Co-bonding manufacturing method of hyperbolic cap type stringer stiffened wall plate

Abstract

The invention provides a co-bonding manufacturing method for a hyperbolic cap type stringer stiffened wall plate. The co-bonding manufacturing method comprises the steps that a plurality of magnets are arranged on demolding cloth at intervals to form a flexible magnet series connection belt; the flexible magnet series connection belt penetrates into the tubular vacuum bag, and then the tubular vacuum bag is laid in a cavity of the hyperbolic cap type stringer; the multiple magnets are installed on the outer surface of the top of the protruding part of the hyperbolic cap type stringer at the positions corresponding to the positions of the multiple magnets in the flexible magnet series connection belt, and the multiple magnets and the corresponding magnets in the flexible magnet series connection belt are attracted to each other; the shape of the tubular vacuum bag in the cavity is adjusted by moving the position of the magnet, so that the tubular vacuum bag uniformly follows the shape of the cavity of the hyperbolic cap type stringer; and after the co-gluing operation is completed, the magnet installed on the outer surface of the top is removed, and then the flexible magnet series connection belt is pulled out of the inner cavity of the tubular vacuum bag.

Description

Technical Field

[0001] The present application relates to the field of aviation, and in particular to a method for manufacturing a hyperbolic hat-shaped long-string reinforced wall panel by co-bonding. Background Art

[0002] Hat-shaped (or Ω-shaped) structures have good stability and high axial load transfer efficiency, so hat-shaped long-string reinforced panels are widely used in the aerospace field as the most typical reinforced panel structure. In particular, the fuselage panels of large passenger aircraft basically adopt hat-shaped long-string reinforced panel structures. At the same time, carbon fiber resin-based composite materials are widely used in the manufacture of structural parts in the aerospace field, such as hat-shaped long-string reinforced panel structures, due to their excellent material mechanical properties and increasingly mature manufacturing processes.

[0003] When using the co-bonding process to manufacture fuselage panels such as the hyperbolic hat-shaped long stringer reinforced wall panels of aircraft, it is necessary to first cure and shape each hat-shaped long stringer part separately, and then co-bond the cured hat-shaped long stringer with the uncured wet skin wall panels. In order to ensure the pressure in the cavity of the hat-shaped long stringer during co-bonding, a tubular vacuum bag needs to be placed in the cavity of the hat-shaped long stringer to ensure that the inside and outside of the hat-shaped long stringer are connected to the tank pressure during the wall panel curing process, thereby pressurizing the skin at the cavity of the hat-shaped long stringer and preventing the hat-shaped long stringer from collapsing.

[0004] The common form of tubular vacuum bags is a multi-layer composite vacuum bag with a straight structure and a certain degree of flexibility. For a shorter hat-shaped long stringer, the tubular vacuum bag can be made to follow the shape of the cavity (also called the hat cavity) in the cavity of the hat-shaped long stringer by simple manual adjustment. Figure 1 The hyperbolic hat-shaped long stringer shown has a large size and curvature. It is difficult to ensure that the tubular vacuum bag follows the shape evenly in the hat cavity by manually adjusting the tubular vacuum bag. In addition, it is very inconvenient to only rely on manual support of the tubular vacuum bag during the joint gluing operation. Summary of the invention

[0005] Therefore, in order to overcome the problem that the existing co-bonding manufacturing method of hyperbolic hat-shaped long girder reinforced wall panels cannot ensure that the tubular vacuum bag uniformly follows the shape of the hyperbolic hat-shaped long girder cavity, and it is difficult to support the tubular vacuum bag during the co-bonding operation, the present application proposes a new co-bonding manufacturing method for hyperbolic hat-shaped long girder reinforced wall panels.

[0006] This application solves the above technical problems through the following technical solutions:

[0007] Specifically, the present application provides a co-bonding manufacturing method for hyperbolic hat-type long-beam reinforced wall panels, which includes forming a flexible magnet series belt by arranging multiple magnets at intervals on a demolding cloth; inserting the flexible magnet series belt into a tubular vacuum bag, and then laying the tubular vacuum bag in the cavity of the hyperbolic hat-type long beam; installing multiple magnets on the top outer surface of the raised part of the hyperbolic hat-type long beam at positions corresponding to the positions of the multiple magnets in the flexible magnet series belt, and making them adsorbed with the corresponding magnets in the flexible magnet series belt respectively; adjusting the shape of the tubular vacuum bag in the cavity by moving the position of the magnet, so that the tubular vacuum bag can evenly follow the shape of the cavity of the hyperbolic hat-type long beam; and after the co-bonding operation is completed, removing the magnets installed on the top outer surface, and then pulling the flexible magnet series belt out from the inner cavity of the tubular vacuum bag.

[0008] The present application utilizes the inner cavity of the tubular vacuum bag, and the flexible magnet series belt passing through the inner cavity of the tubular vacuum bag is designed to be laid together with the tubular vacuum bag in the cavity of the hyperbolic hat-shaped long stringer, and the magnets on the top outer surface of the convex part of the hyperbolic hat-shaped long stringer (i.e., the outer surface of the hat top) are mutually adsorbed, so that the tubular vacuum bag in the cavity can be effectively fixed, so that the subsequent gluing operation can be performed without supporting the tubular vacuum bag during the co-gluing operation. Moreover, the shape of the tubular vacuum bag in the cavity can be adjusted by moving the position of the magnet on the top outer surface, so that the tubular vacuum bag can be easily operated to uniformly follow the shape in the cavity. In addition, the co-gluing manufacturing method does not need to flip the hyperbolic hat-shaped long stringer for adjustment or manually adjust the shape of the tubular vacuum bag by reaching into the cavity, and can effectively prevent the wrinkles of the skin wall panel in the cavity while being convenient to operate. In addition, the aforementioned flexible magnet series belt is based on a demoulding cloth, which is convenient to be detached and pulled out from the inner cavity of the tubular vacuum bag after the co-gluing operation is completed and the magnets at the top outer surface are removed, so that it can be reused many times.

[0009] According to one embodiment of the present application, the co-bonding operation includes positioning a hyperbolic hat-type long stringer with a tubular vacuum bag laid inside it on the skin wall panel of the aircraft; and using a heating and pressing device to heat and pressurize the hyperbolic hat-type long stringer, and simultaneously performing the bonding operation of the hyperbolic hat-type long stringer and the skin wall panel.

[0010] During the co-bonding process, the hyperbolic hat-shaped long stringer is heated and pressurized by a heating and pressing device, which can overcome the elastic deformation and other problems caused by the complex hyperbolic torsion and deflection characteristics of the hyperbolic hat-shaped long stringer after curing, thereby ensuring that the hyperbolic hat-shaped long stringer is bonded in place on the skin wall panel, and avoiding problems such as loose bonding and large-area warping when the cured hyperbolic hat-shaped long stringer is glued to the skin wall panel. The co-bonding quality of the hyperbolic hat-shaped long stringer and the skin wall panel is guaranteed, and then the accuracy and precision of key engineering parameters such as the long stringer axis angle of the manufactured hyperbolic hat-shaped long stringer reinforced wall panel are guaranteed.

[0011] According to one embodiment of the present application, a plurality of positioning reference lines perpendicular to the length direction of the release cloth and spaced apart from each other are pre-drawn on the release cloth, and the magnets are arranged on the release cloth according to the positioning reference lines, thereby forming a flexible magnet series belt.

[0012] By drawing the positioning reference line on the demoulding cloth in advance, it is not only convenient to position and fix the magnet on the demoulding cloth, but also the positioning reference line can be used as a reference for aligning the ends of the tubular vacuum bag. In addition, if a positioning device, a heating and pressing device, and other devices are used for positioning and gluing in the subsequent co-gluing operation, the positions of the positioning reference lines can be referred to in the design and fixing of each device, thereby avoiding interference between the magnet on the top outer surface of the raised part of the hyperbolic hat-shaped long stringer and each device.

[0013] According to an embodiment of the present application, a positioning device for positioning the hyperbolic hat-shaped long girder is fixed in a detachable manner at a certain distance from the positioning reference line, and the positioning device is used to complete the positioning of the hyperbolic hat-shaped long girder on the skin wall panel. The positioning device is used to complete the positioning of the hyperbolic hat-shaped long girder on the skin wall panel, which can ensure that the axis of the entire hyperbolic hat-shaped long girder is fixed and avoid deviations caused by manual positioning.

[0014] According to an embodiment of the present application, the heating and pressurizing device heats and pressurizes the hyperbolic hat-shaped long stringer along the outer contour of the hyperbolic hat-shaped long stringer in the length direction at a spacing of 500mm-1000mm.

[0015] The heating and pressurizing device can apply a certain pressure to the hyperbolic hat-shaped long stringer while heating, which can fully compact the hyperbolic hat-shaped long stringer and the skin wall panel during gluing, thereby preventing the hyperbolic hat-shaped long stringer from warping from the skin wall panel. Moreover, by heating and pressurizing at certain intervals, a heating and pressurizing device that is much smaller than the size of the hyperbolic hat-shaped long stringer can be used for the co-gluing operation, thereby reducing the volume of the device and the required installation space, greatly reducing the weight of the device and effectively saving manufacturing costs. In addition, the co-gluing operation using the heating and pressurizing device can avoid manual operation errors, thereby ensuring that the axis of the entire hyperbolic hat-shaped long stringer remains fixed, so that the firmly bonded hyperbolic hat-shaped long stringer will not be subsequently offset in position.

[0016] According to one embodiment of the present application, an infrared heating lamp is arranged at the position of the heating and pressing device corresponding to the edge strip of the hyperbolic hat-shaped long stringer, so as to heat the adhesive film at the adhesive joint surface of the hyperbolic hat-shaped long stringer through infrared light waves. This method utilizes the penetrability of infrared light waves, and can efficiently heat the adhesive film at the adhesive joint surface without the need for an additional heat transfer medium such as metal for heat transfer, and the heat transfer efficiency is high and the heating is uniform. The heating power (i.e., the heating temperature) of the infrared heating lamp can be designed according to the thickness of the hyperbolic hat-shaped long stringer.

[0017] According to an embodiment of the present application, the heating and pressurizing device includes a cylinder, which is configured to press against the outer surface of the hyperbolic hat-shaped long stringer, thereby applying normal pressure to the hyperbolic hat-shaped long stringer while heating.

[0018] According to one embodiment of the present application, the bottom surface of the heating and pressing device has a shape that is consistent with the outer surface shape of the convex portion in a direction perpendicular to the length direction of the hyperbolic hat-shaped long stringer, so that when the bottom surface abuts against the outer surface of the hyperbolic hat-shaped long stringer, the normal pressure applied by the cylinder is uniformly applied to the hyperbolic hat-shaped long stringer. The cylinder can uniformly apply the normal pressure to the hyperbolic hat-shaped long stringer by abutting the bottom of the heating and pressing device through the bottom surface abutting against the outer surface of the hyperbolic hat-shaped long stringer, and through the interaction between the bottom surface of the heating and pressing device and the outer surface of the hyperbolic hat-shaped long stringer. Under the action of the uniform normal pressure, the edge strip of the hyperbolic hat-shaped long stringer can be fully fitted and compacted on the surface of the skin wall panel.

[0019] According to an embodiment of the present application, the pressure applied by the heating and pressurizing device to the hyperbolic hat-shaped long stringer is greater than or equal to 100N.

[0020] According to one embodiment of the present application, the step of forming a flexible magnet series belt includes arranging a plurality of magnets on the release cloth at intervals along the length direction of the release cloth, and then folding the release cloth in half along the length direction, thereby wrapping the magnets in the release cloth to form a flexible magnet series belt.

[0021] According to one embodiment of the present application, the spacing distances between the multiple magnets in the flexible magnet series belt are determined according to the size and curvature of the hyperbolic hat-shaped long stringer and the attraction between the magnets in the cavity and the magnets on the top outer surface.

[0022] According to an embodiment of the present application, the release cloth is made into a rectangular strip, and the width of the release cloth is equal to or greater than the circumference of the cross section of the magnet perpendicular to the length direction.

[0023] According to one embodiment of the present application, the length of the demoulding cloth is 30 mm to 40 mm longer than the length of the tubular vacuum bag. By designing the length of the demoulding cloth to be longer than the length of the tubular vacuum bag, the end of the flexible magnet series belt extends out from the end of the tubular vacuum bag, thereby facilitating the flexible magnet series belt to be pulled out of the tubular vacuum bag in subsequent operations.

[0024] According to one embodiment of the present application, any one of the aforementioned magnets is a strong magnetic magnet, or all of the aforementioned magnets are strong magnetic magnets.

[0025] According to one embodiment of the present application, the co-bonding manufacturing method also includes sealingly splicing the tubular vacuum bag after the flexible magnet series belt is removed with the external vacuum bag to pressurize its inner cavity, so that the hyperbolic hat-shaped long stringer is evenly fitted on the skin wall panel to form a hyperbolic hat-shaped long stringer reinforced wall panel pre-finished product.

[0026] According to one embodiment of the present application, the co-bonding manufacturing method further includes sealingly splicing the tubular vacuum bag and the external vacuum bag with a putty strip at the tubular vacuum bag at the end of the hyperbolic hat-shaped long stringer. The vacuum bag packaging is performed by using a splicing bag-making method, and the tubular vacuum bag and the external vacuum bag can be connected and sealed by the putty strip, so that the two ends of the tubular vacuum bag are connected to the outside world, thereby facilitating pressurization of the inner cavity of the tubular vacuum bag.

[0027] According to one embodiment of the present application, the co-bonding manufacturing method further includes placing a flexible cover plate between the tubular vacuum bag and the skin panel at the end of the hyperbolic hat-shaped long stringer, and then pressurizing the inner cavity of the tubular vacuum bag. By placing the flexible cover plate between the tubular vacuum bag and the skin panel, the quality of the skin panel at the position where the tubular vacuum bag passes through can be guaranteed, which is conducive to the mass production of large-sized fuselage panels.

[0028] According to one embodiment of the present application, the flexible cover is formed by a double layer of high-permeability air felt wrapped by an isolation film. The flexible cover formed by the high-permeability air felt has a certain degree of ductility while also having a certain degree of hardness. Compared with the traditional composite skin cover, it is easier to conform to the end position of the hyperbolic hat-shaped long stringer, thereby ensuring the quality of the skin wall panel.

[0029] According to one embodiment of the present application, the co-bonding manufacturing method further includes arranging the N4 breathable felt and the external vacuum bag in sequence above the flexible cover plate.

[0030] According to one embodiment of the present application, the co-bonding manufacturing method also includes hot pressing and curing the pre-finished product of the hyperbolic hat-shaped long girder reinforced wall panel. After the curing and cooling, the tubular vacuum bag is extracted from the cavity to obtain the formed hyperbolic hat-shaped long girder reinforced wall panel.

[0031] On the basis of conforming to the common sense in the art, the above-mentioned preferred conditions can be arbitrarily combined to obtain the preferred embodiments of the present application.

[0032] The beneficial technical effects and advantages that can be achieved by the co-bonding manufacturing method of the hyperbolic hat-shaped long-beam reinforced wall panel according to the above embodiment of the present application are:

[0033] By designing the magnets in the flexible magnet series belt and the magnets on the top outer surface of the raised part of the hyperbolic hat-shaped long stringer to be mutually adsorbed, it is possible to avoid the need for manual support and fixing of the tubular vacuum bag during the co-bonding operation, and to ensure that the tubular vacuum bag is uniformly shaped in the cavity of the hyperbolic hat-shaped long stringer in a simple and convenient manner, and to effectively prevent the skin wall panels at the cavity from wrinkling due to the adjustment of the shape of the tubular vacuum bag. Moreover, by using a heating and pressurizing scheme during bonding, the common problems of long stringer warping and weak bonding when the hyperbolic hat-shaped long stringer is co-bonded with the hyperbolic skin wall panels can be solved, thereby ensuring the co-bonding quality of the hyperbolic hat-shaped long stringer reinforced wall panels. In addition, by arranging the flexible cover plate at the end position of the hyperbolic hat-shaped long stringer between the hyperbolic hat-shaped long stringer and the skin wall panels, the quality of the skin wall panels at the position where the tubular vacuum bag passes through can be ensured, and the scheme is simple and has obvious cost advantages, which is conducive to the mass production of large-size fuselage wall panels. BRIEF DESCRIPTION OF THE DRAWINGS

[0034] Figure 1 is an exemplary schematic diagram of a hyperbolic hat-shaped long stringer,

[0035] Figure 2 : is a schematic diagram of a process of a method for co-bonding and manufacturing a hyperbolic hat-shaped long-beam reinforced wall panel according to a preferred embodiment of the present application,

[0036] Figure 3 is an exemplary schematic diagram of a flexible magnet series belt formed according to a preferred embodiment of the present application,

[0037] Figure 4 is an exemplary exploded view of a flexible magnet series belt formed according to a preferred embodiment of the present application,

[0038] Figure 5 This is a schematic diagram of laying a flexible magnet series belt and a tubular vacuum bag in the cavity of a hyperbolic hat-shaped long stringer according to a preferred embodiment of the present application.

[0039] Figure 6 This is an exemplary schematic diagram of heating and pressurizing using a heating and pressurizing device according to a preferred embodiment of the present application.

[0040] Figure 7 for Figure 6 An exemplary schematic diagram of the heating and pressing device in FIG.

[0041] Figure 8 for Figure 6 Another exemplary schematic diagram of the heating and pressing device in FIG.

[0042] Fig. 9 is a schematic diagram of placing a flexible cover according to a preferred embodiment of the present application, and

[0043] Fig.10It is a schematic diagram of the splicing and sealing of a tubular vacuum bag according to a preferred embodiment of the present application. DETAILED DESCRIPTION

[0044] In order to make the purpose, technical solutions and advantages of the present application clearer, the technical solutions in the implementation mode of the present application will be clearly and completely described below in conjunction with the accompanying drawings showing multiple embodiments according to the present application. It should be understood that all other embodiments obtained by ordinary technicians in this field without spending creative work based on the embodiments recorded in the present application will fall within the scope of protection of the present application.

[0045] In the following detailed description, sequential terms, such as "first", "then", etc., are used with reference to the order of steps described in the drawings. The specific steps of the embodiments of the present application can be placed in a variety of different orders, and the sequential terms are used for illustrative purposes rather than limiting.

[0046] like Figure 2 As shown, the co-bonding manufacturing method of the hyperbolic hat-shaped long-beam reinforced wall panel in the preferred embodiment of the present application includes the following steps:

[0047] S1, forming a flexible magnet series belt 4 by arranging a plurality of magnets 3 at intervals on a release cloth 1;

[0048] S2, inserting the flexible magnet series belt 4 into the tubular vacuum bag 5, and then laying the tubular vacuum bag 5 in the cavity of the hyperbolic hat-shaped long stringer 6;

[0049] S3, at positions corresponding to the positions of the multiple magnets 3 in the flexible magnet series belt 4, multiple magnets 19 are mounted on the top outer surface of the raised portion of the hyperbolic hat-shaped long stringer 6, and are respectively adsorbed to the corresponding magnets 3 in the flexible magnet series belt 4;

[0050] S4, adjusting the shape of the tubular vacuum bag 5 in the cavity by moving the position of the magnet 19, so that the tubular vacuum bag 5 can evenly follow the shape of the cavity of the hyperbolic hat-shaped long stringer 6; and

[0051] S5. After the co-bonding operation is completed, the magnet 19 mounted on the top outer surface is removed, and then the flexible magnet series belt 4 is pulled out from the inner cavity of the tubular vacuum bag 5.

[0052] In step S1, for example, an automatic blanking machine is used to blank the release cloth 1 into a rectangular strip, so that its length is longer than the corresponding tubular vacuum bag 5, and its width is equal to or greater than the circumference of the cross section of the magnet 3 perpendicular to the length direction of the release cloth 1, so that the release cloth 1 can wrap the magnet 3. Specifically, a plurality of magnets 3 are arranged on the release cloth 1 at intervals along the length direction of the release cloth 1, and then the release cloth 1 is folded in half along the length direction, so that the magnet 3 is wrapped in the release cloth 1 to form a strip as shown in FIG. Figure 3 The flexible magnet series belt 4 shown. The flexible magnet series belt 4 is based on the demoulding cloth 1, which is easy to separate from the tubular vacuum bag 5, so that it can be easily drawn out from the inner cavity of the tubular vacuum bag 5 for subsequent reuse.

[0053] Preferably, either the magnet 3 or the magnet 19 is a rectangular strong magnetic magnet or both the magnet 3 and the magnet 19 are rectangular strong magnetic magnets, and the width is slightly smaller than the width dimension of the raised portion of the hyperbolic hat-shaped long stringer 6 or slightly smaller than the width dimension of the cavity of the hyperbolic hat-shaped long stringer 6. More preferably, the length of the demoulding cloth 1 is 30mm-40mm longer than the length of the tubular vacuum bag 5, so that the two ends of the flexible magnet series belt 4 can extend from the ends of the tubular vacuum bag 5, thereby facilitating the flexible magnet series belt 4 to be pulled out of the tubular vacuum bag 5 in subsequent operations. Moreover, by limiting the length of the demoulding cloth 1 to a suitable range longer than the length of the tubular vacuum bag 5, it is possible to avoid the length of the flexible magnet series belt 4 extending from the tubular vacuum bag 5 to be too long, thereby preventing the co-bonding manufacturing process from affecting the quality of the aircraft skin panel 10.

[0054] In addition, when the magnets 3 are arranged on the demoulding cloth 1, the spacing distance between the multiple magnets 3 can be determined according to the configuration, size and curvature of the hyperbolic hat-shaped long stringer 6 and the attraction between the magnets 3 in the flexible magnet series belt 4 and the magnets 19 on the top outer surface, so as to ensure that the corresponding magnets inside and outside the cavity can be attracted to each other. Exemplarily, when the magnets 3 and the magnets 19 are both rectangular strong magnetic magnets, the magnets 3 are arranged on the demoulding cloth 1 in a manner of being spaced 200mm-300mm apart from each other along the outer contour of the hyperbolic hat-shaped long stringer 6 in the length direction to form the flexible magnet series belt 4.

[0055] Alternatively, if Figure 4As shown, the step of forming the flexible magnet series belt 4 may also include drawing a plurality of positioning reference lines 2 perpendicular to the length direction of the demoulding cloth 1 and spaced from each other on the demoulding cloth 1 in advance according to the configuration, size, curvature, etc. of the hyperbolic hat-shaped long stringer 6, and arranging the magnets 3 on the demoulding cloth 1 according to the positioning reference lines 2, thereby forming the flexible magnet series belt 4. Optionally, when the demoulding cloth 1 is made by using an automatic blanking machine as required, the positioning reference line 2 is drawn on the demoulding cloth 1 to serve as a positioning reference for the placement of the magnets 3. The positioning reference line 2 can also be used as a reference for aligning with the end of the tubular vacuum bag 5. Moreover, if a positioning device is used to position the hyperbolic hat-shaped long stringer 6 on the skin wall panel 10 in the subsequent co-bonding process, the positioning reference line 2 can be designed according to the placement and fixed position of the predetermined positioning device, so that the positioning reference line 2 is spaced a certain distance from the fixed position of the positioning device and the positioning device, thereby separating the placement position of the magnet 3 from the position of the positioning device to avoid interference between the magnet 3 and the positioning device.

[0056] In step S3, if Figure 5 As shown, after the flexible magnet series belt 4 and the tubular vacuum bag are laid in the cavity of the hyperbolic hat-shaped long stringer 6, magnets 19 are sequentially placed at the positions corresponding to the magnets 3 on the top outer surface of the raised part of the hyperbolic hat-shaped long stringer 6, so that the magnets 19 and the magnets 3 in the flexible magnet series belt 4 are adsorbed one by one. At this time, the position corresponding to the magnet 3 on the top outer surface of the raised part can be determined with reference to the positioning reference line 2 on the demoulding cloth 1 of the flexible magnet series belt 4. When the magnet 19 is placed at the corresponding position of the aforementioned top outer surface, due to the adsorption force between the magnet 3 and the magnet 19, the tubular vacuum bag is fixed in the cavity of the hyperbolic hat-shaped long stringer 6, and at this time, even if the hyperbolic hat-shaped long stringer is turned over, the tubular vacuum bag will not separate from the cavity.

[0057] In step S4, by appropriately moving the magnet 19 outside the hyperbolic hat-shaped long stringer 6, the size and direction of the attraction between the magnet 3 and the magnet 19 can be adjusted, thereby adjusting the shape of the tubular vacuum bag 5 in the cavity, so that the tubular vacuum bag 5, which is initially in a straight structure, follows the shape evenly in the cavity of the hyperbolic hat-shaped long stringer 6, and no wrinkles are generated. The method of adjusting the shape of the tubular vacuum bag 5 in the cavity by adjusting the magnet 19 is not only convenient to operate, but also can effectively prevent the skin wall panel 10 at the cavity from wrinkling due to adjusting the shape of the tubular vacuum bag 5.

[0058] In step S5, Figure 6As shown, the co-bonding operation includes positioning a hyperbolic hat-shaped long stringer 6 with a tubular vacuum bag 5 laid inside on the aircraft skin panel 10, and heating and pressurizing the hyperbolic hat-shaped long stringer 6 using a heating and pressing device 7, while performing the bonding operation of the hyperbolic hat-shaped long stringer 6 and the skin panel 10. Preferably, along the length direction of the hyperbolic hat-shaped long stringer 6, the heating and pressing device 7 is used to heat and pressurize the hyperbolic hat-shaped long stringer 6 along the outer contour of the hyperbolic hat-shaped long stringer 6 at a spacing of 500mm-1000mm.

[0059] By using the heating and pressurizing scheme during bonding, a certain pressure can be applied to the hyperbolic hat-shaped long girder 6 while heating, so that the hyperbolic hat-shaped long girder 6 and the skin wall panel 10 are fully compacted during bonding, thereby solving the problems of long girder warping and loose bonding that are prone to occur when the hyperbolic hat-shaped long girder reinforced wall panel is bonded together, thereby ensuring the final bonding quality of the hyperbolic hat-shaped long girder reinforced wall panel.

[0060] Moreover, by heating and pressurizing at certain intervals, a device much smaller than the size of the hyperbolic hat-shaped long stringer can be used for the co-gluing operation, thereby reducing the volume of the device and the required installation space, greatly reducing the weight of the device and effectively saving manufacturing costs. In addition, the co-gluing operation by the heating and pressurizing device can avoid errors in manual operation, thereby ensuring that the axis of the entire hyperbolic hat-shaped long stringer remains fixed, so that the firmly bonded hyperbolic hat-shaped long stringer will not be subsequently offset. In addition, the heating and pressurizing device is designed according to the shape of the hyperbolic hat-shaped long stringer, and a certain surface expansion is considered relative to the hyperbolic hat-shaped long stringer, which can avoid interference with the hyperbolic hat-shaped long stringer due to the curing deformation of the hyperbolic hat-shaped long stringer.

[0061] It should be noted that the edge strips of the hyperbolic hat-shaped long stringer 6 have been previously coated with adhesive film, or the adhesive film is added in step S5 or any step before it.

[0062] According to one embodiment of the present application, Figure 7 As shown, an infrared heating lamp 8 is provided at the position of the edge strip of the hyperbolic hat-shaped long stringer 6 corresponding to the bottom surface of the heating and pressing device 7, which can heat the adhesive film at the adhesive joint surface of the hyperbolic hat-shaped long stringer through infrared light waves.

[0063] The method utilizes the penetrability of infrared light waves to efficiently heat the adhesive film at the adhesive joint surface of the hyperbolic hat-shaped long stringer without the need for an additional heat transfer medium such as metal for heat transfer, and the heat transfer efficiency is high and the heating is uniform. The heating power (i.e., the heating temperature) of the infrared heating lamp 8 is designed according to the thickness of the hyperbolic hat-shaped long stringer 6. Preferably, the heating temperature transmitted to the adhesive film by the infrared heating lamp 8 reaches 60°C-80°C.

[0064] like Figure 8As shown, the heating and pressing device 7 is also provided with a cylinder 9, and has a shape on the bottom surface of the heating and pressing device 7 that is consistent with the outer surface shape of the convex part of the hyperbolic hat-shaped long stringer 6 in a direction perpendicular to the length direction of the hyperbolic hat-shaped long stringer 6, so that the heating and pressing device 7 can be fixed above the convex part and the bottom surface is in contact with the outer surface of the convex part. Preferably, although the above-mentioned shape at the bottom surface of the heating and pressing device 7 is consistent with the outer surface shape of the convex part of the hyperbolic hat-shaped long stringer 6, its size is slightly expanded relative to the size of the outer surface of the convex part, so as to prevent the hyperbolic hat-shaped long stringer 6 from not matching with the convex part due to deformation, causing the heating and pressing device 7 to be unable to be fixed on the hyperbolic hat-shaped long stringer 6.

[0065] Therefore, the cylinder 9 can press the hyperbolic hat type long stringer 6 by pressing the bottom of the heating and pressing device 7, and the bottom surface abuts against the outer surface of the hyperbolic hat type long stringer 6, thereby applying normal pressure to the hyperbolic hat type long stringer 6. Through the interaction between the bottom surface of the heating and pressing device 7 and the outer surface of the hyperbolic hat type long stringer 6, the normal pressure can be uniformly applied to the hyperbolic hat type long stringer 6, so that the edge strip of the hyperbolic hat type long stringer 6 can be fully fitted and compacted on the skin wall panel 10.

[0066] Preferably, the pressure applied by the heating and pressurizing device 7 to the hyperbolic hat-shaped long stringer 6 is greater than or equal to 100 N. In addition, the heating and pressurizing device 7 is designed according to the shape of the hyperbolic hat-shaped long stringer 6. As described above, the shape of the bottom surface thereof at the position for contacting with the convex portion of the hyperbolic hat-shaped long stringer 6 needs to consider a certain profile expansion relative to the hyperbolic hat-shaped long stringer 6, so as to avoid interference with the hyperbolic hat-shaped long stringer 6 due to solidification deformation.

[0067] The heating and pressing device 7 can be selected as a handheld device or a component in an integral bonding and positioning device according to the degree of automation of the process.

[0068] Optionally, in the co-bonding operation, a positioning device for positioning the hyperbolic hat-shaped long stringer 6 is also used to complete the positioning of the hyperbolic hat-shaped long stringer 6 on the skin wall panel 10. The specific process may include: turning over the hyperbolic hat-shaped long stringer 6 so that the opening of its cavity faces downward, placing the positioning device at a certain distance from the positioning reference line 2 based on a predetermined positioning device fixing position, and fixing the positioning device for positioning the hyperbolic hat-shaped long stringer 6 on the hyperbolic hat-shaped long stringer 6 and / or the skin wall panel 10 in a detachable manner, and then using the positioning device to complete the positioning of the hyperbolic hat-shaped long stringer 6 on the skin wall panel 10. Moreover, after the positioning is completed, the heating and pressing device 7 is used to heat the stringer edge strips at appropriate intervals and apply a certain normal pressure to ensure that each hyperbolic hat-shaped long stringer 6 is firmly bonded to the skin wall panel 10.

[0069] The positioning of the hyperbolic hat-shaped long stringer 6 on the skin panel 10 is completed by the positioning device, which can ensure that the axis of the entire hyperbolic hat-shaped long stringer 6 is fixed and avoid deviation caused by manual positioning.

[0070] In addition, the co-bonding manufacturing method also includes, after the flexible magnet series belt 4 is removed from the inner cavity of the tubular vacuum bag 5, at the tubular vacuum bag 5 at the end of the hyperbolic hat-shaped long girder 6, sealingly splicing the tubular vacuum bag 5 and the external vacuum bag 15 with a putty strip to pressurize the inner cavity of the tubular vacuum bag 5, so that the hyperbolic hat-shaped long girder 6 is evenly fitted on the skin wall panel 10 to form a hyperbolic hat-shaped long girder reinforced wall panel pre-finished product.

[0071] The vacuum bag packaging is carried out by using a bag-making method, and the tubular vacuum bag 5 and the external vacuum bag 15 are connected and sealed by a putty strip 16, so that both ends of the tubular vacuum bag 5 are connected to the outside, thereby facilitating pressurization of the inner cavity of the tubular vacuum bag 5.

[0072] At the same time, the size of the skin panel 10 of the fuselage panel is usually longer than the hyperbolic hat-shaped long stringer 6, so the processing method of the skin panel 10 at the end of the hyperbolic hat-shaped long stringer will seriously affect the quality of the fuselage panel co-bonding. It is known that due to the extension of the tubular vacuum bag 5 at the end of the hyperbolic hat-shaped long stringer, the skin panel 10 is often prone to and very easy to leave an indentation of the tubular vacuum bag 5 at the end, thereby causing wrinkles on the skin panel 10 and other problems. Although the existing method uses a skin cover plate arranged at the end of the long stringer to ensure the molding quality of the skin panel 10. However, for the hyperbolic fuselage panel (i.e., the hyperbolic hat-shaped long stringer reinforced panel), due to the hyperbolic structure of the skin panel 10 and the uneven characteristics of the end of the hyperbolic hat-shaped long stringer, the traditional skin cover plate solution is relatively complex and has high requirements for specificity, high cost, and it is difficult to accurately match and combine the cover plates.

[0073] Therefore, optionally, Fig. 9 As shown, the co-bonding manufacturing method further includes placing the flexible cover plate 11 between the tubular vacuum bag 5 and the skin panel 10 and at the position of the end of the hyperbolic hat-shaped long stringer, and then pressurizing the inner cavity of the tubular vacuum bag 5. By placing the flexible cover plate 11 between the tubular vacuum bag 5 and the skin panel 10, the quality of the skin panel 10 at the position where the tubular vacuum bag 5 passes through can be guaranteed, which is conducive to the mass production of large-sized fuselage panels.

[0074] Preferably, the flexible cover plate 11 is formed by wrapping a double layer of high-permeability air felt 12 with an isolation film 13. The specific operation may include: cutting the high-permeability air felt 12 of appropriate size, and wrapping the double layer of high-permeability air felt 12 with an isolation film 13 to form the flexible cover plate 11. The prepared flexible cover plate 11 is placed under the tubular vacuum bag 5 at the end of the hyperbolic hat-shaped long stringer, and the flexible cover plate 11 is placed in contact with the end position of the end of the hyperbolic hat-shaped long stringer.

[0075] The flexible cover plate 11 formed by the high-permeability air felt 12 has a certain degree of ductility and a certain degree of hardness. Compared with the traditional skin cover plate, it is easier to conform to the end position of the hyperbolic hat-shaped long stringer 6, thereby ensuring the quality of the skin wall panel 10 and having obvious cost advantages. Fig.10 As shown, the co-bonding manufacturing method further includes arranging the N4 breathable felt 14 and the external vacuum bag 15 in sequence above the flexible cover plate 11 to perform bag making and packaging.

[0076] Furthermore, the co-bonding manufacturing method also includes sending the pre-finished product of the hyperbolic hat-shaped long-truss reinforced wall panel after bagging and packaging into a hot press to perform hot pressing and curing on the pre-finished product of the hyperbolic hat-shaped long-truss reinforced wall panel, and after the curing and cooling, the tubular vacuum bag 5 is pulled out of the cavity to obtain the formed hyperbolic hat-shaped long-truss reinforced wall panel.

[0077] Optionally, an automatic laying device is used to automatically lay the skin wall panel 10 on the tooling of the hyperbolic hat-shaped long stringer reinforced wall panel. In addition, before the specific co-bonding operation, the pre-bonding preparations such as deburring pretreatment, adding adhesive film, and preparing for cutting the tubular vacuum bag can be performed on each hyperbolic hat-shaped long stringer 6.

[0078] According to the co-bonding manufacturing method of the hyperbolic hat-shaped long girder reinforced wall panel of the present application, it is not only possible to ensure that the tubular vacuum bag 5 is uniformly shaped in the cavity of the hyperbolic hat-shaped long girder 6 in a simple and convenient way, and there is no need to manually support the tubular vacuum bag 5 during the bonding operation, but also it is possible to effectively prevent the skin wall panel 10 from wrinkling. Moreover, by using a heating and pressurizing scheme during bonding, the common problems of long girder warping and weak bonding when the hyperbolic hat-shaped long girder 6 and the hyperbolic skin wall panel 10 are co-bonded can be solved, thereby ensuring the co-bonding quality of the hyperbolic hat-shaped long girder reinforced wall panel. In addition, by arranging the flexible cover plate 11 at the end position of the hyperbolic hat-shaped long girder between the hyperbolic hat-shaped long girder 6 and the skin wall panel 10, the quality of the skin wall panel 10 at the position where the tubular vacuum bag 5 passes through can be ensured, and the scheme is simple and has obvious cost advantages, which is conducive to the mass production of large-sized fuselage wall panels.

[0079] Although the specific implementation methods of the present application are described above, those skilled in the art should understand that these are only examples, and the protection scope of the present application is defined by the appended claims. Those skilled in the art may make various changes or modifications to these implementation methods without departing from the principles and essence of the present application, but these changes and modifications all fall within the protection scope of the present application.

Claims

1. A method for co-bonding and manufacturing a hyperbolic hat-shaped long-beam reinforced wall panel, wherein: The co-bonding manufacturing method comprises: A flexible magnet series belt (4) is formed by arranging a plurality of magnets (3) at intervals on a release cloth (1); Inserting the flexible magnet series belt (4) into a tubular vacuum bag (5), and then laying the tubular vacuum bag (5) in the cavity of a hyperbolic hat-shaped long stringer (6); A plurality of magnets (19) are mounted on the top outer surface of the raised portion of the hyperbolic hat-shaped long stringer (6) at positions corresponding to the positions of the plurality of magnets (3) in the flexible magnet series belt (4), and are respectively attracted to the corresponding magnets (3) in the flexible magnet series belt (4); The shape of the tubular vacuum bag (5) in the cavity is adjusted by moving the position of the magnet (19), so that the tubular vacuum bag (5) can evenly follow the shape of the cavity of the hyperbolic hat-shaped long stringer (6); and After the co-bonding operation is completed, the magnet (19) mounted on the top outer surface is removed, and then the flexible magnet series belt (4) is pulled out from the inner cavity of the tubular vacuum bag (5).

2. The co-bonding manufacturing method according to claim 1, wherein: The co-bonding operation includes: Positioning a hyperbolic hat-shaped long stringer (6) with the tubular vacuum bag (5) laid inside the long stringer on the aircraft skin panel (10); and The hyperbolic hat-shaped long stringer (6) is heated and pressurized by using a heating and pressurizing device (7), and the hyperbolic hat-shaped long stringer (6) and the skin wall panel (10) are glued together at the same time.

3. The co-bonding manufacturing method according to claim 2, wherein: The release cloth (1) is pre-drawn with a plurality of positioning reference lines (2) perpendicular to the length direction of the release cloth (1) and spaced apart from each other, and the magnets (3) are arranged on the release cloth (1) according to the positioning reference lines (2), thereby forming the flexible magnet series belt (4).

4. The co-bonding manufacturing method according to claim 3, wherein: A positioning device for positioning the hyperbolic hat-shaped long stringer (6) is arranged in a detachable manner at a certain distance from the positioning reference line (2), and the positioning device is constructed to enable positioning of the hyperbolic hat-shaped long stringer (6) on the skin wall panel (10).

5. The co-bonding manufacturing method according to claim 2, wherein: The heating and pressurizing device (7) heats and pressurizes the hyperbolic hat-shaped long stringer (6) along the outer contour of the hyperbolic hat-shaped long stringer (6) in the length direction at a spacing of 500 mm to 1000 mm.

6. The co-bonding manufacturing method according to claim 2, wherein: An infrared heating lamp (8) is arranged at a position of the heating and pressing device (7) corresponding to the edge strip of the hyperbolic hat-shaped long stringer (6) to heat the adhesive film at the adhesive joint surface of the hyperbolic hat-shaped long stringer through infrared light waves.

7. The co-bonding manufacturing method according to claim 2, wherein: The heating and pressing device (7) comprises a cylinder (9) which is configured to press against the outer surface of the hyperbolic hat-shaped long stringer (6), thereby applying normal pressure to the hyperbolic hat-shaped long stringer (6) while heating.

8. The co-bonding manufacturing method according to claim 7, wherein: The bottom surface of the heating and pressing device (7) has a shape that is consistent with the outer surface shape of the raised portion in a direction perpendicular to the length direction of the hyperbolic hat-shaped long stringer (6), so that when the bottom surface abuts against the outer surface of the hyperbolic hat-shaped long stringer (6), the normal pressure applied by the cylinder (9) is uniformly applied to the hyperbolic hat-shaped long stringer (6).

9. The co-bonding manufacturing method according to claim 2, wherein: The pressure applied by the heating and pressurizing device (7) to the hyperbolic hat-shaped long stringer (6) is greater than or equal to 100N.

10. The co-bonding manufacturing method according to claim 1, wherein: The steps of forming the flexible magnet series belt (4) include: A plurality of magnets (3) are arranged on the release cloth (1) at intervals along the length direction of the release cloth (1), and then the release cloth (1) is folded in half along the length direction, so that the magnets (3) are wrapped in the release cloth (1) to form the flexible magnet series belt (4).

11. The co-bonding manufacturing method according to claim 10, wherein: The spacing distances between the plurality of magnets (3) in the flexible magnet series belt are determined according to the size and curvature of the hyperbolic hat-shaped long stringer (6) and the attraction between the magnet (3) in the cavity and the magnet (19) on the top outer surface.

12. The co-bonding manufacturing method according to claim 10, wherein: The release cloth (1) is made into a rectangular strip shape, and the width of the release cloth (1) is equal to or greater than the circumference of the cross section of the magnet (3) perpendicular to the length direction of the release cloth (1).

13. The co-bonding manufacturing method according to claim 10, wherein: The length of the demoulding cloth (1) is 30 mm to 40 mm longer than the length of the tubular vacuum bag (5).

14. The co-bonding manufacturing method according to claim 1, wherein: The magnet (3) and / or the magnet (19) are strong magnets.

15. The co-bonding manufacturing method according to any one of claims 1 to 14, wherein: The co-bonding manufacturing method also includes: The tubular vacuum bag (5) after the flexible magnet series belt (4) is removed is sealed and spliced ​​with the external vacuum bag (15) to pressurize its inner cavity, so that the hyperbolic hat-shaped long stringer (6) is evenly conformed to the skin wall panel (10) to form a hyperbolic hat-shaped long stringer reinforced wall panel pre-finished product.

16. The co-bonding manufacturing method according to claim 15, wherein: The co-bonding manufacturing method also includes: At the tubular vacuum bag (5) at the end of the hyperbolic hat-shaped long stringer, the tubular vacuum bag (5) and the external vacuum bag (15) are sealed and spliced ​​together using a putty strip (16).

17. The co-bonding manufacturing method according to claim 15, wherein: The co-bonding manufacturing method also includes: A flexible cover plate (11) is placed between the tubular vacuum bag (5) and the skin panel (10) at the end of the hyperbolic hat-shaped long stringer, and then the inner cavity of the tubular vacuum bag (5) is pressurized.

18. The co-bonding manufacturing method according to claim 17, wherein: The flexible cover plate (11) is formed by wrapping a double layer of high-permeability air felt (12) with an isolation film (13).

19. The co-bonding manufacturing method according to claim 17, wherein: The co-bonding manufacturing method also includes: The N4 air-permeable felt (14) and the external vacuum bag (15) are sequentially arranged above the flexible cover plate (11).

20. The co-bonding manufacturing method according to claim 15, wherein: The co-bonding manufacturing method also includes: The pre-finished product of the hyperbolic hat-shaped long-beam reinforced wall panel is subjected to hot pressing and curing molding, and after the curing and molding is cooled, the tubular vacuum bag (5) is extracted from the cavity to obtain the molded hyperbolic hat-shaped long-beam reinforced wall panel.

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