Rocket tail section shell structure and preparation method thereof

Abstract

The invention provides a rocket tail section shell structure and a preparation method thereof.The shell structure comprises a shell, the shell comprises a bottom plate and a side plate, the side plate is arranged on one side of the bottom plate and circumferentially surrounds the bottom plate, the bottom plate and the side plate are of an integrally-formed structure, and the side plate comprises a first force bearing structure and a first heat protection structure; the first bearing structure is arranged in the first heat-proof structure; the bottom plate comprises a second load-bearing structure and a second heat-proof structure, the second load-bearing structure is arranged in the second heat-proof structure, the second load-bearing structure is connected with the first load-bearing structure, and the second heat-proof structure is connected with the first heat-proof structure; therefore, the shell disclosed by the invention adopts an integrated molding process, so that the overall size is well controlled, and the weight is relatively light; meanwhile, the situation that part of parts are loosened or fall off is avoided, and the overall reliability is improved; and finally, the shell structure does not need to be assembled subsequently, so that the labor cost is reduced.

Description

Technical Field

[0001] The present application generally relates to the field of rocket technology, and specifically to a rocket tail section shell structure and a preparation method thereof. Background Art

[0002] The tail section casing is located at the tail of the rocket, completely covering the engine and its nozzle, and is a protective cover for the engine. At the same time, the gas flow generated by the ignition of the engine makes the temperature of the bottom of the rocket higher. Thermal protection material needs to be added to the bottom of the tail section casing to prevent the tail section casing of the rocket from being damaged by the gas flow. Most of the existing technologies are rockets that adopt a vertical launch method. When the rocket is upright, the tail section casing plays a role in supporting the rocket body, and the whole bears the circumferential load and the bending moment and shear force caused by the crosswind. After the rocket is launched, it will bear aerodynamic loads. In order to increase the aerodynamic stability of the rocket, some rockets are equipped with tail fins, air rudders, etc. on the tail section casing, so that the tail section casing is in a flight condition.

[0003] At present, most tail section shells adopt a thin-walled reinforced semi-hard shell structure. In terms of material selection, ordinary hard aluminum and super-hard aluminum alloys are used. These materials are formed by splicing or casting plates to construct the structural skeleton of the tail section. However, this method of splicing multiple components is not conducive to controlling the overall size and is heavy. Under complex stress conditions, some components are prone to loosening or even falling off, and the reliability is low. Summary of the invention

[0004] In view of the above-mentioned defects or deficiencies in the prior art, it is desired to provide a rocket tail section shell structure and a preparation method thereof that can solve the above-mentioned technical problems.

[0005] In a first aspect, the present application provides a rocket tail section casing structure, comprising: A shell, the shell comprising a bottom plate and a side plate, the side plate being arranged on one side of the bottom plate and circumferentially surrounding the bottom plate, the bottom plate and the side plate being an integrally formed structure; The side plate comprises: a first load-bearing structure and a first heat-proof structure, wherein the first load-bearing structure is arranged inside the first heat-proof structure; The base plate includes: a second load-bearing structure and a second heat protection structure, the second load-bearing structure is arranged inside the second heat protection structure, the second load-bearing structure is connected to the first load-bearing structure, the second heat protection structure is connected to the first heat protection structure, the first load-bearing structure and the second load-bearing structure are used to bear the load of the fuselage, and the first heat protection structure and the second heat protection structure are used to block heat from being transferred to the inside of the shell.

[0006] According to the technical solution provided in the present application, the first load-bearing structure includes: a first inner skin layer, a first thickened layer and a first metal layer, the first inner skin layer is provided with the first thickened layer on the outside, and the first metal layer is provided with the first thickened layer on the outside.

[0007] According to the technical solution provided in the present application, the first load-bearing structure further includes: a docking layer, which is arranged outside the first inner skin layer and located on a side away from the bottom plate.

[0008] According to the technical solution provided in the present application, the first heat protection structure includes: a first sandwich layer, a first outer skin layer and a first heat protection layer, the first outer skin layer is arranged on the outside of the first metal layer and the butt-jointed layer, the first heat protection layer is arranged on the outside of the first outer skin layer, the first sandwich layer is arranged on the side of the first outer skin layer close to the first metal layer, and the first sandwich layer is arranged between the first thickening layer and the butt-jointed layer.

[0009] According to the technical solution provided in the present application, the second load-bearing structure includes: a second inner skin layer and a second thickened layer, the second thickened layer is arranged on the outside of the second inner skin layer; the second inner skin layer and the first inner skin layer are an integrated structure; the second thickened layer and the first thickened layer are an integrated structure.

[0010] According to the technical solution provided in the present application, the second heat protection structure includes: a second outer skin layer and a second heat protection layer, the second outer skin layer is arranged on the outside of the second thickening layer, the second heat protection layer is arranged on the outside of the second outer skin layer, the second outer skin layer and the first outer skin layer are an integrated structure; the second heat protection layer is connected to the first heat protection layer.

[0011] According to the technical solution provided in the present application, the first inner skin layer, the second inner skin layer, the butt joint layer, the first thickened layer, the second thickened layer, the first outer skin layer and the second outer skin layer are all made of carbon fiber reinforced composite materials.

[0012] According to the technical solution provided in the present application, the first sandwich layer is a heat-resistant sandwich material.

[0013] In a second aspect, the present application provides a method for preparing a rocket tail section shell structure, which is used to prepare the rocket tail section shell structure provided by any one of the first aspects, comprising the following steps: S100: forming the first load-bearing structure and the second load-bearing structure at one time in the mold by using a hot-pressing tank forming process; S200: preforming the first heat protection structure and the second heat protection structure, and processing the preformed first heat protection structure and the second heat protection structure into required sizes and shapes; S300: Adhere the first heat protection structure and the second heat protection structure to the first load-bearing structure and the second load-bearing structure respectively using an adhesive film with a temperature greater than or equal to 180° C.; wherein the shell comprises: a side plate and a bottom plate, the side plate is composed of the first load-bearing structure and the first heat protection structure, and the bottom plate is composed of the second load-bearing structure and the second heat protection structure; S400: The bonded structure is subjected to secondary curing by a vacuum bag pressing process to obtain a shell.

[0014] According to the technical solution provided by the present application, the following steps are also included after step S400: S500: demoulding the shell, and processing a functional structure on the shell to obtain a finished shell structure.

[0015] The beneficial effects of this application are: The present application provides a rocket tail section shell structure and a preparation method thereof, comprising: a shell, the shell comprising a bottom plate and a side plate, the side plate being arranged on one side of the bottom plate and circumferentially arranged around the bottom plate, the bottom plate and the side plate being an integrally formed structure, wherein the side plate comprises: a first load-bearing structure and a first heat-protective structure, the first load-bearing structure being arranged inside the first heat-protective structure; the bottom plate comprises: a second load-bearing structure and a second heat-protective structure, the second load-bearing structure being arranged inside the second heat-protective structure, the second load-bearing structure being connected to the first load-bearing structure, and the second heat-protective structure being connected to the first heat-protective structure; when making the above-mentioned shell, firstly, a hot-pressing tank molding process is used in a mold to form the first load-bearing structure and the second load-bearing structure. The first heat protection structure and the second heat protection structure are preformed at the same time, and the preformed first heat protection structure and the second heat protection structure are processed into the required size and shape; then, the first heat protection structure and the second heat protection structure are bonded to the first load-bearing structure and the second load-bearing structure respectively using a film with a temperature greater than or equal to 180°C, and finally, the bonded structure is secondary cured using a vacuum bag pressing process to obtain a shell, thereby completing the production of the rocket tail section shell structure; it can be seen that the shell of the present application adopts an integrated molding process, the overall size is well controlled, and the weight is light; at the same time, it avoids the situation where some parts become loose or fall off, thereby improving the overall reliability; finally, the shell structure of the present application does not require subsequent assembly, thereby reducing labor costs. BRIEF DESCRIPTION OF THE DRAWINGS

[0016] Other features, objects and advantages of the present application will become more apparent by reading the detailed description of non-limiting embodiments made with reference to the following drawings: Figure 1 It is an internal cross-sectional view of a rocket tail section shell structure provided by the present application; Figure 2It is an external schematic diagram of a rocket tail section shell structure provided by the present application; Figure 3 This is a flow chart of a method for preparing a rocket tail section shell structure provided by the present application; Figure 4 is a schematic diagram of the mold provided by the present application; Figure 5 It is a schematic diagram of the processing flow provided by this application.

[0017] In the figure: 1. side panel; 2. bottom plate; 3. gas rudder structure at steering gear box level; 4. air rudder installation interface; 5. adapter / counterweight connection interface; 6. solid engine docking interface; 7. cable penetration opening; 8. horizontal wing connection interface; 9. first inner skin layer; 10. docking layer; 11. second thickening layer; 12. first metal layer; 13. first sandwich layer; 14. first outer skin layer; 15. first heat protection layer; 16. second heat protection layer; 17. second inner skin layer; 18. first thickening layer; 19. second outer skin layer; 20. mold bottom plate; 21. demoulding ring; 22. mold body; 23. thickening area positioning plate. DETAILED DESCRIPTION

[0018] The present application is further described in detail below in conjunction with the accompanying drawings and embodiments. It is to be understood that the specific embodiments described herein are only used to explain the relevant invention, rather than to limit the invention. It is also necessary to explain that, for ease of description, only the parts related to the invention are shown in the accompanying drawings.

[0019] It should be noted that, in the absence of conflict, the embodiments and features in the embodiments of the present application can be combined with each other. The present application will be described in detail below with reference to the accompanying drawings and in combination with the embodiments.

[0020] Example 1 Please refer to Figure 1 As shown, the present application provides a rocket tail section shell structure, including: The housing comprises a bottom plate 2 and a side plate 1. The side plate 1 is arranged on one side of the bottom plate 2 and circumferentially surrounds the bottom plate 2. The bottom plate 2 and the side plate 1 are an integrally formed structure. The side plate 1 comprises: a first load-bearing structure and a first heat-proof structure, wherein the first load-bearing structure is arranged inside the first heat-proof structure; The bottom plate 2 includes: a second load-bearing structure and a second heat-proof structure, the second load-bearing structure is arranged inside the second heat-proof structure, the second load-bearing structure is connected to the first load-bearing structure, the second heat-proof structure is connected to the first heat-proof structure, the first load-bearing structure and the second load-bearing structure are used to bear the load of the fuselage, and the first heat-proof structure and the second heat-proof structure are used to block heat from being transferred to the inside of the shell.

[0021] Specifically, when manufacturing the shell, first, the first load-bearing structure and the second load-bearing structure are once molded in a mold by using an autoclave molding process, and at the same time, the first heat protection structure and the second heat protection structure are preformed, and the preformed first heat protection structure and the second heat protection structure are processed into required sizes and shapes; then, the first heat protection structure and the second heat protection structure are respectively bonded to the first load-bearing structure and the second load-bearing structure by using an adhesive film with a temperature greater than or equal to 180°C, and finally, the bonded structure is secondary cured by using a vacuum bag pressing process to obtain a shell, thereby completing the manufacture of the rocket tail shell structure; Specifically, a plurality of functional structures are arranged on the shell; in the present embodiment, the functional structures include: a steering gear box-level gas rudder structure 3, an air rudder installation interface 4, an adapter / counterweight connection interface 5, a solid engine docking interface 6, a cable through-cabin opening 7 and a horizontal wing connection interface 8; Among them, Figure 2 As shown, four steering gear box-level gas rudder structures 3 are provided, and the four steering gear box-level gas rudder structures 3 are arranged on the bottom plate 2 at equal intervals in the circumferential direction; that is, in this embodiment, the four steering gear box-level gas rudder structures 3 are arranged in an X shape on the bottom plate 2; The air rudder installation interface 4, the adapter / counterweight connection interface 5, the solid engine docking interface 6, the cable through-cabin opening 7 and the horizontal wing connection interface 8 are all arranged on the side plate 11; There are four air rudder mounting interfaces 4, which are arranged at one end of the side plate 11 close to the bottom plate 2. The air rudder mounting interfaces 4 are arranged one by one with the steering gear box-level gas rudder structure 3, that is, in this embodiment, the four air rudder mounting interfaces 4 are arranged in an X shape on the side plate 1; There are multiple solid engine docking interfaces 6, and multiple fixed engine docking interfaces are arranged at one end of the side plate 11 away from the bottom plate 2, and are arranged circumferentially around the side plate 11; the adapter / counterweight connection interface 5 is arranged on the side plate 11, and is arranged close to the solid engine docking interface 6; Two horizontal wing connection interfaces 8 are provided, which are respectively located in the second and fourth quadrants of the shell structure, and the cable through-cabin opening 7 is located in the third quadrant of the shell structure; Working principle: The shell of the present application adopts an integrated molding process, with good overall size control and light weight; at the same time, it avoids the loosening or falling off of some parts and components, thereby improving overall reliability; finally, the shell structure of the present application does not require subsequent assembly, reducing labor costs.

[0022] In some embodiments, the first load-bearing structure includes: a first inner skin layer 9, a first thickening layer 18 and a first metal layer 12, the first inner skin layer 9 is provided with the first thickening layer 18 outside, and the first metal layer 12 is provided with the first thickening layer 18 outside.

[0023] Specifically, Figure 1 As shown, the first load-bearing structure includes: a first inner skin layer 9, a first thickening layer 18 and a first metal layer 12, the first inner skin layer 9 is provided with the first thickening layer 18 outside, and the first metal layer 12 is provided with the first thickening layer 18 outside; Among them, the first inner skin layer 9 is the main load-bearing structure, which is mainly used to ensure the rigidity and strength requirements of the structural matrix on a large surface load; in this embodiment, the thickness of the first inner skin layer 9 is 5mm; The first thickened layer 18 is a local load-bearing structure, the first thickened layer 18 is used to ensure the stiffness and strength requirements of the tail section shell under local loads such as wings and rudders. In this embodiment, the thickness of the first thickened layer 18 is 10mm; The first metal layer 12 is a local load-bearing structure. On the one hand, the first metal layer 12 is used to ensure that the internal load-bearing structure is evenly loaded when the local load of the nail hole used for connection is converted into a surface load when the tail section shell is subjected to local loads such as wings and rudders; on the other hand, the first metal layer 12 is used for heat insulation and to increase the larger heat sink so that the temperature of the first thickened layer 18 is within its use range; in this embodiment, the thickness of the first metal layer 12 is 5 mm; Specifically, the first metal layer 12 is a metal such as steel or titanium. In this embodiment, the first metal layer 12 is a 7075-T6 aluminum alloy.

[0024] In some embodiments, the first load-bearing structure further includes: a butt joint layer 10 , which is disposed outside the first inner skin layer 9 and located on a side away from the bottom plate 2 .

[0025] Specifically, Figure 1 As shown, the first load-bearing structure further includes: a butt joint layer 10, which is arranged outside the first inner skin layer 9 and located at an end of the first inner skin layer 9 away from the bottom plate 2, and the butt joint layer 10 is connected to the first thickening layer 18; In this embodiment, the docking layer 10 is the main load-bearing structure, and the docking layer 10 is used to ensure the rigidity and strength requirements of the nail holes connected to the engine when the tail section shell is subjected to axial tensile load; in this embodiment, the thickness of the docking layer 10 is 7 mm; Specifically, in this embodiment, if Figure 4 As shown, the mold includes: a mold body 22, a mold base plate 20 is arranged at the bottom of the mold body 22, a demolding ring 21 is sleeved on one end of the mold body 22 close to the mold base plate 20, and the demolding ring 21 is detachably connected to the base plate 2; four thickening area positioning plates 23 are circumferentially evenly spaced at one end of the mold body 22 away from the mold base plate 20, and the thickening area positioning plates 23 are used to position the first thickening layer 18; in the process of laying, for some special parts such as some thickening areas, the thickening area positioning plates 23 should be used for positioning and laying according to the design requirements to ensure that the thickness and shape of these parts meet the requirements.

[0026] In some embodiments, the first heat protection structure includes: a first sandwich layer 13, a first outer skin layer 14 and a first heat protection layer 15, the first outer skin layer 14 is arranged on the outside of the first metal layer 12 and the docking layer 10, the first heat protection layer 15 is arranged on the outside of the first outer skin layer 14, the first sandwich layer 13 is arranged on the side of the first outer skin layer 14 close to the first metal layer 12, and the first sandwich layer 13 is arranged between the first thickening layer 18 and the docking layer 10.

[0027] Specifically, Figure 1 As shown, the first outer skin layer 14 is a structure for maintaining the shape of the shell, and for providing a bonding surface for the first heat protection layer 15; in the present embodiment, the thickness of the first outer skin layer 14 is 1mm; The first sandwich layer 13 is an auxiliary filling structure, which passes through the first metal layer 12 and is arranged between the first thickening layer 18 and the butt joint layer 10 to improve the molding measures of the process; at the same time, the first sandwich layer 13 also plays a role in heat insulation, so that the temperature of the first thickening layer 18 is within its use range; in this embodiment, the thickness of the first sandwich layer 13 is 10 mm; The first heat protection layer 15 is a heat-insulating structure. The first heat protection layer 15 is used to reduce the heat transfer efficiency of the internal structure of the aerodynamic heat chamber of the rocket under high Mach number flight to ensure the use temperature of the internal structure. In this embodiment, the thickness of the first heat protection layer 15 is 3 mm. Specifically, the first sandwich layer 13 is a heat-resistant sandwich material, generally one or more of PVC foam, aluminum honeycomb, fiberglass honeycomb, and aramid paper honeycomb; in this embodiment, the first sandwich layer 13 is PMI foam; Specifically, the change in thickness of the first sandwich layer 13 and the first outer skin layer 14 can increase the heat resistance time of the shell structure at a certain temperature.

[0028] In some embodiments, the second load-bearing structure includes: a second inner skin layer 17 and a second thickening layer 11, the second thickening layer 11 is arranged on the outside of the second inner skin layer 17; the second inner skin layer 17 and the first inner skin layer 9 are an integral structure; the second thickening layer 11 and the first thickening layer 18 are an integral structure.

[0029] Specifically, the second inner skin layer 17 is the main load-bearing structure, which is mainly used to ensure the rigidity and strength requirements of the structural matrix on a large surface load; in this embodiment, the thickness of the second inner skin layer 17 is 5mm; The second thickened layer 11 is a local load-bearing structure, and is used to ensure the rigidity and strength requirements of the tail section shell under local loads such as wings and rudders. In this embodiment, the thickness of the second thickened layer 11 is 10 mm; In this embodiment, the second inner skin layer 17 and the first inner skin layer 9 are both integral structures, and the second thickened layer 11 and the first thickened layer 18 are both integral structures; Specifically, the first inner skin layer 9, the second inner skin layer 17, the first thickened layer 18 and the second thickened layer 11 are all carbon fiber reinforced composite materials, which are composite materials mainly composed of a matrix and a reinforcement, wherein the matrix is ​​a polyimide resin or a bismaleimide resin or a cyanate resin, and the reinforcement is a carbon fiber, a glass fiber, a quartz fiber, or an aramid fiber; in this embodiment, the first inner skin layer 9, the second inner skin layer 17, the first thickened layer 18 and the second thickened layer 11 are epoxy resin-based T700 grade carbon fiber reinforced composite materials; this structure is made of composite materials, which have the advantages of high specific strength and high specific stiffness, and can greatly reduce the overall weight of the shell structure.

[0030] In some embodiments, the second heat protection structure includes: a second outer skin layer 19 and a second heat protection layer 16, the second outer skin layer 19 is arranged on the outside of the second thickening layer 11, the second heat protection layer 16 is arranged on the outside of the second outer skin layer 19, the second outer skin layer 19 and the first outer skin layer 14 are an integrated structure; the second heat protection layer 16 is connected to the first heat protection layer 15.

[0031] Specifically, the second outer skin layer 19 is a structure for maintaining the shape of the shell, and is used to provide a bonding surface for the second heat protection layer 16; in this embodiment, the thickness of the second outer skin layer 19 is 1 mm; Specifically, the second heat protection layer 16 is a heat-insulating structure, and the second heat protection layer 16 is used to reduce the heat transfer efficiency of the solid engine hot air flow to the cabin structure, so as to ensure the use temperature of the internal structure; in this embodiment, the second heat protection layer 16 is 10mm; Specifically, the first outer skin layer 14 and the second outer skin layer 19 are both made of carbon fiber reinforced composite materials, which are composite materials mainly composed of a matrix and a reinforcement, wherein the matrix is ​​a polyimide resin or a bismaleimide resin or a cyanate resin, and the reinforcement is a carbon fiber, a glass fiber, a quartz fiber, or an aramid fiber; in this embodiment, the first outer skin layer 14 and the second outer skin layer 19 are epoxy resin-based T700 grade carbon fiber reinforced composite materials; Specifically, the first heat protection layer 15 and the second heat protection layer 16 are one or more heat protection materials such as heat protection coating, quartz phenolic, cork, high silica phenolic, carbon phenolic, etc., which can realize or change the heat insulation capacity of the structure; in the present embodiment, the first heat protection layer 15 is cork, and the second heat protection layer 16 is high silica phenolic; because the cost of high silica heat protection material is higher than that of cork heat protection material, the present application uses different layout methods of heat insulation materials in different thermal environment zones to reduce the cost of raw materials.

[0032] Example 2 Please refer to Figure 3 and Figure 5 As shown, the present application provides a method for preparing a rocket tail section shell structure, which is used to prepare the rocket tail section shell structure provided in Example 1, and includes the following steps: S100: forming the first load-bearing structure and the second load-bearing structure at one time in the mold by using a hot-pressing tank forming process; S200: preforming the first heat protection structure and the second heat protection structure, and processing the preformed first heat protection structure and the second heat protection structure into required sizes and shapes; S300: using an adhesive film with a temperature greater than or equal to 180° C. to bond the first heat protection structure and the second heat protection structure to the first load-bearing structure and the second load-bearing structure respectively; S400: A vacuum bag pressing process is used to perform secondary curing on the bonded structure to obtain a shell; the shell includes: a side plate and a bottom plate, the side plate is composed of a first load-bearing structure and a first heat-proof structure, and the bottom plate is composed of a second load-bearing structure and a second heat-proof structure.

[0033] In this embodiment, the housing includes a bottom plate 2 and a side plate 1, wherein the side plate 1 is disposed on one side of the bottom plate 2 and circumferentially surrounds the bottom plate 2; the side plate 1 is composed of a first load-bearing structure and a first heat-proof structure, and the bottom plate 2 is composed of a second load-bearing structure and a second heat-proof structure; Specifically, in this embodiment, the mold is a positive mold, which is a mold that molds the material to the outer surface. The mold ensures the inner surface accuracy of the shell and does not affect the installation of the cabin structure. Specifically, the autoclave molding process mainly utilizes the high temperature and high pressure environment inside the autoclave to solidify and mold the composite material prepreg in the mold, thereby obtaining a structural component with excellent performance; since the autoclave can provide a uniform temperature and pressure environment, the molded component has a good fiber volume content, a low porosity and a high fiber orientation accuracy, thereby obtaining excellent mechanical properties and being suitable for manufacturing load-bearing structural components; at the same time, the size and shape of the component can be precisely controlled to meet the high-precision requirements of complex structures; In this embodiment, the specific process of step S100 is as follows: spray or apply a release agent evenly on the outer surface of the mold. After the release agent is cured, lay the prepared prepreg layer by layer on the outer surface of the mold according to the designed laying order and direction; pay attention to the orientation of the fibers when laying the layers to meet the mechanical performance requirements of the rocket shell tail section in different directions; special laying tools, such as rollers, can be used to compact the prepreg and expel the air therein so that each layer of prepreg fits tightly together; after the laying is completed, place the entire mold and prepreg assembly in a vacuum bag; ensure that the vacuum bag can completely cover the mold and the prepreg, and form a good seal between the vacuum bag and the mold; place the sealed mold and vacuum bag assembly in an autoclave, start the autoclave, and start the heating and pressurization process. In this embodiment, The temperature of the autoclave is 120°C; during the heating process, the resin in the prepreg will soften and flow, fill the gaps between the fibers under pressure, and gradually solidify; during the insulation stage, it is necessary to ensure that the resin is fully solidified to form a composite material structure with sufficient strength and performance; after the solidification is completed, the autoclave is cooled at a predetermined cooling rate until the temperature and pressure drop to a safe range; after the cooling is completed, the mold is taken out of the autoclave, the vacuum bag is first removed, and then the demolding ring 21 is carefully installed on the mold. The role of the demolding ring 21 is to provide a fulcrum during the demolding process to help separate the molded rocket shell tail section from the mold; by using a demolding tool (such as a crowbar, etc.), along the junction of the demolding ring 21 and the mold body 22, the molded molding structure is gradually pried up from the outer surface of the mold to separate it from the mold; Specifically, the first heat protection structure includes: a first sandwich layer 13, a first outer skin layer 14 and a first heat protection layer 15, and the second heat protection structure includes: a second outer skin layer 19 and a second heat protection layer 16; wherein the first outer skin layer 14 and the second outer skin layer 19 are an integrated structure; Specifically, different methods are used to preform the first sandwich layer 13, the first heat protection layer 15, the second heat protection layer 16, the first outer skin layer 14 and the second outer skin layer 19 respectively; wherein, The first sandwich layer 13 is processed into the desired shape by foam machine; The first outer skin layer 14 and the second outer skin layer 19 are formed by bag pressing process and cut into required shapes; First heat protection layer 15: Cut the cork into the required shape; The second heat protection layer 16 is made by mixing high silica fiber and phenolic resin in a certain proportion, adopting a compression molding process to form the mixture, and then cutting the mixture into a desired shape.

[0034] In some embodiments, step S400 further includes the following steps: S500: demoulding the shell, and processing a functional structure on the shell to obtain a finished shell structure.

[0035] Specifically, in some embodiments, after the shell is formed, the shell is demoulded, and then the shell is processed to form multiple functional structures on the shell; in this embodiment, the functional structure includes: a steering gear box-level gas rudder structure 3, an air rudder installation interface 4, an adapter / counterweight connection interface 5, a solid engine docking interface 6, a cable through-cabin opening 7, and a horizontal wing connection interface 8; Specifically, in this embodiment, after the shell is demoulded and the functional structure is processed, the shell structure is subjected to non-destructive testing to detect whether there are defects inside and whether the size is accurate.

[0036] The above description is only a preferred embodiment of the present application and an explanation of the technical principles used. Those skilled in the art should understand that the scope of the invention involved in the present application is not limited to the technical solution formed by a specific combination of the above technical features, but should also cover other technical solutions formed by any combination of the above technical features or their equivalent features without departing from the inventive concept. For example, the above features are replaced with (but not limited to) technical features with similar functions disclosed in the present application.

Claims

1. A rocket tail section shell structure, characterized in that: include: A shell, the shell comprising a bottom plate (2) and a side plate (1), the side plate (1) being arranged on one side of the bottom plate (2) and circumferentially surrounding the bottom plate (2), the bottom plate (2) and the side plate (1) being an integrally formed structure; The side plate (1) comprises: a first load-bearing structure and a first heat-proof structure, wherein the first load-bearing structure is arranged inside the first heat-proof structure; The bottom plate (2) comprises: a second load-bearing structure and a second heat-proof structure, the second load-bearing structure is arranged inside the second heat-proof structure, the second load-bearing structure is connected to the first load-bearing structure, the second heat-proof structure is connected to the first heat-proof structure, the first load-bearing structure and the second load-bearing structure are used to bear the load of the fuselage, and the first heat-proof structure and the second heat-proof structure are used to prevent heat from being transferred to the inside of the shell.

2. A rocket tail section casing structure according to claim 1, characterized in that: The first load-bearing structure comprises: a first inner skin layer (9), a first thickening layer (18) and a first metal layer (12); the first inner skin layer (9) is provided with the first thickening layer (18) on the outside, and the first metal layer (12) is provided with the first thickening layer (18) on the outside.

3. A rocket tail section casing structure according to claim 2, characterized in that: The first load-bearing structure further comprises: a butt joint layer (10), the butt joint layer (10) being arranged outside the first inner skin layer (9) and located on a side away from the bottom plate (2).

4. A rocket tail section casing structure according to claim 3, characterized in that: The first heat protection structure comprises: a first sandwich layer (13), a first outer skin layer (14) and a first heat protection layer (15); the first outer skin layer (14) is arranged outside the first metal layer (12) and the butt joint layer (10); the first heat protection layer (15) is arranged outside the first outer skin layer (14); the first sandwich layer (13) is arranged on a side of the first outer skin layer (14) close to the first metal layer (12); and the first sandwich layer (13) is arranged between the first thickening layer (18) and the butt joint layer (10).

5. A rocket tail section casing structure according to claim 4, characterized in that: The second load-bearing structure comprises: a second inner skin layer (17) and a second thickened layer (11), wherein the second thickened layer (11) is arranged outside the second inner skin layer (17); the second inner skin layer (17) and the first inner skin layer (9) are an integrated structure; and the second thickened layer (11) and the first thickened layer (18) are an integrated structure.

6. A rocket tail section casing structure according to claim 5, characterized in that: The second heat protection structure comprises: a second outer skin layer (19) and a second heat protection layer (16); the second outer skin layer (19) is arranged outside the second thickened layer (11); the second heat protection layer (16) is arranged outside the second outer skin layer (19); the second outer skin layer (19) and the first outer skin layer (14) are an integrated structure; and the second heat protection layer (16) is connected to the first heat protection layer (15).

7. A rocket tail section casing structure according to claim 6, characterized in that: The first inner skin layer (9), the second inner skin layer (17), the butt joint layer (10), the first thickened layer (18), the second thickened layer (11), the first outer skin layer (14) and the second outer skin layer (19) are all made of carbon fiber reinforced composite material.

8. A rocket tail section casing structure according to claim 6, characterized in that: The first sandwich layer (13) is a heat-resistant sandwich material.

9. A method for preparing a rocket tail section shell structure, used for preparing the rocket tail section shell structure provided by any one of claims 1 to 8, characterized in that: The steps include: S100: forming the first load-bearing structure and the second load-bearing structure at one time in the mold by using a hot-pressing tank forming process; S200: preforming the first heat protection structure and the second heat protection structure, and processing the preformed first heat protection structure and the second heat protection structure into required sizes and shapes; S300: using an adhesive film with a temperature greater than or equal to 180° C. to bond the first heat protection structure and the second heat protection structure to the first load-bearing structure and the second load-bearing structure respectively; S400: performing secondary curing on the bonded structure by using a vacuum bag pressing process to obtain a shell; the shell comprises: a side panel and a bottom panel, the side panel is composed of the first load-bearing structure and the first heat-proof structure, and the bottom panel is composed of the second load-bearing structure and the second heat-proof structure.

10. The method for preparing a rocket tail section shell structure according to claim 9, characterized in that: After step S400, the following steps are also included: S500: demoulding the shell, and processing a functional structure on the shell to obtain a finished shell structure.

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