Continuous integrated composite forming method for composite material
By performing continuous integrated composite forming on a set of equipment, the problems of low forming efficiency and large error of thin-walled large deformation composite materials in the prior art are solved, and efficient and accurate composite materials are achieved.
Patent Information
- Application Number
- CN202510661174.0
- Authority / Receiving Office
- CN · China
- Patent Type
- Applications(China)
- Current Assignee / Owner
- Filing Date
- 2025-05-21
- Publication Date
- 2025-07-08
AI Technical Summary
The existing composite forming method of thin-wall large-deformed composite materials needs to be carried out on two sets of equipment and is divided into two process links, resulting in inefficiency and two clamping and positioning required, which increases the molding dimensional error and damage risk.
The composite material continuous integrated composite forming method is adopted to continuously traction, convey and process it on a set of forming equipment, including preheating deformation, application of reinforcement material, molding and heat curing, cutting and grinding, etc., to achieve integrated composite forming.
The forming efficiency and forming quality of composite materials are improved, the molding dimensional error and damage risks are reduced, and the high-efficiency and high-precision composite preparation is achieved.
Smart Images
Figure CN120269855A_ABST
Abstract
Description
Technical Field
[0001] The present invention relates to the technical field of composite material preparation, and particularly relates to a continuous integrated composite forming method for composite materials. Background Art
[0002] The existing composite forming method for thin-walled large-deformation composite materials generally first forms prepreg into two rolls of large-deformation composite material components by one set of equipment, then bonds the above two rolls of large-deformation composite material components into a composite material by another set of equipment, and finally winds up the bonded composite material.
[0003] For the above existing composite forming method for thin-walled large-deformation composite materials, it is carried out on two sets of equipment and divided into two process steps. The process steps are relatively numerous, and the efficiency of composite material composite forming is relatively low; and it is necessary to perform clamping and positioning for two material feedings, which significantly increases the forming size error of the composite material; at the same time, the damage risk of the composite material is significantly increased. Summary of the Invention
[0004] In view of this, the present invention provides a continuous integrated composite forming method for composite materials to solve the problems of the existing composite material composite forming method, which is carried out on two sets of equipment, divided into two process steps, with relatively numerous process steps, relatively low efficiency of composite material composite forming; and it is necessary to perform clamping and positioning for two material feedings, which significantly increases the forming size error of the composite material; at the same time, the damage risk of the composite material is significantly increased.
[0005] The present invention provides a continuous integrated composite forming method for composite materials, which is carried out on one set of forming equipment for continuous traction, conveying and processing. The continuous integrated composite forming method for composite materials includes:
[0006] Feeding out two prepreg groups in the form of sheets;
[0007] Respectively performing preheating and deformation on the two prepreg groups, and deforming the prepreg groups from sheets into a designed configuration;
[0008] Applying reinforcing materials to specific regions at the edges of the prepreg groups formed into the designed configuration;
[0009] Performing compression molding and heat curing treatment on the two prepreg groups with the designed configuration, so that the resin matrix in the prepreg groups undergoes a curing reaction, and the prepreg groups are formed into two thin-walled composite material components with specific cross-sectional profiles;
[0010] Two composite material components gradually fit together under the constraint of a tapered mold, and at the same time, heat pressing and curing are performed on the regions where the reinforcing materials are applied at the edges of the two composite material components to obtain an integrated composite material component;
[0011] Cut, grind, and shape the integrated composite component to obtain an integrated composite component that meets the configuration requirements;
[0012] Flatten the integrated composite component that meets the configuration requirements, and wind up the flattened composite component to obtain qualified composite materials. Beneficial effects: By adopting the above technical solutions, this application prepares integrated composite materials through a set of forming equipment, conducts continuous integrated composite forming on the composite materials, reduces process steps by continuously applying reinforcing materials and performing compression molding and heat curing treatment, improves the composite forming efficiency of the composite materials, and at the same time significantly reduces the damage risk of the composite materials; on a set of forming equipment, only through one-time feeding and clamping and positioning, the forming size error of the composite materials is significantly reduced; furthermore, high-efficiency and high-precision integrated composite forming of ultra-long thin-walled and large-deformation composite materials is realized, effectively improving the forming efficiency and forming quality of continuous composite materials.
[0013] Optionally, the prepreg group in sheet form is composed of multiple rolls of unidirectional prepregs laid and combined at different laying angles; and polytetrafluoroethylene release films are attached to the two outer surfaces of the prepreg group in sheet form.
[0014] Optionally, the laying angles are: 0°, +45°, -45°, or 90°.
[0015] Optionally, on the forming equipment, the conveying directions and conveying speeds of the two prepreg groups are the same, and the forming equipment is suitable for timely adjusting the tension of the two prepreg groups respectively.
[0016] Optionally, the resin of the prepreg group is a thermosetting resin; the curing temperature, curing pressure, and curing time of the compression molding and heat curing treatment are determined according to the type of thermosetting resin.
[0017] Optionally, the preheating temperature for preheating and deforming the two prepreg groups is not lower than 40°C; the heating temperature for performing compression molding and heat curing treatment on the two prepreg groups with the designed configuration is not lower than 240°C; the forming pressure for performing compression molding and heat curing treatment on the two prepreg groups with the designed configuration is not lower than 0.4 MPa.
[0018] Optionally, it further includes:
[0019] After performing compression molding and heat curing treatment on the two prepreg groups with the designed configuration, it is also necessary to perform heat preservation treatment on the two composite material components after the compression molding and heat curing treatment. Beneficial effects: By adopting the above technical solutions, through the heat preservation treatment after the compression molding and heat curing treatment, the residual stress inside the composite material components can be reduced, and the comprehensive performance of the prepared composite materials can be enhanced.
[0020] Optionally, applying a reinforcing material to a specific area at the edge of a prepreg group formed into a designed configuration means: placing two prepreg groups formed into a designed configuration in a relatively deformed distribution position, and continuously applying a reinforcing material to the edge positions of the two opposite surfaces respectively.
[0021] Optionally, it further includes: before cutting, grinding, and shaping an integrated composite material component, first performing a contour scanning inspection on the edge of the composite material component. Beneficial effect: By adopting the above technical solution in this application, precise cutting and grinding can be achieved through contour scanning.
[0022] Optionally, the requirement for the relative offset of the edge of the integrated composite material component that meets the configuration requirements within a plane is: the offset within 10 meters is less than 1 millimeter; the single-sided thickness of the qualified composite material does not exceed 0.4 millimeters; the length of the qualified composite material is greater than 100 meters. Description of the Drawings
[0023] In order to more clearly illustrate the specific embodiments of the present invention or the technical solutions in the prior art, the following will briefly introduce the drawings required for use in the description of the specific embodiments or the prior art. Obviously, the drawings in the following description are some embodiments of the present invention. For those of ordinary skill in the art, other drawings can be obtained based on these drawings without creative efforts.
[0024] Figure 1 It is a schematic diagram of the layout structure of the forming equipment provided in the embodiment of the present invention;
[0025] Figure 2 It is a schematic diagram of the process steps of the continuous integrated composite forming method for composite materials provided in the embodiment of the present invention.
[0026] Description of the reference numerals:
[0027] 1. Feeding mechanism; 2. Guiding and deviation-correcting mechanism; 3. Preheating and deformation structure; 4. Reinforcing material applying mechanism; 5. Molding and curing mechanism; 6. Heat preservation mechanism; 7. Traction and guiding mechanism; 8. Cutting and grinding mechanism; 9. Pressing roller structure; 10. Material collecting mechanism. Detailed Embodiments
[0028] To make the objectives, technical solutions, and advantages of the embodiments of the present invention clearer, the following will clearly and completely describe the technical solutions in the embodiments of the present invention with reference to the drawings in the embodiments of the present invention. Obviously, the described embodiments are some, but not all, of the embodiments of the present invention. Based on the embodiments of the present invention, all other embodiments obtained by those of ordinary skill in the art without creative efforts fall within the protection scope of the present invention.
[0029] As Figures 1 to 2 shown in a specific implementation of the continuous integrated composite forming method for composite materials, the continuous integrated composite forming method for composite materials performs continuous traction conveying and processing on a set of forming equipment. The composite materials in this application refer to ultra-long thin-walled and large-deformation composite materials. The continuous integrated composite forming method for composite materials includes the following steps:
[0030] S1. Feed out two prepreg groups in the form of sheets. Specifically, the prepreg groups in the form of sheets are composed of multiple rolls of unidirectional prepregs laid and combined at different laying angles, and the laying angles can be: 0°, +45°, -45°, or 90°; and polytetrafluoroethylene release films are attached to the two outer surfaces of the prepreg groups in the form of sheets. Feed out two prepreg groups in the form of sheets through the feeding mechanism 1. The feeding mechanism 1 is: drums are respectively installed on two controllable feeding shafts, and two prepreg groups in the form of sheets are respectively wound on the two drums.
[0031] S2. Respectively perform preheating deformation on the two prepreg groups, and the prepreg groups are deformed from sheets into the designed configurations; specifically, the preheating temperatures for respectively performing preheating deformation on the two prepreg groups are not lower than 40°C. The two prepreg groups in the form of sheets fed out by the feeding mechanism 1 are conveyed to the preheating deformation structure 3 by the guiding and deviation-correcting mechanism 2 for preheating deformation.
[0032] S3. Apply reinforcing materials to specific regions at the edges of the prepreg groups formed into the designed configurations;
[0033] S4. Perform compression molding and heat curing treatment on the two prepreg groups with the designed configurations, so that the resin matrix in the prepreg groups undergoes a curing reaction, and the prepreg groups are formed into two thin-walled composite material components with specific cross-sectional profiles. Specifically, the resin of the prepreg groups is a thermosetting resin; determine the curing temperature, curing pressure, and curing time of the compression molding and heat curing treatment according to the type of thermosetting resin; the heating temperature for performing compression molding and heat curing treatment on the two prepreg groups with the designed configurations is not lower than 240°C, which belongs to high-temperature curing treatment; the molding pressure for performing compression molding and heat curing treatment on the two prepreg groups with the designed configurations is not lower than 0.4 MPa. Further, after performing compression molding and heat curing treatment on the two prepreg groups with the designed configurations, it is also necessary to perform heat preservation treatment on the two composite material components after the compression molding and heat curing treatment.
[0034] The two prepreg groups with the designed configurations output from the preheating deformation structure 3 enter the reinforcing material application mechanism 4 to apply reinforcing materials to specific regions at the edges of the prepreg groups formed into the designed configurations; then enter the compression molding and curing mechanism 5 for compression molding and heat curing treatment; then the two composite material components after the compression molding and heat curing treatment enter the heat preservation mechanism 6 for post-curing treatment.
[0035] S5. The two composite material components are gradually bonded under the constraint of the gradient die, and at the same time, hot pressing and curing are performed on the reinforcing material application areas at the edges of the two composite material components to obtain an integrated composite material component. Through the hot pressing and curing treatment, the two composite material components are fully cemented.
[0036] S6. Cut, grind, and shape the integrated composite material component to obtain an integrated composite material component that meets the configuration requirements; the requirement for the relative offset of the edge of the integrated composite material component that meets the configuration requirements in the plane is: the offset within 10 meters is less than 1 mm. Specifically, the integrated composite material component after the hot pressing and curing treatment is conveyed by the traction and guiding mechanism 7 to the cutting and grinding mechanism 8. Further, before cutting, grinding, and shaping the integrated composite material component, the edge of the composite material component is first subjected to contour scanning and detection.
[0037] S7. Flatten the integrated composite material component that meets the configuration requirements, and wind up the flattened composite material component to obtain a qualified composite material; the single-sided thickness of the qualified composite material does not exceed 0.4 mm; the length of the qualified composite material is greater than 100 m. Specifically, the integrated composite material component that meets the configuration requirements after cutting, grinding, and shaping is flattened by the pressure roller structure 9, and then the flattened composite material component is wound up by the material receiving mechanism 10. The wound composite material component is convenient for storage and transportation.
[0038] As Figure 1 shown, the material feeding mechanism 1, the guiding and deviation correcting mechanism 2, the preheating and deformation structure 3, the reinforcing material application mechanism 4, the molding and curing mechanism 5, the heat preservation mechanism 6, the traction and guiding mechanism 7, the cutting and grinding mechanism 8, the pressure roller structure 9, and the material receiving mechanism 10 arranged in sequence are provided on the same set of the forming equipment. Through the substantially continuous traction and deviation correction of the guiding and deviation correcting mechanism 2 and the traction and guiding mechanism 7, the forming size error of the composite material is further reduced.
[0039] Further, on the forming equipment, the conveying directions and speeds of the two prepreg groups are the same, and the forming equipment is suitable for timely adjusting the tension of the two prepreg groups respectively.
[0040] Although the embodiments of the present invention have been described in conjunction with the accompanying drawings, those skilled in the art can make various modifications and variations without departing from the spirit and scope of the present invention, and such modifications and variations all fall within the scope defined by the appended claims.
Claims
1. A continuous integrated composite forming method for a composite material, characterized in that, Continuous traction conveying and processing are carried out on a set of forming equipment, and the continuous integrated composite forming method of the composite material includes: Feeding out two prepreg groups in the form of sheets; Preheating and deforming the two prepreg groups respectively, and the prepreg groups are deformed from sheets into the designed configuration; Applying reinforcing materials to specific areas at the edges of the prepreg groups formed into the designed configuration; Performing compression molding and heat curing on the two prepreg groups with the designed configuration, so that the resin matrix in the prepreg groups undergoes a curing reaction, and the prepreg groups are formed into two thin-walled composite material components with specific cross-sectional profiles; the two composite material components are gradually fitted under the constraint of a tapered mold, and at the same time, heat pressing and curing are performed on the areas where the reinforcing materials are applied at the edges of the two composite material components to obtain an integrated composite material component; Cutting, grinding and sizing the integrated composite material component to obtain an integrated composite material component that meets the configuration requirements; Flattening the integrated composite material component that meets the configuration requirements, and winding the flattened composite material component to obtain a qualified composite material.
2. The continuous integrated composite forming method of the composite material according to claim 1, wherein The prepreg group in the form of a sheet is composed of multiple rolls of unidirectional prepregs laid and combined at different laying angles; and polytetrafluoroethylene release films are attached to the two outer surfaces of the prepreg group in the form of a sheet.
3. The method for continuously integrally composite forming of the composite material according to claim 2, characterized in that, The laying angles are: 0°, +45°, -45° or 90°.
4. The continuous integrated composite forming method of the composite material according to any one of claims 1-3, characterized in that, On the forming equipment, the conveying directions and conveying speeds of the two prepreg groups are the same, and the forming equipment is suitable for timely adjusting the tension of the two prepreg groups respectively.
5. The method for continuous integrated composite forming of the composite material according to any one of claims 1 to 3, characterized in that, The resin of the prepreg group is a thermosetting resin; the curing temperature, curing pressure and curing time of the compression molding and heat curing treatment are determined according to the type of the thermosetting resin.
6. The continuous integrated composite forming method of the composite material according to claim 5, characterized in that, The preheating temperature for preheating and deforming the two prepreg groups respectively is not lower than 40°C; the heating temperature for performing compression molding and heat curing on the two prepreg groups with the designed configuration is not lower than 240°C; the molding pressure for performing compression molding and heat curing on the two prepreg groups with the designed configuration is not lower than 0.4 MPa.
7. The continuous integrated composite forming method of the composite material according to any one of claims 1-3, characterized in that It also includes: After performing compression molding and heat curing on the two prepreg groups with the designed configuration, it is also necessary to perform heat preservation treatment on the two composite material components after the compression molding and heat curing treatment.
8. The method for continuously integrally composite forming of the composite material according to any one of claims 1-3, characterized in that, The applying of reinforcing materials to specific areas at the edges of the prepreg groups formed into the designed configuration means: placing the two prepreg groups formed into the designed configuration in a relatively distributed position of deformation, and continuously applying reinforcing materials to the edge positions on the opposite two surfaces respectively.
9. The continuous integrated composite forming method of the composite material according to any one of claims 1-3, characterized in that, It also includes: Before cutting, grinding and sizing the integrated composite material component, first perform contour scanning detection on the edge of the composite material component.
10. The method for continuously integrally composite forming of the composite material according to any one of claims 1-3, characterized in that, The requirement for the relative offset of the edge of the integrated composite material component that meets the configuration requirements in the plane is: the offset within 10 meters is less than 1 mm; the single-sided thickness of the qualified composite material does not exceed 0.4 mm; the length of the qualified composite material is greater than 100 meters.