Integrated butt joint tool and assembly method for C / SiC composite rudder wing cabin

Abstract

The invention discloses an integrated butt joint tool for a C / SiC composite material rudder wing cabin and an assembly method, and mainly solves the technical problems that an existing assembly method is time-consuming and labor-consuming and has safety risks. The butt joint tool comprises a base, a first supporting assembly and a second supporting assembly. The base is divided into a cabin installation area and a wing rudder installation area, the first supporting assembly is located in the cabin installation area, and the second supporting assembly is located in the wing rudder installation area. The first supporting assembly comprises a plurality of first supporting blocks installed on the base and used for supporting the cabin body. The second supporting assembly comprises a supporting seat, a second supporting block and a plurality of third supporting blocks; the supporting seat is located above the base and is in sliding connection with the base, and the sliding direction is perpendicular to the side wall of the cabin body; the second supporting block and the multiple third supporting blocks are installed on the supporting base and used for supporting the wings and the rudders. The invention further provides a rudder and wing cabin integrated assembly method based on the butt joint tool. The method is easy to operate and high in assembly precision and efficiency.

Description

Technical Field

[0001] The invention relates to a rudder-wing cabin docking tool, and in particular to an integrated docking tool for a C / SiC composite material rudder-wing cabin and an assembly method. Background Art

[0002] As a new type of strategic material, C / SiC composite material has the advantages of low density, high strength, high temperature resistance, wear resistance, corrosion resistance, high toughness and oxidation resistance. It is currently widely used in aviation, aerospace, satellites, nuclear energy, photovoltaics and other fields.

[0003] In recent years, the number of large-scale equipment produced using C / SiC composite materials has increased rapidly. During the assembly process of this large-scale equipment, it is usually necessary to dock and assemble a variety of large and complex components, and the difficulty of operation has also increased significantly. Taking the docking assembly of the rudder wing cabin as an example, the existing assembly method is to first hoist the components to be docked, and then manually dock and install them, and then complete them after multiple inspections. This method can ensure a certain assembly accuracy, but at the same time it consumes a lot of manpower and time, and there are also great safety risks during the assembly process. Based on this, it is urgent to design a docking device that is easy to operate. Summary of the invention

[0004] The purpose of the present invention is to solve the technical problems that the existing assembly method is time-consuming, labor-intensive and has safety risks, and to provide an integrated docking tool and assembly method for a C / SiC composite rudder wing cabin.

[0005] To achieve the above objectives, the technical solutions provided by the present invention are:

[0006] An integrated docking tool for a C / SiC composite rudder wing cabin, which is special in that:

[0007] It includes a base, a first support assembly and a second support assembly;

[0008] The base is divided into a cabin installation area and a wing and rudder installation area, wherein the first support assembly is located in the cabin installation area, and the second support assembly is located in the wing and rudder installation area;

[0009] The first support assembly includes a plurality of first support blocks mounted on the base, which are used to support the cabin; positioning pins are respectively installed on the tops of the first support blocks at both ends of the cabin installation area in the length direction, for positioning the two ends of the cabin;

[0010] The second support assembly includes a support seat, a second support block and multiple third support blocks; the support seat is located above the base and is slidably connected to the base, and the sliding direction is perpendicular to the side wall of the cabin; the second support block and multiple third support blocks are respectively installed on the support seat to support the wing and rudder; wherein a hanging point positioning block is installed on the upper surface of the second support block to position the end of the wing close to the rudder.

[0011] Furthermore, the second support assembly further comprises a square shaft positioning block and a round shaft positioning block;

[0012] The square shaft positioning block is installed on the third support block at the end of the wing away from the rudder, and a clamping groove and at least one pressing plate are provided on the upper surface of the square shaft positioning block; the clamping groove is used to clamp the first-stage square shaft at the end of the wing away from the rudder, and the two ends of each pressing plate are respectively connected to the two groove edges of the clamping groove;

[0013] The circular shaft positioning block is installed on the base, and a V-shaped groove is arranged on the upper surface of the circular shaft positioning block, which is used to provide positioning support for the circular shaft of the rudder.

[0014] Further, it also includes a plurality of first gaskets and a plurality of second gaskets;

[0015] The first gasket is located on the top of the first support block and is used to adjust the support height of the cabin;

[0016] The second gasket is located on the top of the third support block and is used to adjust the support height of the wing.

[0017] Further, at least one drilling assembly is included;

[0018] Each of the drilling assemblies comprises a fourth support block and a template; the fourth support block is installed on the base of the cabin installation area; the template is vertically installed above the fourth support block, and the side of the template is adapted to the profile of the side of the cabin; a plurality of through holes are provided on the template, which are used to make connecting holes on the side where the cabin and the wing are fitted in combination with the drilling equipment.

[0019] Furthermore, it also includes a first limit block and a second limit block;

[0020] The first limit block is installed on the base of the cabin installation area, and the second limit block is installed on the base of the wing rudder installation area, and the two are respectively used to limit the two sides of the support seat.

[0021] Furthermore, the first support block, the support seat and the square shaft positioning block are respectively provided with weight-reducing holes.

[0022] At the same time, the present invention also provides an integrated assembly method of a C / SiC composite rudder wing cabin, comprising the following steps:

[0023] Step [1], assembling the integrated docking tooling of the C / SiC composite rudder wing cabin according to the structure of the cabin and the wing, and the position of the square hole of the cabin and the square axis of the wing;

[0024] Step [2], place the cabin on the first support assembly so that the side of the cabin with the square hole faces the rudder installation area, and at the same time, the bottom surface of the cabin is respectively in contact with the upper surface of each first support block, and then the positioning pins are respectively installed on the first support blocks at both ends of the cabin in the length direction to complete the installation of the cabin;

[0025] Step [3], place the wing on the second support assembly so that the side of the wing with the square axis faces the cabin, and the bottom surface of the wing is respectively in contact with the upper surface of each third support block, and the end of the wing close to the rudder is in contact with the upper end surface of the hanging point positioning block on the second support block, thereby completing the installation of the wing;

[0026] Step [4]: ​​Push the support seat toward the cabin until the square axis of the wing is inserted into the square hole of the cabin and the side of the wing fits with the side of the cabin, then connect the side of the cabin and the side of the wing to complete the assembly of the cabin and the wing;

[0027] Step [5], remove the hanging point positioning block on the second support block, insert the circular shaft of the rudder into the end of the wing first, and then insert it into the circular hole of the cabin until the side of the rudder and the side of the cabin are in contact, thereby completing the integrated assembly of the C / SiC composite rudder wing cabin.

[0028] Further, in step [3], when the height of the square axis of the wing is inconsistent with the height of the corresponding square hole after the wing is installed, a second gasket is added between the third support block and the bottom surface of the wing to adjust the height of the wing, or, return to step [2], and add a first gasket between the first support block and the bottom surface of the cabin to adjust the height of the cabin until the square axis corresponds to the height of the corresponding square hole.

[0029] Furthermore, step [2] also includes the step of making a connection hole on the cabin body, specifically:

[0030] When the cabin is installed, install a drilling assembly on the base of the cabin near the wing and rudder installation area, so that the side of the template fits with the side wall of the corresponding position of the cabin, and the through holes on the template correspond to the punching positions of the connecting holes, and then use the hole-making equipment to make connecting holes on the side wall of the cabin, and then remove the drilling assembly.

[0031] Furthermore, in step [4], when the square shaft of the wing is blocked during the process of extending into the square hole of the cabin, the square shaft is adjusted by clamping until the square shaft of the wing extends into the square hole of the cabin and the side surface of the wing fits with the side surface of the cabin;

[0032] In step [4], the connecting of the side of the cabin and the side of the wing means making threaded holes corresponding to the connecting holes on the side of the wing through the connecting holes on the cabin, and then connecting the cabin and the wing with bolts.

[0033] Compared with the prior art, the present invention has the following beneficial effects:

[0034] 1. The present invention comprises a base, a first supporting assembly and a second supporting assembly, wherein the first supporting assembly is used to support the cabin, and the second supporting assembly is used to support the wing and the rudder, and can slide relative to the base. After the cabin, the wing and the rudder are fixed respectively, the supporting seat can be pushed to realize the rapid docking of the cabin, the wing and the rudder. The docking accuracy and efficiency of the tooling are high.

[0035] 2. The present invention also includes a square shaft positioning block and a round shaft positioning block, wherein the square shaft positioning block is used to position the first-stage square shaft at one end of the wing away from the rudder, and the round shaft positioning block is used to provide positioning support for the round shaft of the rudder, thereby improving the stability of the rudder-wing cabin docking process.

[0036] 3. The present invention also includes a plurality of first gaskets and a plurality of second gaskets, which can adjust the support height of the cabin or the wing according to needs, thereby ensuring the docking accuracy between the shaft and the corresponding hole.

[0037] 4. The present invention also includes at least one drilling assembly, which facilitates making connection holes on the cabin after the cabin is installed, and then making corresponding holes on the wing side according to the connection holes, thereby ensuring the compatibility between the cabin and the wing connection holes, thereby improving assembly accuracy.

[0038] 5. The present invention also includes a first limit block and a second limit block, which can limit the sliding of the support seat on the base, thereby improving the safety of the assembly process.

[0039] 6. The integrated assembly method of the C / SiC composite material rudder wing cabin of the present invention is simple to operate, and has high assembly accuracy, assembly efficiency and safety. BRIEF DESCRIPTION OF THE DRAWINGS

[0040] Figure 1 The structure of an integrated docking tooling embodiment of a C / SiC composite rudder wing cabin of the present invention is schematically shown. Figure 1 .

[0041] Figure 2 The structure of an integrated docking tooling embodiment of a C / SiC composite rudder wing cabin of the present invention is schematically shown. Figure 2 .

[0042] Figure 3 This is a reference diagram of the use status of an integrated docking tool for a C / SiC composite material rudder wing cabin of the present invention.

[0043] The reference numerals are as follows:

[0044] 1-base, 2-cabin installation area, 3-wing and rudder installation area, 4-first support block, 5-cabin, 6-support seat, 7-second support block, 71-hanging point positioning block, 8-third support block, 9-wing, 10-rudder, 11-square shaft positioning block, 111-pressure plate, 12-circular shaft positioning block, 13-drilling assembly, 131-fourth support block, 132-template, 14-first limit block, 15-second limit block. DETAILED DESCRIPTION

[0045] In order to make the purpose, advantages and features of the present invention clearer, the present invention is further described in detail below in conjunction with the accompanying drawings and specific embodiments. It should be understood by those skilled in the art that these embodiments are only used to explain the technical principles of the present invention and are not intended to limit the scope of protection of the present invention.

[0046] like Figure 1 and Figure 2 As shown, this embodiment provides an integrated docking tool for a C / SiC composite rudder wing cabin, comprising a base 1, a first support assembly and a second support assembly. The base 1 is divided into a cabin installation area 2 and a wing rudder installation area 3, wherein the first support assembly is located in the cabin installation area 2, and the second support assembly is located in the wing rudder installation area 3.

[0047] The first support assembly includes a plurality of first support blocks 4 mounted on the base 1, which are used to support the cabin 5. Positioning pins are respectively installed on the top of the first support blocks 4 at both ends of the cabin installation area 2 in the length direction, which are used to position the two ends of the cabin 5. After the cabin 5 is installed and positioned, the cabin 5 will not be displaced under the action of gravity due to its large weight. In this embodiment, two protrusions are also respectively provided on the top of each first support block 4, so that when adjusting its installation height later, the first gasket can be inserted into the corresponding two protrusions.

[0048] The second support assembly includes a support seat 6, a second support block 7 and a plurality of third support blocks 8; the support seat 6 is located above the base 1 and is slidably connected to the base 1, and the sliding direction is perpendicular to the side wall of the cabin 5. Specifically, the base 1 is provided with a plurality of parallel slide rails, which are installed on the base 1 and are perpendicular to the side wall of the cabin 5; a slider corresponding to the slide rail is provided at the bottom of the support seat 6, thereby realizing the sliding connection between the support seat 6 and the base 1.

[0049] The second support block 7 and the third support blocks 8 are respectively mounted on the support seat 6 to support the wing 9 and the rudder 10. In this embodiment, a hanging point positioning block 71 is also mounted on the upper surface of the second support block 7 to position the end of the wing 9 close to the rudder 10.

[0050] In order to improve the accuracy of support and positioning, the second support assembly of this embodiment further includes a square shaft positioning block 11 and a round shaft positioning block 12 .

[0051] The square shaft positioning block 11 is installed on the third support block 8 at the end of the wing 9 away from the rudder 10, and a clamping groove and at least one pressing plate 111 are provided on its upper surface; the clamping groove is used to clamp the first-stage square shaft at the end of the wing 9 away from the rudder 10, and the two ends of each pressing plate 111 are respectively connected to the two groove edges of the clamping groove, so as to realize the positioning of the wing 9. It should be noted that the first-stage square shaft of the wing 9 will not extend into the cabin 5 when docking.

[0052] The circular shaft positioning block 12 is installed on the base 1 , and a V-shaped groove is provided on the upper surface of the circular shaft positioning block 12 for providing positioning support for the circular shaft of the rudder 10 .

[0053] In order to ensure the accuracy of docking between the wing 9 and the cabin 5, the present embodiment further includes a plurality of first gaskets and a plurality of second gaskets. The first gasket is located on the top of the first support block 4 and is used to adjust the support height of the cabin 5. The second gasket is located on the top of the third support block 8 and is used to adjust the support height of the wing 9. The first gasket or the second gasket is used according to the actual situation during assembly, thereby improving the assembly accuracy of the wing 9 and the cabin 5.

[0054] This embodiment further includes at least one drilling assembly 13, each of which includes a fourth support block 131 and a template 132. The fourth support block 131 is installed on the base 1 of the cabin installation area 11; the template 132 is vertically installed above the fourth support block 131, and the side of the template 132 is adapted to the profile of the side of the cabin 5. The template 132 is provided with a plurality of through holes, which are used to make corresponding connection holes on the side of the cabin 5 and the wing 9 in combination with the drilling equipment.

[0055] This embodiment also includes a first limit block 14 and a second limit block 15. The first limit block 14 is installed on the base 1 of the cabin installation area 2, and the second limit block 15 is installed on the base 1 of the rudder installation area 3. The two are used to limit the two sides of the support seat 6 close to the cabin 5 and away from the cabin 5, respectively, to ensure the safety of the assembly process. The number and specific positions of the first limit block 14 and the second limit block 15 are generally set according to actual needs.

[0056] In this embodiment, weight-reducing holes are respectively provided on the first support block 4, the support seat 6, and the square shaft positioning block 11, thereby reducing the manufacturing cost and improving the efficiency of tooling assembly.

[0057] Combination Figure 1 , Figure 2 , Figure 3 This embodiment also provides an integrated assembly method of a C / SiC composite rudder wing cabin, comprising the following steps:

[0058] Step [1], assembling the integrated docking tooling of the C / SiC composite rudder wing cabin of the present invention according to the structure of the cabin 5 and the wing 9, and the positions of the square hole of the cabin 5 and the square axis of the wing 9.

[0059] Step [2], place the cabin 5 on the first support assembly so that the side of the cabin 5 with the square hole faces the rudder mounting area 3. At the same time, the bottom surface of the cabin 5 is respectively in contact with the upper surface of each first support block 4, and then the positioning pins are respectively installed on the first support blocks 4 at both ends of the cabin 5 in the length direction, thereby completing the installation of the cabin 5.

[0060] In order to make full use of the docking tooling, after the installation of the cabin 5 is completed, the drilling assembly 13 is installed at the corresponding position on the base 1 of the cabin 5 close to the rudder installation area 3, so that the side of the template 132 is in contact with the side wall of the cabin 5, and the through hole on the template 132 corresponds to the drilling position of the connecting hole, and then a diamond drill bit is used to drill the connecting hole to the cabin 5 through the through hole on the template 132. After the hole is made, the drilling assembly 13 is removed.

[0061] Step [3], place the wing 9 on the second support assembly so that the side of the wing 9 with the square axis faces the cabin 5, and the bottom surface of the wing 9 fits with the upper surface of each third support block 8, and at the same time, the end of the wing 9 close to the rudder 10 fits with the upper end surface of the hanging point positioning block 71 on the second support block 7. In this process, the first-level square axis of the end of the wing 9 away from the rudder 10 is just clamped in the slot of the square axis positioning block 11 at its end, and then the two ends of the pressure plate 111 are respectively connected to the two groove edges of the slot, so as to fix the first-level square axis. At the same time, another pressure block is pressed on the top of the wing 9, and then the pressure block is fastened to the support seat 6 by long bolts to achieve the positioning of the wing from top to bottom, thereby completing the installation and positioning of the wing 9.

[0062] When the wing 9 is installed, if the height of its square axis is inconsistent with the height of the corresponding square hole, it is necessary to add a second gasket between the third support block 8 and the bottom surface of the wing 9 to adjust the height of the wing 9 according to the actual situation; or return to step [2] and add a first gasket between the first support block 4 and the bottom surface of the cabin 5 to adjust the height of the cabin 5 until the square axis corresponds to the height of the corresponding square hole. In the process of adjusting the height of the wing 9, the pressing plate 111 can be removed as needed, and after adjustment, the first-level square axis of the wing 9 can be fixed by the pressing plate 111.

[0063] Step [4]: ​​Push the support seat 6 toward the direction close to the cabin body 5 so that the square shaft of the wing 9 is slowly inserted into the square hole of the cabin body 5. When the square shaft of the wing 9 is blocked in the process of extending into the square hole of the cabin body 5, the corresponding square shaft is adjusted by clamping until the square shaft of the wing 9 can smoothly extend into the square hole of the cabin body 5 and the side of the wing 9 fits with the side of the cabin body 5. Then, the side of the cabin body 5 and the side of the wing 9 are connected to complete the assembly of the cabin body 5 and the wing 9.

[0064] In the present embodiment, connecting the side of the cabin 5 and the side of the wing 9 means that first, threaded holes corresponding to the connecting holes are made on the sides of the wing 9 through the connecting holes on the cabin 5, that is, using the connecting holes on the cabin 5 as a template, holes are punched from the inside of the cabin 5 to the side walls of the wing 9, and then bolts of corresponding specifications are used to connect and fasten the cabin 5 and the wing 9.

[0065] Step [5], remove the hanging point positioning block 71 on the second support block 7, support the rudder 10 with the second support block 7 and the corresponding third support block 8, and then push the rudder 10, and first extend the circular shaft of the rudder 10 into the end of the wing 9 to connect it with the wing 9; then continue to push the rudder 10, so that the circular shaft of the rudder 10 slowly extends into the circular hole of the cabin 3 until the side of the rudder 10 and the side of the cabin 5 are in contact, and then the circular shaft of the rudder 10 is fixed to the cabin 5 from the radial direction by bolts, thereby completing the integrated assembly of the C / SiC composite rudder wing cabin.

[0066] In some embodiments, after the wing 9 and the rudder 10 are installed separately, the support seat 6 can be pushed so that the wing 9 and the rudder 10 are pushed toward the cabin 5 simultaneously, thereby improving the efficiency of assembly.

[0067] The present invention first installs the cabin 5 on the first support assembly; then, the drilling assembly 13 is used to drill the bolt connection hole on the side of the cabin 5, and then the drilling assembly 13 is disassembled; then, the wing 9 is installed on the second support assembly and fixed by a pressure plate to ensure the accuracy of the positioning of the cabin 5 and the wing 9; then, the support seat 6 is pushed toward the cabin 5, and the square shaft of the wing 9 is inserted into the corresponding square hole of the cabin 5. Interference may be encountered during the insertion process, and the interference position can be repaired by clamping until the square shaft of the wing 9 can be smoothly inserted into the square hole of the cabin 5 and the side of the wing 9 fits the side of the cabin 5; then, the bolt connection hole on the side of the cabin 5 is used to drill the bolt connection hole on the side of the wing 9, and the cabin 5 and the wing 9 are connected by bolts. Finally, the round shaft of the rudder 10 is inserted into the corresponding round hole of the cabin 5, and connected and tightened, thereby completing the docking assembly work of the rudder wing cabin. The method is simple to operate, and the assembly accuracy and assembly efficiency are both high.

[0068] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of the present invention, rather than to limit it. Although the present invention has been described in detail with reference to the aforementioned embodiments, those skilled in the art should understand that they can still modify the technical solutions described in the aforementioned embodiments, or replace some or all of the technical features therein with equivalents. However, these modifications or replacements 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. An integrated docking tool for a C / SiC composite rudder wing cabin, characterized by: It comprises a base (1), a first support assembly and a second support assembly; The base (1) is divided into a cabin installation area (2) and a wing and rudder installation area (3), wherein the first support assembly is located in the cabin installation area (2), and the second support assembly is located in the wing and rudder installation area (3); The first support assembly comprises a plurality of first support blocks (4) mounted on the base (1) and used to support the cabin (5); positioning pins are respectively mounted on the tops of the first support blocks (4) at both ends of the cabin installation area (2) in the length direction, used to position the two ends of the cabin (5); The second support assembly comprises a support seat (6), a second support block (7) and a plurality of third support blocks (8); the support seat (6) is located above the base (1) and is slidably connected to the base (1), and the sliding direction is perpendicular to the side wall of the cabin (5); the second support block (7) and the plurality of third support blocks (8) are respectively mounted on the support seat (6) for supporting the wing (9) and the rudder (10); wherein a hanging point positioning block (71) is mounted on the upper surface of the second support block (7) for positioning the end of the wing (9) close to the rudder (10).

2. The integrated docking tool for the C / SiC composite rudder wing cabin according to claim 1, characterized in that: The second support assembly further comprises a square shaft positioning block (11) and a round shaft positioning block (12); The square shaft positioning block (11) is mounted on a third support block (8) at the end of the wing (9) away from the rudder (10), and a clamping groove and at least one pressing plate (111) are provided on the upper surface of the square shaft positioning block (11); the clamping groove is used to clamp the first-stage square shaft at the end of the wing (9) away from the rudder (10), and the two ends of each pressing plate (111) are respectively connected to the two groove edges of the clamping groove; The circular shaft positioning block (12) is mounted on the base (1), and a V-shaped groove is provided on the upper surface of the circular shaft positioning block (12) for providing positioning support for the circular shaft of the rudder (10).

3. The integrated docking tool for the C / SiC composite rudder wing cabin according to claim 1 or 2, characterized in that: Also included are a plurality of first gaskets and a plurality of second gaskets; The first gasket is located on the top of the first support block (4) and is used to adjust the support height of the cabin (5); The second gasket is located on the top of the third support block (8) and is used to adjust the support height of the wing (9).

4. The integrated docking tool for the C / SiC composite rudder wing cabin according to claim 1, characterized in that: Also includes at least one drilling assembly (13); Each of the drilling assemblies (13) comprises a fourth support block (131) and a template (132); the fourth support block (131) is mounted on a base (1) of a cabin installation area (11); the template (132) is vertically mounted above the fourth support block (131), and the side surface of the template (132) is adapted to the profile of the side surface of the cabin (5); a plurality of through holes are provided on the template (132), which are used to make connection holes on the side surface where the cabin (5) and the wing (9) are in contact with each other in combination with a drilling device.

5. The integrated docking tool for the C / SiC composite rudder wing cabin according to claim 1, characterized in that: It also includes a first limiting block (14) and a second limiting block (15); The first limit block (14) is installed on the base (1) of the cabin installation area (2), and the second limit block (15) is installed on the base (1) of the rudder installation area (3), and the two are respectively used to limit the two sides of the support seat (6).

6. The integrated docking tool for the C / SiC composite rudder wing cabin according to claim 2, characterized in that: The first support block (4), the support seat (6) and the square shaft positioning block (11) are respectively provided with weight-reducing holes.

7. An integrated assembly method for a C / SiC composite rudder wing cabin, characterized in that: The following steps are involved: Step [1], assembling the integrated docking tooling of the C / SiC composite rudder wing cabin according to any one of claims 1 to 6 according to the structures of the cabin (5) and the wing (9), and the positions of the square hole of the cabin (5) and the square axis of the wing (9); Step [2], placing the cabin (5) on the first support assembly so that the side of the cabin (5) with the square hole faces the rudder installation area (3), and at the same time, the bottom surface of the cabin (5) is respectively in contact with the upper surface of each first support block (4), and then the positioning pins are respectively installed on the first support blocks (4) at both ends of the cabin (5) in the length direction to complete the installation of the cabin (5); Step [3], placing the wing (9) on the second support assembly, so that the side of the wing (9) with the square axis faces the cabin (5), and the bottom surface of the wing (9) is respectively in contact with the upper surface of each third support block (8), and at the same time, the end of the wing (9) close to the rudder (10) is in contact with the upper end surface of the hanging point positioning block (71) on the second support block (7), thereby completing the installation of the wing (9); Step [4], push the support seat (6) toward the cabin (5) until the square axis of the wing (9) extends into the square hole of the cabin (5) and the side of the wing (9) fits with the side of the cabin (5), then connect the side of the cabin (5) and the side of the wing (9) to complete the assembly of the cabin (5) and the wing (9); Step [5], remove the hanging point positioning block (71) on the second support block (7), and insert the circular axis of the rudder (10) into the end of the wing (9) first, and then insert it into the circular hole of the cabin (3), until the side of the rudder (10) and the side of the cabin (5) are in contact, thereby completing the integrated assembly of the C / SiC composite material rudder and wing cabin.

8. The integrated assembly method of the C / SiC composite rudder wing cabin according to claim 7, characterized in that: In step [3], when the wing (9) is installed and the height of its square axis is inconsistent with the height of the corresponding square hole, a second gasket is added between the third support block (8) and the bottom surface of the wing (9) to adjust the height of the wing (9), or, return to step [2], and a first gasket is added between the first support block (4) and the bottom surface of the cabin (5) to adjust the height of the cabin (5) until the square axis corresponds to the height of the corresponding square hole.

9. The integrated assembly method of the C / SiC composite rudder wing cabin according to claim 7, characterized in that: Step [2] also includes the step of making a connection hole on the cabin (5), specifically: When the cabin (5) is installed, a drilling assembly (13) is installed on the base (1) of the cabin (5) near the rudder installation area (3), so that the side of the template (132) fits with the side wall of the cabin (5) at the corresponding position, and the through hole on the template (132) corresponds to the punching position of the connection hole, and then the connection hole is made on the side wall of the cabin (5) in combination with the hole making equipment, and then the drilling assembly (13) is removed.

10. The integrated assembly method of the C / SiC composite rudder wing cabin according to claim 9, characterized in that: In step [4], when the square shaft of the wing (9) is blocked during the process of extending into the square hole of the cabin (5), the square shaft is adjusted by clamping until the square shaft of the wing (9) extends into the square hole of the cabin (5) and the side surface of the wing (9) fits with the side surface of the cabin (5); In step [4], the side of the cabin (5) and the side of the wing (9) are connected by making threaded holes corresponding to the connection holes on the side of the wing (9) through the connection holes on the cabin (5), and then connecting the cabin (5) and the wing (9) with bolts.

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