Airplane box section product large opening shape maintaining mechanism and shape maintaining method

Abstract

The invention discloses an airplane box section product large opening shape maintaining mechanism and method.The airplane box section product large opening shape maintaining mechanism comprises a beam fixing assembly, a wall plate fixing assembly, a positioning pin assembly, a supporting rod assembly and a plate frame assembly.The method includes the steps that firstly, the beam fixing assembly and the wall plate fixing assembly are installed on the inner molded surfaces of a front beam, a rear beam, an upper wall plate and a lower wall plate of a box section product large opening respectively; then the supporting rod assembly is adjusted to a proper length and is installed on the wall plate fixing assembly through the positioning pin assembly, and finally the plate frame assembly is installed on the beam fixing assembly and the wall plate fixing assembly through the positioning pin assembly. After installation, the shape maintaining mechanism forms an internal framework to change the large opening part of the box section product from a free state to a stable state. Compared with a traditional tool, the whole set of mechanism is easy and convenient to operate, reliable in function and low in cost, adjustment can be made according to the large-opening and small-range shape change of the airplane box section product, and the deformation resistance of the product in the assembling and transporting process is improved.

Description

Technical Field

[0001] This invention relates to the field of shape retention technology for large openings in aircraft box segment products, and particularly to a shape retention mechanism and method for large openings in aircraft box segment products. Background Technology

[0002] The wing box is a crucial component of an aircraft, its primary function being to provide sufficient lift. During aircraft design, it must be incorporated as a high-strength, lightweight structure. However, during the assembly of the wing and center wing, issues such as out-of-tolerance outer edges and uneven seams frequently arise, directly impacting the overall delivery cycle and quality. Therefore, maintaining the shape of the large opening area of ​​the wing box is an extremely important aspect of aircraft production. After the wing box section is removed from the final assembly jig, localized deformation due to the release of internal stress is unavoidable. Furthermore, because there is no frame in the large opening area, this deformation is more pronounced. Due to the influence of internal and external factors such as the condition of the parts themselves, the drilling sequence, and temperature differences for each batch of products, the exact amount of this deformation cannot be fully predicted; it can only be limited within certain dimensional ranges.

[0003] Traditionally, large openings in box-type products are typically maintained using dummy parts or multiple sets of struts. After the product is removed from the factory, the dummy parts or struts are inserted into the opening, and localized deformed areas are corrected using locators or clamping. This method suffers from problems such as limited construction area, difficult operation, high cost, and uncontrollable assembly stress. Summary of the Invention

[0004] To address the problems of limited construction range, difficult operation, high cost, and uncontrollable assembly stress associated with traditional tooling, this invention provides a large-opening shape-maintaining mechanism and method for aircraft box sections. This mechanism employs adjustable struts to achieve product shape correction, enabling fine-tuning within a certain range during assembly based on product deformation. Simultaneously, the internal frame of the shape-maintaining mechanism maintains the product's theoretical internal and external shape stability during long-distance transportation. The technical solution is as follows: On one hand, a shape-maintaining mechanism for a large opening of an aircraft box segment product is provided, comprising m sets of beam fixing components, n sets of wall panel fixing components, p sets of locating pin components, q sets of strut components, and a plate frame component. First, the beam fixing components and wall panel fixing components are installed on the inner surfaces of the front and rear beams and upper and lower wall panels of the large opening of the box segment product, respectively. Then, the m sets of locating pin components are installed on the beam fixing components. Next, the q sets of strut components are adjusted to a suitable length and installed on the wall panel fixing components using the remaining locating pin components. Finally, the plate frame component is installed on the beam fixing components and wall panel fixing components using the locating pin components. After installation, the shape-maintaining mechanism forms an internal skeleton that changes the large opening of the box segment product from a free state to a stable state, where m is greater than or equal to 4, n is greater than or equal to 6, n+m=p, and q=m / 2.

[0005] Compared to the traditional monolithic tooling structure, this conformal fitting mechanism, by decomposing it into five parts, increases the construction space at each station and reduces the operational difficulty at each station. If the product's shape changes during the design process, traditional tooling would have to be scrapped; this conformal fitting mechanism, however, can be fine-tuned to adapt to product changes while maintaining the conformation effect. Each component is relatively independent and can be designed according to the product's shape, exhibiting a high degree of modularity and reusability. This solves the problem of poor versatility caused by the high degree of customization in traditional tooling, saving manufacturing time and reducing production costs. During installation, the conformal fitting mechanism can adapt to localized deformation of the product and correct some deformed areas, reducing the internal stress that box segments need to overcome during long-distance transportation and assembly.

[0006] The beam fixing assembly includes a beam fixing joint, a spherical bearing, a large washer, and high-strength bolts. The beam fixing joint is a machined part; one end is machined to a flat surface and connected to the front and rear beams of the product via high-strength bolts, while the other end has a hole for mounting the spherical bearing. The large washer is a standard machined part used to secure the locating pin assembly. The beam fixing assembly is designed to connect the front and rear beams of the product to the shaping mechanism.

[0007] The panel fixing assembly includes a panel fixing joint, a spherical bearing, and high-strength bolts. The panel fixing joint is a machined part; one end is machined into the inner surface of the panel and connected to the inner surfaces of the upper and lower panel of the product via high-strength bolts. The other end has a hole machined in it to install the spherical bearing. The panel fixing assembly is designed to connect the upper and lower panel of the product to the shaping mechanism.

[0008] The locating pin assembly includes a double-threaded locating pin, a washer, and a nut. The double-threaded locating pin is machined from high-carbon steel and heat-treated, with external threads at both ends and consisting of two smooth sections and a stepped surface in the middle. The washer and nut are installed at both ends of the double-threaded locating pin; one end is used to secure the pin, and the other end is used to secure the plate-frame assembly. The locating pin assembly is designed to connect the beam fixing assembly and the plate-frame assembly, and to connect the wall panel fixing assembly and the strut assembly to the plate-frame assembly in series.

[0009] The strut assembly includes a left-hand screw, a right-hand screw, an internally threaded tube, and a nut. One end of both the left-hand and right-hand screws has a fork-like structure for connecting to the wall panel fixing assembly, while the other end is machined with an external thread. The internally threaded tube is welded from a steel pipe to two internally threaded posts, one side with a left-hand thread and the other with a right-hand thread. The left-hand and right-hand screws are screwed into both ends of the internally threaded tube, and the overall length of the strut assembly is adjusted by the depth of screwing in or out. After adjusting to the appropriate length, the nut is tightened. The strut assembly is used to adjust the overall length of the strut assembly to accommodate product deformation. After installation, the product deformation is corrected by adjusting the length of the strut assembly.

[0010] The plate frame assembly includes the plate frame body and the p-sleeve adjustable receiver assembly. The plate frame body is a machined aluminum part, with its overall outline consistent with the internal outline of the product's large opening. Weight-reduction grooves are machined on both sides, and the outer edge has p-point support arms evenly distributed along the shape. Each support arm has a groove for mounting the adjustable receiver assembly. The plate frame assembly can be designed according to the shape of the product's opening, and each support arm can connect to the product to form an internal skeleton, enhancing the deformation resistance of the large opening area of ​​the box segment.

[0011] The adjustable receiver assembly includes a large cover plate, a small cover plate, a lateral moving block, a longitudinal moving block, a fixing box, and screws. The fixing box is installed in the groove of the support arm on the plate frame body. The lateral moving block is installed inside the fixing box, and the longitudinal moving block is installed within the lateral moving block. The small cover plate is installed on the lateral moving block to prevent it from falling off. The large cover plate is installed on the fixing box to prevent the lateral moving block from falling off. Screws are installed in the lateral and longitudinal threaded holes on the side of the fixing box to push the lateral and longitudinal moving blocks to move in corresponding directions. The longitudinal and lateral moving blocks can slide within the plane of the plate frame assembly, accommodating product deformation within the plane and reducing internal stress generated by the installation of the conforming mechanism.

[0012] On the other hand, a method for maintaining the shape of a large opening in an aircraft box segment product is provided, for use in the large opening shape-maintaining mechanism of the aircraft box segment product described in the first aspect, the method specifically including the following steps: 8-1. Install m sets of beam fixing components and n sets of wall panel fixing components onto the product; 8-2. Install m sets of locating pin assemblies onto the beam fixing assembly; 8-3. Install the q-sleeve strut assembly and the remaining locating pin assembly onto the wall panel fixing assembly; 8-4. Adjust the length of the strut assembly; 8-5. Install the plate frame assembly onto the locating pin assembly; 8-6. After installation, the shaping mechanism forms the internal skeleton, changing the large opening of the box segment product from a free state to a stable state.

[0013] Optionally, the method specifically includes: 1. High-strength bolts are used to install the m-set beam fixing components in two groups on the front and rear beam planes of the product. There are m / 2 sets of each beam, evenly distributed. This connects the front and rear beams of the product with the shaping mechanism. 2. Use high-strength bolts to install n sets of wall panel fixing components in two groups on the inner surface of the upper and lower wall panels of the product. There are n / 2 sets for each upper and lower wall panel, evenly distributed. The effect is to connect the upper and lower wall panels of the product and the shaping mechanism. 3. Install the m sets of positioning pins onto the beam fixing assembly and initially tighten the nuts. This connects the plate frame assembly and the beam fixing assembly. 4. Adjust the strut assembly. Screw the left-hand and right-hand screws into both ends of the internal threaded tube. Adjust the overall length of the strut assembly by screwing in or out to a suitable depth. After adjusting to the appropriate length, tighten the nuts initially. Pass the remaining positioning pins through the fork lugs at both ends of the strut assembly and the corresponding wall panel fixing components. Tighten the nuts in the positioning pins. Install the strut assembly onto the wall panel fixing components. This accommodates product deformation and connects the upper and lower wall panels through the strut assembly and the wall panel fixing components. 5. Measure the product's external appearance to record its actual condition; 6. Adjust the length of the strut assembly to achieve the theoretical shape of the product. Tighten the nuts in the strut assembly. The effect is to correct the shape of the product by lengthening or shortening the strut assembly. 7. Adjusting the screw depth of each adjustable receiver assembly in the plate frame assembly adjusts the position of the horizontal and vertical moving blocks. The effect is to adjust the position of the corresponding adjustable receiver according to the position of each positioning pin assembly after product calibration, thus ensuring the installation effect of the plate frame assembly. 8. Install the plate frame assembly onto the positioning pin assembly and tighten the nuts in the positioning pin assembly. The effect is to connect the various components through the plate frame assembly to form a structurally stable shape-maintaining mechanism. 9. After installation, the shaping mechanism forms an internal skeleton that changes the large opening of the box segment from a free state to a stable state, thereby improving the product's resistance to deformation during assembly and transportation of the large opening.

[0014] The beneficial effects of this invention are at least as follows: This invention proposes a shape-preserving mechanism and method for large openings in aircraft box segments. The shape of the large opening can be adjusted by changing the length of the support rod assembly, controlling the theoretical shape of the product. Operation is simple, and the protective effect is particularly noticeable during long-distance transportation. If the product's shape changes during the design process, traditional tooling can only be scrapped. This shape-preserving mechanism can be fine-tuned, adapting to product changes while maintaining the shape-preserving effect. Each component is relatively independent and can be designed according to the product's shape, exhibiting a high degree of modularity and reusability. This solves the problem of poor versatility caused by the high degree of customization in traditional tooling, saving manufacturing time and reducing production costs. Furthermore, the shape-preserving method can be used for shape-preserving work on large openings of various aircraft models and components. Attached Figure Description

[0015] Figure 1 This is a schematic diagram of the overall structure; Figure 2 Schematic diagram of beam fixing components; Figure 3 Schematic diagram of the wall panel fixing assembly; Figure 4 This is a schematic diagram of the locating pin assembly; Figure 5 This is a schematic diagram of the strut assembly; Figure 6 This is a schematic diagram of an internally threaded pipe structure. Figure 7 This is a schematic diagram of the plate and frame assembly; Figure 8 This is a schematic diagram of an adjustable receiver assembly; Figure 9 This is a schematic diagram of the adjustable receiver assembly structure; Figure 10 This is a schematic diagram showing the connection between the locating pin assembly and the beam fixing assembly; Figure 11 This is a schematic diagram of the strut assembly installation; Figure 12 This is a schematic diagram of the plate and frame assembly installation.

[0016] The components are: 1-Beam fixing assembly; 2-Beam fixing joint; 3-Spherical bearing; 4-Large washer; 5-High-strength bolt; 6-Wall panel fixing assembly; 7-Wall panel fixing joint; 8-Positioning pin assembly; 9-Double-ended threaded positioning pin; 10-Washer; 11-Nut; 12-Strut assembly; 13-Left-hand screw; 14-Right-hand screw; 15-Internal threaded pipe; 16-Steel pipe; 17-Internal threaded column; 18-Nut; 19-Plate frame assembly; 20-Plate frame body; 21-Adjustable receiver assembly; 22-Large cover plate; 23-Small cover plate; 24-Transverse moving block; 25-Longitudinal moving block; 26-Fixing box; 27-Screw. Detailed Implementation In the production and transportation of large-opening components for aircraft box-type products, a modular, low-cost, simple-structured, and easy-to-use shaping mechanism and method are needed. Compared with traditional tooling, the entire system of this invention has a compact structure, reliable function, and can adjust to small-range shape changes in the large opening of the box-type product. It also improves the product's resistance to deformation during transportation and assembly, thereby increasing production efficiency.

[0017] This invention provides a shape-maintaining mechanism and method for correcting the shape of large openings in aircraft box-shaped products and improving the product's resistance to deformation during transportation and assembly. (See also...) Figure 1 A large-opening shape-maintaining mechanism for an aircraft box segment product includes 4 sets of beam fixing components 1, 10 sets of wall panel fixing components 6, 14 sets of positioning pin components 8, 5 sets of support rod components 12, and 1 set of plate frame components 19. First, the 4 sets of beam fixing components 1 and the 10 sets of wall panel fixing components 6 are installed on the inner surfaces of the front and rear beams and the upper and lower wall panels of the large opening of the box segment product, respectively. The beam fixing components 1 are divided into two groups, with 2 sets installed on each of the front and rear beams. The wall panel fixing components 6 are divided into two groups, with 5 sets installed on each of the upper and lower wall panels. Then, the 4 sets of positioning pin components 8 are installed on the beam fixing components 1. Next, the 5 sets of support rod components 12 are adjusted to a suitable length and installed on the wall panel fixing components 6 using the remaining 10 sets of positioning pin components 8. Finally, the plate frame component 19 is installed on the beam fixing components 1 and the wall panel fixing components 6 using the positioning pin components 8.

[0018] The beam fixing assembly 1 includes one beam fixing joint 2, one spherical bearing 3, two large washers 4, and four high-strength bolts 5. The beam fixing joint 2 is a machined part; one end is machined to a flat surface and is connected to the front and rear beam surfaces of the product via the high-strength bolts 5. The other end has a hole machined to install the spherical bearing 3. The large washers 4 are ordinary machined parts used to install the locating pin assembly 8. See also... Figure 2 .

[0019] The wall panel fixing assembly 6 includes one wall panel fixing joint 7, one spherical bearing 3, and four high-strength bolts 5. The wall panel fixing joint 7 is a machined part; one end is machined into the inner surface of the wall panel and is connected to the inner surfaces of the upper and lower wall panels of the product via the high-strength bolts 5; the other end has a hole machined in it to install the spherical bearing 3. See also... Figure 3 .

[0020] The locating pin assembly 8 includes one double-threaded locating pin 9, two washers 10, and two nuts 11. The double-threaded locating pin 9 is machined from high-carbon steel and heat-treated, with external threads at both ends and consisting of two smooth sections and a stepped surface in the middle. The washers 10 and nuts 11 are standard parts, installed at both ends of the double-threaded locating pin 9; one end is used to fix the double-threaded locating pin 9, and the other end is used to fix the plate frame assembly 19. The connecting beam fixing assembly 1 and the plate frame assembly 19 are connected in series, and the wall panel fixing assembly 6 and the strut assembly 12 are connected to the plate frame assembly 19. See also... Figure 4 .

[0021] The strut assembly 12 includes one left-handed screw 13, one right-handed screw 14, one internally threaded tube 15, and two nuts 18. One end of the left-handed screw 13 and the right-handed screw 14 has a fork-shaped lug structure for connecting to the wall panel fixing assembly 6, and the other end is machined with external threads. The internally threaded tube 15 is welded from one steel pipe 16 and two internally threaded posts 17. The two post 17 are welded to both ends of the steel pipe 16, one side with a left-handed thread and the other with a right-handed thread. The left-handed screw 13 and the right-handed screw 14 are screwed into both ends of the internally threaded tube 15, and the overall length of the strut assembly 12 is adjusted by the depth of screwing in or out. After adjusting to the appropriate length, the nuts 18 are tightened. To accommodate product deformation, the overall length of the strut assembly 12 is adjusted to accommodate the amount of deformation. Then, the strut assembly 12 is installed. After installation, the product deformation is corrected by adjusting the length of the strut assembly 12. (See also...) Figure 5 and Figure 6 .

[0022] The plate frame assembly 19 includes one plate frame body 20 and 14 adjustable receiver assemblies 21. The plate frame body 20 is a machined aluminum part, its overall outline consistent with the internal outline of the product's large opening. Weight-reduction grooves are machined on both sides, and the outer edge has 14 support arms evenly distributed along the shape. Each support arm has a groove machined for mounting the adjustable receiver assembly 21. See also... Figure 7 .

[0023] The adjustable receiver assembly 21 includes a large cover plate 22, a small cover plate 23, a transverse moving block 24, a longitudinal moving block 25, a fixing box 26, and four screws 27. The fixing box 26 is mounted on the support arm groove of the plate frame body 20. The transverse moving block 24 is mounted inside the fixing box 26. The longitudinal moving block 25 is mounted within the transverse moving block 24. The small cover plate 23 is mounted on the transverse moving block 24 to prevent the longitudinal moving block 25 from falling off. The large cover plate 22 is mounted on the fixing box to prevent the transverse moving block 24 from falling off. The four screws 27 are respectively installed in the transverse and longitudinal threaded holes on the side of the fixing box 26 to push the transverse moving block 24 and the longitudinal moving block 25 to move in the corresponding directions. See also... Figure 8 and Figure 9 .

[0024] like Figures 1-12 As shown, this application provides a method for maintaining the shape of a large opening in an aircraft box segment product, comprising the following steps: 1. Using high-strength bolts 5, the 4 sets of beam fixing components 1 are divided into two groups and installed on the front and rear beam planes of the product, with 2 sets for each of the front and rear beams, evenly distributed, to connect the front and rear beams of the product and the shaping mechanism; 2. Use high-strength bolts 5 to install 10 sets of wall panel fixing components 6 into two groups on the inner surface of the upper and lower wall panels of the product. There are 5 sets for each upper and lower wall panel, evenly distributed, to connect the upper and lower wall panels of the product and the shaping mechanism. 3. Install the four sets of locating pin assemblies 8 onto the beam fixing assembly 1 and initially tighten the nuts 11 to connect the plate frame assembly 19 and the beam fixing assembly 1. (See attached diagram) Figure 10 ; 4. Adjust the support rod assembly 12. Screw the left-hand screw 13 and the right-hand screw 14 into both ends of the internal threaded tube 15 respectively. Adjust the overall length of the support rod assembly 12 by screwing it in or out to a suitable length. After adjusting to a suitable length, use the nut 18 to initially tighten it. Pass the remaining 10 sets of positioning pin assemblies 8 through the fork lug structures at both ends of the support rod assembly 12 and the corresponding wall panel fixing assembly 6 in sequence. Tighten the nut 11 in the positioning pin assembly 8. Install the support rod assembly 12 on the wall panel fixing assembly 6 to accommodate product deformation. Connect the upper and lower wall panels through the support rod assembly 12 and the wall panel fixing assembly 6. See [link / reference]. Figure 1 and Figure 11 ; 5. Measure the product's external appearance and record its actual condition; 6. Adjust the length of the strut assembly 12 to make the product shape reach the theoretical state, tighten the nut 18 in the strut assembly 12, and achieve the purpose of correcting the product shape by lengthening or shortening the strut assembly 12; 7. Adjust the position of the transverse moving block 24 and the longitudinal moving block 25 by adjusting the screw insertion depth of each adjustable receiver assembly 21 in the plate frame assembly 19. Adjust the position of the corresponding adjustable receiver 21 according to the position of each positioning pin assembly 8 after product calibration to ensure the installation effect of the plate frame assembly 19. 8. Install the plate frame assembly 19 onto the positioning pin assembly 8, and tighten the nut 11 in the positioning pin assembly. See [link / reference]. Figure 12 The various components are connected by the plate and frame assembly 19 to form a structurally stable shape-maintaining mechanism; 9. After installation, the shaping mechanism forms an internal skeleton that changes the large opening of the box segment from a free state to a stable state, improving the product's resistance to deformation during assembly and transportation of the large opening.

[0025] The above description merely illustrates embodiments of the present invention and is quite specific and detailed; however, it should not be construed as limiting the scope of the patent. It should be noted that those skilled in the art can make various modifications and improvements without departing from the concept of the present invention, and these all fall within the scope of protection of the present invention. Furthermore, any parts of the present invention not described in detail are conventional techniques.

Claims

1. A shape-maintaining mechanism for a large opening in an aircraft box segment product, characterized in that, It includes m sets of beam fixing components, n sets of wall panel fixing components, p sets of positioning pin components, q sets of strut components, and plate frame components. First, the beam fixing components and wall panel fixing components are installed on the front and rear beams and the inner surfaces of the upper and lower wall panels of the large opening of the box segment product, respectively. Then, the positioning pin components are installed on the beam fixing components. Next, the strut components are adjusted to a suitable length and installed on the wall panel fixing components through the positioning pin components. The shape of the large opening of the product is finely adjusted by adjusting the length of the strut components. Finally, the plate frame components are installed on the beam fixing components and wall panel fixing components through the positioning pin components. After installation, the shaping mechanism forms an internal skeleton to change the large opening of the box segment product from a free state to a stable state. Where m is greater than or equal to 4, n is greater than or equal to 6, n+m=p, and q=m / 2.

2. The large-opening shape-maintaining mechanism for aircraft box segment products according to claim 1, characterized in that, The beam fixing assembly includes a beam fixing joint, a spherical bearing, a large washer, and high-strength bolts. The beam fixing joint is a machined part, with one end machined into a flat surface and connected to the front and rear beam surfaces of the product by high-strength bolts. The other end is machined with a hole to install the spherical bearing, and the large washer is used to install the locating pin assembly.

3. The large-opening shape-maintaining mechanism for an aircraft box segment product according to claim 1, characterized in that, The wall panel fixing assembly includes a wall panel fixing joint, a spherical bearing, and high-strength bolts. The wall panel fixing joint is a machined part, with one end machined into the inner surface of the wall panel and connected to the inner surface of the upper and lower wall panels of the product by high-strength bolts. The other end is machined with a hole and a spherical bearing is installed.

4. The large-opening shape-maintaining mechanism for an aircraft box segment product according to claim 1, characterized in that, The locating pin assembly includes a double-threaded locating pin, a washer, and a nut. The double-threaded locating pin is made of high-carbon steel and heat-treated. Both ends are machined with external threads, and the middle consists of two smooth rods and a stepped surface. The washer and nut are installed at both ends of the double-threaded locating pin, one end for fixing the double-threaded locating pin and the other end for fixing the plate frame assembly.

5. The large-opening shape-maintaining mechanism for an aircraft box segment product according to claim 1, characterized in that, The strut assembly includes a left-hand screw, a right-hand screw, an internally threaded tube, and a nut. One end of the left-hand and right-hand screws has a fork-shaped lug structure for connecting to the wall panel fixing joint of the wall panel fixing assembly, and the other end is machined with an external thread. The internally threaded tube is welded to a steel pipe and two internally threaded posts, which are respectively welded to both ends of the steel pipe, one side with a left-hand thread and the other side with a right-hand thread. The left-hand and right-hand screws are screwed into both ends of the internally threaded tube, and the overall length of the strut assembly is adjusted by the depth of screwing in or out. After adjusting to the appropriate length, the nut is used for initial tightening.

6. The large-opening shape-maintaining mechanism for an aircraft box segment product according to claim 1, characterized in that, The plate frame assembly includes a plate frame body and p adjustable receiver assemblies; the plate frame body is an aluminum machined part, the overall outline of which is consistent with the inner outline of the large opening of the product, weight reduction grooves are machined on both sides, and p support arms are evenly distributed along the outer shape on the outer edge, and each support arm is machined with a groove for installing the adjustable receiver assembly.

7. The large-opening shape-maintaining mechanism for an aircraft box segment product according to claim 6, characterized in that, The adjustable receiver assembly includes a large cover plate, a small cover plate, a transverse moving block, a longitudinal moving block, a fixing box, and screws. The fixing box is installed on the support arm groove of the plate frame body, the transverse moving block is installed inside the fixing box, the longitudinal moving block is installed in the transverse moving block, and the small cover plate is installed on the transverse moving block to prevent the longitudinal moving block from falling off. The large cover plate is installed on the fixing box to prevent the transverse moving block from falling off. The screws are installed in the transverse and longitudinal threaded holes on the side of the fixing box to push the transverse moving block and the longitudinal moving block to move in the corresponding directions.

8. A method for maintaining the shape of a large opening in an aircraft box segment product, characterized in that, For the large-opening shape-maintaining mechanism of the aircraft box segment product according to any one of claims 1 to 7, the method includes the following steps: 8-1. Install m sets of beam fixing components and n sets of wall panel fixing components onto the product; 8-2. Install m sets of locating pin assemblies onto the beam fixing assembly; 8-3. Install the q-sleeve strut assembly and the remaining locating pin assembly onto the wall panel fixing assembly; 8-4. Adjust the length of the strut assembly; 8-5. Install the plate frame assembly onto the locating pin assembly; 8-6. After installation, the shaping mechanism forms the internal skeleton, changing the large opening of the box segment product from a free state to a stable state.

9. The shape-preserving method according to claim 8, characterized in that, The method specifically includes the following steps: 9-1. Use high-strength bolts to install the m-set beam fixing components in two groups on the front and rear beam planes of the product, with m / 2 sets for each beam, evenly distributed. 9-2. Use high-strength bolts to divide the n sets of wall panel fixing components into two groups and install them on the inner surfaces of the upper and lower wall panels of the product. There are n / 2 sets of upper and lower wall panels, which are evenly distributed. 9-3. Install the m sets of locating pin assemblies onto the beam fixing assembly and initially tighten the nuts; 9-4. Adjust the strut assembly. Screw the left-hand screw and the right-hand screw into both ends of the internal threaded tube. Adjust the overall length of the strut assembly by screwing in or out to a suitable length. After adjusting to a suitable length, tighten the nuts initially. Pass the remaining positioning pins through the fork lugs at both ends of the strut assembly and the corresponding single lug connectors of the wall panel fixing assembly. Tighten the nuts in the positioning pins and install the strut assembly onto the wall panel fixing assembly. 9-5. Measure the product's external appearance; 9-6. Adjust the length of the strut assembly to achieve the theoretical shape of the product, and tighten the nuts in the strut assembly; 9-7. Adjust the position of the transverse and longitudinal moving blocks by adjusting the screw depth of each adjustable receiver assembly in the plate frame assembly; 9-8. Install the plate frame assembly onto the locating pin assembly and tighten the nuts in the locating pin assembly; 9-9. After installation, the shaping mechanism forms an internal skeleton that changes the large opening of the box segment product from a free state to a stable state.

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