CN116280272A - Integrated fiber composite attitude control cabin - Google Patents

Abstract

The invention provides an integral fiber composite attitude control cabin, which comprises: a posture control cabin main body and a baffle plate; the appearance accuse cabin main part adopts fibre combined material integrated into one piece, and it includes: the device comprises an upper flange, a lower flange, an upper cone section, a lower cone section, a central cylinder and a web plate. The central cylinder is positioned between the upper flange and the lower flange so as to form a dumbbell-shaped structure; both the upper cone section and the lower cone section are of cone-shaped funnel structures; the large opening of the upper cone section is connected with the orifice of the upper flange, and the small opening of the upper cone section is connected with the top end of the central cylinder; the large opening of the lower cone section is connected with the orifice of the lower flange, and the small opening of the lower cone section is connected with the bottom end of the central cylinder; the web has a plurality ofly and around central section of thick bamboo axle center circumference distribution in the central section of thick bamboo outside, web top and last flange joint, web bottom and lower flange joint, web medial edge and last cone section, central section of thick bamboo and lower cone section all form the connection. The separator is disposed between the pair of webs. The metal attitude control cabin overcomes the defects of reduced economy and increased attitude adjustment difficulty caused by heavy weight of the existing metal attitude control cabin.

Description

Integrated fiber composite attitude control cabin

Technical Field

The invention relates to the technical field of spacecraft attitude control components, in particular to an integrated fiber composite attitude control cabin.

Background

In order to complete the orbit entering and attitude control of the final stage of the space vehicle, an attitude control cabin-mounted power system is required to carry out attitude adjustment control on pitching, yawing and rolling of the space vehicle so as to ensure that the carrying load can be accurately entered. The existing attitude control cabin is made of metal materials, and the equipment cabin for installing power equipment and the load support for bearing load are designed in a split mode, so that the problem of large weight exists, and the effective load carrying and use economy of a rocket are reduced; the difficulty in posture adjustment is also increased due to the large moment of inertia; in addition, the connection complexity of the split design is high, and the reliability of the product is reduced.

Disclosure of Invention

Therefore, the technical problem to be solved by the invention is to overcome the defects of reduced economy and increased difficulty in posture adjustment caused by heavy weight of the metal posture control cabin in the prior art.

For solving above-mentioned technical problem, this application provides an integrated fiber composite attitude control cabin, includes: a posture control cabin main body and a baffle plate;

the attitude control cabin main body comprises: the device comprises an upper flange, a lower flange, an upper cone section, a lower cone section, a central cylinder and a web plate;

the central cylinder is positioned between the upper flange and the lower flange so as to form a dumbbell-shaped structure;

both the upper cone section and the lower cone section are of cone-shaped funnel structures; the large opening of the upper cone section is connected with the orifice of the upper flange, and the small opening of the upper cone section is connected with the top end of the central cylinder; the large opening of the lower cone section is connected with the orifice of the lower flange, and the small opening of the lower cone section is connected with the bottom end of the central cylinder;

the plurality of webs are circumferentially distributed outside the central cylinder around the axis of the central cylinder, the top of each web is connected with the upper flange, the bottom of each web is connected with the lower flange, one side edge of each web faces inwards, the other side edge of each web faces outwards, and the inner side edge of each web is connected with the upper cone section, the central cylinder and the lower cone section;

the upper flange, the lower flange, the upper cone section, the lower cone section, the central cylinder and the webs are integrally formed by adopting fiber composite materials;

the separator is disposed between the pair of webs.

Further, a central cylinder thickening area protruding out of the outer side surface of the central cylinder is arranged on the central cylinder, and the central cylinder thickening area is annularly arranged around the axis of the central cylinder.

Further, the webs are arranged in pairs, two webs in each pair of webs are parallel to each other, two sides of the partition plate are connected with the webs arranged in pairs in a one-to-one correspondence manner, one end of the partition plate faces outwards and the other end of the partition plate faces inwards, and the inner end of the partition plate is connected with the thickening area of the central cylinder.

Further, the separator includes:

a diaphragm plate of the partition board,

the inner end plate of the baffle plate is arranged at the inner end of the diaphragm plate of the baffle plate and is vertical to the diaphragm plate of the baffle plate;

the baffle outer end plate is arranged at the outer end of the baffle diaphragm and is vertical to the baffle diaphragm;

the two baffle side end plates are arranged on the side edges of the baffle transverse plates and are perpendicular to the baffle transverse plates; the inner end plate of the partition plate, the outer end plate of the partition plate and the side end plates of the two partition plates are surrounded into a frame shape;

the inner end plate and the side end plate of the partition plate are respectively provided with a partition plate connecting hole, the thickened area of the central cylinder and the web plate are respectively provided with a main body connecting hole matched with the partition plate connecting holes, and the partition plate connecting holes are connected with the main body connecting holes through bolts or rivets.

Further, an upper cone section thickening area is arranged in the area, close to the upper flange, of the upper cone section, and the upper cone section thickening area is the same as the upper flange in thickness.

Further, a lower cone section thickening area is arranged in the area, close to the lower flange and the web plate, of the lower cone section, and the thickness of the lower flange of the lower cone section thickening area is the same.

Further, a web thickening area is arranged at the lower part of the outer side edge of the web, and the web thickening area protrudes out of the surface of the web towards the spacing direction away from the space between the paired webs.

Further, a plurality of spacers are provided between the paired webs in the axial direction of the center tube.

Further, the web thickened region is between the lower flange and the bulkhead nearest the lower flange.

Further, a transition region with gradually changing thickness is arranged at the joint of the upper flange, the lower flange, the upper cone section, the lower cone section, the central cylinder, the web plate, the central cylinder thickening region, the upper cone section thickening region, the lower cone section thickening region and the web plate thickening region, and the transition region is realized in a layer losing mode in the carbon fiber composite material layering process.

By adopting the technical scheme, the invention has the following technical effects:

the attitude control cabin main body of the device is formed by integrally forming and manufacturing an upper flange, a lower flange, an upper cone section, a lower cone section and a central cylinder which are connected in a dumbbell shape and are matched with a plurality of webs which are arranged in a dumbbell neutral position and are radially arranged around the axis of the central cylinder, so that a structural body with high structural strength and low material consumption is formed together. After the carbon fiber composite material is adopted for manufacturing, the quality can meet the A-level standard in GJB2895-1997 carbon fiber composite material laminated plate and laminated piece general Specification. And because the attitude control cabin main body is simple and compact in structure, the integral forming process scheme is reasonable and feasible, the die is simple to manufacture and convenient to operate, and the product preparation period is short. And the whole preparation process has the advantages of repeatability, high yield and capability of meeting the requirement of mass production.

Drawings

In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings that are needed in the description of the embodiments or the prior art will be briefly described, and it is obvious that the drawings in the description below are some embodiments of the present invention, and other drawings can be obtained according to the drawings without inventive effort for a person skilled in the art.

Fig. 1 is a schematic perspective view of the structure of embodiment 1 of the present invention;

fig. 2 is a schematic front view of the configuration of the attitude control cabin main body of embodiment 1 of the present invention;

FIG. 3 is a schematic top view of the configuration of the attitude control cabin main body according to embodiment 1 of the present invention;

FIG. 4 is a cross-sectional view at A-A in FIG. 2;

FIG. 5 is a cross-sectional view at B-B in FIG. 3;

FIG. 6 is a partial enlarged view at D in FIG. 5;

FIG. 7 is an enlarged partial view at E in FIG. 5;

FIG. 8 is an enlarged view of a portion of F in FIG. 5;

FIG. 9 is a cross-sectional view taken at C-C of FIG. 2;

FIG. 10 is a schematic perspective view of the structure of the attitude control cabin main body according to the embodiment of the present invention;

fig. 11 is a schematic perspective view of the structure of the first embodiment of the separator according to the embodiment of the present invention;

FIG. 12 is a schematic top view of a first embodiment of a separator according to an embodiment of the present invention;

fig. 13 is a schematic perspective view of a second embodiment of a separator according to an embodiment of the present invention;

fig. 14 is a process flow diagram of the preparation of the attitude control cabin body according to the embodiment of the invention.

Reference numerals illustrate:

the three-dimensional control cabin comprises a 1-dimensional control cabin body, a 2-partition plate, a 3-upper flange, a 4-upper cone section thickening area, a 5-upper cone section, a 6-web plate, a 7-body connecting hole, an 8-central cylinder, a 9-web plate thickening area, a 10-lower flange, a 11-lower cone section, a 12-lower cone section thickening area, a 13-transition area, a 14-central cylinder thickening area, a 15-partition plate inner end plate, a 16-partition plate side end plate, a 17-partition plate diaphragm plate, a 18-partition plate outer end plate, a 19-partition plate connecting hole and a 20-partition plate neutral plate.

Detailed Description

The following description of the embodiments of the present invention will be made apparent and fully in view of the accompanying drawings, in which some, but not all embodiments of the invention are shown. All other embodiments, which can be made by those skilled in the art based on the embodiments of the invention without making any inventive effort, are intended to be within the scope of the invention.

In describing the present invention, it should be noted that the coordinate system adopted in describing the orientation of the present specification is determined by the posture of fig. 2, and the observation angle naming of the corresponding view is also based on this, so that the orientation or positional relationship indicated by the terms "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inner", "outer", etc. of the present specification is based on the orientation or positional relationship shown in the drawings, only for convenience of describing the present invention and simplifying the description, and does not indicate or imply that the device or element referred to must have a specific orientation, be configured and operated in a specific orientation, and thus should not be construed as limiting the present invention.

In the description of the present invention, it should be noted that, unless explicitly specified and limited otherwise, the terms "mounted," "connected," and "connected" are to be construed broadly, and may be either fixedly connected, detachably connected, or integrally connected, for example; can be mechanically or electrically connected; can be directly connected or indirectly connected through an intermediate medium, and can be communication between two elements. The specific meaning of the above terms in the present invention will be understood in specific cases by those of ordinary skill in the art.

In addition, the technical features of the different embodiments of the present invention described below may be combined with each other as long as they do not collide with each other.

The embodiment provides an integrated fiber composite attitude control cabin.

In one embodiment, as shown in fig. 1 to 14, it includes: a posture control cabin body 1 and a baffle plate 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 central cylinder 8 and a web 6.

The central cylinder 8 is located between the upper flange 3 and the lower flange 10, which thereby form a dumbbell-like structure.

Both the upper cone section 5 and the lower cone section 11 are of a cone-shaped funnel structure; the large opening of the upper cone section 5 is connected with the orifice of the upper flange 3, namely the edge of the inner hole of the flange plate, and the small opening of the upper cone section 5 is connected with the top end of the central cylinder 8. The large opening of the lower cone section 11 is connected with the orifice of the lower flange 10, and the small opening of the lower cone section 11 is connected with the bottom end of the central cylinder 8.

The web 6 has a plurality of, and each web 6 is around central section of thick bamboo 8 axle center circumference distribution in the central section of thick bamboo 8 outside, and the top of web 6 is connected with upper flange 3, and the bottom of web 6 is connected with lower flange 10, and one side of web 6 inwards and the other side outwards, and the interior side of web 6 all forms the connection with upper cone section 5, central section of thick bamboo 8 and lower cone section 11.

The upper flange 3, the lower flange 10, the upper cone section 5, the lower cone section 11, the central cylinder 8 and each web 6 are integrally formed by adopting fiber composite materials. Preferably, the carbon fiber reinforced epoxy resin matrix composite unidirectional tape and the carbon fiber reinforced epoxy resin matrix composite fabric can be adopted for manufacturing. Different resin systems (bismaleimide, epoxy, phenolic, etc.) can be selected, and carbon fiber, aramid fiber or glass fiber materials of different grades can be selected according to different strength requirements.

The separator 2 is disposed between a pair of webs 6. The partition board 2 can be made of the same material as the attitude control cabin main body 1, for example, a carbon fiber reinforced epoxy resin matrix composite unidirectional tape and a carbon fiber reinforced epoxy resin matrix composite fabric are adopted, but the requirement on stress is low, and the partition board can also be made of only the carbon fiber reinforced epoxy resin matrix composite fabric.

The attitude control cabin main body 1 and the partition board 2 can be prepared by adopting a composite material autoclave process, namely a process method that a preformed body formed by laying prepregs according to a preset direction is put into an autoclave after being packaged, and then solidification is completed under certain preset temperature and pressure. The specific preparation process flow can be seen in fig. 14: the specific manager comprises the following steps:

1. preparing a prepreg: after the prepreg is taken out of the refrigeration house, when the prepreg reaches the use environment temperature and no condensed water exists on the surface, the plastic sealing bag is opened, and the prepreg is taken out.

2. And (3) blanking: the prepreg is cut into a proper shape and size by using a blanking machine, so that the prepreg is convenient to lay down.

3. And (3) die cleaning: checking the mold, confirming no local damage, and wiping the surface of the mold with clean industrial rag dipped with alcohol to ensure that the surface is clean and free of foreign matters.

4. Paving: and (3) paving the prepreg on the die by using a good material block under a blanking machine according to the paving surface and paving distribution requirements.

5. Prepressing: and 3 layers of pre-pumping are performed every other, air between the interiors of the prepregs is discharged, and internal quality defects of the products are prevented.

6. Curing: and (3) according to the set process curve, putting the die and the whole product into an autoclave for heating and pressurizing.

7. Demolding: and after the product is solidified, demoulding and taking out the product after the surface temperature of the mould is reduced to 60 degrees.

8. Post-treatment: cutting the product according to the cutting line, punching the product according to the bit line, and repairing the edge of the product and burrs in the punching process.

9. Nondestructive flaw detection: and carrying out full-area ultrasonic nondestructive inspection on the product by using ultrasonic scanning equipment.

The attitude control cabin main body 1 of the device is formed by integrally forming and manufacturing an upper flange 3, a lower flange 10, an upper cone section 5, a lower cone section 11 and a central cylinder 8 which are connected in a dumbbell shape, and a plurality of webs 6 which are arranged in a dumbbell neutral position and are radially arranged around the axis of the central cylinder 8 are matched, so that a structural body with high structural strength and low material consumption is formed together. After the carbon fiber composite material is adopted for manufacturing, the quality can meet the A-level standard in GJB2895-1997 carbon fiber composite material laminated plate and laminated piece general Specification. And because the attitude control cabin main body 1 has simple and compact structure, the integrated forming process scheme is reasonable and feasible, the die is simple to manufacture and convenient to operate, and the product preparation period is short. And the whole preparation process has the advantages of repeatability, high yield and capability of meeting the requirement of mass production.

Based on the above embodiment, in a preferred embodiment, as shown in fig. 2, 5 and 7, a central cylinder thickening area 14 protruding from the outer side surface of the central cylinder 8 is provided on the central cylinder 8, and the central cylinder thickening area 14 is provided in a ring shape around the axis of the central cylinder 8. The central tube 8 is used as a bridging core component for connecting the load and the thruster and is a main component for transmitting axial thrust, so that the overall mechanical property of the attitude control cabin main body 1 can be improved by thickening in a proper area. The thickened area 14 of the central cylinder protrudes towards the outer side of the central cylinder 8, so that the die can be conveniently pulled out of the central cylinder 8, and the blocking to the demolding is avoided.

Based on the above embodiment, in a preferred embodiment, as shown in fig. 1 and 2, the webs 6 are arranged in pairs, two webs 6 in each pair of webs 6 are parallel to each other, two sides of the separator 2 are connected to the webs 6 arranged in pairs in a one-to-one correspondence, one end of the separator 2 faces outward and the other end faces inward, and the inner end of the separator 2 is connected to the central cylinder thickening area 14. The partition plate 2 can be used as a platform for carrying the power device on one hand and can be used as a reinforcement for the overall strength of the attitude control cabin on the other hand. However, because the integrally formed bulkhead 2 between the two webs 6 adds to the complexity of the process, it is preferable to manufacture and reassemble the bulkhead 2 with the attitude control cabin body 1 separately. The parallel webs 6 are convenient for installing and connecting the partition plates 2 and installing other regular auxiliary equipment, so that the assembly convenience of the whole attitude control cabin is improved. And the baffle plate 2 is arranged at the thickened area 14 of the central cylinder, so that the connection strength can be enhanced, and the reliability is improved.

Based on the above embodiments, in a preferred embodiment, as shown in fig. 11 to 13, the separator 2 includes: a bulkhead 17, a bulkhead side end plate 16, a bulkhead inner end plate 15, and a bulkhead outer end plate 18. The diaphragm 17 is a main body member of the diaphragm 2. The diaphragm inner end plate 15 is provided at the inner end of the diaphragm plate 17 and is perpendicular to the diaphragm plate 17. The diaphragm outer end plate 18 is provided at the outer end of the diaphragm plate 17 and is perpendicular to the diaphragm plate 17. Two separator side end plates 16 are provided on the sides of the separator diaphragm 17 and are perpendicular to the separator diaphragm 17. The separator inner end plate 15, the separator outer end plate 18, and the two separator side end plates 16 are surrounded into a frame-like structure. A separator neutral plate 20 may also be provided within the frame-like structure to further enhance the strength of the separator 2.

The inner end plate 15 and the side end plate 16 are respectively provided with a baffle connecting hole 19, the central cylinder thickening area 14 and the web 6 are respectively provided with a main body connecting hole 7 matched with the baffle connecting holes 19, and the baffle connecting holes 19 are connected with the main body connecting holes 7 through bolts or rivets.

The mode of trompil is convenient for implement on the product that fibre combined material was made, reduces the shaping complexity, connects two parts through bolt or rivet connection alright high-efficient reliable, has improved assembly work efficiency. And the gesture control cabin main body 1 and each region of the partition plate 2 can be provided with other holes, and the opening forms can be bolt holes, rivet holes, pipeline through holes, lightening holes and the like, so that electric equipment, power supply equipment, satellite supports, initiating explosive device equipment, cable equipment and the like can be conveniently installed.

Based on the above embodiment, in a preferred embodiment, as shown in fig. 2, 5 and 6, the upper cone 5 is provided with an upper cone thickened region 4 near the upper flange 3, and the upper cone thickened region 4 has the same thickness as the upper flange 3. The upper cone section 5 is used as a part for connecting the upper flange 3 and the central cylinder 8, the function of buffering and dispersing axial load is achieved by virtue of the cone structure of the upper cone section 5, the upper flange 3 is used as a part for connecting a carried spacecraft, enough thickness is needed to ensure the strength, the area of the upper cone section 5 close to the upper flange 3 is provided with an upper cone section thickening area 4 which is equal to the upper flange 3 in thickness, the thickness of other parts is reduced, for example, the area of the upper cone section 5 far away from the upper flange 3 can be made into thinner thickness together with the central cylinder 8, so that the weight reduction effect is achieved, the stress critical area is ensured to have enough strength, and accidental breakage caused by the alternating load is avoided.

Based on the above embodiment, in a preferred embodiment, as shown in fig. 2, 5 and 8, the region of the lower cone 11 adjacent to the lower flange 10 and the web 6 is provided with a lower cone thickening 12, the lower flange 10 of the lower cone thickening 12 being of equal thickness. The lower cone section thickening 12 is used similarly to the upper cone section thickening 4, but is different in that the lower cone section 11, which is one of the primary components of the overall attitude control cabin subjected to the thrust cabin forces, acts to disperse the axial thrust to the components, while the web 6 acts as an important component for transmitting the axial thrust, so that a certain reinforcement is required at the connection area of the lower cone section 11 and the web 6 to improve the load distribution effect of the lower cone section 11.

Based on the above embodiment, in a preferred embodiment, as shown in fig. 2, 9 and 10, the lower part of the outer side edge of the web 6 is provided with a web thickening 9, the web thickening 9 protruding from the surface of the web 6 in a direction away from the space between the pair of webs 6. As described above, the web 6 is an important component for transmitting axial thrust, but is a thin-walled part itself, and it is necessary to avoid uneven force transmission due to bending itself. Therefore, the primary part of the stress deformation, namely the lower part of the outer side edge of the web plate 6 is reinforced, so that the transmission stress of each web plate 6 is balanced, and the overall mechanical performance of the attitude control cabin main body 1 is improved.

Based on the above embodiment, in a preferred embodiment, as shown in fig. 1, a plurality of spacers 2 are provided between the paired webs 6 along the axial direction of the central cylinder 8. The partition boards 2 serve as a platform on which power equipment or control equipment can be carried, and the arrangement of the plurality of partition boards 2 can effectively improve the equipment carrying capacity of the attitude control cabin, and is more beneficial to optimizing the equipment layout structure.

Based on the above embodiment, in a preferred embodiment, as shown in fig. 1 and 2, the web-thickening 9 is located between the lower flange 10 and the partition 2 closest to the lower flange 10. The partition plate 2 is used as a connecting part for connecting two webs 6 arranged in pairs, and the structural strength of the web 6 serving as a thin-wall part can be enhanced, so that only the web 6 between the lower flange 10 and the partition plate 2 closest to the lower flange 10 is emphasized and enhanced, the strength of the web 6 after axial thrust is applied can be improved, excessive thickening areas are avoided, and the advantage effect of lightening the attitude control cabin is weakened.

Based on the above embodiment, in a preferred embodiment, as shown in fig. 1, a transition zone 13 with gradually changing thickness is provided at the connection part with the thickness change between the upper flange 3, the lower flange 10, the upper cone section 5, the lower cone section 11, the central cylinder 8, the web 6, the central cylinder thickening zone 14, the upper cone section thickening zone 4, the lower cone section thickening zone 12 and the web thickening zone 9, and the transition zone 13 is realized by a layer loss mode in the layering process of the carbon fiber composite material. The transition area 13 can reduce stress concentration damage of the attitude control cabin main body 1 when the attitude control cabin main body receives alternating load, and the transition is realized in a layer-losing mode, so that the difficulty of a paving process can be reduced, the workload can be reduced, and the production efficiency can be ensured.

It is apparent that the above examples are given by way of illustration only and are not limiting of the embodiments. Other variations or modifications of the above teachings will be apparent to those of ordinary skill in the art. It is not necessary here nor is it exhaustive of all embodiments. And obvious variations or modifications thereof are contemplated as falling within the scope of the present invention.

Claims (10)

1. An integrated fiber composite attitude control cabin, comprising: a posture control cabin main body (1) and a baffle plate (2);

the attitude control cabin main body (1) comprises: the device comprises an upper flange (3), a lower flange (10), an upper cone section (5), a lower cone section (11), a central cylinder (8) and a web plate (6);

the central cylinder (8) is positioned between the upper flange (3) and the lower flange (10) so as to form a dumbbell-shaped structure; both the upper cone section (5) and the lower cone section (11) are of cone-shaped funnel structures; the large opening of the upper cone section (5) is connected with the orifice of the upper flange (3), and the small opening of the upper cone section (5) is connected with the top end of the central cylinder (8); the large opening of the lower cone section (11) is connected with the orifice of the lower flange (10), and the small opening of the lower cone section (11) is connected with the bottom end of the central cylinder (8);

the web plates (6) are provided with a plurality of web plates (6), each web plate (6) is circumferentially distributed outside the central cylinder (8) around the axis of the central cylinder (8), the top of each web plate (6) is connected with the upper flange (3), the bottom of each web plate (6) is connected with the lower flange (10), one side edge of each web plate (6) faces inwards, the other side edge of each web plate faces outwards, and the inner side edge of each web plate (6) is connected with the upper cone section (5), the central cylinder (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 cylinder (8) and each web (6) are integrally formed by adopting fiber composite materials;

the separator (2) is disposed between a pair of webs (6).

2. The integrated fiber composite attitude control cabin according to claim 1, wherein a central cylinder thickening area (14) protruding from the outer side surface of the central cylinder (8) is arranged on the central cylinder (8), and the central cylinder thickening area (14) is annularly arranged around the axis of the central cylinder (8).

3. The integrated fiber composite attitude control cabin according to claim 2, wherein the webs (6) are arranged in pairs, two webs (6) in each pair of webs (6) are parallel to each other, two side edges of the partition plate (2) are connected with the webs (6) arranged in pairs in a one-to-one correspondence manner, one end of the partition plate (2) faces outwards and the other end faces inwards, and the inner end of the partition plate (2) is connected with the central cylinder thickening area (14).

4. A fibre composite control cabin according to claim 3, characterized in that the partition (2) comprises:

a diaphragm plate (17),

a baffle inner end plate (15) which is arranged at the inner end of the baffle diaphragm (17) and is vertical to the baffle diaphragm (17);

the baffle outer end plate (18) is arranged at the outer end of the baffle diaphragm (17) and is vertical to the baffle diaphragm (17);

two partition plate side end plates (16) which are arranged on the side edges of the partition plate transverse plates (17) and are perpendicular to the partition plate transverse plates (17); the inner end plate (15), the outer end plate (18) and the side end plates (16) are surrounded into a frame shape;

baffle connecting holes (19) are formed in the baffle inner end plate (15) and the baffle side end plate (16), main body connecting holes (7) matched with the baffle connecting holes (19) are formed in the central cylinder thickening area (14) and the web plate (6), and the baffle connecting holes (19) are connected with the main body connecting holes (7) through bolts or rivets.

5. An integrated fiber composite attitude control cabin according to claim 3, characterized in that the upper cone section (5) is provided with an upper cone section thickening area (4) in the area close to the upper flange (3), the upper cone section thickening area (4) being the same as the upper flange (3) in thickness.

6. The integrated fiber composite attitude control cabin according to claim 5, wherein the lower cone section (11) is provided with a lower cone section thickening area (12) near the lower flange (10) and the web (6), and the lower cone section thickening area (12) has the same thickness as the lower flange (10).

7. The integrated fiber composite attitude control cabin according to claim 6, wherein the lower part of the outer side edge of the web (6) is provided with a web thickening area (9), and the web thickening area (9) protrudes from the surface of the web (6) toward a spacing direction away from between the paired webs (6).

8. The integrated fiber composite attitude control cabin according to claim 7, wherein a plurality of bulkheads (2) are provided between the paired webs (6) along the central cylinder (8) axial direction.

9. The integrated fiber composite attitude control cabin according to claim 8, wherein the web thickened area (9) is located between the lower flange (10) and the bulkhead (2) closest to the lower flange (10).

10. The integrated fiber composite attitude control cabin according to claim 7, characterized in that a transition zone (13) with gradually changing thickness is provided at the junction with thickness variation between the upper flange (3), the lower flange (10), the upper cone section (5), the lower cone section (11), the central cylinder (8), the web (6), the central cylinder thickening zone (14), the upper cone section thickening zone (4), the lower cone section thickening zone (12) and the web thickening zone (9), and the transition zone (13) is realized by layer loss during the fiber composite layering process.

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