Integral bonding system and integral bonding method for aircraft composite fuselage panels

Abstract

This invention provides an integral bonding system and method for composite material fuselage panels of aircraft. The integral bonding system includes a fixed support device, an integral bonding positioning device, a movable support device, and a molding device. The fixed support device includes a support member. The integral bonding positioning device is connected to the support member and is rotatable relative to the support member. The integral bonding positioning device includes a cylindrical load-bearing body and connecting members at both ends of the load-bearing body. The load-bearing body can accommodate multiple sets of stringers, and the connecting members are connected to the support member. The movable support device is located below the fixed support device and is configured to move relative to the fixed support device. The molding device is located on the movable support device and is configured to accommodate a skin panel. According to the above-described solution of this application, it is beneficial for the mass production of large-size fuselage panels, thereby improving manufacturing efficiency.

Description

Technical Field

[0001] This invention relates to the field of automated manufacturing of composite material parts, and in particular to an integral bonding system and method for composite material fuselage panels of aircraft. Background Technology

[0002] For example, carbon fiber resin-based composite materials are widely used in aerospace structural components due to their excellent properties, such as stiffened panels for large passenger aircraft. For stiffened panels, the manufacturing processes mainly involve two routes: co-bonding and co-curing. For co-bonding, the cap-shaped stringer must be cured first, and then bonded to the uncured skin. This process requires extremely high precision in the stringer's axial position, but achieving accurate positioning in panels that are tens of meters long is extremely difficult.

[0003] Current technologies primarily rely on customized bonding fixtures for overall bonding. Each bonding positioning fixture corresponds to only a single panel configuration. During use, a gantry crane is needed to lift the fixture, transfer it above the forming fixture, control the crane's descent, and combine it with the forming fixture to complete the bonding process between the stringer and the skin. This solution requires multiple connection and lifting processes to complete a single panel bonding, resulting in low manufacturing efficiency. Furthermore, the gantry crane is needed to align and combine the bonding positioning fixture with the curing and forming fixture, requiring repeated adjustments during alignment, making operation difficult. This process also suffers from poor stability, easily causing the stringer to detach from the fixture and damage the stringer components. Moreover, for the production of various fuselage panel configurations, different fixtures need to be switched repeatedly for connection and lifting processes, failing to meet the requirements for mass production and large-scale applications.

[0004] Therefore, there is a need to provide an integral bonding system and method for composite material fuselage panels of aircraft to at least partially solve the above problems. Summary of the Invention

[0005] According to one aspect of the present invention, an integral bonding system for composite fuselage panels of aircraft is provided. The fuselage panel includes a plurality of stringers and skins, wherein the integral bonding system comprises: A fixed support device, the fixed support device including a support member that can be placed on a horizontal support surface; An integral adhesive bonding and positioning device is connected to the support member and configured to rotate relative to the support member. The integral adhesive bonding and positioning device includes a cylindrical bearing body and connecting members disposed at both ends of the bearing body. The bearing body is configured to accommodate multiple sets of stringers, each set of stringers including multiple stringers corresponding to a single fuselage panel. The connecting members are connected to the support member so that the bearing body can be connected to the support member. A movable support device, wherein the movable support device is disposed below the fixed support device and is configured to be movable relative to the fixed support device; and A molding device, which is disposed on the movable support device and configured to allow the skin to be mounted thereon.

[0006] Preferably, the connecting member is detachably connected to the supporting member.

[0007] Preferably, the support member includes a first support seat and a second support seat spaced apart from the first support seat, the integral adhesive positioning device is connected between the first support seat and the second support seat, and the second support seat is configured to be horizontally movable relative to the first support seat.

[0008] Preferably, the fixed support device further includes a slide rail unit that extends along the length of the integral adhesive positioning device, and the second support seat is disposed on the slide rail unit and configured to slide along the slide rail unit.

[0009] Preferably, the connecting member is rotatably connected to the supporting member via a rotating member, so that the load-bearing body can rotate 360 ​​degrees relative to the supporting member.

[0010] Preferably, the fixed support device further includes a lifting component, which is disposed on the support component, and the connecting component is connected to the lifting component, so that the load-bearing body can move up and down in the vertical direction relative to the support component.

[0011] Preferably, the fixed support device further includes a drive component, which is electrically connected to the rotating component and / or the lifting component, so that the drive component can drive the movement of the rotating component and / or the lifting component.

[0012] Preferably, the lifting component is constructed as any one of the following: a lead screw and nut lifting mechanism, a hydraulic lifting mechanism, and a gear and rack lifting mechanism.

[0013] Preferably, the integral bonding system further includes an alignment device, which includes a positioning pin disposed on the support body and a positioning hole disposed on the molding device, wherein when the molding device is positioned below the integral bonding positioning device, the positioning pin can be inserted into the positioning hole.

[0014] Preferably, the alignment device further includes a guide light disposed at the end of the positioning pin, the guide light being configured to emit a laser beam in the same direction as the extension direction of the positioning pin.

[0015] Preferably, the alignment device includes a plurality of positioning pins and a plurality of positioning holes, the plurality of positioning holes having different shapes and / or sizes from one another.

[0016] Preferably, the movable support device is constructed as an AGV (Automated Guided Vehicle).

[0017] According to another aspect of the present invention, a method for integral bonding of composite material fuselage panels for aircraft is provided. The integral bonding method is performed using the integral bonding system described above, wherein the integral bonding method includes the following steps: S1. Connect the integral adhesive positioning device to the fixed support device; S2. Install one or more sets of long trusses on the supporting body, wherein the multiple sets of long trusses are arranged around the circumferential direction of the supporting body; S3. Rotate the overall gluing and positioning device so that one of the single or multiple sets of stringers is in the gluing posture. S4. Place the molding device on the movable support device and move the movable support device below the overall bonding positioning device, so that the skin is aligned with one of the single or multiple stringers in the bonding posture; and S5. Adhere one of the single or multiple sets of stringers to the skin.

[0018] Preferably, when installing multiple sets of stringers, the overall bonding method further includes: S6, repeating the above steps S3-S5 until the bonding of the multiple sets of stringers is completed.

[0019] Preferably, step S2 further includes: driving the overall adhesive positioning device to descend so as to install the multiple sets of long trusses on the supporting body.

[0020] Preferably, step S3 further includes: driving the integral adhesive positioning device to rise before or after rotating the integral adhesive positioning device.

[0021] Preferably, the integral bonding method further includes, after step S4: driving the integral bonding positioning device to descend and fine-tuning the movable support device so that the positioning pin on the bearing body and the positioning hole on the molding device are aligned.

[0022] The overall bonding system and method described above have the following technical advantages: 1. Compared with the traditional method of completing the bonding by controlling the bonding positioning fixture with a gantry crane, the above-mentioned solution of this application can use an integrated bonding system to correspond to the configuration of multiple wall panels of the whole body section, so as to complete the bonding process of multiple wall panels without changing the device. This is conducive to the mass production of large-size body wall panels and improves manufacturing efficiency.

[0023] 2. By using an AGV to transport the forming device, it can be aligned with the overall bonding and positioning device from below. Compared with the overhead crane control for alignment from above, this solution is more flexible, convenient, and easier to adjust, resulting in higher efficiency.

[0024] 3. A laser guide light is installed at the end of the positioning pin. By matching it with the positioning hole, initial positioning can be quickly achieved, improving assembly efficiency.

[0025] 4. The main body is constructed as a cylindrical structure. By rotating it to different angles, multiple sets of stringers corresponding to multiple wall panels of the overall cylindrical section of the fuselage can be glued together. This allows a single device to complete the glued bonding of multiple wall panels of the corresponding cylindrical section of the fuselage without replacement, which is conducive to mass production.

[0026] 5. By setting rotating and lifting components on the fixed support device, the overall adhesive positioning device can rotate 360° and move up and down on it, making it more flexible to use.

[0027] 6. By making the connecting member detachably connected to the supporting member and allowing the second support to move horizontally relative to the first support, it is also possible to replace the overall adhesive positioning device with different configurations and sizes, thus making it more versatile. Attached Figure Description

[0028] To better understand the above and other objects, features, advantages, and functions of the present invention, reference can be made to the preferred embodiments shown in the accompanying drawings. The same or similar reference numerals in the drawings refer to the same or similar parts. Those skilled in the art should understand that the drawings are intended to schematically illustrate preferred embodiments of the invention and do not limit the scope of the invention in any way; the parts in the drawings are not drawn to scale.

[0029] Figure 1 This is a schematic diagram of an integral adhesive bonding system according to a preferred embodiment of the present invention.

[0030] Figure 2 for Figure 1 A schematic diagram of the overall adhesive bonding positioning device for the overall adhesive bonding system shown.

[0031] Figure 3 for Figure 2 The diagram shows the overall adhesive bonding and positioning device placed on the storage rack.

[0032] Figure 4 This is a flowchart of an integral bonding method according to a preferred embodiment of the present invention. Detailed Implementation

[0033] The integral bonding system and integral bonding method according to preferred embodiments of the present invention will now be described in detail with reference to the accompanying drawings. It should be understood that the following description is merely a preferred embodiment of the present invention, and those skilled in the art can conceive of other ways to implement the present invention based on the preferred embodiments; such other ways also fall within the scope of the present invention.

[0034] First, it should be noted that the directional and positional terms used in this invention should be understood as relative directions and positions, rather than absolute directions and positions.

[0035] The following text first refers to Figures 1-3 A detailed description is provided of an integral bonding system 100 for composite fuselage panels of aircraft according to a preferred embodiment of the present invention. A single fuselage panel includes a plurality of stringers 300 and a skin 400 to be bonded to the plurality of stringers 300.

[0036] Figure 1 An integral bonding system 100 according to a preferred embodiment of the present invention is shown. The integral bonding system 100 includes a fixed support device 110, an integral bonding positioning device 120, a movable support device 130, and a forming device 140. The fixed support device 110 includes a support member as a fixed station, which can be fixedly placed on a horizontal support surface, such as the ground. The support member includes a first support base 111a and a second support base 111b spaced apart from the first support base 111a. The two ends of the integral bonding positioning device 120 (described below) can be connected to the first support base 111a and the second support base 111b respectively, so that the integral bonding positioning device 120 can be supported between the first support base 111a and the second support base 111b.

[0037] Preferably, the second support 111b is configured to move horizontally relative to the first support 111a to change the spacing between the first support 111a and the second support 111b. This design allows the support member to be adapted to integral adhesive positioning devices 120 of different sizes and configurations, and by increasing the spacing between the first support 111a and the second support 111b, the installation of the integral adhesive positioning device 120 can be facilitated. For example, when installing the integral adhesive positioning device 120, the second support 111b can be moved first to increase the spacing between the first support 111a and the second support 111b, one end of the integral adhesive positioning device 120 can be connected to the first support 111a, and then the second support 111b can be moved to connect it to the other end of the integral adhesive positioning device 120.

[0038] In a preferred embodiment, the fixed support device 110 further includes a slide rail unit 112, which extends along the length (i.e., axial direction) of the integral adhesive positioning device 120. A second support seat 111b is mounted on the slide rail unit 112 and can slide along the slide rail unit 112 to move closer to or further away from the first support seat 111a. In one embodiment, the slide rail unit 112 is in the form of a linear slide rail, for example, it may include two guide rails. The bottom of the second support seat 111b may be provided with a groove that mates with the two guide rails, and the guide rails extend through the groove. It is understood that those skilled in the art can also adopt slide rail units 112 with other structures according to actual needs. Preferably, the slide rail unit 112 can be placed on the ground.

[0039] Continue to refer to Figure 1 The integral bonding and positioning device 120 is disposed between the first support 111a and the second support 111b, and includes a bearing body 121 and connecting members 122 disposed at both ends of the bearing body 121. The bearing body 121 is generally constructed as a cylindrical structure, matching the inner surface of the fuselage wall section. The bearing body 121 can install multiple sets of stringers 300, which correspond to multiple wall panels of the integral fuselage section, and each set of stringers includes multiple stringers. When installed on the bearing body 121, the multiple sets of stringers 300 can be evenly arranged along the circumference of the bearing body 121. The multiple sets of stringers 300 can be connected to the bearing body 121 by means of, for example, vacuum adsorption or electromagnetic adsorption. The connecting members 122 are detachably connected to the support members. In one embodiment, the connecting members 122 can be constructed as flanges, which can be detachably connected to the first support 111a and the second support 111b by fasteners such as bolts.

[0040] The detachable design of the integral adhesive bonding positioning device 120 and the fixed support device 110 allows one fixed support device 110 to be paired with multiple integral adhesive bonding positioning devices 120 corresponding to different wall panel configurations. In daily production, the two can be fixedly combined and placed together. When the fixed support device 110 needs to be equipped with other types of integral adhesive bonding positioning devices 120, simply hoist the current integral adhesive bonding positioning device 120 to the matching storage support frame 200 (e.g., Figure 3 As shown in the image, this greatly improves equipment utilization.

[0041] Preferably, the fixed support device 110 further includes a rotating component, a lifting component, and a driving component. The connecting component 122 is rotatably connected to the support component through the rotating component, allowing the integral bonding positioning device 120 to rotate 360 ​​degrees relative to the support component. By rotating the integral bonding positioning device 120 to different angles to arrange the corresponding set of stringers 300 in the area, a single integral bonding positioning device 120 can complete the bonding of multiple wall panels of the fuselage section. Taking the installation of four sets of stringers on the integral bonding positioning device 120 as an example, by rotating the integral bonding positioning device 120 to four different corresponding angles, the four sets of stringers corresponding to the four wall panels can be bonded to the skin sequentially without replacing the integral bonding positioning device 120.

[0042] In a preferred embodiment, the rotating member can be a crossed roller bearing, for example, the outer ring of the crossed roller bearing can be fixed to the support member, and the inner ring can be fixed to the connecting member 122 (or vice versa). The connecting member 122 can then achieve a highly rigid 360-degree rotation around the bearing axis. In another embodiment, the rotating member can also be a slewing bearing, for example, the seat ring of the slewing bearing can be fixed to the support member by bolts, and the shaft ring can be fixed to the connecting member 122. Alternatively, those skilled in the art can also provide other forms of rotating members as needed.

[0043] The drive component is electrically connected to the rotating component, enabling the drive component to drive the movement of the rotating component. In one embodiment, the drive component is constructed as a motor. The output shaft of the motor can be connected to the rotating component (such as the inner ring of a crossed roller bearing) to drive its rotation. Preferably, the motor is electrically connected to a controller to receive pulses or communication commands, thereby enabling precise control of the rotation angle or speed.

[0044] A lifting component is mounted on a supporting component, and a connecting component 122 is connected to the lifting component, enabling the overall adhesive positioning device 120 to move vertically relative to the supporting component. Preferably, a driving component is electrically connected to the lifting component, allowing the driving component to drive the movement of the lifting component. In one embodiment, the lifting component can be a screw-nut lifting mechanism; for example, the screw is vertically mounted on the supporting component via a bearing seat, and a motor drives the screw to rotate. The screw nut is fixedly connected to the connecting component 122. When the screw rotates, it can drive the nut to move the connecting component 122 vertically. In other embodiments, the lifting component can also be a hydraulic lifting mechanism or a rack and pinion lifting mechanism, etc. These lifting mechanisms can adopt structures based on the technology in this art, and for simplicity, they will not be described in detail here.

[0045] A movable support device 130 is positioned below the fixed support device 110 and is movable relative to the fixed support device 110. In a preferred embodiment, the movable support device 130 is an AGV (Automated Guided Vehicle). A forming device (also called a panel forming fixture) is used to place the skin 400 to be glued to a set of stringers 300 on the integral bonding positioning device 120. The forming device 140 can be placed on the AGV and can move with the AGV. Preferably, the AGV can autonomously travel to a designated workstation below the integral bonding positioning device 120 according to instructions. When the AGV moves to the designated workstation, the set of stringers 300 on the integral bonding positioning device 120 can be aligned with the skin 400 on the forming device 140 to facilitate subsequent gluing.

[0046] To facilitate the alignment of a set of stringers 300 on the integral bonding positioning device 120 with the skin 400 on the molding device 140, the integral bonding system 100 preferably further includes an alignment device. The alignment device includes positioning pins 151 on the support body 121 and positioning holes (not shown) on the molding device 140. When the molding device 140 is positioned below the integral bonding positioning device 120 (i.e., moved to a designated workstation), the positioning pins 151 can be inserted into the positioning holes. Preferably, the molding device 140 is provided with a set of positioning holes, including multiple positioning holes, for example, four. The support body 121 is provided with multiple sets of positioning pins 151, arranged circumferentially around the support body 121. Each set of positioning pins 151 includes multiple positioning pins 151, the same number as the number of positioning holes, for example, four. As the support body 121 rotates, each set of positioning pins 151 can engage with the aforementioned set of positioning holes. More preferably, the multiple positioning holes can be designed with different shapes or sizes (e.g., round holes, X-axis elongated oval holes, Y-axis elongated oval holes and through holes). This solution can, on the one hand, prevent the positioning pin 151 from being unable to be inserted into the positioning hole due to deformation during long-term use, and on the other hand, form a fault-proof system to ensure that the skin 400 and the corresponding set of stringers 300 are glued in the correct configuration and posture.

[0047] In a preferred embodiment, the ends of the plurality of positioning pins 151 are equipped with guide lights capable of emitting lasers (e.g., green lasers) in the same direction as the extension of the positioning pins 151. This solution allows for clear and convenient determination of the AGV's parking position, achieving alignment between the molding device 140 and the overall adhesive positioning device 120.

[0048] This invention also provides a method for integral bonding of composite material fuselage panels for aircraft. This method can be performed using the integral bonding system 100 described above, which will be discussed in conjunction with the following. Figure 4 The overall bonding method is described in detail.

[0049] First, the operator cleans the bonding station area and connects the selected integral bonding positioning device 120 to the fixed support device 110. Then, the lifting component is controlled to lower the integral bonding positioning device 120, positioning the supporting body 121 at a convenient operating height. By rotating the supporting body 121 to a suitable angle, the worker can install and fix multiple sets of stringers 300 to be bonded on the supporting body 121. After completion, the lifting component is controlled to rise, raising the integral bonding positioning device 120 to a safe height, and the rotating component is controlled to rotate the supporting body 121, so that one set of stringers 300 is in a bonding posture facing the skin 400. The rotation of the supporting body 121 can also be completed before the lifting component rises.

[0050] Meanwhile, the molding device 140, with the uncured skin 400 already laid, is automatically transported to the workstation by an AGV and stops directly below the overall bonding positioning device 120. The operator activates and observes the laser beam projected by the guide light at the end of the positioning pin 151, determining whether the laser has passed through each positioning hole, thus achieving initial vertical alignment of the positioning pin 151 with the positioning hole. After initial positioning, the overall bonding positioning device 120 can be driven down until it approaches the molding device 140. The AGV then fine-tunes the position of the molding device 140 to align the positioning pins 151 with the positioning holes, ensuring all positioning pins 151 easily fall into their corresponding positioning holes.

[0051] Finally, the overall bonding positioning device 120 is lowered above the forming device 140, and the bonding process (such as applying downward pressure) is performed to bond the corresponding set of stringers 300 to the skin 400, thereby completing the bonding of this panel. After bonding is completed, the overall bonding positioning device 120 is raised, and the AGV transport forming device 140 is moved out. Then, the supporting body 121 can be rotated to put the next set of stringers 300 into a bonding position, and the above process is repeated until all stringers 300 on the supporting body 121 are bonded.

[0052] Compared to the traditional method of using a gantry crane to control the gluing and positioning fixtures for gluing, the integrated gluing system and method provided by this invention can achieve the configuration of multiple wall panels corresponding to a single integral section of the machine body through a single integrated gluing system. This allows for the completion of the gluing process for multiple wall panels without changing the equipment, which is beneficial for the mass production of large-size machine body wall panels and improves manufacturing efficiency. In addition, by using an AGV to transport the forming device, it can be aligned with the integrated gluing and positioning device from below. Compared to the gantry crane control for alignment from above, this solution is more flexible, convenient, and easier to adjust, resulting in higher efficiency.

[0053] Furthermore, by making the connecting member detachably connected to the supporting member and allowing the second support to move horizontally relative to the first support, it is possible to replace the overall adhesive positioning device with different configurations and sizes, thus making it more versatile.

[0054] The above description of various embodiments of the present invention is provided for illustrative purposes to a person skilled in the art. It is not intended to limit the invention to a single disclosed embodiment. As taught above, those skilled in the art will understand various alternatives and variations of the invention. Therefore, although some alternative embodiments have been specifically described, those skilled in the art will understand or relatively easily develop other embodiments. The present invention is intended to include all alternatives, modifications, and variations of the invention described herein, as well as other embodiments falling within the spirit and scope of the invention described above.

Claims

1. An integral bonding system (100) for composite material fuselage panels of aircraft, said fuselage panels comprising a plurality of stringers (300) and skin (400), characterized in that, The integral adhesive bonding system (100) includes: A fixed support device (110) includes a support member that can be placed on a horizontal support surface; An integral adhesive bonding positioning device (120) is connected to the support member and configured to rotate relative to the support member. The integral adhesive bonding positioning device (120) includes a cylindrical bearing body (121) and connecting members (122) disposed at both ends of the bearing body (121). The bearing body (121) is configured to accommodate multiple sets of the stringers (300) mounted thereon, each set of the multiple sets of stringers including multiple stringers. The connecting members (122) are connected to the support member so that the bearing body (121) can be connected to the support member. A movable support device (130) is disposed below the fixed support device (110) and configured to be movable relative to the fixed support device (110); and A molding device (140) is disposed on the movable support device (130) and configured to allow the skin (400) to be mounted thereon. The integral bonding and positioning device is configured to be able to arrange the set of long stringers in the corresponding area by rotating to different angles, so as to enable a single integral bonding and positioning device to complete the bonding of multiple wall panels of the fuselage section.

2. The integral adhesive bonding system (100) according to claim 1, characterized in that, The connecting member (122) is detachably connected to the supporting member.

3. The integral adhesive bonding system (100) according to claim 1, characterized in that, The support member includes a first support seat (111a) and a second support seat (111b) spaced apart from the first support seat (111a). The integral adhesive positioning device (120) is connected between the first support seat (111a) and the second support seat (111b). The second support seat (111b) is configured to be horizontally movable relative to the first support seat (111a).

4. The integral adhesive bonding system (100) according to claim 3, characterized in that, The fixed support device (110) further includes a slide rail unit (112) that extends along the length of the integral adhesive positioning device (120), and the second support base (111b) is disposed on the slide rail unit (112) and configured to slide along the slide rail unit (112).

5. The integral adhesive bonding system (100) according to claim 1, characterized in that, The connecting member (122) is rotatably connected to the supporting member via a rotating member, so that the bearing body (121) can rotate 360 ​​degrees relative to the supporting member.

6. The integral adhesive bonding system (100) according to claim 5, characterized in that, The fixed support device (110) further includes a lifting component, which is disposed on the support component, and the connecting component (122) is connected to the lifting component, so that the bearing body (121) can be raised and lowered relative to the support component in the vertical direction.

7. The integral adhesive bonding system (100) according to claim 6, characterized in that, The fixed support device (110) further includes a drive member electrically connected to the rotating member and / or the lifting member, such that the drive member can drive the movement of the rotating member and / or the lifting member.

8. The integral adhesive bonding system (100) according to claim 6, characterized in that, The lifting component can be constructed as any one of the following: a lead screw and nut lifting mechanism, a hydraulic lifting mechanism, and a gear and rack lifting mechanism.

9. The integral adhesive bonding system (100) according to claim 1, characterized in that, The integral bonding system (100) further includes an alignment device, which includes a positioning pin (151) disposed on the support body (121) and a positioning hole disposed on the molding device (140), wherein the positioning pin (151) can be inserted into the positioning hole when the molding device (140) is positioned below the integral bonding positioning device (120).

10. The integral adhesive bonding system (100) according to claim 9, characterized in that, The alignment device also includes a guide light disposed at the end of the positioning pin (151), the guide light being configured to emit a laser beam in the same direction as the extension direction of the positioning pin (151).

11. The integral adhesive bonding system (100) according to claim 9, characterized in that, The alignment device includes a plurality of positioning pins (151) and a plurality of positioning holes, the plurality of positioning holes having different shapes and / or sizes from one another.

12. The integral adhesive bonding system (100) according to claim 1, characterized in that, The movable support device (130) is constructed as an AGV.

13. A method for integral bonding of composite material fuselage panels for aircraft, said integral bonding method being performed using an integral bonding system (100) as described in any one of claims 1-12, characterized in that, The integral bonding method includes the following steps: S1. Connect the integral adhesive positioning device (120) to the fixed support device (110). S2. Install one or more sets of long trusses (300) on the supporting body (121), wherein the multiple sets of long trusses (300) are arranged around the circumferential direction of the supporting body (121); S3. Rotate the overall bonding positioning device (120) so that one of the single stringers or multiple stringers (300) is in the bonding posture. S4. Place the molding device (140) on the movable support device (130) and move the movable support device (130) below the integral bonding positioning device (120), so that the skin (400) is aligned with one of the single or multiple sets of stringers (300) in the bonding posture; and S5. Glue one of the single or multiple sets of stringers (300) together with the skin (400).

14. The integral bonding method according to claim 13, characterized in that, When installing multiple sets of stringers, the overall bonding method further includes: S6, repeating the above steps S3-S5 until the bonding of the multiple sets of stringers (300) is completed.

15. The integral bonding method according to claim 13, characterized in that, Step S2 further includes: driving the overall adhesive positioning device (120) to descend so as to install the multiple sets of long trusses (300) on the supporting body (121).

16. The integral bonding method according to claim 13, characterized in that, Step S3 further includes: driving the integral adhesive positioning device (120) upward before or after rotating the integral adhesive positioning device (120).

17. The integral bonding method according to claim 13, characterized in that, The integral bonding method further includes, after step S4: driving the integral bonding positioning device (120) to descend and fine-tuning the movable support device (130) so that the positioning pin (151) on the bearing body (121) and the positioning hole on the molding device (140) are aligned.

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