Vertical assembly tool and assembly method for ceramic matrix composite rudder and wing products

Abstract

The invention discloses a vertical assembly tool and method for ceramic matrix composite rudder wing products, and aims to solve the technical problems that according to an existing assembly method, the position precision of a rudder shaft is poor, the profile precision of the assembled products is not high, and the products are difficult to repair. The assembling tool comprises a shaft sleeve, a base, a side supporting block, a bottom supporting block, a positioning pin and a tool support. The base is of a long-strip-shaped structure, and a mounting hole is formed in one end of the base in the length direction. The shaft sleeve is installed on the lower side of one end of the base through the installation hole, and the tool support is installed on the lower side of the other end of the base. The internal molded surface and size of the shaft sleeve are matched with the external molded surface and size of the rudder shaft; the length of the positioning pin is greater than the radial dimension of the shaft sleeve; the side supporting block is installed on the upper side of the other end of the base in the length direction. The tops of the side supporting blocks are inclined faces inclining towards the center of the base. The bottom supporting block is installed on the upper side of the middle of the base and used for supporting the bottom of the lower beam sealing skin, and the upper surface of the bottom supporting block is matched with the molded surface of the bottom of the lower beam sealing skin.

Description

Technical Field

[0001] This invention relates to an auxiliary assembly device for ceramic matrix composite products, specifically to a vertical assembly fixture and assembly method for ceramic matrix composite rudder products. Background Technology

[0002] As a novel thermally structural / functional integrated material combining the advantages of metallic, ceramic, and carbon materials, ceramic matrix composites possess characteristics such as high temperature resistance, low density, high strength, and oxidation resistance, and have wide applications in aerospace, nuclear energy, and photovoltaic fields. With continuous technological advancements, the dimensional and positional tolerance requirements for ceramic matrix composite products are also increasing.

[0003] Currently, rudder wing products, which constitute a large proportion of ceramic matrix composites, mostly employ a horizontal assembly method. Specifically, this involves first using assembly fixtures to locally position and restrict the rudder shaft, then installing the frame components horizontally onto the fixtures, which then limit their movement. Similarly, after the frame components are installed, the skin and endplate components are sequentially installed and positioned using the same fixtures. However, this method, which relies on supporting the sides of components, limiting the top and bottom, and positioning the rudder shaft, is complex and highly susceptible to machining errors on the sides of the components and the effects of chemical vapor deposition. Errors after assembly often accumulate on a single side of the component, leading to positional deviations of the rudder shaft relative to the product. Furthermore, products assembled using this horizontal method are difficult to rework entirely, resulting in high rework difficulty and an inability to eliminate errors generated during densification and assembly. This makes it difficult to meet the increasingly demanding assembly precision requirements of ceramic matrix composite rudder wing products. Summary of the Invention

[0004] The purpose of this invention is to provide a vertical assembly fixture and assembly method for ceramic matrix composite rudder products, in order to solve the technical problems of poor rudder shaft position accuracy, low surface contour accuracy after product assembly, and difficulty in rework in existing assembly methods.

[0005] To achieve the above objectives, the technical solution provided by this invention is as follows: A vertical assembly fixture for ceramic matrix composite rudder wing products, the ceramic matrix composite rudder wing products including a rudder shaft, a lower sealing beam skin, a frame, an upper sealing beam skin, and side skins; the rudder shaft and frame are located within the space enclosed by the lower sealing beam skin, the upper sealing beam skin, and the side skins; its special feature is: Includes bushings, base, side support blocks, bottom support blocks, locating pins, and tooling brackets; The base is a long strip structure with a mounting hole at one end along its length; the bushing is a cylindrical structure that is mounted on the lower side of the base through the mounting hole; the tooling bracket is mounted on the lower side of the base away from the bushing at the other end, and is used to support the base. The bushing is used to assemble the rudder shaft, and its internal profile and dimensions are adapted to the external profile and dimensions of the rudder shaft; the length of the locating pin is greater than the radial dimension of the bushing, and it is used to position the rudder shaft by passing radially through the locating hole on the bushing and the rudder shaft. The side support block is installed on the upper side of the base away from the bushing; the side support block is a vertically placed block with a slope at the top that is inclined toward the center of the base. This slope is used to support the side of the lower sealing beam skin away from the rudder shaft and is adapted to the profile of the side of the lower sealing beam skin away from the rudder shaft. The bottom support block is installed on the upper side of the middle part of the base to support the bottom of the lower sealing beam skin, and its upper surface is adapted to the profile of the bottom of the lower sealing beam skin.

[0006] Furthermore, it also includes a detection component, which includes two detection blocks and two detection holes disposed on the base; the two detection blocks are used to perform auxiliary detection on the profiles of the lower sealing beam skin, the upper sealing beam skin, and the side skin; The two detection holes are elongated holes that are adapted to and correspond one-to-one with the two detection blocks. The length direction of the elongated holes is consistent with the length direction of the base. The two elongated holes are evenly distributed on both sides of the width direction of the bottom support block.

[0007] Furthermore, the internal profile and dimensional accuracy of the bushing are higher than those of the corresponding external profile and dimensional accuracy of the rudder shaft.

[0008] This invention also provides a vertical assembly method for ceramic matrix composite rudder products, characterized by the following steps: Step 1: Assemble the above-mentioned ceramic matrix composite rudder wing product vertical assembly fixture and place it upright on the workbench; Step 2: Insert the rudder shaft into the bushing through the mounting holes on the base, and position it using the locating pin; Step 3: Fit the lower sealing beam skin onto the rudder shaft so that it fits snugly against the rudder shaft, while the side away from the rudder shaft fits snugly against the inclined surface of the top of the side support block and the bottom fits snugly against the upper surface of the bottom support block. Step 4: Place the frame on the lower sealing beam skin, ensuring that its relative position with the rudder shaft and the lower sealing beam skin is correct, and that it is in contact with the side wall of the rudder shaft and all surfaces that meet the lower sealing beam skin. Step 5: Place the upper sealing beam skin on the lower sealing beam skin, ensuring that its relative position with the rudder shaft and the lower sealing beam skin is correct, and that it is in contact with the side wall of the rudder shaft, the lower sealing beam skin, and all surfaces that meet the frame. Step 6: Place the side skin on the lower sealing beam skin, so that it is located on the side of the frame away from the upper sealing beam skin, and at the same time fit with the various surfaces that are connected to the rudder shaft, the lower sealing beam skin, the frame and the upper sealing beam skin to obtain a complete ceramic matrix composite rudder wing product. Step 7: Use a coordinate measuring machine (CMM) to inspect the surface profile of the complete ceramic matrix composite rudder wing product obtained in Step 6. If the inspection is qualified, proceed to Step 8; otherwise, perform overall CMM rework based on the rudder shaft until the inspection is qualified, and then proceed to Step 8. Step 8: According to the preset process requirements, prepare connection holes on the rudder shaft, lower sealing beam skin, frame, upper sealing beam skin and side skin respectively, and use screws to connect them through the corresponding connection holes to complete the assembly of ceramic matrix composite rudder wing products.

[0009] Furthermore, in step 2, during the process of inserting the rudder shaft into the bushing through the mounting hole on the base, the step also includes a step of fitting the outer wall of the lower part of the rudder shaft to the inner wall of the bushing by clamping.

[0010] Furthermore, step 3 also includes clamping the bottom of the lower sealing beam skin so that the side away from the rudder shaft fits against the inclined surface of the top of the side support block, and the bottom fits against the upper surface of the bottom support block, to ensure the installation angle and installation position of the lower sealing beam skin.

[0011] Furthermore, step 3 also includes using two detection blocks to pass through the corresponding detection holes from bottom to top, and testing the distance between the two detection blocks and the two sides of the lower sealing beam skin in the thickness direction. If the distance meets the design requirements, proceed to step 4; otherwise, repair the side of the lower sealing beam skin in the thickness direction according to the test results until the distance meets the requirements.

[0012] Furthermore, step 4 also includes trimming the surfaces corresponding to the skeleton until they fit together with the surfaces that are connected to the lower sealing beam skin.

[0013] Furthermore, step 5 also includes trimming the surface corresponding to the upper sealing beam skin until it fits snugly against the surfaces that connect with the lower sealing beam skin and the frame.

[0014] Furthermore, step 6 also includes trimming the corresponding surfaces of the side skin until they fit snugly against the surfaces that mate with the rudder shaft, lower sealing beam skin, frame, and upper sealing beam skin.

[0015] Compared with the prior art, the beneficial effects of the present invention are as follows: 1. The present invention provides a vertical assembly fixture for ceramic matrix composite rudder products, including a bushing, a base, a side support block, a bottom support block, a locating pin, and a fixture bracket. The whole assembly adopts a vertical assembly method. First, the rudder shaft is installed into the bushing and positioned with the locating pin. Then, with the rudder shaft as the reference, the lower sealing beam skin, the skeleton, the upper sealing beam skin, and the side skin are assembled in sequence with the side support block and the bottom support block. This not only solves the problem of difficult positioning of the rudder shaft during the assembly process, but also improves the positional accuracy of the rudder shaft in the product and the overall assembly accuracy.

[0016] 2. The present invention provides a vertical assembly method for ceramic matrix composite rudder products. By using a vertical assembly method, the problem of assembly errors accumulating on a single side of the product is solved, resulting in more uniform and consistent product dimensions after assembly and improving the accuracy of the product's outline.

[0017] 3. The present invention provides a vertical assembly method for ceramic matrix composite rudder products, which uses the rudder shaft as a reference and performs overall rework on the remaining parts of the product, which can greatly improve the surface accuracy of the product.

[0018] 4. The present invention provides a vertical assembly fixture for ceramic matrix composite rudder products, which also includes a detection block and detection holes set on the base. During the vertical assembly of the product, auxiliary detection of the product surface can be realized. The operation is simple and inspection can be carried out as the product is assembled, which can greatly improve the assembly efficiency and assembly accuracy. Attached Figure Description

[0019] Figure 1 An exploded view of a ceramic matrix composite rudder / wing product; Figure 2 This is a schematic diagram of a vertical assembly fixture for a ceramic matrix composite rudder-type product according to an embodiment of the present invention; Figure 3 This is a schematic diagram of the installation structure in step 2 of an embodiment of a vertical assembly method for ceramic matrix composite rudder products of the present invention; Figure 4 This is a schematic diagram of the installation structure in step 3 of an embodiment of a vertical assembly method for ceramic matrix composite rudder products of the present invention; Figure 5 This is a schematic diagram of the installation structure in step 4 of an embodiment of a vertical assembly method for ceramic matrix composite rudder products of the present invention; Figure 6 This is a schematic diagram of the installation structure in step 5 of an embodiment of a vertical assembly method for ceramic matrix composite rudder products of the present invention; Figure 7 This is a schematic diagram of the installation structure in step 6 of an embodiment of a vertical assembly method for ceramic matrix composite rudder products of the present invention; Figure 8This is a schematic diagram of a ceramic matrix composite rudder wing product assembled according to an embodiment of the vertical assembly method of the present invention.

[0020] The attached figures are labeled as follows: 1-Sleeve, 2-Base, 3-Side support block, 4-Bottom support block, 5-Positioning pin, 6-Tooling bracket, 7-Inspection hole, 8-Mounting hole, 11-Rudder shaft, 12-Lower sealing beam skin, 13-Frame, 14-Upper sealing beam skin, 15-Side skin. Detailed Implementation

[0021] To make the objectives, advantages, and features of the present invention clearer, the present invention will be further described in detail below with reference to the accompanying drawings and specific embodiments. Those skilled in the art should understand that these embodiments are merely used to explain the technical principles of the present invention and are not intended to limit the scope of protection of the present invention.

[0022] like Figure 1 As shown, the ceramic matrix composite rudder wing product to be assembled in this embodiment includes a rudder shaft 11, a lower sealing beam skin 12, a frame 13, an upper sealing beam skin 14, and a side skin 15. Each component is connected to the rudder shaft 11, and the rudder shaft 11 and the frame 13 are located within the space enclosed by the lower sealing beam skin 12, the upper sealing beam skin 14, and the side skin 15.

[0023] like Figure 2 As shown, this embodiment provides a vertical assembly fixture for ceramic matrix composite rudder products, including a bushing 1, a base 2, a side support block 3, a bottom support block 4, a locating pin 5, and a fixture bracket 6. This assembly fixture not only has a simple structure, but also solves the problem of difficult positioning of the rudder shaft 11 during assembly, improving the positional accuracy of the rudder shaft 11 in the product.

[0024] The base 2 is a long strip structure with a mounting hole 8 at one end along its length to provide a mounting channel for the rudder shaft 11. The bushing 1 is a cylindrical structure that is mounted on the lower side of the base 2 through the mounting hole 8. The tooling bracket 6 is mounted on the lower side of the base 2 away from the bushing 1 to support the base 2. The base 2 serves as the reference base for assembling the tooling. In use, the bottom of the bushing 1 can be placed on the ground, and the other end can be supported by the tooling bracket 6 to ensure the stability of the base 2.

[0025] The bushing 1 is used to assemble the rudder shaft 11, and its internal shape and dimensions are adapted to the shape and dimensions of the lower outer wall of the rudder shaft 11. The rudder shaft 11 is provided with a positioning hole that corresponds to and is adapted to the positioning pin 5. The length of the positioning pin 5 is greater than the radial dimension of the bushing 1. When the lower part of the rudder shaft 11 is installed into the bushing 1, the positioning pin 5 is used to radially pass through the positioning hole on the bushing 1 and the rudder shaft 11 to position the rudder shaft 11.

[0026] Generally, the surface and dimensional accuracy of the inner part of the bushing 1 should be higher than that of the outer part of the corresponding rudder shaft 11, so that the rudder shaft 11 can be finely finished during the assembly process.

[0027] The side support block 3 is installed on the upper side of the base 2 away from the bushing 1. The side support block 3 is a vertically placed block support body with a sloping surface at the top that slopes towards the center of the base 2. This sloping surface is used to support the side of the lower sealing beam skin 12 away from the rudder shaft 11 and is adapted to the profile of the side of the lower sealing beam skin 12 away from the rudder shaft 11. The distance between the side support block 3 and the mounting hole 8 is set according to the size of the product to be assembled, so that after the lower sealing beam skin 12 is connected to the rudder shaft 11, the side away from the rudder shaft 11 fits against the sloping surface at the top of the side support block 3 and the bottom fits against the upper surface of the bottom support block 4. This design not only ensures the assembly angle accuracy and positional accuracy between the lower sealing beam skin 12 and the rudder shaft 11, but also allows for fine finishing of the lower sealing beam skin 12, improving the dimensional accuracy of the lower sealing beam skin 12.

[0028] The bottom support block 4 is installed on the upper side of the middle part of the base 2 to support the bottom of the lower sealing beam skin 12. The upper surface of the bottom support block 4 is adapted to the profile of the bottom of the lower sealing beam skin 12.

[0029] To improve assembly accuracy, this embodiment also includes a detection component, which comprises two detection blocks and two detection holes 7 disposed on the base 2. The two detection blocks are used to assist in the detection of the profiles of the lower sealing beam skin 12, the upper sealing beam skin 14, and the side skin 15, and the profiles of the two detection blocks are adapted to the profiles of the corresponding components. The two detection holes 7 are elongated holes that are adapted to and correspond one-to-one with the two detection blocks, and the length direction of the elongated holes is consistent with the length direction of the base 2; the two elongated holes are evenly distributed on both sides of the bottom support block 4 in the width direction.

[0030] This embodiment enables vertical assembly of ceramic matrix composite rudder products, thereby solving the defect of assembly errors accumulating on a single side of the product during assembly and improving the product's assembly accuracy and shape profile.

[0031] In addition, this embodiment also provides a vertical assembly method for ceramic matrix composite rudder products, including the following steps: Step 1: Assemble a vertical assembly fixture for a ceramic matrix composite rudder product and place the assembled fixture on the workbench in an upright manner.

[0032] Prior to this, each component of the ceramic matrix composite rudder wing product to be assembled will have a process allowance in the corresponding part according to the assembly relationship. Its size is slightly larger than the required size of the corresponding finished part, so as to provide space for size reduction during the product repair process and ensure the final dimensional accuracy of the product.

[0033] Step 2: As Figure 3 As shown, the rudder shaft 11 is inserted into the bushing 1 through the mounting hole 8 on the base 2 and positioned by the locating pin 5. During the assembly of the rudder shaft 11, if its size is too large, its surface can be adjusted by CNC milling or grinding according to the actual situation until its lower outer wall fits against the inner wall of the bushing 1.

[0034] Step 3: As Figure 4 As shown, the lower sealing beam skin 12 is vertically fitted onto the rudder shaft 11 from top to bottom, ensuring that it is fully fitted with the rudder shaft 11; at the same time, the side away from the rudder shaft 11 is fitted with the inclined surface of the top of the side support block 3, and the bottom is fitted with the upper surface of the bottom support block 4.

[0035] During this process, taking the rudder shaft 11 as a reference, if the side of the lower sealing beam skin 12 away from the rudder shaft 11 is not in contact with the inclined surface at the top of the side support block 3, or the bottom is not in contact with the upper surface of the bottom support block 4, the corresponding contact surface of the lower sealing beam skin 12 can be adjusted by clamping (generally the bottom of the lower sealing beam skin 12) until the side of the lower sealing beam skin 12 away from the rudder shaft 11 is in contact with the inclined surface at the top of the side support block 3, and the bottom is in contact with the upper surface of the bottom support block 4, to ensure the installation angle and installation position of the lower sealing beam skin 12.

[0036] In addition, two detection blocks are required to pass through the corresponding detection holes 7 from bottom to top, and the distance between the two detection blocks and the two sides of the lower sealing beam skin 12 in the thickness direction is tested to detect the dimension of the lower sealing beam skin 12 in the thickness direction. If the distance meets the design requirements, proceed to step 4; otherwise, the side of the lower sealing beam skin 12 in the thickness direction is repaired according to the detection results until the distance meets the requirements.

[0037] Step 4: As Figure 5 As shown, the frame 13 is placed on the lower sealing beam skin 12, ensuring its relative position to the rudder shaft 11 and the lower sealing beam skin 12 is correct, and that it is in contact with the side wall of the rudder shaft 11 and all mating surfaces of the lower sealing beam skin 12. During this process, using the rudder shaft 11 as a reference, if any mating surface of the frame 13 and the lower sealing beam skin 12 is not fully in contact, the corresponding surface of the frame 13 is adjusted until it is fully in contact with all mating surfaces of the lower sealing beam skin 12.

[0038] In some embodiments, the skeleton 13 further includes multiple components. In this case, the components can be assembled into a complete part first. During the assembly process, the corresponding mating surfaces can be processed and repaired according to the actual assembly situation, and then assembled according to the above steps.

[0039] Step 5: As Figure 6As shown, the upper sealing beam skin 14 is placed on the lower sealing beam skin 12, so that it fits against the side wall of the rudder shaft 11, and also fits against the surfaces of the lower sealing beam skin 12 and the frame 13. During this process, using the rudder shaft 11 as a reference, if some or all of the mating surfaces of the upper sealing beam skin 14 and the lower sealing beam skin 12 and the frame 13 are not fitted, or if the side of the upper sealing beam skin 14 is not flush with the side of the lower sealing beam skin 12, then the corresponding surface of the upper sealing beam skin 14 is trimmed until it fits against the surfaces of the lower sealing beam skin 12 and the frame 13, and is flush with the side of the lower sealing beam skin 12. When the side of the upper sealing beam skin 14 protrudes significantly relative to the side of the lower sealing beam skin 12, it can be machined using CNC milling.

[0040] Step 6: As Figure 7 As shown, the side skin 15 is placed on the lower sealing beam skin 12, positioned on the side of the frame 13 away from the upper sealing beam skin 14, and simultaneously bonded to the surfaces of the rudder shaft 11, lower sealing beam skin 12, frame 13, and upper sealing beam skin 14, thus obtaining a complete ceramic matrix composite rudder wing product. During this process, using the rudder shaft 11 as a reference, if some or all of the mating surfaces of the side skin 15 with the lower sealing beam skin 12, frame 13, and upper sealing beam skin 14 are not bonded, the corresponding surfaces of the side skin 15 are repaired until all surfaces of the side skin 15 are fully bonded to the rudder shaft 11, lower sealing beam skin 12, frame 13, and upper sealing beam skin 14.

[0041] Step 7: Use a coordinate measuring machine (CMM) to inspect the surface profile of the complete ceramic matrix composite rudder / wing product obtained in Step 6. If the inspection is qualified, proceed to Step 8; otherwise, use the rudder shaft 11 as a reference to perform overall machining and rework on the surface profiles of other components until the inspection is qualified, and then proceed to Step 8. When using the CMM, the surface profiles of each component can also be assisted by the inspection block and inspection hole 7, thereby improving assembly efficiency and assembly accuracy.

[0042] Step 8: According to the preset process requirements, prepare connecting holes at corresponding positions on the rudder shaft 11, lower sealing beam skin 12, frame 13, upper sealing beam skin 14, and side skin 15, and connect them through the corresponding connecting holes to complete the assembly of the ceramic matrix composite rudder wing product. Figure 8 As shown.

[0043] In summary, traditional horizontal assembly methods only allow for machining and rework on one side during assembly. This method results in large dimensional deviations, uneven wall thickness, and can easily cause changes in the product's center of gravity, thus affecting subsequent use. This embodiment, however, uses the rudder shaft 11 as a reference and employs a vertical assembly method to install the remaining components. This not only solves the problem of assembly errors accumulating on a single side of the product, resulting in a more uniform and consistent product size, but also allows for the detection of relative errors in specific components, achieving high-precision assembly between all parts. Furthermore, it ensures uniform wall thickness for all components, thereby meeting the accuracy requirements for product dimensions and outer contour.

[0044] The above embodiments are only used to illustrate the technical solutions of the present invention, and are not intended to limit it. Although the present invention has been described in detail with reference to the foregoing embodiments, those skilled in the art should understand that modifications can still be made to the technical solutions described in the foregoing embodiments, or equivalent substitutions can be made to some or all of the technical features therein, and such modifications or substitutions do not cause the essence of the corresponding technical solutions to deviate from the scope of the technical solutions of the present invention.

Claims

1. A vertical assembly fixture for a ceramic matrix composite rudder wing product, the ceramic matrix composite rudder wing product comprising a rudder shaft (11), a lower sealing beam skin (12), a frame (13), an upper sealing beam skin (14), and side skins (15); the rudder shaft (11) and the frame (13) are located within the space enclosed by the lower sealing beam skin (12), the upper sealing beam skin (14), and the side skins (15); characterized in that: It includes bushing (1), base (2), side support block (3), bottom support block (4), positioning pin (5) and tooling bracket (6); The base (2) is a long strip structure with a mounting hole (8) at one end along its length; the bushing (1) is a cylindrical structure and is installed on the lower side of the base (2) through the mounting hole (8); the tooling bracket (6) is installed on the lower side of the base (2) away from the bushing (1) and is used to support the base (2). The bushing (1) is used to assemble the rudder shaft (11), and its internal shape and size are adapted to the shape and size requirements of the lower end of the rudder shaft (11); the length of the positioning pin (5) is greater than the radial dimension of the bushing (1), and it is used to position the rudder shaft (11) by passing through the positioning hole on the bushing (1) and the rudder shaft (11) radially. The side support block (3) is installed on the upper side of the base (2) away from the bushing (1); the side support block (3) is a vertically placed block with a slope at the top that is inclined toward the center of the base (2). This slope is used to support the side of the lower sealing beam skin (12) away from the rudder shaft (11) and is adapted to the profile of the side of the lower sealing beam skin (12) away from the rudder shaft (11). The bottom support block (4) is installed on the upper side of the middle part of the base (2) to support the bottom of the lower sealing beam skin (12), and the upper surface is adapted to the shape of the bottom of the lower sealing beam skin (12).

2. The vertical assembly fixture for ceramic matrix composite rudder products according to claim 1, characterized in that: It also includes a detection component, which includes two detection blocks and two detection holes (7) set on the base (2); the two detection blocks are used to perform auxiliary detection on the surface of the lower sealing beam skin (12), the upper sealing beam skin (14) and the side skin (15); The two detection holes (7) are elongated holes that are adapted to and correspond one-to-one with the two detection blocks. The length direction of the elongated holes is consistent with the length direction of the base (2). The two elongated holes are evenly distributed on both sides of the width direction of the bottom support block (4).

3. The vertical assembly fixture for ceramic matrix composite rudder products according to claim 1 or 2, characterized in that: The internal profile and dimensional accuracy of the bushing (1) are higher than those of the external profile and dimensional accuracy of the corresponding rudder shaft (11).

4. A vertical assembly method for ceramic matrix composite rudder-type products, characterized in that, Includes the following steps: Step 1: Assemble the vertical assembly fixture for the ceramic matrix composite rudder product as described in claim 1, 2 or 3, and place it upright on the workbench; Step 2: Insert the rudder shaft (11) into the bushing (1) through the mounting hole (8) on the base (2) and position it using the locating pin (5); Step 3: Fit the lower sealing beam skin (12) onto the rudder shaft (11) from top to bottom, so that it fits against the rudder shaft (11), while the side away from the rudder shaft (11) fits against the inclined surface of the top of the side support block (3) and the bottom fits against the upper surface of the bottom support block (4). Step 4: Place the frame (13) on the lower sealing beam skin (12) so that its relative position with the rudder shaft (11) and the lower sealing beam skin (12) is correct, and at the same time it is in contact with the side wall of the rudder shaft (11) and the various surfaces that are connected to the lower sealing beam skin (12). Step 5: Place the upper sealing beam skin (14) on the lower sealing beam skin (12) so that it fits against the side wall of the rudder shaft (11) and at the same time fits against the various surfaces of the lower sealing beam skin (12) and the frame (13). Step 6: Place the side skin (15) on the lower sealing beam skin (12), so that it is located on the side of the frame (13) away from the upper sealing beam skin (14), and at the same time, it is in contact with the various surfaces of the rudder shaft (11), the lower sealing beam skin (12), the frame (13) and the upper sealing beam skin (14) to obtain a complete ceramic matrix composite rudder wing product. Step 7: Use the coordinate measuring machine to inspect the surface of the complete ceramic matrix composite rudder wing product obtained in Step 6. If the inspection is qualified, proceed to Step 8; otherwise, use the rudder shaft (11) as the reference for rework until the inspection is qualified, and then proceed to Step 8. Step 8: According to the preset process requirements, connection holes are prepared on the rudder shaft (11), lower sealing beam skin (12), frame (13), upper sealing beam skin (14) and side skin (15), and screws are used to connect them through the corresponding connection holes to complete the assembly of ceramic matrix composite rudder wing products.

5. The vertical assembly method for ceramic matrix composite rudder-type products according to claim 4, characterized in that: In step 2, during the process of inserting the rudder shaft (11) into the bushing (1) through the mounting hole (8) on the base (2), the step of making the outer wall of the lower part of the rudder shaft (11) fit with the inner wall of the bushing (1) by clamping is also included.

6. The vertical assembly method for ceramic matrix composite rudder-type products according to claim 4, characterized in that: Step 3 also includes trimming the bottom of the lower sealing beam skin (12) so that the side away from the rudder shaft (11) fits against the slope of the top of the side support block (3) and the bottom fits against the upper surface of the bottom support block (4).

7. The vertical assembly method for ceramic matrix composite rudder-type products according to claim 4, characterized in that: Step 3 also includes using two detection blocks to pass through the corresponding detection holes (7) from bottom to top, and testing the distance between the two detection blocks and the two sides of the thickness direction of the lower sealing beam skin (12). If the distance meets the design requirements, proceed to step 4; otherwise, repair the side of the lower sealing beam skin (12) in the thickness direction according to the detection results until the distance meets the requirements.

8. The vertical assembly method for ceramic matrix composite rudder products according to claim 4, characterized in that: Step 4 also includes trimming the surfaces of the skeleton (13) until they fit together with the surfaces of the lower sealing beam skin (12).

9. The vertical assembly method for ceramic matrix composite rudder products according to claim 4, characterized in that: Step 5 also includes trimming the surface of the upper sealing beam skin (14) until it fits together with the surfaces of the lower sealing beam skin (12) and the frame (13).

10. The vertical assembly method for ceramic matrix composite rudder-type products according to claim 4, characterized in that: Step 6 also includes trimming the corresponding surfaces of the side skin (15) until they fit together with the surfaces of the rudder shaft (11), the lower sealing beam skin (12), the frame (13), and the upper sealing beam skin (14).

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