A method for high-quality assembly and connection of large-size skin and complex framework structure

Abstract

The application relates to a high-quality assembly and connection integrated method for a large-size skin and a complex framework structure, and relates to a connection method for a large-size skin and a framework structure. The application aims at solving the problems of difficult installation, positioning misalignment, weak connection strength, distortion and over-difference of a large-size wing surface skin and a complex framework structure of an existing aircraft rudder wing, wing and the like. The method comprises the following steps: S1, manufacturing of a framework structure bolt; S2, positioning and punching of a large-size skin plate surface; and S3, assembly and connection of the large-size skin plate surface and the framework. The application is used for high-quality assembly and connection integration of a large-size skin and a complex framework structure.

Description

Technical Field

[0001] This invention relates to a method for connecting a large-sized skin to a skeleton structure. Background Technology

[0002] In the modern aerospace field, the demand for lightweight wings and control wings is becoming increasingly urgent. These wings often employ complex, multi-layered structures with large-sized wing surfaces, which not only provide thermal insulation but also contribute significantly to weight reduction. Currently, these complex multi-layered structures use a frame to support and connect the wing skin. However, as the thickness of multi-layered structures decreases, the large-sized skin cannot be disassembled to ensure overall integrity, and the numerous and dense contact points between the complex frame and skin lead to installation difficulties and positioning inaccuracies. Assembling and achieving high-quality connections between large-sized skin and complex frame structures is becoming increasingly challenging.

[0003] Traditional riveting and screwing methods suffer from failure and weak connections; welding, on the other hand, lacks sufficient weld strength and is prone to causing skeleton deformation. When there are many weld points, it is even more difficult to guarantee the positioning of complex skeleton structures and skins, which can easily lead to distortion or deviations.

[0004] Therefore, achieving precise assembly and connection of large-size skins and complex skeleton structures is the key to realizing the manufacturing of aircraft wing skins. Summary of the Invention

[0005] This invention aims to solve the problems of difficult installation and inaccurate positioning of large-size wing skins and complex skeleton structures such as control wings and wings of existing aircraft, as well as weak connection strength, which easily leads to distortion or deviation. It provides a high-quality integrated method for assembling and connecting large-size skins and complex skeleton structures.

[0006] A high-quality integrated method for assembling and connecting large-size skin and complex skeleton structures, comprising the following steps:

[0007] I. Manufacturing of the pins for the skeleton structure:

[0008] A pin structure is machined on the end face where the skeleton structure contacts the large-size skin panel, and the end face of the skeleton where the pin structure is located is a pin platform, thus obtaining a skeleton structure with a pin structure.

[0009] II. Positioning punching for large-size skin panels:

[0010] Large-sized skin panels are punched, and then the holes are polished smooth to obtain the punched skin panel surface.

[0011] The location and shape of the punch holes are consistent with the pin structure;

[0012] III. Assembly and connection of large-size skin panels and frame;

[0013] One side of the punched skin panel is placed parallel to the frame structure with the pin structure, so that the punched position of the skin panel corresponds to the position of the pin structure. Then, the pin structure is inserted into the punched hole of the skin panel. Using a through welding process, the pin structure and pin platform are tightly connected to the skin panel on the other side. Finally, the pin structure that protrudes from the skin panel is cut off and polished, thus completing the high-quality assembly and connection of the large-size skin and the complex frame structure.

[0014] The beneficial effects of this invention are:

[0015] Compared to existing methods for connecting large-sized skin panels to complex frame structures, this invention, through a special pin structure design, simplifies the process and reduces costs while significantly improving connection precision. This results in a tighter fit between the frame and the outer skin panels of the wing and rudder wings, ensuring that the frame does not shift position due to stress or deformation. The frame's structural integrity is also better preserved, enabling it to better transfer stress and allowing the connected rudder wings or wings to withstand greater loads.

[0016] Compared to existing methods for connecting large-size skin panels and complex frame structures, this invention changes the screw and nut connection to through welding, significantly improving connection strength and making the connected panel surface smoother. It also avoids the connection instability caused by screw and nut detachment due to thermal expansion in alternating high and low temperature environments and by long-term corrosion. This allows the connected structure to be suitable for a wider range of more demanding service environments.

[0017] This invention enables high-precision and high-strength assembly and connection of large-size skin panels and complex skeleton structures in rudder wings and wings. While simplifying the process and reducing costs, it significantly improves the connection accuracy and strength of the structure, and further reduces the high-temperature resistance and corrosion resistance of the connected components, making it more widely applicable.

[0018] In addition to the aforementioned large-size skin and complex support frame structure for aerospace vehicle wings, this invention is also applicable to other fields, such as ships or rockets, involving high-precision and high-quality assembly and connection of large-size skin panels and complex internal frames.

[0019] This invention relates to a high-quality integrated method for assembling and connecting large-size skin and complex skeleton structures. Attached Figure Description

[0020] Figure 1 This is a schematic diagram of the structure after the three-dimensional skin panel and frame structure are assembled in step one of the specific implementation methods.

[0021] Figure 2 A schematic diagram of the perforated skin panel surface structure prepared in step two of the specific implementation method;

[0022] Figure 3 A schematic diagram illustrating the high-quality assembly and connection process of a large-size skin and complex skeleton structure as a specific implementation method;

[0023] Figure 4 This is a schematic diagram illustrating the structure in which the contact surface edge between the sixth pin structure and the pin platform is located within the pin platform, as described in the specific implementation method.

[0024] Figure 5 A schematic diagram of the structure in which the six-pin structure is located is divided into multiple pin platforms by the pin structure at the end face of the skeleton.

[0025] Figure 6 This is a schematic diagram illustrating the threaded connection between the pin structure and the skeleton structure in the seventh specific implementation method.

[0026] Figure 7 This is a physical diagram showing the assembly and connection of the skeleton structure, pin structure, and large-size skin panel in Embodiment 1.

[0027] Figure 8 This is a physical image of the skin panel after high-quality assembly and connection of the large-size skin and complex skeleton structure in Example 1.

[0028] Figure 9 This is a comparison diagram of a typical welded connection. Detailed Implementation

[0029] The technical solution of the present invention is not limited to the specific embodiments listed below, but also includes any combination of the specific embodiments.

[0030] Specific implementation method one, combined with Figures 1 to 3 Detailed explanation: This embodiment describes a high-quality integrated assembly and connection method for large-size skin and complex skeleton structures, which is carried out according to the following steps:

[0031] I. Manufacturing of the pins for the skeleton structure:

[0032] A pin structure is machined on the end face where the skeleton structure contacts the large-size skin panel, and the end face of the skeleton where the pin structure is located is a pin platform, thus obtaining a skeleton structure with a pin structure.

[0033] II. Positioning punching for large-size skin panels:

[0034] Large-sized skin panels are punched, and then the holes are polished smooth to obtain the punched skin panel surface.

[0035] The location and shape of the punch holes are consistent with the pin structure;

[0036] III. Assembly and connection of large-size skin panels and frame;

[0037] One side of the punched skin panel is placed parallel to the frame structure with the pin structure, so that the punched position of the skin panel corresponds to the position of the pin structure. Then, the pin structure is inserted into the punched hole of the skin panel. Using a through welding process, the pin structure and pin platform are tightly connected to the skin panel on the other side. Finally, the pin structure that protrudes from the skin panel is cut off and polished, thus completing the high-quality assembly and connection of the large-size skin and the complex frame structure.

[0038] In this embodiment, step one adds a special pin structure to the skeleton structure. The shape of the pin is adjusted according to the shape of the area where it connects to the skeleton structure. Furthermore, a pin platform is present at the bottom of the pin to provide a locking structure for subsequent welding.

[0039] In step two of this implementation method, the large-size skin panel is precisely punched. The shape of the holes matches the shape of the pins, and the positions of the holes correspond one-to-one with the distribution of the pins.

[0040] In step three of this embodiment, the skin panel is placed parallel above the frame, and the skin panel is lowered after the pin structure mates with the corresponding perforations on each skin panel. When the skin panel is in uniform contact with each pin platform, a through-welding process is used on the other side of the skin panel to ensure a tight bond between the pin structure and the pin platform and the skin panel.

[0041] In step one of this specific implementation method, after adding pins to the skeleton, the remaining positions of the skeleton can form a bottom locking platform and a pin platform. The platform provides support for subsequent welding, thereby realizing bottom locking welding.

[0042] In step one of this specific implementation method, the pin positions are distributed such that they do not coincide with stress concentration points on the skeleton structure, and they avoid relatively complex and variable positions in the skeleton structure.

[0043] After the welding process is completed in step three of this specific implementation method, the welded surface of the skin panel needs to be polished to make the outer surface of the skin panel smooth and without protrusions, thereby avoiding the generation of stress points and corrosion points.

[0044] The beneficial effects of this embodiment are:

[0045] Compared to existing methods for connecting large-sized skin panels to complex frame structures, this embodiment utilizes a special pin structure design. This simplifies the process and reduces costs while significantly improving connection precision. It ensures a tighter fit between the frame and the outer skin panels of the wing and control wings, preventing positional shifts due to stress and deformation. The frame's structural integrity is further enhanced, allowing for better stress transfer and enabling the connected control wings or wings to withstand greater loads.

[0046] Compared to existing methods for connecting large-size skin panels and complex frame structures, this embodiment changes the screw and nut connection to through welding, significantly improving connection strength and making the connected panel surface smoother. It also avoids connection instability issues caused by screw and nut detachment due to thermal expansion in alternating high and low temperature environments and long-term corrosion. This allows the connected structure to be suitable for a wider range of more demanding service environments.

[0047] This implementation method enables high-precision and high-strength assembly and connection of large-size skin panels and complex skeleton structures in rudder wings and wings. While simplifying the process and reducing costs, it significantly improves the connection accuracy and strength of the structure, and further reduces the high-temperature resistance and corrosion resistance of the connected components, making it more widely applicable.

[0048] In addition to the aforementioned large-size skin and complex support frame structure for aerospace vehicle wings, this embodiment is also applicable to other fields, such as ships or rockets, involving high-precision and high-quality assembly and connection of large-size skin panels and complex internal frames.

[0049] Specific Implementation Method Two: This implementation method differs from Specific Implementation Method One in that: in step two, the length of the large-size skin panel is set to L, the width to M, and the thickness to H, with 200mm ≤ L, 200mm ≤ M, and 0.5mm ≤ H ≤ 5mm. Everything else is the same as in Specific Implementation Method One.

[0050] Specific Implementation Method Three: This implementation method differs from Specific Implementation Method One or Two in that: the height of the pin structure in step one is set to h, where h = H + 1 mm. Everything else is the same as in Specific Implementation Method One or Two.

[0051] Specific Implementation Method Four: This implementation method differs from Specific Implementation Methods One to Three in that the skeleton structure described in step one is a multi-column structure, a multi-row frame structure, a truss structure, a truss beam structure, or a rib or reinforcing bar structure. Everything else is the same as in Specific Implementation Methods One to Three.

[0052] Specific Implementation Method Five: This implementation method differs from Specific Implementation Methods One to Four in that the cross-sectional shape of the pin structure described in step one is square, circular, or polygonal; the distance between the two farthest points on the cross-section of the pin structure is denoted as D, where D = (0.001~0.035)L1, and L1 = min{L,M}. Everything else is the same as in Specific Implementation Methods One to Four.

[0053] Specific implementation method six, combined with Figures 4 to 5Specific Explanation: This embodiment differs from one of the specific embodiments one to five in the following ways: Let the cross-sectional area of ​​the pin structure in step one be s; when the edge of the contact surface between the pin structure and the pin platform is located within the pin platform, let the area of ​​the frame end face in step one be S, then the area of ​​the pin platform M = Ss, M ≥ 2s; when the frame end face where the pin structure is located is divided into multiple pin platforms by the pin structure, let the area of ​​each pin platform be K, K ≥ s. Everything else is the same as in specific embodiments one to five.

[0054] Specific implementation method seven, combined with Figure 6 Specific explanation: This embodiment differs from one of the specific embodiments one to six in that: the pin structure in step one is specifically formed by integral machining or mechanical assembly; the mechanical assembly connection is a plug-in or threaded connection. Everything else is the same as in specific embodiments one to six.

[0055] Specific Implementation Method Eight: This implementation method differs from Specific Implementation Methods One to Seven in that: the positional accuracy error of the pin structure in step one is ≤0.15mm; the positional accuracy error of the punching hole in step two is ≤0.15mm. Everything else is the same as Specific Implementation Methods One to Seven.

[0056] Specific Implementation Method Nine: This implementation method differs from Specific Implementation Methods One to Eight in that: in step three, a through-welding process is used, employing a bottom-locking welding method to tightly bond the pin structure to the skin panel on the other side; the through-welding process described in step three is laser welding or electron beam welding. Everything else is the same as in Specific Implementation Methods One to Eight.

[0057] Specific Implementation Method Ten: This implementation method differs from Specific Implementation Methods One to Nine in that the pin structure described in step three and the punching hole on the skin panel are in a clearance fit, with a fit tolerance of Tf, where Tf = (0.01~0.05)D. Everything else is the same as in Specific Implementation Methods One to Nine.

[0058] The beneficial effects of the present invention are verified using the following embodiments:

[0059] Example 1:

[0060] A high-quality integrated method for assembling and connecting large-size skin and complex skeleton structures, comprising the following steps:

[0061] I. Manufacturing of the pins for the skeleton structure:

[0062] A pin structure is machined on the end face where the skeleton structure contacts the large-size skin panel, and the end face of the skeleton where the pin structure is located is a pin platform, thus obtaining a skeleton structure with a pin structure.

[0063] II. Positioning punching for large-size skin panels:

[0064] Large-sized skin panels are punched, and then the holes are polished smooth to obtain the punched skin panel surface.

[0065] The location and shape of the punch holes are consistent with the pin structure;

[0066] III. Assembly and connection of large-size skin panels and frame;

[0067] One side of the punched skin panel is placed parallel to the frame structure with the pin structure, so that the punched position of the skin panel corresponds to the position of the pin structure. Then, the pin structure is inserted into the punched hole of the skin panel. Using a through welding process, the pin structure and pin platform are tightly connected to the skin panel on the other side. Finally, the pin structure that protrudes from the skin panel is cut off and polished, thus completing the high-quality assembly and connection of the large-size skin and the complex frame structure.

[0068] In step two, let the length of the large-size skin panel be L, the width be M, and the thickness be H, where L = 1000mm, M = 600mm, and H = 1mm.

[0069] Let the height of the pin structure in step one be h, where h = H + 1mm = 2mm.

[0070] The skeleton structure mentioned in step one is a truss structure.

[0071] The cross-sectional shape of the pin structure described in step one is rectangular; let the distance between the two farthest points of the cross-section of the pin structure be D, D = 10.2 mm, and let L1 = min{L, M} = 600 mm.

[0072] In step one, the end face of the skeleton containing the pin structure is divided into two pin platforms by the pin structure. Let the cross-sectional area of ​​the pin structure in step one be s, and the area of ​​each pin platform be K, where K = 40 mm. 2 s = 20mm 2 .

[0073] In step one, the pin structure is manufactured by integrally forming it using machining.

[0074] The positional accuracy error of the pin structure in step one is 0.1mm; the positional accuracy error of the punch in step two is 0.1mm.

[0075] In step three, a through-welding process is used, employing a bottom-locking welding method, to tightly bond the pin structure to the skin panel on the other side of the skin panel; the through-welding process described in step three is laser welding.

[0076] The pin structure described in step three and the punched hole on the skin panel are clearance fits, with a fit tolerance of Tf, where Tf = 0.25 mm.

[0077] Comparative Example 1 differs from Example 1 in that steps one and two are omitted, and laser welding is directly used to assemble and connect the large-size skin panel to the frame structure. Everything else is the same as in Example 1.

[0078] Figure 7 This is a physical diagram showing the assembly and connection of the skeleton structure, pin structure, and large-size skin panel in Embodiment 1. Figure 8 The image shows the actual skin panel after high-quality assembly and connection of the large-size skin and complex frame structure in Example 1. As can be seen from the image, the connected panel surface in Example 1 is smoother, the frame and the outer skin panel of the rudder are tightly fitted, there is no deformation or defect, and the strength is higher.

[0079] Figure 9 The diagram shows a typical welded connection as an example. As can be seen, in complex skeleton structures, the initial welding of certain sections causes deformation of the unwelded parts of the skeleton. This leads to welding failures, structural damage, and stress concentration during the subsequent welding of the skeleton to the skin. Consequently, the final assembly connection often fails to meet the requirements for high-quality and high-precision assembly and connection.

Claims

1. A method for high-quality assembly and connection of large-size skin and complex skeleton structure, characterized in that... It is done in the following steps: I. Manufacturing of the pins for the skeleton structure: A pin structure is machined on the end face where the skeleton structure contacts the large-size skin panel, and the end face of the skeleton where the pin structure is located is a pin platform, thus obtaining a skeleton structure with a pin structure. II. Positioning punching for large-size skin panels: Large-sized skin panels are punched, and then the holes are polished smooth to obtain the punched skin panel surface. The location and shape of the punch holes are consistent with the pin structure; III. Assembly and connection of large-size skin panels and frame; One side of the punched skin panel is placed parallel to the frame structure with the pin structure, so that the punched position of the skin panel corresponds to the position of the pin structure. Then, the pin structure is inserted into the punched hole of the skin panel. Using a through welding process, the pin structure and pin platform are tightly connected to the skin panel on the other side. Finally, the pin structure that protrudes from the skin panel is cut off and polished, thus completing the high-quality assembly and connection of the large-size skin and the complex frame structure.

2. The method for high-quality assembly and connection of large-size skin and complex skeleton structure according to claim 1, characterized in that... In step two, the length of the large-size skin panel is L, the width is M, and the thickness is H, with 200mm≤L, 200mm≤M, and 0.5mm≤H≤5mm.

3. The method for high-quality assembly and connection of large-size skin and complex skeleton structure according to claim 2, characterized in that... Let the height of the pin structure in step one be h, where h = H + 1 mm.

4. The method for high-quality assembly and connection of large-size skin and complex skeleton structure according to claim 1, characterized in that... The skeleton structure mentioned in step one is a multi-column structure, a multi-row frame structure, a truss structure, a truss beam structure, or a rib or stiffener structure.

5. The method for high-quality assembly and connection of large-size skin and complex skeleton structure according to claim 2, characterized in that... The cross-sectional shape of the pin structure described in step one is square, circular, or polygonal; let the distance between the two farthest points on the cross-section of the pin structure be D, where D = (0.001~0.035)L1, and L1 = min{L,M}.

6. The method for high-quality assembly and connection of large-size skin and complex skeleton structure according to claim 1, characterized in that... Let the cross-sectional area of ​​the pin structure in step one be s; when the edge of the contact surface between the pin structure and the pin platform is located inside the pin platform, let the area of ​​the end face of the skeleton in step one be S, then the area of ​​the pin platform is M=Ss, M≥2s; when the end face of the skeleton where the pin structure is located is divided into multiple pin platforms by the pin structure, let the area of ​​each pin platform be K, K≥s.

7. The method for high-quality assembly and connection of large-size skin and complex skeleton structure according to claim 1, characterized in that... In step one, the pin structure is manufactured by integral machining or mechanical assembly; the mechanical assembly connection is either a plug or a thread.

8. The method for high-quality assembly and connection of large-size skin and complex skeleton structure according to claim 1, characterized in that... The positional accuracy error of the pin structure in step one is ≤0.15mm; the positional accuracy error of the punching in step two is ≤0.15mm.

9. The method for high-quality assembly and connection of large-size skin and complex skeleton structure according to claim 1, characterized in that... In step three, a through-welding process is used, employing a bottom-locking welding method, to tightly bond the pin structure to the skin panel on the other side of the skin panel. The through-welding process described in step three is laser welding or electron beam welding.

10. The method for high-quality assembly and connection of large-size skin and complex skeleton structure according to claim 5, characterized in that... The pin structure described in step three and the punching holes on the skin panel are clearance fits with a tolerance of Tf, where Tf = (0.01~0.05)D.

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