Mold and method for integrally manufacturing a thermoplastic hat stringer panel using automated fiber placement

Abstract

The application provides a mold design and method for integrally manufacturing a thermoplastic hat stringer wallboard by using an automatic fiber placement process. The mold comprises a base, a hat stringer core mold and a self-heating system, the base is provided with a stringer profile groove and a thickness limiting positioning groove, a thickness limiting positioning block is arranged in the thickness limiting positioning groove, and the self-heating system comprises a control unit, a temperature measuring sensor and a plurality of heating rods. The method comprises hat stringer preparation, mold pretreatment, automatic fiber placement forming and cooling demolding. The mold and method for integrally manufacturing a thermoplastic hat stringer wallboard by using an automatic fiber placement process can effectively coordinate the fiber placement process parameters, realize online in-situ manufacturing, the mold can provide effective profile support and simple demolding for the formed structure, and the integrative, high-precision and high-efficiency manufacturing of the thermoplastic hat stringer wallboard is realized, the mechanical properties and the qualified rate of the hat stringer wallboard are improved, the production cost is reduced, and the application requirements of aviation are met.

Description

Technical Field

[0001] This invention relates to the field of thermoplastic composite material molding technology, specifically to a mold and method for integrally manufacturing thermoplastic cap-shaped stringer panels using an automated fiber placement process. Background Technology

[0002] The composite material fuselage panels of aircraft widely adopt the hat-shaped stringer structure design, and its manufacturing process directly determines the structural performance, production cycle and manufacturing cost of the whole aircraft.

[0003] Currently, cap-shaped stringer panels are mainly manufactured using thermosetting composite materials in autoclave processes. The main manufacturing technologies fall into two categories: one is the "automatic fiber placement + integral autoclave curing" process. While this process achieves precise manufacturing, thermosetting resins generally have long curing cycles, and autoclave equipment is expensive and energy-intensive. Furthermore, once cured, thermosetting resins cannot be reprocessed, making it difficult to repair local defects and resulting in a high scrap rate of parts during service life, thus leading to high manufacturing costs. For this approach, numerous patented technologies have emerged regarding process control and mold design. Among them, patent CN113771389B, "Hollow Core Mold and Processing Method Suitable for Manufacturing Cap-Shaped Stringer Panel Components," mentions using airbags as supports for the cap-shaped stringer structure during manufacturing to achieve structural forming. Patent CN112477190A, "An Integrated Manufacturing Process for Hat-Shaped Truss Composite Material Panels" (now withdrawn), mentions a method of "laying flat sheet material + compacting with multiple irregularly shaped rollers" to achieve efficient molding of the hat-shaped truss, followed by the use of foam or rubber as support for the hat-shaped truss structure to achieve structural molding. Another method is to use a "separate molding + secondary assembly" process, that is, to first manufacture the hat-shaped truss and skin separately, and then connect the structure by gluing or mechanical assembly. This not only increases the manufacturing cost, but also easily leads to stress concentration at the connection points, reducing the overall structural reliability of the panel.

[0004] Thermoplastic composites, with their reversible "melting upon heating and solidifying upon cooling" properties, as well as excellent mechanical properties, repairability, and recyclability, are gradually replacing thermosetting composites as the preferred materials for aerospace applications. Automated fiber placement, as an advanced composite molding technology, boasts advantages such as high placement accuracy, high efficiency, and the ability to achieve complex structures. Combining it with thermoplastic composites has become a development trend in aerospace manufacturing.

[0005] However, aerospace-grade thermoplastic resins such as polyetheretherketone (PEEK) and polyaryletherketone (PAEK) have higher viscosity and melting points compared to thermosetting resins. Therefore, the molding process requires high temperature and high pressure. If the first type of technical route mentioned above is adopted, ordinary rubber and airbags as supports are difficult to adapt to the high temperature and high pressure process conditions. Currently, existing overseas application cases of manufacturing thermoplastic composite cap-shaped stringer panels using automated fiber placement processes basically follow the manufacturing approach of the second type of thermosetting composite panel mentioned above. That is, the skin and stringer are first manufactured and solidified in an autoclave (or oven) using automated fiber placement (or molding), and the structure is then connected by welding or mechanical assembly.

[0006] In the existing technology, when using the automatic wire placement process to manufacture thermoplastic cap-shaped stringer panels, the following key problems still exist: First, it is difficult to achieve coordination between the wire placement process parameters. The heating temperature, placement speed, and compaction pressure of the automatic wire placement process are not precisely matched with the cooling rate of the mold, resulting in severe deformation of the panel and large fluctuations in mechanical properties. It is difficult to achieve online in-situ consolidation and molding, and post-processing is generally required after the wire placement is completed. Second, it is difficult to achieve effective support of the mold for the cap-shaped stringer structure and to achieve simple demolding. After the thermoplastic composite material cools and solidifies, it is easy to adhere to the mold surface. Forced demolding can easily damage the surface of the panel. Summary of the Invention

[0007] This invention addresses the problems of difficult demolding and coordination of process parameters. Its purpose is to provide a mold and method for integrally manufacturing thermoplastic cap-shaped stringer panels using an automated wire-layout process. This method achieves effective coordination of wire-layout process parameters, enabling online in-situ manufacturing. Simultaneously, the mold provides effective surface support for the formed structure and facilitates easy demolding. This results in integrated, high-precision, and efficient manufacturing of thermoplastic cap-shaped stringer panels, improving their mechanical properties and yield rate, reducing production costs, and meeting the needs of aerospace applications.

[0008] This invention provides a mold for integrally manufacturing thermoplastic cap-shaped stringer panels using an automated wire-laying process. The mold comprises: a base with a stringer-shaped groove on its top surface and thickness-limiting positioning grooves at both ends of the groove; a cap-shaped stringer core mold disposed within the stringer-shaped groove; and a self-heating system. The thickness-limiting positioning groove on the base contains a thickness-limiting positioning block, and a heating rod channel is located inside the base portion near the thickness-limiting positioning groove area. The cap-shaped stringer core mold consists of an upper part made of steel and a lower part made of rigid foam. The self-heating system includes a heating rod, a temperature sensor, and a control unit. The heating rod is embedded in the heating rod channel, and the control unit is electrically connected to the heating rod and the temperature sensor.

[0009] The mold for integrally manufacturing thermoplastic cap-shaped stringer panels using an automatic fiber-laying process provided by the present invention may also have the following feature: wherein the rigid foam material is one of PMI, PU or PVC.

[0010] The mold for integrally manufacturing thermoplastic cap-shaped stringer panels using an automatic wire-laying process provided by the present invention may also have the following feature: wherein the thickness limiting positioning block is made of A3 steel or INVAR steel and has a thickness of not less than 1mm.

[0011] The mold for integrally manufacturing thermoplastic cap-shaped stringer wall panels using an automatic wire-laying process provided by the present invention may also have the following features: the self-heating system includes multiple heating rods, the heating rods are electrically heated, the temperature adjustment range is 0-200℃, the spacing between adjacent heating rods is 5-10cm, and the heating power of a single heating rod is not less than 3KW / m.

[0012] The present invention also provides a method for integrally manufacturing thermoplastic cap-shaped stringer panels using an automated wire-laying process, characterized by the following features:

[0013] S1, Hat-shaped stringer preparation: Prepare continuous carbon fiber reinforced thermoplastic prepreg. According to the pre-set layup structure of the hat-shaped stringer, the corresponding prepregs are preheated by infrared in sequence, transferred to the molding press for heating and pressing, mold opening and cooling, and demolding to obtain hat-shaped stringer parts of corresponding size and shape.

[0014] S2, Mold pretreatment: Check the installation accuracy of each part of the mold, clean the surface of the cap-shaped stringer core mold, wrap the surface with isolation material, and preheat the mold to the characteristic temperature of thermoplastic resin molding through the self-heating system.

[0015] S3, Automatic filament placement forming: The hat-shaped stringer part obtained in step S1 is placed into the stringer-shaped groove of the mold, and then the hat-shaped stringer core mold is placed in the hat-shaped recess of the hat-shaped stringer part. The thickness limiting positioning block is placed in the thickness limiting positioning groove to position the relative position between the automatic filament placement machine and the mold. The prepreg filament bundles are laid layer by layer on the surface of the hat-shaped stringer part through the filament placement head of the automatic filament placement machine. During the filament placement process, the filament placement temperature, filament placement speed and compaction pressure are controlled according to the preset filament placement program.

[0016] S4, Cooling and Demolding: After the filament laying is completed, turn off the self-heating system to cool the mold. When demolding, break the lower part of the core mold of the rigid foam material, pull out the upper part of the core mold, and finally lift the processed part as a whole to separate the part from the mold and remove the thickness limiting positioning block.

[0017] The method for integrally manufacturing thermoplastic cap-shaped stringer panels using an automated wire-laying process provided by the present invention may also have the following feature: in step S1, the prepreg is CF / PEEK or CF / PAEK prepreg.

[0018] The method for integrally manufacturing thermoplastic cap-shaped stringer panels using an automatic wire-laying process provided by the present invention may also have the following feature: in step S2, the insulating material is a PI film with a thickness not exceeding 0.05 mm.

[0019] The method for integrally manufacturing thermoplastic cap-shaped stringer panels using an automatic wire-laying process provided by the present invention may also have the following feature: in step S2, the heating temperature of the mold is controlled at 120-200℃.

[0020] The method for integrally manufacturing thermoplastic hat-shaped stringer panels using an automatic wire-laying process provided by the present invention may also have the following features: in step S3, when the hat-shaped stringer core mold is placed, the upper outer surface of the core mold is flush with the edge strip of the hat-shaped stringer part, and the lower part of the core mold is in close contact with the top of the hat and the two sides of the waist of the hat of the stringer part.

[0021] The method for integrally manufacturing thermoplastic cap-shaped stringer panels using an automatic filament laying process provided by the present invention may also have the following features: In step 3, when the prepreg filaments are laid layer by layer on the surface of the cap-shaped stringer part, the layup angle is 0°, ±45°, or 90°. During the filament laying process, the filament laying speed is 0.1-0.25 m / s, the filament laying temperature is controlled at 340-380°C, and local compaction is performed every 2-3 layers, with a compaction pressure of 1000-2000 N.

[0022] Compared with the prior art, the functions and effects of the present invention include:

[0023] This invention relates to a mold for integrally manufacturing thermoplastic cap-shaped stringer panels using an automated wire-layout process. This allows for the overall molding of the thermoplastic stringer panel. The cap-shaped stringer core mold employs a combined structure of "upper steel material + lower rigid foam material." Since both steel and rigid foam are rigid materials, and the upper part of the core mold is made of steel, it is heat-resistant and thus provides support for the cap-shaped stringer. Furthermore, the rigid foam material can be mechanically destroyed and removed after manufacturing, leaving only the upper part of the steel core mold as the supporting structure. This reduces the contact area between the steel and rigid foam, making demolding easier. The mold uses a self-heating system to ensure a uniform temperature field during wire-layout, solving the defects of warping, deformation, and performance gradient fluctuations caused by uneven temperature fields in traditional molds. The design of the thickness-limiting positioning block allows for adaptation to the manufacturing of cap-shaped stringer panels with different configurations by replacing the block.

[0024] The present invention discloses a method for integrally manufacturing thermoplastic cap-shaped stringer panels using an automated wire-laying process. By achieving precise and coordinated control of wire-laying temperature, wire-laying pressure, mold temperature, and wire-laying speed during the automated wire-laying process, the online in-situ curing and molding of the panel skin is ensured, realizing the integral manufacturing of the panel. Simultaneously, the elimination of autoclave curing shortens the molding cycle, reduces production costs, and is compatible with various high-performance thermoplastic composite materials, exhibiting strong flexibility and adaptability to large-scale mass production needs. Attached Figure Description

[0025] Figure 1 This is a schematic diagram of the overall structure of the mold in an embodiment of the present invention;

[0026] Figure 2 This is a partially enlarged view of the cross-section of the mandrel core mold in the embodiment of the present invention;

[0027] Figure 3 This is a flowchart of a method for integrally manufacturing thermoplastic cap-shaped stringer panels using an automated wire-laying process, as described in an embodiment of the present invention.

[0028] Figure 4 This is a metallographic structure diagram of region A of the part manufactured in an embodiment of the present invention;

[0029] Figure 5 This is a metallographic structure diagram of region B of the part manufactured in an embodiment of the present invention;

[0030] Figure 6 These are photographs of actual parts manufactured in the embodiments of the present invention.

[0031] In the diagram: 100. Mold; 1. Base; 11. Thickness limiting positioning block; 2. Hat-shaped stringer core mold; 21. Upper part of core mold; 22. Lower part of core mold; 31. Heating rod; 4. Hat-shaped stringer parts; 5. Wire laying head. Detailed Implementation

[0032] In the description of this application, it should be noted that, unless otherwise expressly specified and limited, the terms "installation," "connection," and "linking" should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral connection; they can refer to a mechanical connection, an electrical connection, or a connection that allows communication between them; they can refer to a direct connection or an indirect connection through an intermediate medium; they can refer to the internal communication between two components or the interaction between two components. Those skilled in the art can understand the specific meaning of the above terms in this application according to the specific circumstances.

[0033] To make the technical means, creative features, objectives and effects of the present invention easy to understand, the following embodiments, in conjunction with the accompanying drawings, specifically illustrate the mold and method for integrally manufacturing thermoplastic cap-shaped stringer panels using an automatic wire-laying process.

[0034] Example:

[0035] Figure 1 This is a schematic diagram of the overall structure of the mold in an embodiment of the present invention.

[0036] like Figure 1 As shown: This embodiment provides a mold 100 for integrally manufacturing thermoplastic cap-shaped stringer panels using an automatic wire laying process, including: a base 1, a cap-shaped stringer core mold 2, and a self-heating system.

[0037] Figure 2 This is a partially enlarged view of the cross-section of the hat-shaped stringer core mold in an embodiment of the present invention.

[0038] Specifically, such as Figure 2 As shown: The top surface of the base 1 has a long stringer-shaped groove with a hat-shaped cross-section for placing the hat-shaped long stringer core mold 2. Thickness-limiting positioning grooves are provided at both ends of the hat-shaped rim of the long stringer-shaped groove for placing thickness-limiting positioning blocks 11. The thickness-limiting positioning blocks 11 are made of A3 steel or INVAR steel with a thickness of not less than 1mm. A heating rod 31 channel is provided inside the part of the base 1 near the thickness-limiting positioning groove area.

[0039] The hat-shaped stringer core mold 2 consists of a steel upper core mold 21 and a rigid foam core mold lower core mold 22. The upper core mold 21 is made of A3 steel, while the rigid foam core mold lower core mold 22 can be made of PMI, PU, ​​or PVC, etc.

[0040] The self-heating system includes a control unit, a temperature sensor, and multiple heating rods 31. The heating rods 31 are resistance rods, evenly embedded in the heating rod channels of the base 1. The heating method is electric heating, with a temperature adjustment range of 0-200℃. Adjacent heating rods 31 are spaced 5-10cm apart, and the heating power of a single heating rod 31 is not less than 3KW / m. The control unit is electrically connected to the temperature sensor and each heating rod 31. Based on the temperature signal fed back by the temperature sensor, it automatically adjusts the heating power of the heating rods 31 to achieve closed-loop temperature control of the mold 100, ensuring that the temperature of the mold 100 matches the material properties of the thermoplastic resin during the fiber laying process.

[0041] Figure 3 This is a flowchart of a method for integrally manufacturing thermoplastic cap-shaped stringer panels using an automated wire-laying process, as described in an embodiment of the present invention.

[0042] like Figure 3As shown: This embodiment also provides a method for integrally manufacturing thermoplastic cap-shaped stringer panels using an automated wire-laying process, including the following steps S1-S4.

[0043] S1, Hat-shaped stringer preparation: Prepare continuous carbon fiber reinforced thermoplastic prepreg. According to the preset layup structure of the hat-shaped stringer, the corresponding prepregs are preheated by infrared in sequence, transferred to the molding press for heating and pressing, mold opening and cooling, and demolding to obtain hat-shaped stringer parts 4 of corresponding size and shape.

[0044] Specifically, in this embodiment, the continuous carbon fiber reinforced thermoplastic prepreg uses CF / PAEK prepreg, specifically VICTREX's AE250 prepreg sheet with a layup of (0 / 45 / 90 / -45)s. It is cut into 800mm×15mm pieces using an automatic cutting machine, and then subjected to infrared preheating (340℃±10℃, 3min±0.5min), transferred to a molding press for heating and pressing (340℃±10℃, 0.4MPa±0.04MPa, 5min±0.5min), mold opening and cooling, and demolding to obtain a hat-shaped stringer part 4 with corresponding dimensions and profile (outer R8mm, inner R6mm).

[0045] S2, Mold 100 pretreatment: Check the installation accuracy of each component of mold 100, clean the surface of the upper part 21 of the core mold and the thickness limiting positioning block 11, wrap the surface with isolation material, and preheat the mold 100 to the characteristic temperature of thermoplastic resin molding through the self-heating system.

[0046] Specifically, before checking the installation accuracy of each component of mold 100, the dimensions of each component are checked: the radius of the R-angle of the hat-shaped stringer core mold 2 (upper part 21 and lower part 22 of the core mold) is 8mm, and the size of the thickness limiting positioning block 11 is 800mm×10mm×1mm (thickness). Then, the installation accuracy of each component of mold 100 is checked to ensure that the hat-shaped stringer core mold 2 can be accurately installed and positioned, and that the self-heating system can operate normally. In this embodiment, the release coating on the surface of the upper part 21 of the core mold and the thickness limiting positioning block 11 is cleaned to remove impurities and oil stains. The isolation material is a polyimide film, i.e., PI film, with a thickness not exceeding 0.05mm, specifically the Thermalimide RCBS high-temperature isolation film from AIRTECH. The thickness limiting positioning block 11 and the upper part 21 of the core mold are wrapped with this isolation film, and the isolation film is fixed with AIRKAP pressure-sensitive tape. The mold 100 is heated to 160℃±10℃ by the self-heating system.

[0047] S3, Automatic filament placement: Place the hat-shaped stringer part 4 obtained in step S1 into the stringer-shaped groove of the mold 100, and then place the hat-shaped stringer core mold 2 into the hat-shaped recess of the hat-shaped stringer part 4. The outer surface of the upper part 21 of the core mold is flush with the edge strip of the hat-shaped stringer part 4, and the lower part 22 of the core mold is close to the top of the hat and the two sides of the hat waist of the stringer part. Place the thickness limiting positioning block 11 in the thickness limiting positioning groove to position the relative position between the automatic filament placement machine and the mold 100. The prepreg filament bundles are laid layer by layer on the surface of the hat-shaped stringer part 4 through the filament placement head 5 of the automatic filament placement machine. The layup angles are 0°, ±45°, and 90°. During the filament placement process, the filament placement temperature, filament placement speed, and compaction pressure are controlled according to the preset filament placement program.

[0048] Specifically, during the fiber placement process, VICTREX AE250 prepreg narrow strips (1 / 4 inch wide) were used. The prepreg fiber bundle was melted in situ using laser heating via the placement head 5 of the automatic fiber placement machine, with the temperature controlled above the melting point of the prepreg resin. Simultaneously, a pressure of 1800N±180N was applied through the placement head 5 to ensure close adhesion between the molten prepreg and the surface of the cap-shaped stringer part 4. The fiber placement temperature was controlled at 340±10℃, and the fiber placement speed was set to 0.2m / s for skin placement. The layup structure was (0 / 45 / 90 / -45) s. During the process, the heating and pressurizing operation was repeated every three layers, with the parameters remaining constant.

[0049] S4, Cooling and Demolding: After the filament laying is completed, turn off the self-heating system and cool the mold 100. When demolding, break the lower part 22 of the rigid foam material core mold, pull out the upper part 21 of the core mold, and finally lift the processed part as a whole to separate the part from the mold 100 and remove the thickness limiting positioning block 11.

[0050] Specifically, the cooling mold 100 uses air cooling to slowly cool the wall panel. When the temperature of the mold 100 drops below 60°C, the lower part 22 of the core mold is manually broken, and the demolding is completed by continuing the operation.

[0051] This embodiment verifies the feasibility and effectiveness of the mold 100 and manufacturing method of the present invention. The product performance of the mold 100 meets the technical requirements of the corresponding field and has broad engineering application prospects.

[0052] The following performance tests were performed on the carbon fiber reinforced thermoplastic composite parts prepared using the molds and methods described in the above embodiments:

[0053] (1) Tensile strength (MPa): Tested according to ASTM F3039;

[0054] (2) Interlaminar shear strength (MPa): Tested according to ASTM D2344;

[0055] (3) Cross-section metallography: Internal quality was observed using a metallographic microscope (BX53MRF-S).

[0056] The results of the mechanical property tests are shown in Table 1 below:

[0057] Table 1

[0058] Tensile properties 6 1559 3.0 Interlaminar shear properties 6 107.1 2.8

[0059] As can be seen from the table above, the parts manufactured using the mold and method in this embodiment exhibit good tensile and interlaminar shear properties.

[0060] The 0° tensile strength of existing T300 grade carbon fiber thermosetting prepregs used in civil aircraft does not exceed 1448 MPa, and the interlaminar shear strength does not exceed 95 MPa, both of which do not exceed the test data in Table 1. Therefore, the manufacturing level achievable using the mold and method in this embodiment meets the requirements for composite material manufacturing structures in civil aircraft.

[0061] The results of the metallographic test are as follows Figure 4 and Figure 5 As shown in the photos, the actual parts are as follows: Figure 6 As stated. From Figure 4 and Figure 5 It can be concluded that the parts manufactured by this patent have virtually no internal pores and a porosity close to 0, which meets the requirement in the civil aircraft acceptance conditions that the maximum porosity of composite material structures should not exceed 0.5%. Therefore, it can be concluded that this patented technology is applicable to the field of civil aviation composite material structure manufacturing.

[0062] The functions and effects of the embodiments include:

[0063] The mold 100 in this embodiment, which uses an automated wire-laying process to manufacture thermoplastic cap-shaped stringer panels as a whole, can achieve the overall molding of the thermoplastic stringer panels. The cap-shaped stringer core mold 2 adopts a combined structure of "upper part of steel material + lower part of rigid foam material", which can both support the cap-shaped stringer structure and facilitate demolding. The mold 100 uses a self-heating system to ensure a uniform temperature field during the wire-laying process, which solves the defects such as warping deformation and performance gradient fluctuation caused by the uneven temperature field of traditional molds 100. Through the design of the thickness limiting positioning block 11, different configurations of cap-shaped stringer panels can be adapted for manufacturing by replacing the thickness limiting positioning block 11.

[0064] The method for integrally manufacturing thermoplastic cap-shaped stringer panels using an automated fiber placement process in this embodiment achieves precise and coordinated control of fiber placement temperature, fiber placement pressure, mold temperature, and fiber placement speed during the automated fiber placement process. This ensures online in-situ curing and molding of the panel skin, enabling integral manufacturing of the panel. Simultaneously, the elimination of autoclave curing shortens the molding cycle, reduces production costs, and allows for compatibility with various high-performance thermoplastic composite materials, offering strong flexibility and adaptability to large-scale mass production needs.

[0065] Those skilled in the art should understand that this invention is not limited to the above embodiments. The embodiments and descriptions in the specification are merely illustrative of the principles of the invention. Various changes and modifications can be made to this invention without departing from its spirit and scope, and all such changes and modifications fall within the scope of the invention as claimed. The scope of protection of this invention is defined by the appended claims and their equivalents.

Claims

1. A mold for integrally manufacturing thermoplastic cap-shaped stringer panels using an automated wire-laying process, characterized in that, include: The base has a stringer-shaped groove on its top surface and thickness-limiting positioning grooves located at both ends of the stringer-shaped groove. A hat-shaped stringer core mold is disposed within the groove of the stringer surface; and Self-heating system; Specifically, a thickness-limiting positioning block is provided within the thickness-limiting positioning groove on the base, and a heating rod channel is provided inside the base portion near the thickness-limiting positioning groove area. The hat-shaped stringer core mold consists of a steel core mold upper part and a rigid foam core mold lower part. The self-heating system includes a heating rod, a temperature sensor, and a control unit. The heating rod is embedded in the heating rod channel, and the control unit is electrically connected to the heating rod and the temperature sensor.

2. The mold for integrally manufacturing thermoplastic cap-shaped stringer panels using an automated wire-laying process as described in claim 1, characterized in that: in, The rigid foam material is one of PMI, PU or PVC.

3. The mold for integrally manufacturing thermoplastic cap-shaped stringer panels using an automated wire-laying process as described in claim 1, characterized in that: in, The thickness-limiting positioning block is made of A3 steel or INVAR steel, with a thickness of not less than 1mm.

4. The mold for integrally manufacturing thermoplastic cap-shaped stringer panels using an automated wire-laying process as described in claim 1, characterized in that: in, The self-heating system includes multiple heating rods, which are electrically heated with a temperature range of 0-200℃. The adjacent heating rods are spaced 5-10cm apart, and the heating power of a single heating rod is not less than 3KW / m.

5. A method for integrally manufacturing thermoplastic cap-shaped stringer panels using an automated wire-laying process, comprising using the mold described in any one of claims 1-4, characterized in that, include: S1, preparation of hat-shaped stringer: prepare continuous carbon fiber reinforced thermoplastic prepreg, according to the preset layup structure of the hat-shaped stringer, the corresponding prepreg is preheated by infrared in sequence, transferred to the molding press for heating and pressing, mold opening and cooling, and demolding to obtain hat-shaped stringer parts of corresponding size and shape. S2, Mold pretreatment: Check the installation accuracy of each component of the mold, clean the surface of the hat-shaped stringer core mold, wrap the surface with isolation material, and preheat the mold to the characteristic temperature of thermoplastic resin molding through the self-heating system; S3, Automatic filament placement: The cap-shaped stringer part obtained in step S1 is placed into the stringer-shaped groove of the mold. Then, the cap-shaped stringer core mold is placed in the cap-shaped recess of the cap-shaped stringer part. The thickness limiting positioning block is placed in the thickness limiting positioning groove to position the relative position between the automatic filament placement machine and the mold. The filament bundles of the prepreg are laid layer by layer on the surface of the cap-shaped stringer part through the filament placement head of the automatic filament placement machine. During the filament placement process, the filament placement temperature, filament placement speed and compaction pressure are controlled according to the preset filament placement program. S4, Cooling and Demolding: After the filament laying is completed, the self-heating system is turned off to cool the mold. When demolding, the lower part of the core mold of the rigid foam material is destroyed, and the upper part of the core mold is pulled out. Finally, the processed part is lifted up as a whole to separate the part from the mold and remove the thickness limiting positioning block.

6. The method for integrally manufacturing thermoplastic cap-shaped stringer panels using an automated wire-laying process according to claim 5, characterized in that: In step S1, the prepreg is CF / PEEK or CF / PAEK prepreg.

7. The method for integrally manufacturing thermoplastic cap-shaped stringer panels using an automated wire-laying process according to claim 5, characterized in that: In step S2, the insulating material is a PI film with a thickness not exceeding 0.05 mm.

8. The method for integrally manufacturing thermoplastic cap-shaped stringer panels using an automated wire-laying process according to claim 5, characterized in that: In step S2, the heating temperature of the mold is controlled at 120-200℃.

9. The method for integrally manufacturing thermoplastic cap-shaped stringer panels using an automated wire-laying process according to claim 5, characterized in that: In step S3, when the cap-shaped stringer core mold is placed, the upper outer surface of the core mold is flush with the edge strip of the cap-shaped stringer part, and the lower part of the core mold is in close contact with the top of the cap and the two sides of the waist of the cap-shaped stringer part.

10. The method for integrally manufacturing thermoplastic cap-shaped stringer panels using an automated wire-laying process according to claim 5, characterized in that: In step 3, when the prepreg filaments are laid layer by layer on the surface of the hat-shaped stringer, the layup angles are 0°, ±45°, and 90°. During the layup process, the layup speed is 0.1-0.25 m / s, the layup temperature is controlled at 340-380°C, and local compaction is performed every 2-3 layers with a compaction pressure of 1000-2000 N.

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