Method for forming a component of a composite material, formed component and aircraft

Abstract

The application relates to a composite material component forming method in the aerospace field, a formed component and an aircraft. The method comprises the following steps: laying a prepreg of a composite material on the outer periphery of a first core mold to respectively obtain a first preformed body corresponding to an open beam; the first core mold is a hollow structure which can be removed; laying the prepreg of the composite material on the outer periphery of a second core mold to respectively obtain a second preformed body corresponding to a closed beam; the second core mold is a solid structure which cannot be removed; combining the first preformed body and the second preformed body in corresponding positions in a cavity of a forming mold, and laying the prepreg on each joint part of the first preformed body and the second preformed body to obtain a preformed body; after the forming mold with the preformed body is integrally vacuum bagged, the forming mold is placed in a hot press tank for curing to obtain an integrally formed formed component. The scheme provided by the application can efficiently and at low cost produce a lightweight and high-strength integrally formed component.

Description

Technical Field

[0001] This application relates to the field of aerospace composite material preparation technology, and in particular to a composite material component molding method, molded component, and aircraft. Background Technology

[0002] In the aerospace field, with the development of the low-altitude economy, composite materials are generally used to fabricate large structures to meet the lightweight requirements of aircraft. For simple or regular components, such as linear hollow structures, composite prepreg can be laid on the surface of a metal mandrel and then cured. However, for complex components, such as complex frame structures with multiple intersecting beams and longitudinal beams, the molding method is generally to first mold each beam separately using composite materials, and then cure them together by adhesive bonding.

[0003] Currently, the molding process for complex and large structures is extremely cumbersome. For mass production, it requires the replication and investment of a large amount of equipment and metal molds, failing to meet the demands for efficient and low-cost production. Furthermore, the repeated high-temperature curing during the molding process easily leads to defects such as deformation and aging, resulting in a low product qualification rate.

[0004] Therefore, designing a manufacturing method that is low in production cost and can meet the quality requirements of large and complex structures in the aerospace field is a technical problem that urgently needs to be solved. Summary of the Invention

[0005] To address or partially address the problems existing in related technologies, this application provides a method for molding composite material components, a molded component, and an aircraft, which can efficiently and cost-effectively produce high-quality molded composite material components.

[0006] The first aspect of this application provides a method for molding composite material components for preparing molded components of a frame structure, the method comprising:

[0007] A prepreg of composite material is laid on the outer periphery of a pre-prepared first core mold to obtain a first preform corresponding to an open beam; wherein, the first core mold is a removable hollow structure.

[0008] A prepreg of composite material is laid on the outer periphery of a pre-prepared second core mold to obtain a second preform corresponding to the closed beam; wherein, the second core mold is a solid structure that cannot be removed, and the initial outer diameter of the second core mold is larger than the preset inner diameter of the closed beam;

[0009] The first preform and the second preform are placed into corresponding positions in the cavity of the molding mold and combined, and the prepreg is laid at each joint of the first preform and the second preform to obtain a preform;

[0010] After the molding mold containing the preform is vacuum-sealed, it is placed in a hot autoclave for curing to obtain an integrally molded part.

[0011] The molded part is removed from the cooled mold and reheated, and the softened first core mold is removed.

[0012] In some embodiments, the first core mold is prepared in advance in the following manner:

[0013] Multiple memory sheets are laid on the surface of a first core, and the inner cavity structure of the first core and the open beam are designed to conform to the shape. The first core with the memory sheets laid on it is placed in a first mold for overall vacuum bagging, and then placed in a thermostatic jar for curing, so that the multiple memory sheets are cross-linked into one, to obtain the first core mold.

[0014] In some embodiments, the curing temperature of the preform is lower than the curing temperature of the memory sheet; the curing temperature of the preform is higher than the glass transition temperature of the memory sheet.

[0015] In some embodiments, the curing temperature of the preform is 120℃~150℃, and the curing pressure is 0.8MPa~1.0MPa; the curing temperature of the memory sheet is 160℃~180℃, and the curing pressure is 0.8MPa~1.6MPa; the glass transition temperature of the memory sheet is 100℃~120℃.

[0016] In some embodiments, the wall thickness of the first core mold is not uniform, and the wall thickness is 2mm to 4mm.

[0017] In some embodiments, during the curing process in an autoclave, the initial outer diameter of the second mandrel is reduced to be equal to the preset inner diameter of the closed beam.

[0018] In some embodiments, the second core mold is a foam core mold, the heat resistance temperature of which is greater than the curing temperature of the preform; preferably, the foam core mold is made of polymethacrylimide.

[0019] The second aspect of this application provides a molded component prepared according to the component molding method of the composite material described in any one of the first aspects.

[0020] A third aspect of this application provides an aircraft, characterized in that it includes the molded component described in the second aspect.

[0021] In some embodiments, the open beam is arranged along the length of the cabin, and the closed beam is arranged along the width of the cabin.

[0022] The technical solution provided in this application may include the following beneficial results:

[0023] The composite material component molding method of this application improves the beam structure. Based on a frame-type component structure composed of hollow beams and closed beams, a first core mold made of removable and reusable memory foam sheet and a second core mold that does not need to be removed and is lightweight and high-strength can be quickly assembled into a preform within the cavity of a molding die. This preform is then cured into a single integrated structure. Finally, it is reheated at a low temperature to quickly and easily remove the softened first core mold, avoiding any impact on the molded component. This design improves production efficiency, reduces production costs, and ensures the lightweight nature of the molded component while increasing the overall product rigidity.

[0024] It should be understood that the above general description and the following detailed description are exemplary and explanatory only, and do not limit this application. Attached Figure Description

[0025] The above and other objects, features and advantages of this application will become more apparent from the more detailed description of exemplary embodiments thereof in conjunction with the accompanying drawings, wherein the same reference numerals generally represent the same components in the exemplary embodiments thereof.

[0026] Figure 1 This is a schematic diagram of the structure of a molded component shown in an embodiment of this application;

[0027] Figure 2 This is a schematic flowchart illustrating a method for molding composite material components according to an embodiment of this application;

[0028] Figure 3 This is a schematic diagram of the lower mold structure of a molding die according to an embodiment of this application;

[0029] Figure label:

[0030] 10. Crossbeam; 20. Longitudinal beam; Joint area 100;

[0031] Lower mold 30; cavity 310; crossbeam cavity position 311; longitudinal beam cavity position 312. Detailed Implementation

[0032] Embodiments of this application will now be described in more detail with reference to the accompanying drawings. While embodiments of this application are shown in the drawings, it should be understood that this application may be implemented in various forms and should not be limited to the embodiments set forth herein. Rather, these embodiments are provided to make this application more thorough and complete, and to fully convey the scope of this application to those skilled in the art.

[0033] The terminology used in this application is for the purpose of describing particular embodiments only and is not intended to be limiting of the application. The singular forms “a,” “the,” and “the” used in this application and the appended claims are also intended to include the plural forms unless the context clearly indicates otherwise. It should also be understood that the term “and / or” as used herein refers to and includes any or all possible combinations of one or more of the associated listed items.

[0034] It should be understood that although the terms "first," "second," "third," etc., may be used in this application to describe various information, this information should not be limited to these terms. These terms are only used to distinguish information of the same type from one another. For example, without departing from the scope of this application, first information may also be referred to as second information, and similarly, second information may also be referred to as first information. Thus, a feature defined as "first" or "second" may explicitly or implicitly include one or more of that feature. In the description of this application, "multiple" means two or more, unless otherwise explicitly specified.

[0035] In aircraft, the main structure of the cabin is a frame structure, for example... Figure 1 The illustrated frame structure is a support frame consisting of two crossbeams 10 (beams arranged along the length of the aircraft cabin) and three longitudinal beams 20 (beams arranged along the width of the aircraft cabin), used to support the aircraft cabin. In related technologies, to achieve lightweighting, both the crossbeams and longitudinal beams are hollow structures made of composite materials. To manufacture this frame structure, a process is used where each hollow beam is individually molded with a metal mandrel and then bonded together. For mass production, this requires the replication and investment of a large amount of equipment and metal mandrels. The cost of the metal mandrels is high, and disassembly also requires considerable manpower, failing to meet the demands for efficient and low-cost production. Furthermore, the product undergoes multiple high-temperature curing processes during molding—one curing before bonding and another after bonding and assembly—and different molds are required for the two curing processes, resulting in high costs. Additionally, the molded parts are prone to deformation and aging defects, leading to a low product yield.

[0036] To address the aforementioned issues, this application provides a method for molding composite material components, which can efficiently and cost-effectively produce lightweight and high-strength integrated molded components.

[0037] The technical solutions of the embodiments of this application are described in detail below with reference to the accompanying drawings.

[0038] Figure 2 This is a schematic flowchart illustrating a method for molding composite material components according to an embodiment of this application.

[0039] See Figure 2The composite material component molding method shown in the embodiments of this application includes:

[0040] S110, a prepreg of composite material is laid on the outer periphery of the pre-prepared first core mold to obtain the first preform corresponding to the open beam; wherein, the first core mold is a removable hollow structure.

[0041] In some embodiments of this application, the open beam is a hollow beam structure, and the open beam is arranged along the length direction of the aircraft cabin. To obtain each hollow beam structure, a prepreg of composite material is laid on the surface of a specific first mandrel, and the prepreg is supported by the first mandrel to form a hollow structure. Furthermore, the first mandrel is removable; that is, after obtaining the molded part in subsequent steps, the first mandrel is removed and separated from the molded part.

[0042] Unlike the solid metal core molds used in related technologies, the first core mold of this application has a hollow structure. In some specific embodiments, the first core mold is prepared in advance according to the following method:

[0043] S111, multiple memory sheets are laid on the surface of the first core, and the inner cavity structure of the first core and the open beam is designed to conform to the shape.

[0044] The memory sheet in this application refers to a material that can deform through temperature changes, used to prepare a one-piece molded first core. Upon reaching the curing temperature, the memory sheet transforms from a flexible material into a rigid material; upon reaching the glass transition temperature, it transforms from a rigid material into a flexible material. Multiple recycling is achieved by adjusting the ambient temperature, saving material costs.

[0045] To ensure that the cured memory sheet maintains its performance during the curing of the prepreg in the composite material, the material of the memory sheet is selected based on the curing temperature of the prepreg. In some embodiments, the curing temperature of the preform is lower than the curing temperature of the memory sheet; the curing temperature of the preform is higher than the glass transition temperature of the memory sheet. That is, the curing temperature of the memory sheet is higher than the curing temperature of the prepreg, ensuring that the pre-cured memory sheet maintains rigidity during the curing process of the prepreg and preventing the hollow structure from collapsing. Furthermore, the glass transition temperature of the memory sheet is lower than the curing temperature of the prepreg, ensuring that after the prepreg has cured, the memory sheet softens again upon heating to the glass transition temperature, facilitating rapid removal of the memory sheet and ensuring that the molded composite material does not deform. For example, the memory sheet in this application can be a silicone-containing natural rubber; this is merely an example and not a limitation.

[0046] Furthermore, in this application, based on the contour and dimensions of the inner cavity of the open beam, the outer periphery contour and dimensions of the corresponding first core are designed accordingly, so that the memory sheets to be laid form a corresponding first core mold based on the contour dimensions of the first core. Multiple memory sheets are laid one by one on the outer periphery of the first core, with adjacent memory sheets overlapping each other to ensure gapless laying.

[0047] In some embodiments, the wall thickness of the first core mold is non-uniform, ranging from 2mm to 4mm. That is, the first core mold formed from the memory sheet has a non-uniform wall thickness. To achieve this non-uniform wall thickness, memory sheets of different thicknesses are applied to corresponding locations on the first core. Optionally, each layer of memory sheet has the same thickness, and the thickness of different locations is changed by stacking different numbers of memory sheets. For example, each layer of memory sheet is 1mm thick, and the corresponding wall thickness is achieved by applying 2 to 4 layers of memory sheets.

[0048] It is understandable that the molded memory sheet is used to support the prepreg to form a preform, and further supports the prepreg in the high temperature and pressure of the autoclave during molding. The wall thickness of the molded component varies due to different structural strength requirements in different parts. Accordingly, the thickness of the memory sheet used to support the prepreg in different parts is inversely proportional to the wall thickness of the corresponding part of the molded component. For example, if the open beam of the molded component is non-linear, the smaller the curvature, the greater the required thickness. Accordingly, the thickness of the memory sheet is inversely proportional, meaning fewer layers are laid in areas with smaller curvature to achieve a thinner memory sheet. Based on the wall thickness variations in different parts of the molded component, by pre-adjusting the thickness of the memory sheet at the corresponding contact positions, the space occupied by the prepreg in the composite material is changed during the molding process, thus affecting the final wall thickness of the prepreg after curing. Furthermore, the prepreg of composite materials exhibits a certain shrinkage rate during molding, which cannot be precisely controlled, thus compromising the wall thickness accuracy of the finished product. However, the thickness of each memory sheet is precise. By adjusting the thickness of the memory sheet, the molding space of the prepreg within the molding die can be precisely adjusted. In other words, by precisely adjusting the known dimensions in the early stages, the wall thickness variation caused by the unknown shrinkage rate in the later stages can be controlled. By using controllable methods to manage variable results, the molding dimensional accuracy of the finished product can be improved, thereby increasing product yield.

[0049] S112, after placing the first core with the memory sheet material inside the first mold and vacuum-packing it as a whole, it is placed in a hot autoclave for curing, so that multiple memory sheets are cross-linked into one, and the first core mold is obtained.

[0050] After the memory foam sheet is laid in layers of the required thickness for different parts around the outer periphery of the first core, the entire assembly is placed into the corresponding first mold for vacuum bagging. The first mold is understood to be a mold used to form the memory foam sheet into a single, integral core. It can also be understood that, based on the support of the first core, the first core mold, which forms the memory foam sheet into a hollow structure, then serves as a removable core mold for the prepreg.

[0051] Optionally, to extend service life, the first mold and the first core can be made of metal, such as a steel mold. After vacuuming, the first mold is placed in an autoclave and heated and pressurized for approximately 1 to 2 hours. The thicker the memory sheet, the longer the curing time, to ensure the memory sheet is cured and formed. In some embodiments, the curing temperature of the memory sheet is 160°C to 180°C, and the curing pressure is 0.8 MPa to 1.6 MPa. High temperature and high pressure cause chemical cross-linking of the memory sheet, forming a network structure to ensure its rigidity during subsequent prepreg curing. After the first mold cools, it is demolded, and the first core is removed from the first core mold; the first core can be reused.

[0052] The above describes one embodiment of pre-preparing the first mandrel. Based on the first mandrel, a prepreg of the composite material is laid on the outer periphery of the first mandrel. It can be understood that the prepreg is laid in multiple layers, and the number of layers in different parts is set according to the wall thickness of the finished product. After the laying is completed, based on the support of the first mandrel, the prepreg can form the first preform of the open beam.

[0053] In some embodiments, the prepreg is vacuumed after every predetermined number of layers. For example, after the first layer of prepreg is laid, an initial vacuuming process can be performed to ensure that the first layer of prepreg adheres smoothly to the surface of the elastic airbag, avoiding wrinkles or air bubbles and improving the bonding tightness and quality of the prepreg. A pre-vacuuming process is performed after every three layers of prepreg to prevent accumulated wrinkles or gaps between excessively thick prepreg layers. Optionally, the vacuuming pressure can be 0.05 MPa to 0.1 MPa, and the vacuuming time can be 5 to 10 minutes. This design effectively removes air without excessively compressing the prepreg, maintaining its original structure and properties, while promoting resin flow without causing excessive resin loss; additionally, the sufficiently short time can reduce the production cycle and improve production efficiency. For example, the vacuuming pressure can be 0.08 MPa, and the vacuuming time can be 10 minutes. This is merely an example and is not intended to be limiting.

[0054] In some embodiments, the composite material of this application may be carbon fiber composite material, quartz fiber composite material, polyimide fiber composite material, aramid fiber composite material, basalt fiber composite material, etc., which are only examples and are not limited. Optionally, the resin system used for the prepreg of the composite material may be epoxy resin, phenolic resin, bismaleimide resin or other resin systems, which are only examples and are not limited.

[0055] S120, a prepreg of composite material is laid on the outer periphery of the pre-prepared second core mold to obtain the second preform corresponding to the closed beam; wherein, the second core mold is a solid structure that cannot be removed, and the initial outer diameter of the second core mold is larger than the preset inner diameter of the closed beam.

[0056] like Figure 1 As shown, the closed beam in this application is a beam (longitudinal beam) arranged along the width direction of the aircraft cabin. Unlike the hollow longitudinal beam structure in other embodiments, this application uses a lightweight and high-strength solid second core mold filled within the prepreg to form a sandwich structure. This structure supports the prepreg during curing and molding while increasing the strength of the longitudinal beam and ensuring lightweight design. After the prepreg is laid, the prepreg and the second core mold together form the second preform.

[0057] It is understandable that the loads along the width direction (longitudinal beams) of an aircraft cabin are primarily shear and torque (such as landing impacts and asymmetric loads). Solid beams allow for more efficient transmission of shear stress through continuous fiber arrangement. Unlike related technologies that pursue extreme lightweighting with entirely hollow structures, the combined structure of hollow open beams and solid closed beams in this application is easier to fabricate into a single-piece frame structure, while simultaneously meeting the structural requirements of lightweighting and high strength.

[0058] In this step, the second core mold is also prefabricated. Unlike the detachable structure of the first core mold, the second core mold of this application is integrally formed with the prepreg and cannot be removed to fill the closed beam as a solid structure. To improve weight reduction, in some embodiments, the second core mold is a foam core mold, and the heat resistance temperature of the foam core mold is higher than the curing temperature of the preform. By using a foam core mold, the weight reduction of the solid structure can be ensured. At the same time, the material selection of the foam core mold needs to ensure that its heat resistance temperature, i.e., its heat distortion temperature, is higher than the curing temperature of the preform. During the curing process of the prepreg, the foam core mold will not collapse due to heat, ensuring that it maintains the rigidity to support the molding of the prepreg.

[0059] In some preferred embodiments, the foam core mold can be made of polymethacrylimide. For example, polymethacrylimide can be foamed and molded into a second core mold within a corresponding mold using a foaming process.

[0060] At room temperature, the initial outer diameter of the second core mold is larger than the preset inner diameter of the closed beam. This can be understood as the second core mold serving as the filling structure for the closed beam. After the prepreg is laid onto the surface of the second core mold, and before the prepreg begins to heat and cure, a larger initial outer diameter is set to increase the contact area between the second and first preforms, making their assembly more stable. Then, the excess shrinkage during the subsequent curing process restores the outer diameter of the second core mold to the preset size.

[0061] Optionally, in this step, the fibers of the prepreg laid on the surface of the second core mold can be the same as or different from the fibers of the prepreg in S110, but the curing parameters of the resin in the prepreg must be consistent. It can be understood that by selecting composite materials of different materials on different beams, the strength performance requirements of different parts can be met.

[0062] S130, the first preform and the second preform are placed into the corresponding positions in the cavity of the molding mold and combined, and prepreg is laid at each joint of the first preform and the second preform to obtain a preform.

[0063] like Figure 3 The lower mold 30 in the molded die shown includes a cavity 310 corresponding to the molding component. The overall outline dimensions of the cavity are designed to conform to the molding component. Each first preform is placed into its corresponding crossbeam cavity 311, and each second preform is placed into its corresponding longitudinal beam cavity 312. Prepreg is applied again to the surface of the joint 100 between the second and first preforms to allow for a transition through the added prepreg, thus forming an integrated structure and creating a continuous and complete preform from the first and second preforms.

[0064] It is understandable that space can be reserved at the splicing parts corresponding to the cavity, so that prepreg can be laid at the splicing parts for connection and transition.

[0065] S140: After vacuum forming the mold containing the preformed body, the mold is placed in a hot autoclave for curing to obtain an integrally formed part.

[0066] In this step, after the molding mold is closed, the molding mold is vacuum-packed as a whole according to relevant technology and vacuumed; after maintaining the vacuum state for a certain period of time, such as 5 to 10 minutes, it can be placed in an autoclave for curing and molding.

[0067] In some embodiments, the curing temperature of the preform is 120℃~150℃, and the curing pressure is 0.8MPa~1.0MPa. The temperature can be increased at a rate of less than or equal to 2℃ / min. The curing temperature limits the maximum temperature after heating, and the curing pressure limits the maximum pressure after pressurization. The maximum curing pressure of the preform is less than the curing pressure of the memory sheet during curing, thus avoiding damage to the first core mold due to excessive pressure. After gradually reaching the curing temperature and pressure, the molding die is held at temperature and pressure in an autoclave for a certain period of time, for example, 20min~40min, to ensure complete curing and shaping of the resin in the prepreg. The entire curing process, from placing the molding die in the autoclave until completion, takes approximately 4 hours.

[0068] In some embodiments, during the curing process in the autoclave, the initial outer diameter of the second mandrel shrinks to be equal to the preset inner diameter of the closed beam. The second mandrel, i.e., the foam mandrel, shrinks slightly under pressure, causing its initial outer diameter to shrink to the preset inner diameter of the closed beam. In some embodiments, the initial outer diameter A = preset inner diameter + (0.5~1) mm. That is, the initial outer diameter of the foam mandrel is slightly larger than the preset inner diameter of the longitudinal beam by 0.5 mm to 1 mm. Under the influence of pressure in the autoclave, the initial outer diameter of the second mandrel can be reduced to be equal to the preset inner diameter of the closed beam, thereby producing a closed beam (longitudinal beam) that meets dimensional accuracy and has a stable connection.

[0069] It is understandable that the curing temperature of the preform is higher than the glass transition temperature of the memory sheet. This ensures that the prepreg does not soften the pre-cured memory sheet during the curing process, so that the first core mold always maintains sufficient support to shape the first preform.

[0070] After curing, the preform is integrally molded into a molded part in the molding die.

[0071] S150, the molded part is removed from the cooled molding mold for reheating, and the softened first core mold is removed.

[0072] After the molding die cools, the die is opened, and the molded part is removed. At this time, the molded part carries the first core mold. The molded part is placed in a heating device, such as an oven, for reheating for a preset time, such as 20 to 30 minutes, at the glass transition temperature of the memory sheet. In some embodiments, the glass transition temperature of the memory sheet is 100°C to 120°C. It is understood that the molded part remains rigid at this glass transition temperature and will not collapse, while the first core mold softens upon heating and can be quickly and easily removed from the molded part.

[0073] The composite material component molding method of this application improves the beam structure. Based on a frame-type component structure composed of hollow beams and closed beams, a first core mold made of removable and reusable memory foam sheet and a second core mold that does not need to be removed and is lightweight and high-strength can be quickly assembled into a preform within the cavity of a molding die. This preform is then cured into a single integrated structure. Finally, it is reheated at a low temperature to quickly and easily remove the softened first core mold, avoiding any impact on the performance of the molded component. This design improves production efficiency, reduces production costs, and ensures the lightweight nature of the molded component while increasing the overall rigidity of the product.

[0074] One embodiment of this application also provides an aircraft, which includes a molded component made of composite material. The molded component is manufactured using the method described in any of the above embodiments. Optionally, the aircraft can be a manned aircraft or an unmanned aerial vehicle, and there is no limitation thereto.

[0075] In some embodiments, the molded component includes a frame structure composed of open beams and closed beams, wherein the open beams are arranged along the length direction of the cabin, and the closed beams are arranged along the width direction of the cabin. The number of open beams and closed beams can be customized and is not limited here.

[0076] It is understandable that hollow open beams can reduce the weight of the machine body, while the hollow structure can be used for cable routing, which is conducive to improving space utilization within the limited machine body; solid closed beams can improve the torsional strength of the machine body, and the combination of hollow beams and solid beams is more conducive to rapid prototyping, improving production efficiency and reducing production costs.

[0077] The various embodiments of this application have been described above. These descriptions are exemplary and not exhaustive, nor are they limited to the disclosed embodiments. Many modifications and variations will be apparent to those skilled in the art without departing from the scope and spirit of the described embodiments. The terminology used herein is chosen to best explain the principles, practical application, or improvement of the technology in the market, or to enable others skilled in the art to understand the embodiments disclosed herein.

Claims

1. A method for molding a component made of composite materials, characterized in that, Molded components used to manufacture frame structures include: A prepreg of composite material is laid on the outer periphery of a pre-prepared first core mold to obtain a first preform corresponding to an open beam; wherein, the first core mold is a removable hollow structure; the first core mold is obtained by hot pressing and curing multiple memory sheets; A prepreg of composite material is laid on the outer periphery of a pre-prepared second core mold to obtain a second preform corresponding to the closed beam; wherein, the second core mold is a solid structure that cannot be removed, and the initial outer diameter of the second core mold is larger than the preset inner diameter of the closed beam; The first preform and the second preform are placed into corresponding positions in the cavity of the molding mold and combined, and the prepreg is laid at each joint of the first preform and the second preform to obtain a preform; After the molding mold containing the preform is vacuum-sealed, it is placed in a hot autoclave for curing to obtain an integrally molded part. The molded part is removed from the cooled mold and reheated, and the softened first core mold is removed.

2. The component forming method according to claim 1, characterized in that, The first core mold is prepared in advance according to the following method: Multiple memory sheets are laid on the surface of the first core, and the inner cavity structure of the first core and the open beam are designed to conform to the shape. After the first core with the memory sheet laid on it is placed in the first mold and vacuum-packed as a whole, it is placed in a thermostatic precipitator for curing, so that multiple memory sheets are cross-linked into one, and the first core mold is obtained.

3. The component forming method according to claim 1 or 2, characterized in that: The curing temperature of the preform is lower than the curing temperature of the memory sheet; The curing temperature of the preform is greater than the glass transition temperature of the memory sheet.

4. The component forming method according to claim 3, characterized in that: The curing temperature of the preform is 120℃~150℃, and the curing pressure is 0.8MPa~1.0MPa; The curing temperature of the memory sheet is 160℃~180℃, and the curing pressure is 0.8MPa~1.6MPa; The glass transition temperature of the memory sheet is 100℃~120℃.

5. The component forming method according to claim 1 or 2, characterized in that: The wall thickness of the first core mold is unevenly distributed, ranging from 2mm to 4mm.

6. The component forming method according to claim 1, characterized in that: During the curing process in the autoclave, the initial outer diameter of the second core mold is reduced to be equal to the preset inner diameter of the closed beam.

7. The component forming method according to claim 1, characterized in that: The second core mold is a foam core mold, and the heat resistance temperature of the foam core mold is greater than the curing temperature of the preform.

8. The component forming method according to claim 7, characterized in that: The foam core mold is made of polymethacrylimide.

9. A molded component, characterized in that, The composite material component is prepared by any one of claims 1 to 8.

10. An aircraft, characterized in that, Includes the molded component as described in claim 9.

11. The aircraft according to claim 10, characterized in that: The open beam is arranged along the length of the cabin, and the closed beam is arranged along the width of the cabin.

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