Integrated fiber composite attitude control cabin

Abstract

The present invention provides an integrated fiber composite attitude control cabin, comprising: an attitude control cabin body and a bulkhead. The attitude control cabin body is integrally formed from fiber composite material and includes an upper flange, a lower flange, an upper cone section, a lower cone section, a center tube, and a web. The center tube is located between the upper and lower flanges, forming a dumbbell-shaped structure. Both the upper and lower cone sections have conical funnel-shaped structures. The large opening of the upper cone section is connected to the opening of the upper flange, and the small opening of the upper cone section is connected to the top of the center tube. The large opening of the lower cone section is connected to the opening of the lower flange, and the small opening of the lower cone section is connected to the bottom of the center tube. Multiple webs are provided and distributed around the axis of the center tube. The top of the web is connected to the upper flange, the bottom of the web is connected to the lower flange, and the inner side of the web is connected to the upper cone section, the center tube, and the lower cone section. The bulkhead is disposed between the paired webs. This design overcomes the drawbacks of existing metal attitude control cabins, which suffer from heavy weight, resulting in reduced economic efficiency and increased difficulty in attitude adjustment.

Description

Technical Field

[0001] The present invention relates to the technical field of spacecraft attitude control components, and in particular to an integrated fiber composite material attitude control cabin. Background Art

[0002] To achieve orbital insertion and attitude control, the final stage of a space launch vehicle requires a power system onboard an attitude control module to adjust the vehicle's pitch, yaw, and roll to ensure precise orbital insertion of the payload. Existing attitude control modules are constructed of metal, with separate components for the equipment compartment housing the power equipment and the payload support. This creates a heavy load, reducing the rocket's payload capacity and economical efficiency. Furthermore, the high moment of inertia makes attitude control more difficult. Furthermore, the complex connections of this split design reduce product reliability. Summary of the Invention

[0003] Therefore, the technical problem to be solved by the present invention is to overcome the defects of the metal attitude control cabin in the prior art, which results in reduced economy and increased difficulty in attitude adjustment due to its heavy weight.

[0004] In order to solve the above technical problems, the present application provides an integrated fiber composite attitude control cabin, comprising: an attitude control cabin body and a partition;

[0005] The main body of the attitude control cabin includes: upper flange, lower flange, upper cone section, lower cone section, center tube and web;

[0006] The center tube is located between the upper flange and the lower flange to form a dumbbell-shaped structure;

[0007] Both the upper cone section and the lower cone section are in a conical funnel structure; the large opening of the upper cone section is connected to the orifice of the upper flange, and the small opening of the upper cone section is connected to the top end of the center tube; the large opening of the lower cone section is connected to the orifice of the lower flange, and the small opening of the lower cone section is connected to the bottom end of the center tube;

[0008] There are multiple webs, each of which is distributed around the circumference of the central tube axis on the outside of the central tube, the top of the web is connected to the upper flange, the bottom of the web is connected to the lower flange, one side of the web faces inward and the other side faces outward, and the inner side of the web is connected to the upper cone section, the central tube and the lower cone section;

[0009] The upper flange, lower flange, upper cone section, lower cone section, center tube and each web are integrally formed using fiber composite materials;

[0010] The partition plate is provided between the paired webs.

[0011] Furthermore, a center tube thickening area protruding from the outer side surface of the center tube is provided on the center tube, and the center tube thickening area is provided in a ring shape around the axis of the center tube.

[0012] Furthermore, the webs are arranged in pairs, the two webs in each pair are parallel to each other, the two side edges of the partition are connected to the paired webs one by one, one end of the partition faces outward and the other end faces inward, and the inner end of the partition is connected to the thickened area of ​​the center tube.

[0013] Furthermore, the partition includes:

[0014] Partition horizontal board,

[0015] The inner end plate of the partition is arranged at the inner end of the partition transverse plate and is perpendicular to the partition transverse plate;

[0016] The outer end plate of the partition is arranged at the outer end of the partition transverse plate and is perpendicular to the partition transverse plate;

[0017] Two partition side end plates are arranged on the sides of the partition transverse plate and are perpendicular to the partition transverse plate; the partition inner end plate, the partition outer end plate and the two partition side end plates are combined to form a frame shape;

[0018] Partition connection holes are provided on the inner end plate and the side end plate of the partition, and main body connection holes that are compatible with the partition connection holes are provided on the thickened area of ​​the central tube and the web. The partition connection holes and the main body connection holes are connected by bolts or rivets.

[0019] Furthermore, an upper cone section thickened area is provided in an area of ​​the upper cone section close to the upper flange, and the upper cone section thickened area has the same thickness as the upper flange.

[0020] Furthermore, a lower cone section thickened area is provided in an area of ​​the lower cone section close to the lower flange and the web, and the thickness of the lower cone section thickened area is the same as that of the lower flange.

[0021] Furthermore, a web thickening area is provided at the lower portion of the outer side of the web, and the web thickening area protrudes from the surface of the web in a direction away from the space between the paired webs.

[0022] Furthermore, a plurality of partitions are arranged between the paired webs along the axial direction of the central tube.

[0023] Furthermore, the web thickened area is located between the lower flange and the partition closest to the lower flange.

[0024] Furthermore, a transition zone with gradually changing thickness is provided at the connection where the thickness changes among the upper flange, the lower flange, the upper cone section, the lower cone section, the center tube, the web, the center tube thickening area, the upper cone section thickening area, the lower cone section thickening area and the web thickening area. The transition zone is realized by dropping layers during the laying process of the carbon fiber composite material.

[0025] By adopting the above technical solution, the present invention has the following technical effects:

[0026] The attitude control module of this device consists of an upper flange, a lower flange, an upper cone section, a lower cone section, and a central tube connected in a dumbbell shape. These are combined with multiple webs positioned within the dumbbell's center and arranged radially around the central tube's axis, forming a structure with high structural strength and low material consumption. Furthermore, this structure can be manufactured using carbon fiber cloth, which is laid out in a mold and then pressed and cured in an autoclave. This makes the fiber composite attitude control module even lighter, achieving a significant weight reduction of 40% compared to metal-based modules. When used on a standard launch vehicle, this module can increase the payload by over 45 kg, improving the vehicle's economic efficiency. It also reduces the payload's moment of inertia during attitude adjustments, enhancing controllability and saving fuel, thereby reducing fuel consumption and further increasing the vehicle's payload capacity. Made of carbon fiber composite, this module meets the Class A standard in the "GJB2895-1997 General Specification for Carbon Fiber Composite Laminates and Laminated Components." The attitude control cabin's main structure is simple and compact, and its integrated molding process is rational and feasible. The mold is simple and easy to manufacture, resulting in a short product production cycle. The overall manufacturing process is repeatable and has a high yield rate, meeting the needs of mass production. BRIEF DESCRIPTION OF THE DRAWINGS

[0027] In order to more clearly illustrate the specific embodiments of the present invention or the technical solutions in the prior art, the following briefly introduces the drawings required for use in the specific embodiments or the description of the prior art. Obviously, the drawings described below are some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying any creative work.

[0028] Figure 1 This is a schematic structural perspective diagram of Example 1 of the present invention;

[0029] Figure 2 This is a schematic front view of the structure of the attitude control cabin body according to Example 1 of the present invention;

[0030] Figure 3 This is a schematic top view of the structure of the attitude control cabin body according to Example 1 of the present invention;

[0031] Figure 4 for Figure 2 Cross-sectional view at AA in the middle;

[0032] Figure 5 for Figure 3 Cross-sectional view at the middle BB;

[0033] Figure 6 for Figure 5 A partial enlarged view of point D in the middle;

[0034] Figure 7 for Figure 5 A partial enlarged view of point E in the middle;

[0035] Figure 8 for Figure 5 A partial enlarged view of point F in the middle;

[0036] Figure 9 for Figure 2 Cross-sectional view at CC;

[0037] Figure 10 This is a schematic structural perspective view of the attitude control cabin body according to an embodiment of the present invention;

[0038] Figure 11 A schematic perspective view of the structure of a first embodiment of a partition according to an embodiment of the present invention;

[0039] Figure 12 A schematic top view of the structure of a first embodiment of a partition according to an embodiment of the present invention;

[0040] Figure 13 A schematic perspective view of the structure of a second embodiment of a partition according to an embodiment of the present invention;

[0041] Figure 14 This is a flow chart of the preparation process of the attitude control cabin body according to an embodiment of the present invention.

[0042] Description of reference numerals:

[0043] 1- Attitude control cabin body, 2- Bulkhead, 3- Upper flange, 4- Upper cone section thickened area, 5- Upper cone section, 6- Web plate, 7- Main body connection hole, 8- Center tube, 9- Web plate thickened area, 10- Lower flange, 11- Lower cone section, 12- Lower cone section thickened area, 13- Transition area, 14- Center tube thickened area, 15- Bulkhead inner end plate, 16- Bulkhead side end plate, 17- Bulkhead transverse plate, 18- Bulkhead outer end plate, 19- Bulkhead connection hole, 20- Bulkhead neutral plate. DETAILED DESCRIPTION

[0044] The technical solution of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the embodiments described are only some embodiments of the present invention, not all embodiments. All other embodiments obtained by ordinary technicians in this field based on the embodiments of the present invention without making any creative efforts shall fall within the scope of protection of the present invention.

[0045] It should be noted that the coordinate system used in the description of the present invention is based on Figure 2The orientation or position relationship indicated by the terms "center", "up", "down", "left", "right", "vertical", "horizontal", "inside" and "outside" in this specification is based on the orientation or position relationship shown in the accompanying drawings, and is only for the convenience of describing the present invention and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore cannot be understood as limiting the present invention.

[0046] In the description of the present invention, it should be noted that, unless otherwise expressly specified or limited, the terms "mounted," "connected," and "connected" should be understood in a broad sense. For example, they may refer to fixed, detachable, or integral connections; mechanical or electrical connections; direct or indirect connections through an intermediate medium; and internal communication between two components. Those skilled in the art will understand the specific meanings of the above terms in the present invention based on the specific circumstances.

[0047] In addition, the technical features involved in the different embodiments of the present invention described below can be combined with each other as long as they do not conflict with each other.

[0048] This embodiment provides an integrated fiber composite material attitude control cabin.

[0049] In one embodiment, Figures 1 to 14 As shown, it includes: an attitude control cabin body 1 and a partition 2.

[0050] The attitude control cabin body 1 includes: an upper flange 3, a lower flange 10, an upper cone section 5, a lower cone section 11, a central tube 8 and a web 6.

[0051] The central tube 8 is located between the upper flange 3 and the lower flange 10 , and the three form a dumbbell-shaped structure.

[0052] Both the upper conical section 5 and the lower conical section 11 have a conical funnel structure. The large opening of the upper conical section 5 is connected to the opening of the upper flange 3, that is, the edge of the inner hole of the flange, and the small opening of the upper conical section 5 is connected to the top of the center tube 8. The large opening of the lower conical section 11 is connected to the opening of the lower flange 10, and the small opening of the lower conical section 11 is connected to the bottom end of the center tube 8.

[0053] There are multiple webs 6, and each web 6 is distributed on the outside of the center tube 8 around the axis of the center tube 8. The top of the web 6 is connected to the upper flange 3, and the bottom of the web 6 is connected to the lower flange 10. One side of the web 6 faces inward and the other side faces outward. The inner side of the web 6 is connected to the upper cone section 5, the center tube 8 and the lower cone section 11.

[0054] The upper flange 3, lower flange 10, upper cone section 5, lower cone section 11, center tube 8, and webs 6 are integrally formed from a fiber composite material. Preferably, they are made from carbon fiber-reinforced epoxy resin-based composite unidirectional tapes and carbon fiber-reinforced epoxy resin-based composite fabrics. Different resin systems (such as bismaleimide, epoxy, and phenolic resins) can also be selected, as can different grades of carbon fiber, aramid fiber, or glass fiber, depending on strength requirements.

[0055] The bulkhead 2 is disposed between the paired webs 6. The bulkhead 2 can be made of the same material as the attitude control cabin body 1, such as carbon fiber reinforced epoxy resin-based composite unidirectional tape and carbon fiber reinforced epoxy resin-based composite fabric. However, due to its lower stress requirements, it can also be made of only carbon fiber reinforced epoxy resin-based composite fabric.

[0056] The above-mentioned attitude control cabin body 1 and partition 2 can be prepared by composite material autoclave process, that is, a process method in which a preformed body made of prepreg is placed in an autoclave after being packaged in a preset direction, and then cured at a certain preset temperature and pressure. The specific preparation process flow can be found in the attached Figure 14 :Specific steps are as follows:

[0057] 1. Prepreg preparation: After the prepreg is taken out of the cold storage, when it reaches the ambient temperature and there is no condensation on the surface, open the plastic sealed bag and take out the prepreg.

[0058] 2. Blanking: Use a blanking machine to cut the prepreg into suitable shapes and sizes for easy laying.

[0059] 3. Mold cleaning: Check the mold to confirm that there is no local damage. Use a clean industrial cloth dipped in alcohol to wipe the mold surface to ensure that the surface is clean and free of foreign matter.

[0060] 4. Laying: According to the lay-up table and lay-up distribution requirements, use the material blocks unloaded by the blanking machine to lay the prepreg on the mold.

[0061] 5. Pre-pressing: Pre-press every 3 layers to expel the air between the prepregs to prevent internal quality defects in the product.

[0062] 6. Curing: According to the set process curve, the mold and product are placed in the autoclave for heating and pressurization.

[0063] 7. Demolding: After the product is cured, wait until the mold surface temperature drops to 60° before demoulding and removing the product.

[0064] 8. Post-processing: Cut the product according to the cutting line, punch the product according to the hole line, and then repair the burrs on the product edge and the punching process.

[0065] 9. Non-destructive testing: Use ultrasonic scanning equipment to perform ultrasonic non-destructive testing on the entire area of ​​the product.

[0066] The attitude control cabin body 1 of this device is connected in a dumbbell shape through an upper flange 3, a lower flange 10, an upper cone section 5, a lower cone section 11 and a central tube 8, and is combined with a plurality of webs 6 arranged in the dumbbell gap and radially arranged roughly around the axis of the central tube 8, together forming a structure with high structural strength but low material consumption. In addition, the structure can also be made of carbon fiber cloth and laid out in conjunction with a mold, and then integrated into a mold through a hot autoclave pressing and curing process, thereby making the attitude control cabin body 1 made of fiber composite materials more lightweight and having a significant weight reduction effect. Compared with an attitude control cabin made of metal materials, it can reduce weight by 40%. When applied to a general-sized launch vehicle, it can increase the payload by more than 45 kg, improve the economy of the launch vehicle, and reduce the moment of inertia of the payload when adjusting the attitude, improve the controllability of the attitude adjustment, and save fuel consumed for the attitude adjustment, thereby reducing the amount of carried fuel and further increasing the payload of the launch vehicle. Made of carbon fiber composite materials, its quality meets the Class A standard in the "GJB2895-1997 General Specification for Carbon Fiber Composite Laminates and Laminated Parts." Furthermore, due to the simple and compact structure of the attitude control cabin body 1, its integrated molding process is rational and feasible, mold manufacturing is simple and easy to operate, and the product production cycle is short. Furthermore, the overall manufacturing process is repeatable and has a high yield rate, meeting the needs of mass production.

[0067] Based on the above embodiment, in a preferred embodiment, as Figure 2 、 5 As shown in Figure 7, the center tube 8 is provided with a thickened center tube area 14 protruding from the outer side of the center tube 8. The thickened center tube area 14 is arranged in an annular shape around the axis of the center tube 8. The center tube 8 serves as a core bridge connecting the load and thruster, and is the primary component for transmitting axial thrust. Therefore, thickening in appropriate areas can improve the overall mechanical properties of the attitude control cabin body 1. The thickened center tube area 14 protrudes toward the outside of the center tube 8, facilitating the mold's removal from the center tube 8 and preventing any obstruction to demolding.

[0068] Based on the above embodiment, in a preferred embodiment, as Figure 1 and 2As shown, the webs 6 are arranged in pairs, and the two webs 6 in each pair of webs 6 are parallel to each other. The two side edges of the partition 2 are connected to the paired webs 6 in a one-to-one correspondence, one end of the partition 2 faces outward and the other end faces inward, and the inner end of the partition 2 is connected to the center tube thickening area 14. On the one hand, the partition 2 can be used as a platform for carrying the power unit, and on the other hand, it can also be used as a reinforcement for the overall strength of the attitude control cabin. However, because the integral molding of the partition 2 between the two webs 6 increases the complexity of the process, it is preferred to manufacture the partition 2 and the attitude control cabin body 1 separately and then combine and install them. The parallel arrangement of the webs 6 facilitates the installation and connection of the partition 2, and also facilitates the installation of other regular auxiliary equipment, thereby improving the ease of assembly of the attitude control cabin. Moreover, the installation of the partition 2 in the center tube thickening area 14 can enhance the connection strength and improve reliability.

[0069] Based on the above embodiment, in a preferred embodiment, as Figures 11 to 13 As shown, the partition 2 includes: a partition transverse plate 17, a partition side end plate 16, a partition inner end plate 15 and a partition outer end plate 18. The partition transverse plate 17 is the main component of the partition 2. The partition inner end plate 15 is arranged at the inner end of the partition transverse plate 17 and is perpendicular to the partition transverse plate 17. The partition outer end plate 18 is arranged at the outer end of the partition transverse plate 17 and is perpendicular to the partition transverse plate 17. The two partition side end plates 16 are arranged on the side edges of the partition transverse plate 17 and are perpendicular to the partition transverse plate 17. The partition inner end plate 15, the partition outer end plate 18 and the two partition side end plates 16 together form a frame-like structure. A partition neutral plate 20 can also be arranged in the frame-like structure to further enhance the strength of the partition 2.

[0070] Partition connection holes 19 are provided on the partition inner end plate 15 and the partition side end plate 16, and main body connection holes 7 that are compatible with the partition connection holes 19 are provided on the center tube thickening area 14 and the web 6. The partition connection holes 19 and the main body connection holes 7 are connected by bolts or rivets.

[0071] This hole-forming method is easy to implement on products made of fiber composite materials, reducing molding complexity. Bolting or rivet connections allow for efficient and reliable connection of two components, improving assembly efficiency. Furthermore, various areas of the attitude control cabin body 1 and bulkhead 2 can be provided with other holes. These holes can take the form of bolt holes, rivet holes, pipeline holes, and weight-reducing holes, facilitating the installation of electrical equipment, power supplies, satellite mounts, pyrotechnics, and cabling.

[0072] Based on the above embodiment, in a preferred embodiment, as Figure 2 、 5As shown in Figure 6, the upper cone section 5 is provided with an upper cone section thickened area 4 in the area near the upper flange 3, and the upper cone section thickened area 4 has the same thickness as the upper flange 3. As a component connecting the upper flange 3 and the center tube 8, the upper cone section 5 relies on its tapered structure to buffer and disperse the axial load. The upper flange 3, as a component connecting the carried spacecraft, needs to have sufficient thickness to ensure strength. The upper cone section 5 is provided with an upper cone section thickened area 4 in the area near the upper flange 3, which has the same thickness as the upper flange 3. On the one hand, this reduces the thickness of other parts. For example, the area of ​​the upper cone section 5 away from the upper flange 3 can be made thinner together with the center tube 8, thereby achieving a weight reduction effect. On the other hand, it ensures that the key stress-bearing areas have sufficient strength to avoid accidental fracture due to the action of alternating loads in the key areas.

[0073] Based on the above embodiment, in a preferred embodiment, as Figure 2 、 5 As shown in Figure 8 , the lower cone section 11 is provided with a lower cone section thickened area 12 near the lower flange 10 and the web 6. This thickened area 12 has the same thickness as the lower flange 10. The lower cone section thickened area 12 functions similarly to the upper cone section thickened area 4, but differs in that the lower cone section 11, as one of the primary components of the attitude control module subjected to the thrust module, is responsible for distributing the axial thrust to various components. The web 6, a key component for transmitting axial thrust, therefore requires some reinforcement at the junction between the lower cone section 11 and the web 6 to enhance the load distribution function of the lower cone section 11.

[0074] Based on the above embodiment, in a preferred embodiment, as Figure 2 、 9 As shown in Figures 10 and 10, a thickened web region 9 is provided at the lower portion of the outer edge of the web 6. This thickened web region 9 protrudes from the surface of the web 6, away from the space between the paired webs 6. As mentioned above, the web 6 is a crucial component for transmitting axial thrust, but as a thin-walled component, it is important to avoid uneven force transmission due to inherent bending. Therefore, reinforcement is applied to the lower portion of the outer edge of the web 6, the primary location subject to deformation and stress. This ensures balanced force transmission across the webs 6, improving the overall mechanical performance of the attitude control cabin body 1.

[0075] Based on the above embodiment, in a preferred embodiment, as Figure 1 As shown, multiple partitions 2 are arranged axially along the center tube 8 between the paired webs 6. The partitions 2 serve as platforms for carrying power equipment or control equipment. Providing multiple partitions 2 can effectively increase the equipment carrying capacity of the attitude control cabin and is more conducive to optimizing the equipment layout structure.

[0076] Based on the above embodiment, in a preferred embodiment, as Figure 1 and 2As shown, the web thickened area 9 is located between the lower flange 10 and the bulkhead 2 closest to the lower flange 10. The bulkhead 2, as a connecting component connecting the two paired webs 6, can enhance the structural strength of the thin-walled webs 6. Therefore, by focusing on strengthening the webs 6 between the lower flange 10 and the bulkhead 2 closest to the lower flange 10, the strength of the webs 6 after being subjected to axial thrust can be improved, avoiding the need for excessive thickened areas, which would weaken the lightweight advantage of the attitude control cabin.

[0077] Based on the above embodiment, in a preferred embodiment, as Figure 1 As shown, a transition zone 13 with a gradually varying thickness is provided at the thickness-varying joints between the upper flange 3, lower flange 10, upper cone section 5, lower cone section 11, center tube 8, web 6, center tube thickened area 14, upper cone section thickened area 4, lower cone section thickened area 12, and web thickened area 9. This transition zone 13 is achieved by dropping layers during the carbon fiber composite layup process. The provision of transition zone 13 reduces stress concentration damage to the attitude control cabin body 1 when subjected to alternating loads. Achieving this transition through layer dropping reduces the difficulty and workload of the layup process, thereby ensuring production efficiency.

[0078] Obviously, the above embodiments are merely examples for clarity of explanation and are not intended to limit the implementation methods. Those skilled in the art will appreciate that other variations or modifications can be made based on the above description. It is not necessary and impossible to enumerate all implementation methods here. Obvious variations or modifications derived therefrom remain within the scope of protection of the present invention.

Claims

1. An integrated fiber composite material attitude control cabin, characterized in that: include: Attitude control cabin body (1) and partition (2); The attitude control cabin body (1) includes: an upper flange (3), a lower flange (10), an upper cone section (5), a lower cone section (11), a center tube (8) and a web (6); The central tube (8) is located between the upper flange (3) and the lower flange (10) to form a dumbbell-shaped structure; Both the upper cone section (5) and the lower cone section (11) are conical funnel structures; the large opening of the upper cone section (5) is connected to the orifice of the upper flange (3), and the small opening of the upper cone section (5) is connected to the top end of the central tube (8); the large opening of the lower cone section (11) is connected to the orifice of the lower flange (10), and the small opening of the lower cone section (11) is connected to the bottom end of the central tube (8); There are a plurality of webs (6), each of which is distributed around the axis of the central tube (8) on the outside of the central tube (8), the top of the web (6) is connected to the upper flange (3), the bottom of the web (6) is connected to the lower flange (10), one side of the web (6) faces inward and the other side faces outward, and the inner side of the web (6) is connected to the upper cone section (5), the central tube (8) and the lower cone section (11); The upper flange (3), the lower flange (10), the upper cone section (5), the lower cone section (11), the central tube (8) and each web (6) are integrally formed using a fiber composite material; The partition plate (2) is arranged between the paired webs (6); A center tube thickening area (14) protruding from the outer side surface of the center tube (8) is provided on the center tube (8), and the center tube thickening area (14) is arranged in a ring shape around the axis of the center tube (8); The partition (2) comprises: Partition cross plate (17), The inner end plate (15) of the partition is arranged at the inner end of the partition transverse plate (17) and is perpendicular to the partition transverse plate (17); A partition outer end plate (18) is provided at the outer end of the partition transverse plate (17) and is perpendicular to the partition transverse plate (17); Two partition side end plates (16) are arranged on the sides of the partition transverse plate (17) and are perpendicular to the partition transverse plate (17); the partition inner end plate (15), the partition outer end plate (18) and the two partition side end plates (16) are combined to form a frame shape; A partition connecting hole (19) is provided on both the partition inner end plate (15) and the partition side end plate (16), and a main body connecting hole (7) adapted to the partition connecting hole (19) is provided on the center tube thickened area (14) and the web (6), and the partition connecting hole (19) and the main body connecting hole (7) are connected by bolts or rivets; An upper cone section thickening area (4) is provided in an area of ​​the upper cone section (5) close to the upper flange (3), and the upper cone section thickening area (4) has the same thickness as the upper flange (3).

2. The integrated fiber composite material attitude control cabin according to claim 1, characterized in that: The webs (6) are arranged in pairs, and the two webs (6) in each pair of webs (6) are parallel to each other. The two sides of the partition (2) are connected to the paired webs (6) in a one-to-one correspondence. One end of the partition (2) faces outward and the other end faces inward. The inner end of the partition (2) is connected to the thickened area (14) of the central tube.

3. The integrated fiber composite material attitude control cabin according to claim 2, characterized in that: A lower cone section thickened area (12) is provided in an area of ​​the lower cone section (11) close to the lower flange (10) and the web (6), and the thickness of the lower cone section thickened area (12) is the same as that of the lower flange (10).

4. The integrated fiber composite material attitude control cabin according to claim 3, characterized in that: A web thickening area (9) is provided at the lower portion of the outer side of the web (6), and the web thickening area (9) protrudes from the surface of the web (6) in a direction away from the space between the paired webs (6).

5. The integrated fiber composite material attitude control cabin according to claim 4, characterized in that: A plurality of partition plates (2) are arranged axially along the central tube (8) between the paired web plates (6).

6. The integrated fiber composite material attitude control cabin according to claim 5, characterized in that: The web thickened area (9) is located between the lower flange (10) and the partition (2) closest to the lower flange (10).

7. The integrated fiber composite material attitude control cabin according to claim 6, characterized in that: A transition zone (13) with gradually changing thickness is provided at the connection with thickness variation among the upper flange (3), the lower flange (10), the upper cone section (5), the lower cone section (11), the center tube (8), the web (6), the center tube thickening area (14), the upper cone section thickening area (4), the lower cone section thickening area (12) and the web thickening area (9). The transition zone (13) is realized by dropping layers during the fiber composite material laying process.

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