Aircraft fastening screw with safety function

Abstract

This invention discloses a fastening screw with a safety function for use in aviation transportation equipment. The aviation transportation equipment includes at least a wing component, and the screw is installed on the wing component. The screw structure includes a head component and a screw member connected to a first end of the head component. The outer surface of the screw member is sequentially connected from the first end to a first set of components, a first limiting component, a second limiting component, a second set of components, and a nut component. The first set of components and the second set of components have the same structure. The first set of components includes a first body with a first through groove. The inner wall of the first through groove is provided with a protruding component. The protruding component is made of shape memory metal and has a first state and a second state, with the size of the first state being smaller than the size of the second state.

Description

Technical Field

[0001] This invention relates to the field of aviation transportation equipment technology, and in particular to a fastening screw with a safety function for aviation applications. Background Technology

[0002] In the aerospace industry, wing components are the primary load-bearing parts of an aircraft, making the stability and safety of their fasteners crucial. While traditional fastening screws can provide a secure fastening function, their stability and safety are difficult to guarantee under high loads and complex environments. Therefore, a fastening screw with a safety feature is needed to improve both the fastening effect and safety. Summary of the Invention

[0003] The purpose of this invention is to overcome the shortcomings of the prior art and provide a fastening screw with a safety function for aviation. Compared with the prior art, the screw in this invention can improve the fastening effect and safety, and ensure the stability and safety of wing components.

[0004] The present invention is achieved through the following technical solution: The present invention discloses a fastening screw with a safety function for aviation, which is used in aviation transportation equipment. The aviation transportation equipment includes at least a wing component. The screw is installed on the wing component. The screw structure includes a head component and a screw component connected to a first end of the head component. The outer surface of the screw component is sequentially connected with a first set of components, a first limiting component, a second limiting component, a second set of components, and a nut component from the first end.

[0005] The first set of components and the second set of components have the same structure. The first set of components includes a first body with a first through groove. The inner wall of the first through groove is provided with a protruding component. The protruding component is made of shape memory metal and has a first state and a second state. The size of the first state is smaller than the size of the second state. When the temperature is lower than a first threshold, the protruding component extends towards the axis of the first through groove until it changes to the second state. When the temperature is higher than the first threshold, the protruding component contracts towards the inner wall of the first through groove until it changes to the first state. The outer surface of the screw component is provided with a limiting recess corresponding to the position of the protruding component of the first set of components and the second set of components.

[0006] The fastening screw of this invention features a protruding member made of shape-memory metal. Utilizing the shape-memory effect of the metal, the protruding member widens and expands at lower temperatures, engaging between the outer surface of the screw component and the limiting recess, thus enhancing the fastening effect. Simultaneously, at higher temperatures, the protruding member narrows and expands, disengaging from the limiting recess and allowing the screw to loosen, preventing excessive stress concentration caused by temperature changes. Through the shape-memory effect of the protruding member, the fastening screw achieves a safety function.

[0007] In practical implementation, this fastening screw can be applied to wing components, and its performance can be verified by utilizing the high strength requirements of wing components. During installation, the screw component is first screwed into the hole in the wing component. Then, the first and second sets of components are heated to above a first threshold using a heating device. At this point, the protruding component contracts and narrows, allowing the screw component to rotate freely. Once rotated to the appropriate position, heating is stopped. As the temperature decreases, the protruding component returns to its second state, engaging between the outer surface of the screw and the limiting recess, thus enhancing the fastening effect. The fastening screw of this invention has a safety function, improving the fastening effect and safety, and ensuring the stability and safety of the wing component. Simultaneously, the safety function is achieved by utilizing the shape memory effect of shape memory metal, making operation simple and reliable. This fastening screw is of great significance for improving the performance and safety of aviation transportation equipment.

[0008] Preferably, the temperature of the first threshold is between -10°C and -70°C. That is, when the temperature is below this range, the protruding member will extend towards the axis of the first through groove until it changes to the second state; while when the temperature is above this range, the protruding member will contract towards the inner wall of the first through groove until it changes to the first state. This setting allows the fastening screw to achieve a better tightening effect at lower temperatures, while allowing the screw to loosen at higher temperatures, thus preventing excessive stress concentration caused by temperature changes and facilitating screw removal.

[0009] Preferably, the structure of the first set of components further includes a first protective member disposed at one end of the first body. The protective member covers the surface of the first body portion. The first protective member can protect the surface of the first body portion from external damage or contamination, thereby improving the reliability and service life of the screw. For example, when installing or removing the screw, the protective member can prevent the screw from being scratched or contaminated by dust or other pollutants, thereby ensuring the stability of its shape memory effect. In addition, the protective member can also improve the wear resistance and corrosion resistance of the screw, enabling it to be used for a long time under harsh environmental conditions.

[0010] Preferably, the first limiting member is fixedly embedded inside the wing member, and the end face of the first set of members away from the first protective member presses against the first limiting member. The setting of the first limiting member can limit the range of movement of the first set of members and prevent it from extending or retracting excessively.

[0011] Preferably, the first limiting member includes a second body, which has a threaded through hole and a cavity. The cavity and the threaded through hole are in communication, meaning they are connected. An adhesive is injected into the cavity, and the adhesive flows through the opening inside the threaded through hole to the inner wall of the threaded through hole, connecting the first limiting member and the screw member to form a whole.

[0012] This structural design facilitates a reliable connection between the first limiting component and the screw component. An adhesive, a substance capable of bonding two surfaces together, provides a reliable fixing method. By injecting the adhesive into the cavity, it flows through the opening in the threaded through-hole to the inner wall of the hole, connecting the first limiting component and the screw component into a single, integrated structure. This connection method enhances the tightening effect and stability of the screw, improves the pull-out resistance and vibration resistance of the wing component, and ensures its stability and safety.

[0013] Furthermore, because the cavity and the threaded through-hole are in a connected state, the adhesive can flow through the opening inside the threaded through-hole to the inner wall of the through-hole, making the connection smoother and the operation more convenient. This structural design also facilitates automated production, improving production efficiency and quality.

[0014] In summary, this technical feature achieves a reliable connection between the first limiting component and the screw component by injecting an adhesive into the cavity, enhancing the tightening effect and stability of the screw, improving the pull-out resistance and vibration resistance of the wing component, and ensuring its stability and safety.

[0015] Preferably, a support plate component is arranged on the outside of the second body, and the support plate component is embedded inside the wing component to increase the contact area between the first limiting component and the wing and enhance the stability of the embedding.

[0016] Preferably, the first set of components and the second set of components are fixed to the surface of the wing component by an adhesive, wherein the first set of components and the second set of components respectively contact the first limiting component and the second limiting component, and compress the first limiting component and the second limiting component.

[0017] This design facilitates a reliable connection of wing components. By fixing the first and second sets of components to the surface of the wing components using adhesive, a reliable fixing method is provided, allowing the two wing components to be stably connected together. Furthermore, by having the first and second sets of components respectively contact and compress the first and second limiting components, the stability and tightness of the connection are further enhanced. This structure also improves the pull-out resistance and vibration resistance of the wing components, ensuring their stability and safety.

[0018] This invention also discloses a screw installation method for connecting two wing components together. The following is a detailed explanation of each step:

[0019] Align the connection points of the two wing components to be assembled, ensuring that the connection surfaces of the two wing components are accurately aligned so that a smooth and reliable connection can be achieved when installing the screws;

[0020] The first set of components and the first limiting component are grouped together, and the second limiting component and the second set of components are grouped together, respectively located on different sides of different wing components; then the limiting components and the corresponding kits are combined together and installed in appropriate positions on different wing components;

[0021] The first and second limiting components are moved to the connection position of the wing component, and then welded to fix their positions to the wing component. Welding is a method of fixing two metal parts together, achieved through heating and pressurization. Welding fixes the first and second limiting components to the connection position of the wing component to ensure their stable and accurate positioning.

[0022] The first and second sets of components are moved to the positions of the first and second limiting components and fixed to the wing components using adhesive. The purpose of this step is to secure the kit to the limiting components using adhesive, a substance that can bond two surfaces together, providing a reliable fixing method.

[0023] An adhesive is injected inside the cavity to connect the first and second limiting members to the screw member as a whole. The cavity is a space within the wing member where adhesives and other substances can be injected. In this step, the first and second limiting members are connected to the screw member by injecting adhesive inside the cavity, forming a single integrated structure.

[0024] The connecting nut component allows the threaded component to press against the second set of components, completing the screw installation. The final step is to install the nut component by connecting it to the screw component, thus fully installing the screw. The nut component engages with the second set of components through its threaded component, pressing against the second set of components to tighten the screw.

[0025] The screw installation method of the present invention, through the structural design of limiting components and kits, can achieve precise positioning and stable fixing, thereby improving the reliability and stability of the connection; through the use of reliable connection methods such as welding and adhesives, the quality and effect of screw installation can be ensured, and the strength and durability of the connection can be improved.

[0026] This invention discloses a fastening screw with a safety function for aviation applications, which, compared with the prior art:

[0027] The fastening screw of this invention features a protruding member made of shape-memory metal. Utilizing the shape-memory effect of the metal, the protruding member widens and expands at lower temperatures, engaging between the outer surface of the screw component and the limiting recess, thus enhancing the fastening effect. Simultaneously, at higher temperatures, the protruding member narrows and expands, disengaging from the limiting recess and allowing the screw to loosen, preventing excessive stress concentration caused by temperature changes. Through the shape-memory effect of the protruding member, the fastening screw achieves a safety function. Attached Figure Description

[0028] Figure 1 This is a schematic diagram of the screw structure in this invention;

[0029] Figure 2 This is a schematic diagram of the screw installation position in this invention;

[0030] Figure 3 This is a schematic diagram of the first set of component structures in one embodiment.

[0031] Figure 4 This is a schematic diagram of the structure of the first limiting member in one embodiment;

[0032] Figure 5 This is a schematic diagram of the screw component in one embodiment. Detailed Implementation

[0033] The following description, provided with reference to the accompanying drawings, is intended to aid in a thorough understanding of the various exemplary embodiments of the present disclosure as defined by the claims and their equivalents. This description includes numerous details to aid understanding, but these details will be considered exemplary only. Accordingly, those skilled in the art will recognize that various changes and modifications can be made to the various embodiments described herein without departing from the scope and spirit of the present disclosure. Furthermore, for clarity and brevity, descriptions of well-known functions and structures may be omitted.

[0034] In the following, exemplary embodiments of the present invention will be described in detail with reference to the accompanying drawings.

[0035] It will be understood that when an element or layer is referred to as being “on,” “connected to,” or “linked to” another element or layer, it may be directly on, directly connected to, or linked to that other element or layer, or one or more intermediate elements or layers may be present. When an element is referred to as being “directly on,” “directly connected to,” or “directly linked to” another element or layer, no intermediate elements or layers are present. For example, when a first element is described as being linked to or connected to a second element, the first element may be directly linked to or connected to the second element, or the first element may be indirectly linked to or connected to the second element via one or more intermediate elements. The same reference numerals refer to the same elements. As used herein, the term “and / or” includes any and all combinations of one or more of the associated listed items. Furthermore, when describing embodiments of the invention, the use of “may” refers to “one or more embodiments of the invention.” When expressions such as “at least one of…” follow a list of elements, they modify the entire list of elements and not individual elements in the list. Furthermore, the term “exemplary” is intended to refer to an example or illustration. As used in this article, the terms “use,” “using,” and “used” can be considered synonyms with the terms “utilize,” “utilizing,” and “utilized,” respectively.

[0036] It will be understood that while the terms first, second, third, etc., may be used herein to describe various elements, components, regions, layers, and / or segments, these elements, components, regions, layers, and / or segments should not be limited to these terms. These terms are used to distinguish one element, component, region, layer, or segment from another element, component, region, layer, or segment. Therefore, without departing from the teachings of the exemplary embodiments, the first element, first component, first region, first layer, or first segment discussed below may be referred to as a second element, second component, second region, second layer, or second segment. In the accompanying drawings, for clarity of illustration, the dimensions of various elements, layers, etc., may be exaggerated.

[0037] For ease of description, spatial relative terms such as “beneath,” “below,” “lower,” “above,” and “upper” are used herein to describe the relationship between one element or feature and another element (or feature) or feature (or feature) as shown in the accompanying drawings. It will be understood that, in addition to the orientations depicted in the drawings, the spatial relative terms are intended to also include different orientations of the device in use or operation. For example, if the device in the drawings is flipped, an element described as “below” or “below” other elements or features will be oriented as “above” or “above” other elements or features. Therefore, the term “below” can include both orientations of above and below. The device may be otherwise oriented (e.g., rotated 90 degrees or in other orientations), and the spatial relative descriptive terms used herein should be interpreted accordingly.

[0038] The terminology used herein is for the purpose of describing specific exemplary embodiments of the invention only and is not intended to limit the described exemplary embodiments of the invention. As used herein, unless the context clearly indicates otherwise, the singular forms “a” and “an” are intended to include the plural forms as well. It will also be understood that, when used in this specification, the terms “include,” “including,” “comprise,” and / or “comprising” designate the presence of a feature, integral, step, operation, element, and / or component, but do not preclude the presence or addition of one or more other features, integrals, steps, operations, elements, components, and / or groups thereof.

[0039] This invention is achieved through the following technical solution: This invention discloses a fastening screw with a safety function used in aviation, applied to aviation transportation equipment, such as... Figure 1 and Figure 2 As shown, air transport equipment includes at least wing components. Figure 2 The screw is a wing component with a screw at position A. The screw is installed on the wing component. The screw has a head component 1 and a screw member 2 connected to the first end of the head component 1. The outer surface of the screw member 2 is connected in sequence from the first end to a first set of components 3, a first limiting component 4, a second limiting component 5, a second set of components 6, and a nut component 7.

[0040] The first set of components 3 and the second set of components 6 have the same structure. The first set of components 3 includes a first body 31, which has a first through groove. The inner wall of the first through groove is provided with a protruding component 33. The protruding component is made of shape memory metal and has a first state and a second state. The size of the first state is smaller than the size of the second state. When the temperature is lower than a first threshold, the protruding component extends towards the axis of the first through groove until it changes to the second state. When the temperature is higher than the first threshold, the protruding component contracts towards the inner wall of the first through groove until it changes to the first state. The outer surface of the screw component is provided with a limiting recess corresponding to the position of the protruding component 33 of the first set of components 3 and the second set of components 6.

[0041] The fastening screw of this invention features a protruding member 33 made of shape-memory metal. Utilizing the shape-memory effect of the metal, the protruding member widens and extends at lower temperatures, engaging between the outer surface of the screw member 2 and the limiting recess, thus enhancing the fastening effect. Simultaneously, at higher temperatures, the protruding member narrows and expands, disengaging from the limiting recess and allowing the screw to loosen, preventing excessive stress concentration caused by temperature changes. Through the shape-memory effect of the protruding member, the fastening screw achieves its safety function.

[0042] In practical implementation, this fastening screw can be applied to wing components, and its performance can be verified by utilizing the high strength requirements of wing components. During installation, the screw component 2 is first screwed into the hole in the wing component. Then, the first set of components 3 and the second set of components 6 are heated to above a first threshold temperature using a heating device. At this point, the protruding component 33 contracts and narrows, allowing the screw component 2 to rotate freely. Once rotated to the appropriate position, heating is stopped. As the temperature decreases, the protruding component 33 returns to its second state, engaging between the outer surface of the screw and the limiting recess, thus enhancing the fastening effect. The fastening screw of this invention has a safety function, improving the fastening effect and safety, and ensuring the stability and safety of the wing component. Simultaneously, the safety function is achieved by utilizing the shape memory effect of shape memory metal, making operation simple and reliable. This fastening screw is of great significance for improving the performance and safety of aviation transportation equipment.

[0043] In one embodiment, the temperature of the first threshold is between -10°C and -70°C. That is, when the temperature is below this range, the protruding member will extend towards the axis of the first through groove until it changes to the second state; while when the temperature is above this range, the protruding member will contract towards the inner wall of the first through groove until it changes to the first state. This setting allows the fastening screw to achieve a better fastening effect at lower temperatures, while allowing the screw to loosen at higher temperatures, thus preventing excessive stress concentration caused by temperature changes and facilitating screw removal.

[0044] One implementation example Figures 3 to 5As shown, the structure of the first set of components 3 also includes a first protective component 32 disposed at one end of the first body 31. The protective component 32 covers a portion of the surface of the first body 31. The first protective component 32 can protect a portion of the surface of the first body 31 from external damage or contamination, thereby improving the reliability and service life of the screw. For example, when installing or removing the screw, the protective component 32 can prevent the screw from being scratched or contaminated by dust or other pollutants, thereby ensuring the stability of its shape memory effect. In addition, the protective component 32 can also improve the wear resistance and corrosion resistance of the screw, enabling it to be used for a long time under harsh environmental conditions.

[0045] In one embodiment, the first limiting member 4 is fixedly embedded inside the wing member, and the end face of the first set of members 3 away from the first protective member 32 presses against the first limiting member 4. The setting of the first limiting member 4 can limit the range of movement of the first set of members 3 and prevent it from extending or retracting excessively.

[0046] In one embodiment, the first limiting member includes a second body, which has a threaded through hole and a cavity. The cavity and the threaded through hole are in communication, meaning they are connected. An adhesive is injected into the cavity, and the adhesive flows through an opening inside the threaded through hole to the inner wall of the threaded through hole, connecting the first limiting member and the screw member to form a whole.

[0047] This structural design facilitates a reliable connection between the first limiting component and the screw component. An adhesive, a substance capable of bonding two surfaces together, provides a reliable fixing method. By injecting the adhesive into the cavity, it flows through the opening in the threaded through-hole to the inner wall of the hole, connecting the first limiting component and the screw component into a single, integrated structure. This connection method enhances the tightening effect and stability of the screw, improves the pull-out resistance and vibration resistance of the wing component, and ensures its stability and safety.

[0048] Furthermore, because the cavity and the threaded through-hole are in a connected state, the adhesive can flow through the opening inside the threaded through-hole to the inner wall of the through-hole, making the connection smoother and the operation more convenient. This structural design also facilitates automated production, improving production efficiency and quality.

[0049] In summary, this technical feature achieves a reliable connection between the first limiting component and the screw component by injecting an adhesive into the cavity, enhancing the tightening effect and stability of the screw, improving the pull-out resistance and vibration resistance of the wing component, and ensuring its stability and safety.

[0050] In addition, a support plate component is arranged on the outside of the second body. The support plate component is embedded inside the wing component to increase the contact area between the first limiting component and the wing and enhance the stability of the embedding. The first set of components and the second set of components are fixed to the surface of the wing component by adhesive. The first set of components and the second set of components respectively contact the first limiting component and the second limiting component and squeeze the first limiting component and the second limiting component.

[0051] This design facilitates a reliable connection of wing components. By fixing the first and second sets of components to the surface of the wing components using adhesive, a reliable fixing method is provided, allowing the two wing components to be stably connected together. Furthermore, by having the first and second sets of components respectively contact and compress the first and second limiting components, the stability and tightness of the connection are further enhanced. This structure also improves the pull-out resistance and vibration resistance of the wing components, ensuring their stability and safety.

[0052] This invention also discloses a screw installation method for connecting two wing components together. The following is a detailed explanation of each step:

[0053] Align the connection points of the two wing components to be assembled, ensuring that the connection surfaces of the two wing components are accurately aligned so that a smooth and reliable connection can be achieved when installing the screws;

[0054] The first set of components and the first limiting component are grouped together, and the second limiting component and the second set of components are grouped together, respectively located on different sides of different wing components; then the limiting components and the corresponding kits are combined together and installed in appropriate positions on different wing components;

[0055] The first and second limiting components are moved to the connection position of the wing component, and then welded to fix their positions to the wing component. Welding is a method of fixing two metal parts together, achieved through heating and pressurization. Welding fixes the first and second limiting components to the connection position of the wing component to ensure their stable and accurate positioning.

[0056] The first and second sets of components are moved to the positions of the first and second limiting components and fixed to the wing components using adhesive. The purpose of this step is to secure the kit to the limiting components using adhesive, a substance that can bond two surfaces together, providing a reliable fixing method.

[0057] An adhesive is injected inside the cavity to connect the first and second limiting members to the screw member as a whole. The cavity is a space within the wing member where adhesives and other substances can be injected. In this step, the first and second limiting members are connected to the screw member by injecting adhesive inside the cavity, forming a single integrated structure.

[0058] The connecting nut component allows the threaded component to press against the second set of components, completing the screw installation. The final step is to install the nut component by connecting it to the screw component, thus fully installing the screw. The nut component engages with the second set of components through its threaded component, pressing against the second set of components to tighten the screw.

[0059] The screw installation method of the present invention, through the structural design of limiting components and kits, can achieve precise positioning and stable fixing, thereby improving the reliability and stability of the connection; through the use of reliable connection methods such as welding and adhesives, the quality and effect of screw installation can be ensured, and the strength and durability of the connection can be improved.

[0060] In summary, the fastening screw of the present invention, by incorporating a protruding member 33 made of shape-memory metal, utilizes the shape-memory effect of the metal to allow the protruding member to widen and extend at lower temperatures, engaging between the outer surface of the screw member 2 and the limiting recess, thereby enhancing the fastening effect. Simultaneously, at higher temperatures, the protruding member shrinks and narrows, disengaging from the limiting recess and allowing the screw to loosen, thus preventing excessive stress concentration caused by temperature changes. Through the shape-memory effect of the protruding member, the fastening screw achieves a safety function.

[0061] The above are merely preferred embodiments of the present invention, but the scope of protection of the present invention is not limited thereto. Any equivalent substitutions or modifications made by those skilled in the art within the scope of the technology disclosed in the present invention, based on the technical solution and inventive concept of the present invention, should be covered within the scope of protection of the present invention.

[0062] It should be noted that, in this document, relational terms such as "first" and "second" are used merely to distinguish one entity or operation from another, and do not necessarily require or imply any such actual relationship or order between these entities or operations. Furthermore, the terms "comprising," "including," or any other variations thereof are intended to cover non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements includes not only those elements but also other elements not expressly listed, or elements inherent to such a process, method, article, or apparatus. Without further limitations, an element defined by the phrase "comprising one..." does not exclude the presence of other identical elements in the process, method, article, or apparatus that includes said element.

Claims

1. A fastening screw with a safety function for aircraft applications, characterized in that, The screw is used in an air transport device, which includes at least a wing component. The screw is installed on the wing component. The screw has a structure including a head component (1) and a screw component (2) connected to the first end of the head component (1). The outer surface of the screw component (2) is connected sequentially from the first end to a first set of components (3), a first limiting component (4), a second limiting component (5), a second set of components (6), and a nut component (7). Among them, the first set of components (3) and the second set of components (6) have the same structure. The first set of components (3) includes a first body (31). The first body (31) has a first through groove. The inner wall of the first through groove is provided with a protruding component (33). The protruding component is made of memory metal and has a first state and a second state. The size of the first state is smaller than the size of the second state. When the temperature is lower than the first threshold, the protruding component extends towards the axis of the first through groove until it changes to the second state. When the temperature is higher than the first threshold, the protruding component shrinks towards the inner wall of the first through groove until it changes to the first state. The outer surface of the screw component is provided with a limit recess corresponding to the position of the protruding component (33) of the first set of components (3) and the second set of components (6). The structure of the first set of components (3) also includes a first protective component (32) arranged at one end of the first body (31), the protective component (32) covering part of the surface of the first body (31); The first limiting member (4) is fixedly embedded inside the wing member, and the end face of the first set of members (3) away from the first protective member (32) presses against the first limiting member (4). The structure of the first limiting member includes a second body (41), the second body (41) having a threaded through hole (42), and the second body (42) having a cavity (43), the cavity (43) being in communication with the environment of the threaded through hole (42).

2. The aviation-grade fastening screw with a safety function as described in claim 1, characterized in that, The temperature of the first threshold is between -10°C and -70°C.

3. A fastening screw with a safety function for aviation applications as described in any one of claims 1 to 2, characterized in that, The second body (41) is also provided with a support plate component (44) on its exterior, which is embedded inside the wing component.

4. A fastening screw with a safety function for aviation applications as described in claim 3, characterized in that, The first set of components (3) and the second set of components (6) are fixed to the surface of the wing component by adhesive, wherein the first set of components (3) and the second set of components (6) respectively contact the first limiting component (4) and the second limiting component (5) to compress the first limiting component (4) and the second limiting component (5).

5. A fastening screw with a safety function for aviation applications as described in claim 4, characterized in that, The screw installation method includes the following steps: Align the connection points of the two wing components to be assembled; The first set of components (3) and the first limiting component (4) are grouped together, and the second limiting component (5) and the second set of components (6) are grouped together. The two groups are located on different sides of different wing components. Move the first limiting member (4) and the second limiting member (5) to the connection position of the wing member, and fix the positions of the first limiting member (4) and the second limiting member (5) to the wing member by welding; Move the first set of components (3) and the second set of components (6) to the positions of the first limiting component (4) and the second limiting component (5), and fix them to the positions of the wing components with adhesive; An adhesive is injected into the cavity (43) to connect the first limiting member (4) and the second limiting member (5) to the screw member (2) as a whole; Connect the nut component (7) to make the threaded component (7) press against the second set of components, and complete the screw installation of the nut component (7).

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