Forming preparation method of special-shaped surface composite material structural member with sharp corner structure

Abstract

The invention relates to the technical field of forming of composite material structural parts, and provides a forming preparation method of a special-shaped surface composite material structural part with a sharp-corner structure, which comprises the following steps: S1, utilizing Fibersim software simulation design to be matched with a laser positioning layering system and a tool mold to precisely position a layering parting line and a layering lap joint splicing line; s2, prepreg is laid on the surface of the tool mold based on the positioned laying layer parting line and the laying layer lap joint seam line; s3, a hot suction glue pressurization tool is installed, and the structural parts on which the prepreg is laid are compacted through hot suction glue; s4, a rubber soft mold is used for pressurizing the sharp corner structure of the special-shaped face, a rigid pressing plate is used for pressurizing the special-shaped face and the corner ridge, and the special-shaped face and the corner ridge enter an autoclave for heating and curing; and S5, the autoclave is moved out, and the structural part is demolded. According to the method, the laying layer reference is accurately positioned, the forming precision of the special-shaped surface composite material structural part is improved, and the problem that the fiber angle is greatly deflected due to sudden change of the structural surface is solved.

Description

Technical Field

[0001] The present invention relates to the technical field of forming composite structural parts, specifically, to a forming and preparation method of composite structural parts with sharp-angled structural profiles, and especially to a forming and preparation method of composite structural parts with sharp-angled structural profiles and large wall thickness. Background Art

[0002] With the development of lightweight and high-performance equipment, the application of composite materials in the aerospace field continues to deepen. Advanced resin-based composite materials have become the preferred solution for the preparation of key load-bearing components due to their designability, light weight and high strength.

[0003] To simultaneously meet multiple requirements such as load bearing and spatial avoidance, demanding geometric conditions are unavoidable, especially for composite structural parts with sharp corners and thick walls, which inevitably appear in aerospace structures. This composite structural configuration undoubtedly significantly reduces the manufacturability of structural part manufacturing. First, for composite structures with special-shaped surfaces, asymmetric and multi-curvature free-form surfaces will lead to an increase in the distortion rate of fiber layups. The fiber distortion makes the structural parts at risk of interface failure and aggravates the degree of structural deformation, which is not conducive to ensuring the dimensional accuracy and internal quality of the structural parts. Secondly, for composite structures with special-shaped surfaces with sharp corners, it is difficult to ensure the accuracy of the layup angle in the sharp-angle structure area. The fiber direction deviation will lead to a decrease in mechanical properties, and the fibers will also wrinkle due to sudden changes in curvature. This sharp corner effect causes severe stress concentration and reduces the bearing capacity of the sharp corners. Finally, for composite structures with large wall thickness and special-shaped surfaces with sharp corners, the use of traditional rigid pressing plates will lead to difficulties in compaction of the sharp-angle structure area due to the large wall thickness and local overhead, large porosity, and defects such as poly-glue, delamination, and looseness. The high stiffness of the rigid pressing plate will also cause steps to appear in the sharp-angle structure area, causing fiber buckling, difficulty in smoothly transmitting interlayer loads, and a significant decrease in structural bearing efficiency. Summary of the Invention

[0004] In view of the defects in the prior art, the purpose of the present invention is to provide a method for forming and preparing a composite material structural part with a sharp-angled structural profile.

[0005] According to the present invention, a method for forming and preparing a composite material structural part with a sharp-angled structural profile surface includes the following steps:

[0006] Step S1: Using Fibersim software simulation design and laser positioning of the layup system and tooling mold to accurately locate the layup parting line and the layup overlap seam line;

[0007] Step S2: Laying prepreg on the surface of the tooling mold based on the located ply parting line and ply overlap seam line;

[0008] Step S3: Installing a hot glue adsorption pressurizing tool to compact the structural parts on which the prepreg is laid by hot glue adsorption;

[0009] Step S4: using a rubber soft mold to pressurize the sharp corner structure of the profiled surface, and a rigid pressing plate to pressurize the profiled surface and the corner ridges, and then putting the product into an autoclave for heating and curing;

[0010] Step S5: remove the autoclave, dismantle the pressurizing tooling, and demould the structural component.

[0011] Preferably, step S1 includes the following sub-steps:

[0012] Step S1.1: Use Fibersim software to simulate and design the ply parting line and ply lap seam line, and generate a projection program file;

[0013] Step S1.2: Based on the ply overlap seam lines designed by Fibersim software simulation, ply marking lines are set layer by layer on both sides of the end frame of the tooling mold profile;

[0014] Step S1.3: Projecting the program file into the laser positioning laying system;

[0015] Step S1.4: Use a laser positioning layup system to locate the layup parting position and the layup overlap joint position on the tooling mold surface.

[0016] Preferably, the S1 adopts: the circumferential direction of the profiled surface is 0°, the ply is 0° on the profiled surface, the busbar direction at the 1 / 4 position of the profiled surface at both ends is taken as the 0° ply overlap seam benchmark, the fiber does not deform, and the fiber continuity in the sharp-angle structure area is taken as the principle, the 0° ply overlap seam line is simulated and designed using Fibersim software, and the ply is laid continuously and gradually symmetrically in a double-seam overlap laying method.

[0017] Preferably, the S1 adopts: +45° and -45° ply laying, with the principle of accurate fiber laying angle without distortion and fiber continuity in the sharp-angle structure area, and the use of Fibersim software to simulate and design the +45° and -45° ply parting lines; with the corner edge line as the +45° and -45° ply overlap seam reference, with the principle of straight fibers and fiber continuity in the sharp-angle structure area, and the use of Fibersim software to simulate and design the +45° and -45° ply overlap seam lines, and continuous and gradual symmetrical laying in a double-seam overlap laying manner.

[0018] Preferably, the S2 adopts: 0° layer laying on the special-shaped surface, using one 0° prepreg to lay the double-seam overlap surrounding area projected by the laser positioning layup system, double-seam overlap the special-shaped surface to the straight surface area, using the straight surface area as the 0° layup reference in the circumferential direction, laying rectangular prepreg across the corner ridge line and extending to the double-seam overlap position, and filling the remaining area with triangular prepreg.

[0019] Preferably, the S2 adopts: laying layers at +45° and -45° on the special-shaped surface, laying prepreg according to the +45° and -45° ply parting lines, and laying prepreg in the sharp-angle structure area according to the +45° and -45° ply overlap seams combined with the tooling mold ply marking lines.

[0020] Preferably, the S3 adopts: hot glue absorption is performed when the plying is halfway done and after the plying is completed.

[0021] Preferably, in S4, the rubber soft mold is in an annular segmented form, and a flexible pressure plate is placed under the rubber soft mold at the end frame; a rigid pressure plate is used to pressurize the special-shaped surface and the corner edge respectively, and the rigid pressure plate is designed according to the structural surface and laid on the special-shaped surface in multiple sections, wherein the outer side of the rubber soft mold is limited by a strip, and the rubber soft mold located on the special-shaped surface serves as a pressure relief surface and is not constrained by the pressure plate.

[0022] Preferably, there is a gap between the rubber soft mold and the rigid pressure plate on the special-shaped surface, and the gap spacing is a preset value. A flexible pressure plate is arranged below the gap, and the flexible pressure plate is divided into petals in an annular direction at the special-shaped surface. The joints of the flexible pressure plate and the joints of the rubber soft mold are staggered; the flexible pressure plate is pressed by a preset length on both sides of the rubber soft mold and the rigid pressure plate.

[0023] Preferably, the rigid pressing plate on the special-shaped surface is notched at the sharp-angle structure area, and the rigid pressing plate and the flexible pressing plate at the corner edge are notched at the sharp-angle structure area, and the notch spacing is a preset value.

[0024] Compared with the prior art, the present invention has the following beneficial effects:

[0025] 1. The present invention ensures the accuracy of fiber angles, effectively improves fiber distortion, accurately locates the ply datum, improves the forming accuracy of special-shaped composite structural parts, reduces structural deformation, ensures the effective transfer of interlayer loads in structural parts, and eliminates the problem of large-scale deflection of fiber angles due to sudden changes in structural surfaces.

[0026] 2. The present invention can ensure that the fibers are continuous and smooth in the sharp-angle structure area, ensure the flatness of the fibers in the sharp-angle geometric structure of the special-shaped surface, effectively solve the problem of fiber buckling, greatly weaken the stress concentration at the sharp-angle structure, and make the load at the sharp-angle part be smoothly transferred, thereby improving the bearing capacity of the structural parts.

[0027] 3. The present invention utilizes the high adaptability of the rubber soft mold to the structural surface, and applies pressure to the sharp-angle structural area through the rubber soft mold, avoiding uneven pressure caused by local bridging of the rigid pressure plate, and significantly improving the internal quality of the large-wall-thick sharp-angle structural area.

[0028] 4. The present invention adopts a structural mode of pressurizing by the cooperation of the rubber soft mold, the rigid pressing plate and the flexible pressing plate on the special-shaped surface. The rubber soft mold tensions the fiber, the rigid pressing plate evenly presses the surface, and the flexible pressing plate eliminates steps, thereby ensuring that the surface of the structural part is smooth and flat, the fiber is straight, and improving the apparent quality, dimensional accuracy and internal quality of the special-shaped surface and large-walled thick composite material structural parts. BRIEF DESCRIPTION OF THE DRAWINGS

[0029] Other features, objects and advantages of the present invention will become more apparent upon reading the detailed description of non-limiting embodiments with reference to the following drawings:

[0030] Figure 1 Schematic diagram of composite material structure

[0031] Figure 2 This is a schematic diagram of the 0° laying method for special-shaped surfaces of structural parts simulated by Fibersim software;

[0032] Figure 3 Schematic diagram of 0° ply layup on the profiled surface of a structural part;

[0033] Figure 4 This is a schematic diagram of the +45° and -45° laying methods for special-shaped surfaces of structural parts simulated by Fibersim software;

[0034] Figure 5 Schematic diagram of +45° and -45° layup of structural parts with special-shaped surfaces;

[0035] Figure 6 Schematic diagram of the pressurized structure of the special-shaped surface (with sharp corners) of the structural part.

[0036] The figure shows:

[0037] 1-Special-shaped surface;

[0038] 2-pointed corners;

[0039] 3-face;

[0040] 4- Corner ridges;

[0041] 5-large end frame;

[0042] 6- small end frame;

[0043] 7-1 / 4 position of the special-shaped surface;

[0044] 8-0° ply lap joints;

[0045] 9-+45°, -45° ply parting;

[0046] 10-+45°, -45° ply lap joints;

[0047] 11- Rigid pressure plate;

[0048] 12-flexible pressure plate;

[0049] 13-rubber soft mold;

[0050] 14 pressure plate;

[0051] 15-Surrounding strips. DETAILED DESCRIPTION

[0052] The present invention will be described in detail below with reference to specific embodiments. The following examples will help those skilled in the art to further understand the present invention, but are not intended to limit the present invention in any form. It should be noted that, for those skilled in the art, several changes and improvements can be made without departing from the scope of the present invention. These all fall within the scope of protection of the present invention.

[0053] Example 1:

[0054] The present invention provides a method for forming and preparing a composite material structural part with a sharp-angled structural profile, comprising the following steps:

[0055] Step S1: Use Fibersim software simulation design to coordinate with laser positioning of the ply system and tooling mold to accurately locate the ply parting line and ply overlap seam line. Step S1 specifically adopts:

[0056] Step S1.1: Use Fibersim software to simulate and design the ply parting line and ply lap seam line, and generate a projection program file;

[0057] Step S1.2: According to the ply overlap seam lines designed by Fibersim software simulation, ply marking lines are set layer by layer on both sides of the end frame of the tooling mold profile surface (1);

[0058] Step S1.3: Projecting the program file into the laser positioning laying system;

[0059] Step S1.4: Use the laser positioning laying system to locate the laying parting position and the laying overlap seam position on the tooling mold surface. Specifically, the annular direction of the profiled surface (1) is 0°, and the 0° laying is performed on the profiled surface (1). The busbar direction at the 1 / 4 position (7) of the profiled surface at both ends is used as the 0° laying overlap seam (8) benchmark. The fiber does not deform and the fiber in the sharp-angle structure area is continuous. The 0° laying overlap seam (8) line is simulated and designed using Fibersim software, and is laid symmetrically and continuously in a double-seam overlapping laying method. In addition, the +45° and -45° laying are accurately laid with the fiber laying angle. Based on the principle of fiber continuity in the non-twisted and sharp-angled structural area, the +45° and -45° ply parting lines (9) are simulated and designed using Fibersim software; with the corner ridgeline (4) as the benchmark for the +45° and -45° ply overlap seams (10), based on the principle of fiber straightness and fiber continuity in the sharp-angled structural area, the +45° and -45° ply overlap seams (10) are simulated and designed using Fibersim software, and the ply is laid continuously and gradually symmetrically in a double-seam overlap manner;

[0060] Step S2: prepreg is laid on the surface of the tooling mold based on the positioned ply parting line and ply overlap seam line. Specifically, S2 adopts: 0° ply laying on the profiled surface (1), using one 0° prepreg to lay the double-seam overlap surrounding area projected by the laser positioning ply system, double-seam overlap the profiled surface (1) to the straight surface area, taking the straight surface area as the 0° ply datum, and laying rectangular prepreg across the corner ridge line (4) and extending to the double-seam overlap position, and filling the remaining area with triangular prepreg to ensure that the fiber is continuous in the sharp-angle structure area of ​​the profiled surface (1); +45° and -45° ply laying on the profiled surface (1), laying prepreg according to the +45° and -45° ply parting line (9), and laying prepreg in the sharp-angle structure area according to the +45° and -45° ply overlap seam (10) lines combined with the tooling mold ply marking line;

[0061] Step S3: Installing a hot glue adsorption pressurizing tool to compact the structural parts on which the prepreg is laid by hot glue adsorption; wherein, hot glue adsorption is performed when the prepreg is halfway laid and after the prepreg is completed;

[0062] Step S4: using a rubber soft mold (13) to pressurize the sharp corner structure of the profiled surface (1), using a rigid pressing plate (11) to pressurize the profiled surface (1) and the corner ridge (4), and then putting the profiled surface into an autoclave for heating and solidification. S4 adopts: using a rubber soft mold (13) to pressurize the sharp corner structure of the profiled surface (1), wherein the rubber soft mold (13) adopts a circumferential segmented form to eliminate the risk of internal tension offsetting the molding pressure, ensuring that the fibers here are straight, placing a flexible pressing plate (12) below the rubber soft mold (13) at the end frame to ensure that the surface of the end frame is flat; using a rigid pressing plate (11) to pressurize the profiled surface (1) and the corner ridge (4) respectively, and the rigid pressing plate (11) is designed according to the structural profile and is evenly laid on the profiled surface (1) in several sections. The outer side of the rubber soft mold (13) is limited by a surrounding strip (15), and the rubber soft mold (13) located on the special-shaped surface (1) serves as a pressure relief surface and is not constrained by the pressure plate (14), thereby ensuring the surface quality of the sharp-angle structure.

[0063] It should be noted that there is a gap between the rubber soft mold (13) and the rigid pressing plate (11) on the profiled surface (1), and the gap spacing is a preset value. A flexible pressing plate (12) is arranged below the gap, and the flexible pressing plate (12) is circumferentially divided at the profiled surface (1). The joints of the flexible pressing plate (12) and the joints of the rubber soft mold (13) need to be staggered. The flexible pressing plate (12) is pressed by a preset length on both sides of the rubber soft mold (13) and the rigid pressing plate (11) to eliminate the steps caused by the large difference in rigidity between the rigid pressing plate (11) and the rubber soft mold (13). On the profiled surface (1), the rigid pressing plate (11) is notched at the sharp-angle structure area, and at the corner ridge (4), the rigid pressing plate (11) and the flexible pressing plate (12) are notched at the sharp-angle structure area, and the notch spacing is a preset value.

[0064] Step S5: remove the autoclave, dismantle the pressurizing tooling, and demould the structural component.

[0065] Example 2:

[0066] This embodiment is a preferred embodiment of the first embodiment. This embodiment provides a method for forming and preparing a composite material structural part with a sharp-angled structural profile, comprising the following steps:

[0067] Step 1: The composite structural part takes the circumferential direction of the profiled surface 1 as the 0° direction and the generatrix direction as the 90° direction;

[0068] Step 2: Use Fibersim software to locate the 0° overlap seam (8) position and the +45° and -45° overlap seam (10) positions of the sharp corner 2 structure of the special-shaped surface 1, and generate a projection program file and a cloth cutting program file; specifically, according to the 0° overlap seam 8 line and the +45° and -45° overlap seam (10) lines simulated and designed by Fibersim software, set layer-by-layer overlap lines on both sides of the end frame of the special-shaped surface 1 of the tooling mold;

[0069] Step 3: According to the simulation of +45°, -45° ply parting line (9), 0° ply overlap seam (8), +45°, -45° ply overlap seam (10) lines by Fibersim software, set layer-by-layer ply marking lines on both sides of the end frame of the tooling mold profile 1; use Fibersim software in conjunction with the laser positioning ply system to accurately locate the +45°, -45° ply parting line (9), 0° ply overlap seam (8), +45°, -45° ply overlap seam (10) positions on the tooling mold surface;

[0070] Step 4: Input the laser positioning laying system according to the projection program file;

[0071] Step 5: Use a laser positioning laying system to locate the special-shaped surface 1, +45°, -45° laying parting (9) positions and 0° laying overlap joint (8) positions, +45°, -45° laying overlap joint (10) positions on the surface of the tooling mold and lay the prepreg; specifically, the special-shaped surface 1 is laid at 0°, with the busbar direction of the 1 / 4 position (7) of the special-shaped surface at both ends as the 0° laying overlap joint (8) reference, the laying joint overlap is 10mm, and the laying is continuous and gradual symmetrical in a double-seam overlapping laying method. For the +45° and -45° layup of the profiled surface 1, the +45° and -45° layup parting lines (9) are designed based on the fiber laying angle ≤ 3′, and the corner ridgeline (4) is used as the basis for the +45° and -45° layup lap joints (10). The lap joint overlap is 10mm, and the layup is performed in a continuous and gradual symmetrical manner using a double-stitch lap joint. For the 0° layer laying of the profiled surface 1, a sheet of 0° prepreg is used to lay the double-stitch lapped area projected by the laser positioning layup system. The profiled surface 1 is double-stitched to the straight surface 3 area, and the circumferential direction of the straight surface 3 area is used as the 0° layup basis. A rectangular prepreg is laid across the corner ridgeline (4) and extended to the double-stitch lap position. The remaining area is filled with triangular prepreg. The special-shaped surface 1 is laid in layers at +45° and -45°, and the prepreg is laid according to the +45° and -45° ply parting lines (9). The sharp corner 2 structural area is laid in the +45° and -45° ply overlap joint lines (10) combined with the tooling mold ply marking lines.

[0072] Step 6: Install the hot glue adsorption and pressurizing tooling to compact the prepreg-laid structural parts by hot glue adsorption. Specifically, hot glue adsorption is performed when the layers are halfway through and after the layers are completed. The hot glue adsorption temperature is 70-90°C, the pressure is 0.2-0.4 MPa, and the temperature is kept at this temperature for 2-5 hours.

[0073] Step 7: Use the rubber soft mold (13) to pressurize the structure of the sharp corner 2 of the special-shaped surface 1, and the rigid pressing plate (11) to pressurize the special-shaped surface 1 and the corner edge line (4), and put it into the hot autoclave for heating and solidification. Specifically, the rubber soft mold (13) is divided into 2 to 6 sections in an annular direction, and a flexible pressing plate (12) is placed under the rubber soft mold (13) at the end frame. The flexible pressing plate (12) is divided into 2 to 4 sections in an annular direction; the rigid pressing plate (11) is designed according to the structural surface and is laid on the special-shaped surface 1 in an even manner; the rubber soft mold (13) on the special-shaped surface 1 and the rigid pressing plate (11) have There is a gap, the gap value is 5 to 20 mm; a flexible pressing plate (12) is arranged below the gap, the flexible pressing plate (12) is divided into petals in an annular direction, the number of petals is ≥3, and the joints of the flexible pressing plate (12) and the joints of the rubber soft mold (13) are staggered; the flexible pressing plate (12) is pressed 5 to 20 mm on both sides of the rubber soft mold (13) and the rigid pressing plate (11); the rigid pressing plate (11) at the special-shaped surface 1, the rigid pressing plate (11) at the corner edge (4), and the flexible pressing plate (12) are notched in the sharp corner 2 structural area, and the notch spacing is 10 to 30 mm;

[0074] Step 8: Remove the autoclave, dismantle the pressurized tooling, and demould the structural parts.

[0075] Example 3:

[0076] Example 3 is another preferred example of Example 1.

[0077] like Figures 1 to 6 As shown, this embodiment provides a method for forming and manufacturing a composite structural component with a sharp-angled profile. In this embodiment, the composite structural component is a profiled surface with a Z-shaped cross-section. The main body is a three-dimensional skin with a hyperbolic profile. The height direction includes a vertical step, a sharp corner 2 of the profile, an outward-turned large end frame 5, and an inward-turned small end frame 6. The profile is circumferentially oriented at 0°, and the generatrix of the profile is oriented at 90°. The maximum length of the structure is 2725mm, the maximum width is 986mm, the height is 223.7mm, and the wall thickness is 6.25mm.

[0078] In order to realize the molding preparation of composite structural parts with sharp-angled structural profiles, the designed 0° ply was simulated and designed using Fibersim software, and the projection program was generated. Figure 2 As shown in the figure, the design principle is to ensure that the fibers in the sharp-angle structural area are continuous, the fibers do not deform, the 0° ply joints are staggered in order, and the structural deformation is reduced. The 0° ply lap joint (8) line is required to take the busbar direction at the 1 / 4 position (7) of the two end profiled surfaces as the 0° ply lap joint (8) reference center line, and refer to Figure 3The layers are laid symmetrically and continuously from both sides to the reference center in a double-stitched lap manner, with a lap amount of 10 mm. In the design of the tooling mold, according to the lap stitching lines designed by Fibersim software simulation, lap stitching lines are set on both sides of the end frame of the tooling mold special-shaped surface (1) layer by layer to facilitate layer identification. In the actual laying process, the projection program is input into the laser positioning laying system, and the laser positioning laying system is used to accurately locate the 0° lap stitching line (8). A piece of 0° prepreg is used to lay the projected double-stitched surrounding area. The special-shaped surface (1) is double-stitched to the straight surface area. The 0° direction of the straight surface area is used as the laying reference. Rectangular prepreg is used to lay from the straight surface area across the corner edge line (4) to the double-stitched position. The lap positions are staggered in order according to the designed laser projection lines. The remaining area is filled with triangular prepreg to ensure that the fiber is continuous in the sharp-angle structure area of ​​the special-shaped surface (1).

[0079] During the implementation of the present invention, in order to realize the molding preparation of composite material structural parts with sharp-angled structural profiles (1), the designed +45° and -45° plies are simulated and designed using Fibersim software. The +45° and -45° ply parting lines (9) are then generated, and a cutting program and a projection program are generated. Figure 4 As shown in the figure, with the fiber angle deviation ≤ 3′, fiber laying without twisting, and fiber continuity in the sharp-angle structure area as the design principle, several +45° and -45° ply parting lines (9) are designed on the special-shaped surface (1); Fibersim software is used to simulate the design of +45° and -45° ply overlap seams (10), and a projection program is generated. Figure 5 As shown, the design principle is to make the fibers straight, the fibers in the sharp-angle structural area continuous, and the +45° and -45° ply joints staggered in order to reduce structural deformation. The +45° and -45° ply overlap joints (10) are clearly defined with the corner edge line (4) as the +45° and -45° ply overlap joints (10) reference center line. The ply is laid symmetrically from both sides to the reference center in a double-seam overlap manner, and the ply overlap amount is 10mm. In the design of the tooling mold, according to the ply overlap joint lines designed by Fibersim software simulation, ply overlap joint marking lines are set on both sides of the end frame of the tooling mold special-shaped surface (1) layer by layer to facilitate ply identification. During the actual laying process, the cloth cutting program is input into the automatic cloth cutting machine, and the special-shaped surface (1) is cut and laid according to the preset cloth cutting program. The projection program is input into the laser positioning laying system, and the laser positioning laying system is used to accurately locate the +45°, -45° laying parting line (9) and the laying overlap seam line. The prepreg is laid according to the +45°, -45° laying parting line (9), and the prepreg is overlapped and laid according to the +45°, -45° laying overlap seam (10) line combined with the tooling mold laying marking line. The overlap positions are staggered in order according to the designed laser projection line to ensure that the fibers are continuous in the sharp-angle structure area of ​​the special-shaped surface (1).

[0080] The present invention provides a method for forming and preparing a composite material structural part with a sharp-angle structure and a special-shaped surface. The method comprises performing hot glue absorption at a temperature of 70-90°C, a pressure of 0.2-0.4 MPa, and maintaining the heat for 2-5 hours. Figure 6 As shown, the special-shaped surface (1) sharp corner structure and the small end frame 6 are pressurized using a rubber soft mold (13). The rubber soft mold (13) adopts a circumferential segmented form. The outer side of the rubber soft mold (13) is limited by a surrounding strip (15). The other side serves as a pressure relief surface and is not constrained by the rigid pressing plate (11). Through the pressure relief surface, the internal stress of the rubber soft mold (13) is consistent with the air pressure, and the curing pressure is controllable, thereby ensuring the surface quality at the sharp corner. The rigid pressing plate (11) is used to pressurize the special-shaped surface (1) and the corner edge (4) respectively. The rigid pressing plate (11) is designed according to the structural profile and is notched at the sharp corner structure area where the profile suddenly changes. The notch spacing is 10 to 30 mm. There is a gap between the rubber soft mold (13) and the rigid pressing plate (11) on the special-shaped surface (1), and the gap length is 5 to 20 mm. A flexible pressing plate (12) is arranged below the gap. The flexible pressing plate (12) presses 5 to 20 mm on both sides of the rubber soft mold (13) and the rigid pressing plate (11). The flexible pressing plate (12) is circumferentially divided into petals at the special-shaped surface (1). The joints of the flexible pressing plate (12) and the joints of the rubber soft mold (13) need to be staggered to ensure the surface quality, dimensional accuracy and internal quality of the special-shaped surface (1).

[0081] In the description of this application, it should be understood that the terms "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside", "outside", etc., indicating the orientation or position relationship, are based on the orientation or position relationship shown in the accompanying drawings, and are only for the convenience of describing this application and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore cannot be understood as a limitation on this application.

[0082] The above describes specific embodiments of the present invention. It should be understood that the present invention is not limited to the specific embodiments described above, and those skilled in the art may make various changes or modifications within the scope of the claims, which do not affect the essence of the present invention. The embodiments of this application and the features in the embodiments may be combined with each other in any manner unless there is a conflict.

Claims

1. A method for forming and preparing a composite material structural part with a sharp-angled structural profile, characterized in that: The steps include: Step S1: Using Fibersim software simulation design and laser positioning of the layup system and tooling mold to accurately locate the layup parting line and the layup overlap seam line; Step S2: Laying prepreg on the surface of the tooling mold based on the located ply parting line and ply overlap seam line; Step S3: Installing a hot glue adsorption pressurizing tool to compact the structural parts on which the prepreg is laid by hot glue adsorption; Step S4: using a rubber soft mold (13) to pressurize the sharp corner structure of the profiled surface (1), and using a rigid pressing plate (11) to pressurize the profiled surface (1) and the corner ridge (4), and then putting the product into an autoclave for heating and curing; Step S5: remove the autoclave, dismantle the pressurizing tooling, and demould the structural component.

2. The method for forming and preparing a composite material structural part with a sharp-angled structural profile according to claim 1, characterized in that: The step S1 includes the following sub-steps: Step S1.1: Use Fibersim software to simulate and design the ply parting line and ply lap seam line, and generate a projection program file; Step S1.2: According to the ply overlap seam lines designed by Fibersim software simulation, ply marking lines are set layer by layer on both sides of the end frame of the tooling mold profile surface (1); Step S1.3: Projecting the program file into the laser positioning laying system; Step S1.4: Use a laser positioning layup system to locate the layup parting position and the layup overlap joint position on the tooling mold surface.

3. The method for forming and preparing a composite material structural part with a sharp-angled structural profile according to claim 1 or 2, characterized in that: The S1 adopts: the annular direction of the profiled surface (1) is 0°, the profiled surface (1) is laid at 0°, the busbar direction at the 1 / 4 position (7) of the profiled surface at both ends is taken as the 0° ply overlap joint (8) benchmark, the fiber does not deform, and the fiber continuity in the sharp-angle structure area is taken as the principle, the 0° ply overlap joint (8) line is simulated and designed using Fibersim software, and the ply is laid continuously and gradually symmetrically in a double-seam overlap laying method.

4. The method for forming and preparing a composite material structural part with a sharp-angled structural profile according to claim 1 or 2, characterized in that: The S1 adopts: +45° and -45° ply laying, with the principle of accurate fiber laying angle without distortion and fiber continuity in the sharp-angle structure area, using Fibersim software to simulate and design the +45° and -45° ply parting lines (9); using the corner edge line (4) as the +45° and -45° ply overlap joints (10) benchmark, with the principle of straight fibers and fiber continuity in the sharp-angle structure area, using Fibersim software to simulate and design the +45° and -45° ply overlap joints (10), and laying continuously and gradually symmetrically in a double-seam overlap laying method.

5. The method for forming and preparing a composite material structural part with a sharp-angled structural profile according to claim 1, characterized in that: The S2 adopts: laying a 0° layer on the special-shaped surface (1), using a 0° prepreg to lay the double-seam overlap surrounding area projected by the laser positioning laying system, the special-shaped surface (1) is double-seam overlapped to the straight surface area, and the straight surface area is used as the 0° laying reference in the circumferential direction. A rectangular prepreg is laid across the corner ridge line (4) and extended to the double-seam overlap position, and the remaining area is filled with triangular prepreg.

6. The method for forming and preparing a composite material structural part with a sharp-angled structural profile according to claim 1 or 5, characterized in that: The S2 adopts: laying the prepreg at +45° and -45° layers on the special-shaped surface (1), laying the prepreg according to the +45° and -45° ply parting lines (9), and laying the prepreg in the sharp-angle structure area according to the +45° and -45° ply overlap joint lines (10) combined with the tooling mold ply marking lines.

7. The method for forming and preparing a composite material structural part with a sharp-angled structural profile according to claim 1, characterized in that: The S3 adopts the following method: hot glue absorption is performed when the ply is halfway through and after the ply is completed.

8. The method for forming and preparing a composite material structural part with a sharp-angled structural profile according to claim 1, characterized in that: In the S4, the rubber soft mold (13) is in an annular segmented form, and a flexible pressure plate (12) is placed below the rubber soft mold (13) at the end frame; a rigid pressure plate (11) is used to pressurize the special-shaped surface (1) and the corner edge line (4) respectively, and the rigid pressure plate (11) is designed according to the structural surface and is evenly laid on the special-shaped surface (1) in multiple sections, wherein the outer side of the rubber soft mold (13) is limited by a surrounding strip (15), and the rubber soft mold (13) located on the special-shaped surface (1) serves as a pressure relief surface and is not constrained by the pressure plate.

9. The method for forming and preparing a composite material structural part with a sharp-angled structural profile according to claim 1, characterized in that: A gap is provided between the rubber soft mold (13) on the profiled surface (1) and the rigid pressing plate (11), wherein the gap spacing is a preset value, and a flexible pressing plate (12) is arranged below the gap. The flexible pressing plate (12) is annularly divided into petals at the profiled surface (1), and the joints of the flexible pressing plate (12) and the joints of the rubber soft mold (13) are staggered and laid; the flexible pressing plate (12) is pressed by a preset length on both sides of the rubber soft mold (13) and the rigid pressing plate (11).

10. The method for forming and preparing a composite material structural part with a sharp-angled structural profile according to claim 1, characterized in that: The rigid pressing plate (11) on the special-shaped surface (1) is notched in the sharp-angle structure area, and the rigid pressing plate (11) and the flexible pressing plate (12) are notched in the sharp-angle structure area at the corner ridge (4), and the notch spacing is a preset value.

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