the wing. A wing spar is set between any two adjacent rows of wing ribs. The wing ribs in the same row are spaced apart along the length direction of the wing spars.

[0102] Furthermore, in some embodiments, the wing ribs and wing spars are sequentially mounted onto the central wing lower skin, including:

[0103] Along the width direction of the central wing assembly frame 1, install the wing ribs first, then the wing spars, and repeat the alternating installation of the wing ribs and wing spars to pre-install the wing ribs and wing spars onto the lower skin of the central wing.

[0104] Mark the positions of each rib and each spars;

[0105] Remove all wing ribs and wing spars;

[0106] Grind and apply adhesive to the bonding areas of each rib and each spars.

[0107] Along the width of the central wing assembly frame 1, install the wing ribs first, then the wing spars, and repeat the alternating installation of the wing ribs and wing spars, fixing the wing ribs and wing spars to the lower skin of the central wing according to the marked positions.

[0108] In other words, during the installation of wing ribs and wing spars, the wing ribs and wing spars are pre-assembled separately. Along the width of the central wing assembly frame 1, the wing ribs are installed first, then the wing spars, and this process is repeated alternately. The wing ribs and wing spars are pre-assembled sequentially onto the central wing lower skin to complete the positioning and fixation of the wing ribs and wing spars. The contact positions between the wing spars and the central wing lower skin are marked. Then, each wing rib and wing spar is removed. The bonding positions of each wing rib and wing spar are sanded and glued. Then, along the width of the central wing assembly frame 1, the wing ribs are installed first, then the wing spars, and this process is repeated alternately. The wing ribs and wing spars are then fixed to the central wing lower skin again according to the marked positions. This scheme, through pre-assembly, marking, disassembly, treatment of bonding positions, and secondary installation, achieves the installation of wing ribs and wing spars, which helps ensure the accuracy of the overall positioning of the central wing frame and the reliability of the installation.

[0109] Furthermore, such as Figure 8 As shown, in some embodiments, the central wing assembly frame 1 is provided with a first positioning seat 12, a second positioning seat 13 and a first positioning block 14. The first positioning seat 12 is provided with a first positioning hole, and the first positioning block 14 can be adjusted to be connected to the second positioning seat 13 along the height direction of the central wing assembly frame 1.

[0110] The wing ribs and wing spars are sequentially installed onto the underside skin of the central wing, including:

[0111] Place the wing sparb onto the lower skin of the central wing, align the process hole of the wing sparb with the first positioning hole, insert the positioning pin into the process hole and the first positioning hole to complete the positioning of the wing sparb;

[0112] Place the rib onto the lower skin of the central wing, so that the end of the rib away from the lower skin of the central wing is in contact with one side of the first positioning block 14, thus completing the positioning of the rib along the length of the central wing assembly frame 1.

[0113] It is understandable that the wing spars are continuous structures with process holes along their width. The wing spars are placed on the central wing underskin, aligning their process holes with the first positioning holes of the first positioning seat 12. Then, a positioning pin is inserted to complete the wing spar positioning. It should be noted that the number of first positioning seats 12 can be equal to the number of wing spars, and one first positioning seat 12 corresponds to one wing spar.

[0114] In addition, this embodiment uses a first positioning block 14 to stop and limit the wing rib on one side, thereby limiting the position of the wing rib along the length direction of the central wing assembly frame 1. It is understood that the wing rib's width direction limitation along the central wing assembly frame 1 can be achieved by the installed wing beam, and the outermost wing rib's width direction limitation along the central wing assembly frame 1 can be achieved by the longitudinal beam of the central wing assembly frame 1. Furthermore, it is understood that the first positioning block 14 can be adjusted to a suitable position along the height direction of the central wing assembly frame 1 to limit wing ribs of different sizes at the edge. Exemplarily, a second positioning seat 13 is provided on the upper contour support plate, which is used to press and limit the upper skin of the central wing.

[0115] In some embodiments, the central wing assembly frame 1 is provided with a lower contour support plate 15, a second positioning block and a third positioning block;

[0116] Positioning the lower skin of the central wing onto the central wing assembly frame 1 includes:

[0117] Place the lower skin of the central wing onto the lower contour support plate 15;

[0118] Secure the end of the central wing lower skin in the width direction to the second positioning block;

[0119] Secure the end of the central wing lower skin along its length that faces the flap lower skin to the third positioning block.

[0120] In other words, this embodiment uses a lower contour support plate 15 to make the arc surface of the lower skin of the central wing fit against the lower contour support plate 15, so that the lower contour support plate 15 supports the lower skin of the central wing, which improves the support effect and enhances the reliability of the support for the lower skin of the central wing. At the same time, this embodiment uses a second positioning block to clamp the end of the lower skin of the central wing in the width direction, and a third positioning block to clamp the end of the lower skin of the central wing in the length direction facing the lower skin of the flap, thereby realizing the positioning and fixing of the lower skin of the central wing, which helps to improve the reliability of the installation position of the lower skin of the central wing.

[0121] Additionally, it should be noted that when installing the wing ribs, the wing ribs can be aligned with the lower contour support plate 15. That is, the arrangement of the lower contour support plate 15 is set according to the position of the wing ribs. This alignment of the wing ribs with the lower contour support plate 15 helps to improve the reliability of the lower contour support plate 15 in supporting the overall wing.

[0122] It should be noted that the above embodiments do not specifically limit the method of assembling the outer wing on the outer wing assembly frame 2, as long as the assembly of the outer wing on the outer wing assembly frame 2 can be achieved.

[0123] In some embodiments, the method of assembling the outer wing on the outer wing assembly frame 2 is the same as the method of assembling the central wing on the central wing assembly frame 1.

[0124] In other words, following the method described above for installing the central wing on the central wing assembly frame 1, the outer wing is installed onto the outer wing assembly frame 2 in the same manner. That is, the outer wing lower skin, outer wing frame, third connecting seat, outer wing aileron lower skin, fourth connecting seat, outer wing aileron frame, outer wing upper skin, and outer wing aileron upper skin are installed in sequence. This achieves process reuse between the central wing and the outer wing, reducing the difficulty of on-site operation.

[0125] It is understandable that the positioning components on the outer wing assembly frame 2 and the positioning components on the central wing assembly frame 1 (such as the first positioning seat 12, the second positioning seat 13, the first positioning block 14, the lower contour support plate 15, the second positioning block and the third positioning block, etc.) have the same structure and the same positioning method, so as to achieve the unified assembly standard of the outer wing and the central wing, which is conducive to achieving the consistency of the overall wing size and solving the problem of large size deviation between the central wing and the outer wing in related technologies.

[0126] In addition, in some embodiments, the two outer wings are respectively connected to the two ends of the central wing, including:

[0127] Connect the third connecting seat of the outer wing to the first connecting seat.

[0128] In other words, during the outer wing assembly process, after the outer wing frame is installed, the third connecting seat is connected to the outer wing frame. After the two outer wing assembly frames 2 are respectively connected to the two ends of the central wing assembly frame 1, the connecting holes of the first connecting seat and the third connecting seat are enlarged and reamed using hole-expanding and hole-reaming tools, in conjunction with the hole-reaming auxiliary device, so that the first connecting seat and the third connecting seat are connected, thus realizing the connection between the outer wing and the central wing.

[0129] In addition to the wing assembly methods mentioned above, such as Figure 4 , Figure 5 , Figure 6 and Figure 7 As shown, this embodiment of the invention also provides a wing assembly device, which is used to assemble a wing using the wing assembly method disclosed in any of the above embodiments. The wing includes a central wing and two outer wings respectively disposed at both ends of the central wing. The wing assembly device includes a central wing assembly frame 1 and two outer wing assembly frames 2. The central wing assembly frame 1 is used to assemble the central wing, and docking seats 11 are respectively provided at both ends of the central wing assembly frame 1. The two outer wing assembly frames 2 are used to assemble the two outer wings respectively. The outer wing assembly frames 2 are provided with docking end connectors 21, and the docking end connectors 21 are used to detachably connect with the docking seats 11.

[0130] In other words, this embodiment of the invention uses a central wing assembly frame 1 to assemble the central wing and an outer wing assembly frame 2 to assemble the outer wing. Then, the outer wing assembly frame 2 is joined to the central wing assembly frame 1, connecting the docking seat 11 of the central wing assembly frame 1 to the docking end connector 21 of the outer wing assembly frame 2. After the outer wing assembly frame 2 is connected to the central wing assembly frame 1, the central wing assembled on the central wing assembly frame 1 is connected to the outer wing assembled on the outer wing assembly frame 2. This solution avoids disassembling the assembled outer wing and the outer wing assembly frame 2, and then installing the assembled outer wing onto the central wing assembly frame 1. This allows for simultaneous assembly of the central wing and outer wing on different assembly frames, improving assembly efficiency. Furthermore, it avoids secondary installation and positioning of the assembled outer wing, eliminating the need to change tooling for either the central wing or the outer wing, simplifying the assembly steps, further improving assembly efficiency, and enhancing assembly accuracy.

[0131] In some embodiments, one of the docking seat 11 and the docking end connector 21 is provided with a groove 111, and the other is provided with a boss 211 that slides and engages with the groove 111. The docking seat 11 is provided with a first pin hole and a first fixing hole, and the docking end connector 21 is provided with a second pin hole and a second fixing hole. The first pin hole is used to connect with the second pin hole through a docking positioning pin 3, and the first fixing hole is used to connect with the second fixing hole through a fastener 4.

[0132] The specific connection method between the docking seat 11 and the docking end connector 21 can be referred to the description of the corresponding embodiment of the wing assembly method above, and will not be repeated here.

[0133] like Figure 8 As shown, in some embodiments, the central wing includes a wing spars, and the central wing assembly frame 1 is provided with a first positioning seat 12. The first positioning seat 12 is provided with a first positioning hole, which is used to align with the process hole of the wing spars and connect through a positioning pin.

[0134] In other words, this embodiment uses the first positioning seat 12 to position the wing beam. The wing beam is a continuous structure, and process holes are provided on the side of the wing beam along its width direction. The wing beam is placed on the central wing lower skin, with its process holes aligned with the first positioning holes of the first positioning seat 12. Then, the positioning pin is inserted to complete the positioning of the wing beam.

[0135] like Figure 8 As shown, in some embodiments, the central wing includes a wing rib, and the central wing assembly frame 1 is provided with a second positioning seat 13 and a first positioning block 14. The first positioning block 14 can be adjusted to be connected to the second positioning seat 13 along the height direction of the central wing assembly frame 1. The first positioning block 14 is used to limit the wing rib along the length direction of the central wing assembly frame 1.

[0136] In other words, this embodiment uses a first positioning block 14 to stop and limit the wing rib on one side, thereby limiting the position of the wing rib along the length direction of the central wing assembly frame 1. It is understood that the wing rib's width direction limitation along the central wing assembly frame 1 can be achieved by the installed wing beam, and the outermost wing rib's width direction limitation along the central wing assembly frame 1 can be achieved by the longitudinal beam of the central wing assembly frame 1. Furthermore, it is understood that the first positioning block 14 can be adjusted to a suitable position along the height direction of the central wing assembly frame 1 to limit wing ribs of different sizes at the edge. Exemplarily, a second positioning seat 13 is provided on the upper contour support plate, which is used to press and limit the upper skin of the central wing.

[0137] like Figure 8 As shown, in some embodiments, the central wing assembly frame 1 is provided with a lower contour support plate 15, a second positioning block and a third positioning block. The lower contour support plate 15 is used to provide matching support for the lower skin of the central wing; the second positioning block is used to clamp the end of the lower skin of the central wing in the width direction; and the third positioning block is used to clamp the end of the lower skin of the central wing in the length direction and facing the lower skin of the flap.

[0138] In other words, this embodiment uses a lower contour support plate 15 to make the arc surface of the lower skin of the central wing fit against the lower contour support plate 15, so that the lower contour support plate 15 supports the lower skin of the central wing, which improves the support effect and enhances the reliability of the support for the lower skin of the central wing. At the same time, this embodiment uses a second positioning block to clamp the end of the lower skin of the central wing in the width direction, and a third positioning block to clamp the end of the lower skin of the central wing in the length direction facing the lower skin of the flap, thereby realizing the positioning and fixing of the lower skin of the central wing, which helps to improve the reliability of the installation position of the lower skin of the central wing.

[0139] In some embodiments, the positioning structure of the outer wing assembly frame 2 for positioning the outer wing is the same as the positioning structure of the central wing assembly frame 1 for positioning the central wing.

[0140] In other words, in this embodiment, the positioning method of the outer wing assembly frame 2 for each component of the outer wing is the same as the positioning method of the central wing assembly frame 1 for each component of the central wing. This achieves a unified assembly standard for the outer wing and the central wing, which is conducive to achieving consistency in the overall size of the wing and solving the problem of large size deviation between the central wing and the outer wing in related technologies.

[0141] It should also be noted that, in this specification, relational terms such as first and second are used only to distinguish one entity or operation from another entity or operation, and do not necessarily require or imply any such actual relationship or order between these entities or operations.

[0142] The various embodiments in this specification are described in a progressive manner, with each embodiment focusing on the differences from other embodiments. The same or similar parts between the various embodiments can be referred to each other.

[0143] The wing assembly method and wing assembly device provided by the present invention have been described in detail above. Specific examples have been used to illustrate the principles and implementation methods of the present invention. The descriptions of the above embodiments are only for the purpose of helping to understand the method and core ideas of the present invention. It should be noted that those skilled in the art can make several improvements and modifications to the present invention without departing from the principles of the present invention, and these improvements and modifications also fall within the protection scope of the present invention.

Claims

1. A method for assembling an airfoil, characterized in that, For assembling an aircraft wing, the wing includes a central wing and two outer wings respectively disposed at both ends of the central wing, and the wing assembly method includes: The central wing is assembled on the central wing assembly frame (1), and the two outer wings are assembled on the two outer wing assembly frames (2) respectively. The two outer wing assembly frames (2) assembled with the outer wings are respectively hoisted to the two ends of the central wing assembly frame (1) assembled with the central wing, and the two outer wing assembly frames (2) are respectively connected to the two ends of the central wing assembly frame (1). The two outer wings are respectively connected to the two ends of the central wing.

2. The wing assembly method according to claim 1, characterized in that, The central wing assembly frame (1) is provided with a docking seat (11), and the outer wing assembly frame (2) is provided with a docking end connector (21). One of the docking seat (11) and the docking end connector (21) is provided with a sliding groove (111), and the other is provided with a boss (211) that slides with the sliding groove (111). The docking seat (11) is provided with a first pin hole and a first fixing hole, and the docking end connector (21) is provided with a second pin hole and a second fixing hole. Connecting the two outer wing assembly frames (2) to the two ends of the central wing assembly frame (1) respectively, including: The outer wing assembly frame (2) is slidably installed into the position where it docks with the central wing assembly frame (1) through the boss (211) and the slide groove (111), so that the first pin hole is aligned with the second pin hole and the first fixing hole is aligned with the second fixing hole; Insert the docking positioning pin (3) into the first pin hole and the second pin hole; Connect the fastener (4) to the first fixing hole and the second fixing hole respectively.

3. The wing assembly method according to claim 1, characterized in that, The central wing includes a lower skin of the central wing, a central wing frame, a first connecting seat, a lower skin of the flap, a second connecting seat, a flap frame, an upper skin of the flap, and an upper skin of the central wing. Assemble the central wing on the central wing assembly frame (1), including: Position the lower skin of the central wing onto the central wing assembly frame (1); The central wing frame is mounted onto the lower skin of the central wing; One end of the first connecting seat is connected to the central wing frame, and the first connecting seat is used to connect the outer wing; Position the lower flap skin onto the central wing assembly frame (1); Connect the second connecting seat to the central wing frame; Install the flap frame onto the lower flap skin and connect the flap frame to the second connecting seat; The upper skin of the central wing is installed onto the central wing frame, and the upper skin of the flap is installed onto the flap frame.

4. The wing assembly method according to claim 3, characterized in that, The central wing frame includes wing spars and wing ribs; Mounting the central wing frame onto the central wing underskin includes: Along the width direction of the central wing assembly frame (1), the wing ribs and wing beams are installed sequentially onto the lower skin of the central wing in the manner of first installing the wing ribs, then installing the wing beams, and repeating the alternating installation of the wing ribs and wing beams.

5. The wing assembly method according to claim 4, characterized in that, The wing ribs and wing spars are sequentially installed onto the lower skin of the central wing, including: Along the width direction of the central wing assembly frame (1), the wing ribs and wing beams are pre-installed onto the lower skin of the central wing in the manner of first installing the wing ribs, then installing the wing beams, and repeating the alternating installation of the wing ribs and wing beams. The positions of each of the ribs and spars are marked respectively; Remove each of the aforementioned ribs and each of the aforementioned spars; The bonding locations of each of the ribs and spars are sanded and glued. Along the width direction of the central wing assembly frame (1), the wing ribs are installed first, then the wing spars are installed, and the wing ribs and wing spars are installed alternately and repeatedly, and the wing ribs and wing spars are fixed to the lower skin of the central wing according to the marked positions.

6. The wing assembly method according to claim 4, characterized in that, The central wing assembly frame (1) is provided with a first positioning seat (12), a second positioning seat (13) and a first positioning block (14). The first positioning seat (12) is provided with a first positioning hole, and the first positioning block (14) can be connected to the second positioning seat (13) in an adjustable position along the height direction of the central wing assembly frame (1). The wing ribs and wing spars are sequentially installed onto the lower skin of the central wing, including: Place the wing sparb onto the central wing underskin, align the process hole of the wing sparb with the first positioning hole, and insert the positioning pin into the process hole and the first positioning hole to complete the positioning of the wing sparb. Place the rib on the lower skin of the central wing, so that the end of the rib away from the lower skin of the central wing is attached to one side of the first positioning block (14), thus completing the positioning of the rib along the length direction of the central wing assembly frame (1).

7. The wing assembly method according to claim 3, characterized in that, The central wing assembly frame (1) is provided with a lower contour support plate (15), a second positioning block and a third positioning block; Positioning the lower skin of the central wing onto the central wing assembly frame (1) includes: Place the central wing lower skin onto the lower contour support plate (15); The end of the central wing underskin in the width direction is fastened to the second positioning block; The end of the central wing lower skin that faces the flap lower skin along its length is fastened to the third positioning block.

8. The wing assembly method according to any one of claims 3-7, characterized in that, The method of assembling the outer wing on the outer wing assembly frame (2) is the same as the method of assembling the central wing on the central wing assembly frame (1).

9. The wing assembly method according to any one of claims 3-7, characterized in that, Connecting the two outer wings to the two ends of the central wing respectively includes: Connect the third connecting seat of the outer wing to the first connecting seat.

10. A wing assembly device, characterized in that, A wing assembly device is used to assemble a wing using the wing assembly method according to any one of claims 1-9, the wing comprising a central wing and two outer wings respectively disposed at both ends of the central wing, the wing assembly device comprising: A central wing assembly frame (1) is used to assemble the central wing, and docking seats (11) are respectively provided at both ends of the central wing assembly frame (1). Two outer wing assembly frames (2) are used to assemble the two outer wings respectively. The outer wing assembly frames (2) are provided with docking end connectors (21), which are used to detachably connect with the docking seat (11).

11. The wing assembly apparatus according to claim 10, characterized in that, One of the docking seat (11) and the docking end connector (21) is provided with a groove (111), and the other is provided with a boss (211) that slides and engages with the groove (111). The docking seat (11) is provided with a first pin hole and a first fixing hole, and the docking end connector (21) is provided with a second pin hole and a second fixing hole. The first pin hole is used to connect with the second pin hole through a docking positioning pin (3), and the first fixing hole is used to connect with the second fixing hole through a fastener (4).

12. The wing assembly apparatus according to claim 10, characterized in that, The central wing includes a wing spars. The central wing assembly frame (1) is provided with a first positioning seat (12). The first positioning seat (12) is provided with a first positioning hole. The first positioning hole is used to align with the process hole of the wing spars and is connected by a positioning pin.

13. The wing assembly apparatus according to claim 10, characterized in that, The central wing includes a wing rib. The central wing assembly frame (1) is provided with a second positioning seat (13) and a first positioning block (14). The first positioning block (14) can be connected to the second positioning seat (13) in an adjustable position along the height direction of the central wing assembly frame (1). The first positioning block (14) is used to limit the wing rib along the length direction of the central wing assembly frame (1).

14. The wing assembly apparatus according to claim 10, characterized in that, The central wing assembly frame (1) is provided with: The lower contour support plate (15) is used to provide matching support for the lower skin of the central wing; The second positioning block is used to clamp the end of the central wing lower skin in the width direction; The third positioning block is used to clamp the end of the central wing lower skin along its length and facing the flap lower skin.

15. The wing assembly apparatus according to any one of claims 10-14, characterized in that, The positioning structure of the outer wing assembly frame (2) for positioning the outer wing is the same as the positioning structure of the central wing assembly frame (1) for positioning the central wing.

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