Treatment method for improving strength of carbon fiber aeronautical part

Abstract

The invention provides a treatment method for improving the strength of a carbon fiber aeronautical part, and belongs to the technical field of material treatment.The tensile strength of the part reaches 2000-3000 MPa through pretreatment for impurity removal, three-dimensional weaving, accurate control over resin impregnation and hot press molding conditions and the like, the strength is improved by 30%-50% compared with that of an untreated part, and the load bearing capacity of the part is enhanced. In aviation application, the requirements for strength and rigidity of fuselage, wings and other parts are met, safe flight is guaranteed, and due to the low density of carbon fibers, the weight can be reduced, the fuel efficiency and flight performance are improved, and the operation cost is reduced. From the aspect of process improvement, many problems of a traditional process are solved, parameters are accurately controlled, the precision and the quality stability are improved, and the part performance is optimized through nitrogen atmosphere aftertreatment. In conclusion, the treatment method provides an efficient and reliable means for manufacturing of the carbon fiber aeronautical parts, promotes development of the aeronautical technology, and brings wide application prospects and economic benefits.

Description

Technical Field

[0001] The invention belongs to the technical field of material processing, and in particular relates to a processing method for improving the strength of carbon fiber aviation parts. Background Art

[0002] In today's aviation field, the pursuit of lighter, stronger and more durable materials has always been a key goal. With the continuous development of aviation technology, the performance requirements of aircraft are increasing, and higher standards are also put forward for the quality and performance of parts. For example, the fuselage, wings and other structural parts of the aircraft need to have sufficient strength and rigidity to withstand various loads during flight, while also reducing weight as much as possible to improve fuel efficiency and flight performance. Carbon fiber materials have become one of the ideal material choices in the aviation field because of their excellent properties such as high strength, high modulus and low density.

[0003] However, carbon fiber parts that have not been specially treated have some limitations in practical applications. Traditional carbon fiber manufacturing processes may not be able to fully utilize the performance advantages of carbon fiber, and its strength and other mechanical properties may not meet increasingly stringent aviation standards. For example, in some cases, the strength of carbon fiber parts may not be high enough, and they are prone to damage or failure when subjected to greater stress. Moreover, traditional processes may have problems such as residual impurities, unreasonable fiber weaving structure, and insufficient resin impregnation during the manufacturing process, all of which will affect the final performance of carbon fiber parts.

[0004] With the continuous advancement of science and technology, various advanced material processing technologies have gradually emerged. In the field of carbon fiber materials, researchers have been exploring how to improve the strength and other properties of carbon fiber parts by optimizing the processing process. The processing method of this case was produced in this context. It pre-treats the carbon fiber raw materials to remove impurities, adopts a specific three-dimensional weaving method, precisely controls the resin impregnation and hot pressing conditions, and a series of reasonable post-processing steps to solve the problems existing in traditional processes, improve the strength of carbon fiber aviation parts, make them better adapt to the needs of the aviation field, and ensure the safe flight and high-performance operation of aircraft. At the same time, it also provides new technical support for the wider application of carbon fiber materials in the aviation field. Summary of the invention

[0005] The purpose of the present invention is to provide a processing method for improving the strength of carbon fiber aviation parts, aiming to solve the problems in the prior art.

[0006] To achieve the above object, the present invention provides the following technical solutions:

[0007] A method for improving the strength of carbon fiber aviation parts, characterized in that it comprises the following steps:

[0008] Pre-treating the carbon fiber raw materials to remove surface impurities, the pre-treatment adopts ultrasonic cleaning method, and is carried out at 40°C-60°C and 30 minutes-60 minutes;

[0009] The pretreated carbon fibers are woven in a three-dimensional manner to form a carbon fiber fabric with specific mechanical properties.

[0010] The woven carbon fiber fabric is impregnated with resin, the resin used is epoxy resin, the impregnation process is carried out at 2MPa-4MPa and 80℃-100℃, and the impregnation time is 2 hours-3 hours;

[0011] The carbon fiber fabric impregnated with resin is placed in a specific mold and hot-pressed at 150°C-180°C and 5MPa-8MPa for 1 hour-1.5 hours;

[0012] The carbon fiber aviation parts after hot pressing are post-processed, and the post-processing includes keeping warm at 120℃-140℃ for 2 hours-3 hours, and then naturally cooling to room temperature.

[0013] As a preferred solution of the present invention, the specifications of the carbon fiber raw material are that the fiber diameter is in the range of 5 μm-8 μm and the length is in the range of 5 mm-10 mm.

[0014] As a preferred solution of the present invention, during the weaving process, the warp and weft densities of the fibers are 10 to 15 fibers / cm in the warp direction and 8 to 12 fibers / cm in the weft direction.

[0015] As a preferred solution of the present invention, the shape and size of the mold are designed and manufactured according to the specific requirements of the required carbon fiber aviation parts. For example, the wing part mold should have an aerodynamic curved surface shape, and the dimensional deviation is controlled within ±0.1mm.

[0016] As a preferred solution of the present invention, during the hot pressing process, the heating rate is controlled at 5°C / min-8°C / min.

[0017] As a preferred solution of the present invention, the heat preservation environment during the post-treatment process is a nitrogen atmosphere, and the purity of the nitrogen is above 99.9%.

[0018] As a preferred solution of the present invention, the part has a tensile strength of 2000MPa-3000MPa, which is 30%-50% higher than that of carbon fiber parts not treated by the treatment method.

[0019] As a preferred solution of the present invention, a device for pretreating carbon fiber raw materials is provided with equipment such as an ultrasonic generator and a cleaning tank, and can accurately control the temperature in the range of 40°C to 60°C and the cleaning time in the range of 30 minutes to 60 minutes;

[0020] Equipment for carbon fiber weaving, which can realize three-dimensional weaving, and has the function and structural characteristics of accurately controlling the fiber warp and weft density to 10-15 strands / cm in the warp direction and 8-12 strands / cm in the weft direction;

[0021] Equipment for resin impregnation, which includes a pressure control system that can be accurately controlled at 2MPa-4MPa, a temperature control system that can be accurately controlled at 80℃-100℃, and a timing device that can accurately control the impregnation time to 2 hours-3 hours;

[0022] The equipment used for hot pressing molding is equipped with a precise temperature control system that can control the temperature at 150°C-180°C, a pressure control system that can control the pressure at 5MPa-8MPa, and a timing device that can accurately control the hot pressing molding time to 1 hour-1.5 hours;

[0023] The equipment used for post-processing has a precise temperature control system, which can control the temperature at 120°C-140°C, a heat preservation timing device which can accurately control the heat preservation time to 2 hours-3 hours, and a function of providing a nitrogen atmosphere with a purity of more than 99.9%.

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

[0025] First of all, from the perspective of improving material performance, by pre-treating the carbon fiber raw materials to remove surface impurities, it can ensure that the combination of fiber and resin in the subsequent process is tighter and purer. The three-dimensional weaving method is adopted and the fiber warp and weft density is precisely controlled to make the carbon fiber fabric have specific mechanical properties, which enhances the overall strength and stability of the parts. The precisely controlled resin impregnation and hot pressing molding conditions, such as temperature, pressure and time, ensure that the resin is fully impregnated into the carbon fiber fabric to form a good composite structure, and improve the tensile strength of the parts to 2000MPa-3000MPa, which is 30%-50% higher than the untreated parts, greatly enhancing its ability to withstand various loads in the aviation field. Secondly, in terms of aviation applications, the carbon fiber aviation parts manufactured by this treatment method can meet the high requirements of strength and stiffness of structural components such as aircraft fuselages and wings, ensuring the safe flight of the aircraft. At the same time, due to The low density of carbon fiber materials can reduce weight while improving the strength of parts, which helps to improve fuel efficiency and flight performance and reduce operating costs. Furthermore, from the perspective of process improvement, the processing method of this case solves the problems of impurity residue, unreasonable fiber weaving structure, insufficient resin impregnation, etc. in traditional processes. By precisely controlling the process parameters of each link, such as the temperature and time of ultrasonic cleaning, the dimensional deviation control of the mold, etc., the production accuracy and quality stability are improved, and the poor performance of parts caused by process defects is reduced. Moreover, the post-processing insulation environment of the nitrogen atmosphere ensures the performance optimization of the parts under specific conditions, further improving the quality and reliability of the parts. In short, the processing method of this case provides an efficient and reliable technical means for the manufacture of carbon fiber aviation parts, which is not only conducive to promoting technological development in the aviation field, but also can bring broader application prospects and economic benefits to related industries. DETAILED DESCRIPTION

[0026] The technical solutions in the embodiments of the present invention will be described clearly and completely below in combination with the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0027] Example 1

[0028] The present invention provides the following technical solutions:

[0029] A method for improving the strength of carbon fiber aviation parts, characterized in that it comprises the following steps:

[0030] Pre-treating the carbon fiber raw materials to remove surface impurities, the pre-treatment adopts ultrasonic cleaning method, and is carried out at 40°C-60°C and 30 minutes-60 minutes;

[0031] The pretreated carbon fibers are woven in a three-dimensional manner to form a carbon fiber fabric with specific mechanical properties.

[0032] The woven carbon fiber fabric is impregnated with resin, the resin used is epoxy resin, the impregnation process is carried out at 2MPa-4MPa and 80℃-100℃, and the impregnation time is 2 hours-3 hours;

[0033] The carbon fiber fabric impregnated with resin is placed in a specific mold and hot-pressed at 150°C-180°C and 5MPa-8MPa for 1 hour-1.5 hours;

[0034] The carbon fiber aviation parts after hot pressing are post-processed, and the post-processing includes keeping warm at 120℃-140℃ for 2 hours-3 hours, and then naturally cooling to room temperature.

[0035] In a specific embodiment of the present invention, in the pretreatment step, an ultrasonic cleaning method is used to remove impurities on the surface of the carbon fiber raw material under the conditions of 40°C-60°C and 30 minutes-60 minutes. This approach can first effectively remove impurities and make the carbon fiber surface cleaner. In the subsequent process, the pure carbon fiber surface is conducive to better bonding with the resin. If there are impurities on the surface, it may affect the effect of resin impregnation, resulting in loose bonding, which in turn affects the overall strength of the parts. By precisely controlling the temperature and time, it can be ensured that the impurities are removed more thoroughly. For example, within the temperature range of 40°C-60°C, the cavitation effect of ultrasound can fully play a role, and the cleaning effect will not be poor due to too low temperature, nor will the performance of carbon fiber be damaged due to too high temperature. The cleaning time of 30 minutes to 60 minutes can ensure that there is enough time for ultrasound to fully clean the surface of the carbon fiber, so that there is no impurity residue. In this way, when entering the subsequent weaving and impregnation links, the carbon fiber can be better combined with other materials, laying the foundation for the manufacture of high-strength aviation parts.

[0036] In the carbon fiber weaving step, a three-dimensional weaving method is used to form a carbon fiber fabric with specific mechanical properties. Three-dimensional weaving can make carbon fiber have good mechanical properties in different directions. Compared with traditional plane weaving, it can enhance the overall strength and stability of parts. In practical applications, aviation parts are subjected to forces from different directions during flight, such as the impact of airflow, vibration of the fuselage, etc. Three-dimensional woven carbon fiber fabrics can better withstand these complex forces. Moreover, by precisely controlling the weaving structure, the warp and weft density of 10 / cm-15 / cm in the warp direction and 8 / cm-12 / cm in the weft direction can make the structure of the fabric more compact and reasonable. The higher fiber density in the warp direction can provide better strength support in the main force direction, and the appropriate fiber density in the weft direction can ensure a certain stability in the lateral direction. This reasonable weaving structure makes the parts less likely to deform and crack during use, greatly improves their service life and safety, and meets the requirements of the aviation field for high performance of parts.

[0037] In the resin impregnation step, the impregnation is carried out at 2MPa-4MPa and 80℃-100℃, and the impregnation time is 2 hours-3 hours. Accurately controlled pressure, temperature and impregnation time are crucial to improving the performance of parts. Under a pressure of 2MPa-4MPa, epoxy resin can better penetrate into the internal pores of carbon fiber fabric. Too low pressure may lead to insufficient resin impregnation, while too high pressure may damage the structure of carbon fiber fabric. The temperature range of 80℃-100℃ can make the epoxy resin have suitable fluidity and accelerate its diffusion in the fiber. Too low temperature has poor resin fluidity and poor impregnation effect; too high temperature may cause chemical changes in the resin and affect its performance. The impregnation time of 2 hours to 3 hours ensures that the resin has enough time to fully impregnate into the carbon fiber fabric to form a good composite structure. This composite structure can give full play to the respective advantages of carbon fiber and epoxy resin. Carbon fiber provides high strength and high modulus, and epoxy resin plays a role in bonding and transferring stress, thereby significantly improving the mechanical properties such as tensile strength of the parts, making it more suitable for bearing various complex loads in the aviation field.

[0038] In the hot pressing step, hot pressing is carried out at 150℃-180℃ and 5MPa-8MPa, and the hot pressing time is 1 hour-1.5 hours. This process further consolidates the structure and performance of the parts. At a temperature of 150℃-180℃, the epoxy resin can be further cured and better bonded to the carbon fiber fabric. At the same time, the pressure of 5MPa-8MPa can make the structure of the parts tighter and eliminate possible pores and defects inside. The hot pressing time is controlled at 1 hour-1.5 hours, which can not only ensure sufficient curing and molding process, but also avoid energy waste and low production efficiency due to too long time. Through hot pressing, the parts initially have the required shape and strength, providing a reliable foundation for subsequent applications.

[0039] In the post-processing step, the temperature is kept at 120℃-140℃ for 2 hours to 3 hours, and then naturally cooled to room temperature. Post-processing plays a key role in optimizing part performance and improving quality reliability. During the insulation process at 120℃-140℃, the residual stress inside the part can be further eliminated and its dimensional stability can be improved. The insulation time setting of 2 hours to 3 hours can ensure that the residual stress is fully released, making the performance of the part more stable. Moreover, the natural cooling method in the post-processing process can avoid the thermal stress caused by rapid cooling and further improve the quality of the parts. In the aviation field, the dimensional stability and performance stability of parts are crucial to the safe flight of aircraft. Through such post-processing, carbon fiber aviation parts can better adapt to the complex flight environment and improve their service life and reliability.

[0040] Specifically, the specifications of the carbon fiber raw material are that the fiber diameter is in the range of 5 μm-8 μm and the length is in the range of 5 mm-10 mm.

[0041] In this embodiment: First, the fiber diameter is within the range of 5μm-8μm, which has an important influence on the performance of carbon fiber. The finer fiber diameter makes the carbon fiber have a larger specific surface area. In the subsequent pretreatment process, the larger specific surface area means that surface impurities are easier to be removed. For example, during ultrasonic cleaning, the ultrasonic wave can act more fully on the fiber surface to ensure the thorough removal of impurities. At the same time, during the resin impregnation process, the larger specific surface area is conducive to better bonding of epoxy resin with carbon fiber. Epoxy resin can more fully infiltrate the fiber surface to form a stronger composite structure, thereby improving the overall strength of the part. In addition, the finer fiber diameter also has advantages in the weaving process. It can make the weaving more compact and fine, which is conducive to achieving precisely controlled fiber warp and weft density, such as 10 / cm-15 / cm in the warp direction and 8 / cm-12 / cm in the weft direction. Such a tightly woven structure can further enhance the mechanical properties of the part and improve its strength and stability. Secondly, the fiber length is also of great significance in the range of 5mm-10mm. The appropriate fiber length can ensure good connection and interaction between fibers during the weaving process. If the fiber length is too short, the fiber may break or the connection may be loose during weaving, affecting the overall structure and performance of the fabric. The fiber length of 5mm-10mm can provide sufficient length to form a stable weaving structure during the weaving process. In three-dimensional weaving, fibers of this length can be better interwoven in different directions to enhance the integrity of the fabric. At the same time, in the subsequent resin impregnation and hot pressing molding process, fibers of appropriate length can form good support and reinforcement inside the parts. When subjected to external forces, longer fibers can better transfer stress and improve the mechanical properties of parts such as tensile strength. Moreover, in practical applications in the aviation field, this specification of carbon fiber raw materials can better adapt to the manufacturing needs of aviation parts of different shapes and sizes. For example, when manufacturing parts with complex curved shapes such as wings, carbon fibers of appropriate length and diameter can better fit the mold to ensure the manufacturing accuracy and quality of the parts.

[0042] Specifically, during the weaving process, the warp and weft densities of the fibers are 10 to 15 fibers / cm in the warp direction and 8 to 12 fibers / cm in the weft direction.

[0043] In this embodiment: From the perspective of mechanical properties, a higher fiber density in the radial direction (10 roots / cm-15 roots / cm) can provide stronger support in the main force direction. In the actual use of aviation parts, parts are often subjected to a variety of complex forces, among which the forces in certain specific directions are more concentrated. A higher fiber density in the warp direction can better withstand these forces and improve the strength of the parts in this direction. For example, when the aircraft is in flight, the carbon fiber aviation parts of the wing part need to withstand greater aerodynamic forces and vibrations in the warp direction. A higher warp fiber density can ensure that the parts have enough strength in this direction to resist these external forces and reduce the possibility of deformation or damage caused by excessive force. At the same time, a fiber density of 8 roots / cm-12 roots / cm in the weft direction plays an important role in ensuring the lateral stability of the parts. When aviation parts are subjected to forces in different directions, lateral stability is crucial to the integrity of the overall structure. An appropriate weft fiber density can give the parts a certain rigidity and toughness in the lateral direction to prevent excessive distortion or deformation when subjected to lateral forces. This reasonable combination of fiber density in the warp and weft directions enables carbon fiber aviation parts to have good mechanical properties in all directions and adapt to the complex aviation operating environment.

[0044] From the perspective of structural stability, the precisely controlled fiber warp and weft density can make the structure of carbon fiber fabrics more compact and regular. During the weaving process, the fibers are arranged more orderly according to the specified warp and weft density. This orderly arrangement helps to improve the overall stability of the fabric and reduce internal pores and defects. When resin impregnation is performed, the tight fabric structure can ensure that the epoxy resin is more fully filled into the gaps between the fibers to form a good composite structure. During the hot pressing process, this tight structure is also conducive to better molding of parts under the action of pressure and temperature, reducing the problems of uneven molding or internal stress concentration caused by loose structure. Moreover, in the field of aviation, the structural stability of parts is directly related to the safe flight of aircraft. Tight and reasonable fiber warp and weft density can improve the reliability and service life of parts and reduce safety hazards caused by structural problems.

[0045] From the perspective of manufacturing process, clearly defined fiber warp and weft densities provide accurate parameter standards for the production process. In actual production, workers can perform precise operations and controls according to these standards. For example, on carbon fiber weaving equipment, the fiber warp and weft densities of 10 / cm-15 / cm in the warp direction and 8 / cm-12 / cm in the weft direction can be achieved by adjusting relevant parameters. This precise control helps to improve production consistency and quality stability. At the same time, in subsequent process links, such as resin impregnation and hot pressing molding, the known fiber warp and weft density is also conducive to more accurate calculation of the required resin dosage and process parameters, optimization of the production process, and improvement of production efficiency. In addition, for the manufacture of different types of carbon fiber aviation parts, this standardized fiber warp and weft density can be appropriately adjusted and optimized according to specific needs to meet diverse production requirements, providing strong support for the large-scale production and quality control of carbon fiber aviation parts.

[0046] Specifically, the shape and size of the mold are designed and manufactured according to the specific requirements of the required carbon fiber aviation parts. For example, the wing part mold should have an aerodynamic curved surface shape, and the dimensional deviation should be controlled within ±0.1 mm.

[0047] In this embodiment: From the perspective of optimizing the performance of parts, the shape of the mold is designed and manufactured according to the specific requirements of carbon fiber aviation parts, so that the produced parts can better meet their functional requirements in the aviation field. Taking wing parts as an example, a mold with an aerodynamic curved surface shape can ensure that the manufactured wing parts can reduce air resistance during flight and improve the flight efficiency and performance of the aircraft. The aerodynamic shape can make the air flow more smoothly over the wing surface, reduce the force of air on the wing, and reduce energy loss. At the same time, for other aviation parts, such as fuselage parts, the appropriate mold shape can also ensure that it is well matched with other parts during installation and use, and improve the stability and functionality of the overall structure. The high-precision requirement of dimensional deviation control within ±0.1mm is crucial to the performance of parts. In the aviation field, the dimensional accuracy of parts directly affects the assembly accuracy and performance of aircraft. Such a small dimensional deviation can ensure a close fit between parts and reduce problems such as gaps, looseness or stress concentration caused by inaccurate dimensions. For example, in the assembly process of the aircraft fuselage, parts with high dimensional accuracy can ensure the sealing and structural strength of the fuselage and improve the overall safety and reliability of the aircraft.

[0048] From the perspective of production technology, designing and manufacturing molds according to specific requirements provides higher flexibility and adaptability for the production of carbon fiber aviation parts. Different types of aviation parts have different shape and size requirements. Through customized mold design and manufacturing, diversified production needs can be met. For example, for the production of parts for new models of aircraft, the corresponding molds can be quickly manufactured according to their unique design requirements, improving production efficiency and response speed. Moreover, the high-precision manufacturing requirements with dimensional deviations controlled within ±0.1mm have put forward higher challenges to the mold manufacturing process and promoted the continuous advancement of mold manufacturing technology. In the mold manufacturing process, advanced processing technology and precise measurement methods are needed to ensure dimensional accuracy. This not only improves the quality of the mold itself, but also provides support for the improvement of the production process level of the entire carbon fiber aviation parts. At the same time, precise mold size is also conducive to more accurate part molding in processes such as hot pressing and improving the quality consistency of parts.

[0049] From the perspective of cost and benefit, although customized mold design and manufacturing may require high initial investment, the long-term benefits are significant. High-quality carbon fiber aviation parts produced by precisely designed and manufactured molds can reduce rework and repair costs caused by part quality problems. For example, if the mold size deviation is large, the produced parts may not meet the assembly requirements and require secondary processing or replacement, which will increase production costs. High-precision molds can ensure that the parts are qualified in one molding, improve production efficiency, and reduce overall production costs. At the same time, high-performance parts can improve the reliability and service life of aircraft, reduce aircraft maintenance and operating costs, and bring greater economic benefits to users such as airlines. In addition, high-quality parts also help to enhance the market competitiveness of enterprises and win more opportunities for the development of enterprises in the aviation field.

[0050] Specifically, during the hot pressing process, the heating rate is controlled at 5°C / min-8°C / min.

[0051] In this embodiment: From the perspective of material performance protection, a suitable heating rate can avoid adverse effects on carbon fiber and epoxy resin due to rapid temperature changes during hot pressing. If the heating rate is too fast, carbon fiber and epoxy resin may experience thermal stress concentration due to a sharp rise in temperature. The generation of thermal stress may cause damage to the internal structure of the material, such as the breakage of carbon fiber or the decrease in the bonding strength between epoxy resin and carbon fiber, thereby affecting the final performance of the part. Controlling the heating rate within the range of 5°C / min-8°C / min can allow carbon fiber and epoxy resin enough time to adapt to temperature changes and reduce the generation of thermal stress. At this heating rate, the temperature gradient inside the material is relatively gentle, and each part can be heated more evenly, which is conducive to maintaining the structural integrity and performance stability of the material.

[0052] From the perspective of the hot pressing process effect, a heating rate of 5℃ / min-8℃ / min helps the epoxy resin reach a good curing state within a suitable time. The curing process of epoxy resin is a complex chemical reaction process, and its curing degree and performance are closely related to temperature and time. In the hot pressing process, a suitable heating rate can give the epoxy resin enough time to fully cure after reaching the curing temperature. If the heating rate is too slow, it may lead to low production efficiency and extend the production cycle; if the heating rate is too fast, the epoxy resin may not be fully cured, affecting its bonding performance and mechanical strength. Controlling the heating rate at 5℃ / min-8℃ / min can improve production efficiency while ensuring that the epoxy resin is fully cured, so that the parts can obtain good mechanical properties and dimensional stability during the hot pressing process.

[0053] From the perspective of part quality consistency, precise control of the heating rate is crucial for the mass production of carbon fiber aviation parts. In large-scale production, if the heating rate is inconsistent, different parts may have performance differences during the hot pressing process. For example, parts with too fast a heating rate may have internal defects or unstable performance, while parts with too slow a heating rate may have low production efficiency and increase costs. By controlling the heating rate within the range of 5℃ / min-8℃ / min, it can be ensured that the mass-produced parts have high quality consistency and meet the strict requirements of the aviation field for part quality stability. Whether it is manufacturing aircraft fuselage parts or wing parts, parts with consistent quality can better guarantee the overall performance and safety of the aircraft.

[0054] Specifically, the heat preservation environment during the post-treatment process is a nitrogen atmosphere, and the purity of the nitrogen is above 99.9%.

[0055] In this embodiment: nitrogen is an inert gas, which can effectively prevent carbon fiber parts from being oxidized during the heat preservation process. At a higher temperature of 120℃-140℃, if it is in an ordinary air environment, the carbon fiber and resin in the parts may react with the oxygen in the air, resulting in a decrease in material performance, while the nitrogen atmosphere avoids this situation and ensures the chemical stability of the parts. Secondly, high-purity nitrogen can create a pure environment to prevent impurity gases from mixing in and adversely affecting the performance of the parts. For example, if there is moisture or other impurity gases, tiny pores may be formed inside the parts or the curing effect of the resin may be affected, thereby reducing the strength and quality of the parts. Nitrogen with a purity of more than 99.9% ensures a high degree of purity in the post-processing environment, which is conducive to further optimization and stabilization of the internal structure of the parts. Furthermore, heat preservation in such a nitrogen atmosphere can promote further curing and cross-linking of the resin in the carbon fiber fabric. Make the bond between the resin and the carbon fiber tighter and firmer, thereby improving the overall mechanical properties of the parts. This close bond can better transmit stress, making the parts more reliable when bearing various loads in aviation flight, and reducing the risk of part damage caused by stress concentration. At the same time, the stable nitrogen atmosphere also helps to maintain temperature uniformity during post-processing, so that all parts of the parts can receive uniform heat treatment, avoiding local performance differences, further improving the quality consistency and reliability of the parts, and providing a strong guarantee for the safe application of carbon fiber aviation parts in the aviation field.

[0056] Specifically, the part has a tensile strength of 2000MPa-3000MPa, which is 30%-50% higher than that of a carbon fiber part that has not been treated by the treatment method.

[0057] In this embodiment: From the perspective of safety, for the aviation field, the aircraft will be subjected to various complex stresses during flight, including aerodynamics, impact force during takeoff and landing, etc. Carbon fiber aviation parts with higher strength can better withstand these stresses, reduce the risk of damage or failure of parts during flight, and greatly improve the flight safety of the aircraft. For example, in key parts such as wings, high-strength parts can ensure the integrity of the wing structure, and even in the event of bad weather or complex flight conditions, they can maintain stable performance and ensure the safe navigation of the aircraft. From the perspective of economic benefits, the improvement of strength means that the amount of material used can be reduced to a certain extent when designing and manufacturing aircraft. Because stronger materials can bear loads more effectively, there is no need to increase thickness or use more supporting structures to meet strength requirements like lower-strength materials. This not only reduces material costs, but also reduces the overall weight of the aircraft, further improves fuel efficiency, and reduces operating costs. Taking a medium-sized passenger aircraft as an example, the use of high-strength carbon fiber parts can save a lot of fuel costs every year. In addition, the increase in strength also extends the service life of carbon fiber parts. In the aviation field, the replacement and maintenance costs of parts are high, while higher-strength parts can withstand longer use and harsher working environments, reducing the need for frequent replacement of parts, reducing maintenance costs, and improving the overall operating efficiency of aircraft, bringing tangible economic benefits to airlines and other related companies. At the same time, this high-strength carbon fiber part also provides strong support for technological innovation and development in the aviation field, and promotes the development of the aviation industry towards lighter, stronger and more efficient directions.

[0058] Specifically, the equipment used for pretreatment of carbon fiber raw materials is equipped with equipment such as an ultrasonic generator and a cleaning tank, and can accurately control the temperature in the range of 40°C to 60°C and the cleaning time in the range of 30 minutes to 60 minutes;

[0059] Equipment for carbon fiber weaving, which can realize three-dimensional weaving, and has the function and structural characteristics of accurately controlling the fiber warp and weft density to 10-15 strands / cm in the warp direction and 8-12 strands / cm in the weft direction;

[0060] Equipment for resin impregnation, which includes a pressure control system that can be accurately controlled at 2MPa-4MPa, a temperature control system that can be accurately controlled at 80℃-100℃, and a timing device that can accurately control the impregnation time to 2 hours-3 hours;

[0061] The equipment used for hot pressing molding is equipped with a precise temperature control system that can control the temperature at 150°C-180°C, a pressure control system that can control the pressure at 5MPa-8MPa, and a timing device that can accurately control the hot pressing molding time to 1 hour-1.5 hours;

[0062] The equipment used for post-processing has a precise temperature control system, which can control the temperature at 120°C-140°C, a heat preservation timing device which can accurately control the heat preservation time to 2 hours-3 hours, and a function of providing a nitrogen atmosphere with a purity of more than 99.9%.

[0063] In this embodiment: For the carbon fiber raw material pretreatment equipment, it has equipment such as an ultrasonic generator and a cleaning tank and can accurately control the temperature in the range of 40°C-60°C and the cleaning time in the range of 30 minutes-60 minutes. This makes it possible to efficiently remove impurities on the surface of carbon fiber raw materials in actual production life. Accurate temperature control ensures that the effect of ultrasonic cleaning is in the best state. In the temperature range of 40°C-60°C, the activity of the cleaning agent can be better exerted, which can fully dissolve and remove impurities without adversely affecting the performance of carbon fiber. The cleaning time range of 30 minutes-60 minutes ensures the thoroughness of cleaning, can completely remove surface impurities, and provide high-quality pure carbon fiber for subsequent processes. In this way, the consistency and quality stability of the product can be improved in actual production, and the performance differences of parts caused by residual impurities can be avoided. Secondly, the carbon fiber weaving equipment can realize three-dimensional weaving, and has the function and structural characteristics of accurately controlling the fiber warp and weft density to be 10 / cm-15 / cm in the warp direction and 8 / cm-12 / cm in the weft direction. This precise weaving control is of great significance in practical applications. The three-dimensional weaving method makes the carbon fiber fabric have better mechanical properties, and its strength and stability in all directions are enhanced. The precisely controlled fiber warp and weft density further optimizes this mechanical property. The different density ranges in the warp and weft directions can be adjusted according to the specific stress conditions of the parts, so that the parts can better withstand stress in different directions during use. For example, in the aircraft fuselage structure, the stress conditions of different parts are different. The parts made by this precisely woven carbon fiber fabric can better adapt to these stress characteristics and improve the overall strength and reliability of the fuselage. Furthermore, the equipment used for resin impregnation includes a pressure control system that can be accurately controlled at 2MPa-4MPa, a temperature control system that can be accurately controlled at 80℃-100℃, and a timing device that accurately controls the impregnation time of 2 hours-3 hours. In actual production, precise pressure control ensures that the epoxy resin can fully penetrate into the internal pores of the carbon fiber fabric, so that the resin and the fiber are fully combined. Temperature control in the range of 80℃-100℃ can promote the fluidity and chemical reactivity of the resin and improve the impregnation effect. The 2-3 hour impregnation time ensures that the resin has enough time to fully impregnate and form a uniform composite structure with good performance. This is crucial to improving the overall strength and quality of the parts, so that the produced carbon fiber aviation parts have better mechanical properties and reliability. In addition, the equipment used for hot pressing is equipped with a precise temperature control system that can control the temperature at 150℃-180℃, a pressure control system that can control the pressure at 5MPa-8MPa, and a timing device that accurately controls the hot pressing time to 1 hour-1.5 hours. In actual production life, such precise hot pressing conditions can enable parts to obtain the best physical and chemical properties during the molding process.The appropriate temperature and pressure range can promote the further curing of the resin, enhance the bonding force between the resin and the carbon fiber, and make the parts have a denser structure, improving their strength and stiffness. The precisely controlled hot pressing molding time ensures the stable molding quality of the parts and avoids performance defects caused by too long or too short time. For example, in the aviation field, such high-quality molded parts can better adapt to the complex stress environment of the aircraft during flight and improve the overall performance and safety of the aircraft. Finally, the equipment used for post-processing has a precise temperature control system that can control the temperature at 120℃-140℃, a heat preservation timing device that can accurately control the heat preservation time to 2 hours-3 hours, and a nitrogen atmosphere with a purity of more than 99.9%. In practical applications, precise temperature and time control can further optimize the performance of the parts during post-processing. The heat treatment at this stage can release the stress inside the parts and make the organizational structure more stable. The provision of nitrogen atmosphere, as mentioned above, can prevent the oxidation of parts, ensure the chemical stability of parts, and improve the quality and reliability of parts. This complete set of professional equipment provides a strong guarantee for the high-quality production of carbon fiber aviation parts, making the entire production process more precise and efficient, meeting the strict requirements of the aviation field for high performance of parts and promoting the development of the aviation industry.

[0064] The working principle and use process of the present invention:

[0065] First, in the pretreatment stage of carbon fiber raw materials, the carbon fiber raw materials are placed in a device equipped with an ultrasonic generator and a cleaning tank. The temperature is precisely controlled at 40℃-60℃, the cleaning time is 30 minutes-60 minutes, and the surface impurities are removed by ultrasonic cleaning. This step can provide pure carbon fiber for subsequent processes and ensure better combination of fiber and resin. Next, the carbon fiber weaving link is entered. Equipment capable of three-dimensional weaving is used to precisely control the fiber warp and weft density to 10 / cm-15 / cm in the warp direction and 8 / cm-12 / cm in the weft direction. This specific weaving method enables the carbon fiber fabric to form a structure with good mechanical properties, laying the foundation for the strength and stability of the parts. Then comes the resin impregnation process. In the equipment including a pressure control system and a temperature control system, the pressure is precisely controlled at 2MPa-4MPa, the temperature is 80℃-100℃, and the impregnation time is 2 hours-3 hours, so that the epoxy resin is fully impregnated into the carbon fiber fabric to form an excellent composite structure. After that, the impregnation The resin-treated carbon fiber fabric is placed in a specific mold designed and manufactured according to the specific requirements of the required carbon fiber aviation parts. In the hot pressing molding equipment, the temperature is precisely controlled at 150℃-180℃, the pressure is 5MPa-8MPa, the heating rate is controlled at 5℃ / min-8℃ / min, and the hot pressing molding time is 1 hour-1.5 hours, so that the parts are initially formed and have a certain strength. Finally, in the post-processing stage, in a device with a precise temperature control system and a nitrogen atmosphere with a purity of more than 99.9%, the temperature is precisely controlled at 120℃-140℃, the insulation time is 2 hours-3 hours, and then naturally cooled to room temperature. This process further optimizes the performance of the parts and improves the quality and reliability. In actual production and life, such an operation process can effectively improve the strength and other properties of carbon fiber aviation parts, meet the high standards for parts in the aviation field, and ensure the safe flight and high-performance operation of aircraft. At the same time, it also helps to reduce operating costs and promote the development of related industries, which has important practical application value.

[0066] Finally, it should be noted that the above description is only a preferred embodiment of the present invention and is not intended to limit the present invention. Although the present invention has been described in detail with reference to the aforementioned embodiments, those skilled in the art can still modify the technical solutions described in the aforementioned embodiments or replace some of the technical features therein by equivalents. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present invention shall be included in the protection scope of the present invention.

Claims

1. A method for improving the strength of carbon fiber aviation parts, characterized in that: The following steps are involved: Pre-treating the carbon fiber raw materials to remove surface impurities, the pre-treatment adopts ultrasonic cleaning method, and is carried out at 40°C-60°C and 30 minutes-60 minutes; The pretreated carbon fibers are woven in a three-dimensional manner to form a carbon fiber fabric with specific mechanical properties. The woven carbon fiber fabric is impregnated with resin, the resin used is epoxy resin, the impregnation process is carried out at 2MPa-4MPa and 80℃-100℃, and the impregnation time is 2 hours-3 hours; The carbon fiber fabric impregnated with resin is placed in a specific mold and hot-pressed at 150°C-180°C and 5MPa-8MPa for 1 hour-1.5 hours; The carbon fiber aviation parts after hot pressing are post-processed, and the post-processing includes keeping warm at 120℃-140℃ for 2 hours-3 hours, and then naturally cooling to room temperature.

2. A method for improving the strength of carbon fiber aviation parts according to claim 1, characterized in that: The specifications of the carbon fiber raw material are that the fiber diameter is in the range of 5 μm-8 μm and the length is in the range of 5 mm-10 mm.

3. A method for improving the strength of carbon fiber aviation parts according to claim 2, characterized in that: During the weaving process, the warp and weft density of the fibers is 10 to 15 fibers / cm in the warp direction and 8 to 12 fibers / cm in the weft direction.

4. A method for improving the strength of carbon fiber aviation parts according to claim 3, characterized in that: The shape and size of the mold are designed and manufactured according to the specific requirements of the required carbon fiber aviation parts. For example, the wing part mold should have an aerodynamic curved surface shape, and the size deviation is controlled within ±0.1mm.

5. A method for improving the strength of carbon fiber aviation parts according to claim 4, characterized in that: During the hot pressing process, the heating rate is controlled at 5°C / min-8°C / min.

6. A method for improving the strength of carbon fiber aviation parts according to claim 5, characterized in that: The heat preservation environment during the post-processing process is a nitrogen atmosphere with a nitrogen purity of more than 99.9%.

7. A method for improving the strength of carbon fiber aviation parts according to claim 6, characterized in that: The part has a tensile strength of 2000MPa-3000MPa, which is 30%-50% higher than that of carbon fiber parts that have not been treated by the treatment method.

8. A device for implementing the method for improving the strength of carbon fiber aviation parts according to any one of claims 1 to 7, characterized in that: include: Equipment for pretreatment of carbon fiber raw materials, which is equipped with ultrasonic generators, cleaning tanks and other equipment, and can accurately control the temperature in the range of 40°C-60°C and the cleaning time in the range of 30 minutes-60 minutes; Equipment for carbon fiber weaving, which can realize three-dimensional weaving, and has the function and structural characteristics of accurately controlling the fiber warp and weft density to 10-15 strands / cm in the warp direction and 8-12 strands / cm in the weft direction; Equipment for resin impregnation, which includes a pressure control system that can be accurately controlled at 2MPa-4MPa, a temperature control system that can be accurately controlled at 80℃-100℃, and a timing device that can accurately control the impregnation time to 2 hours-3 hours; The equipment used for hot pressing molding is equipped with a precise temperature control system that can control the temperature at 150°C-180°C, a pressure control system that can control the pressure at 5MPa-8MPa, and a timing device that can accurately control the hot pressing molding time to 1 hour-1.5 hours; The equipment used for post-processing has a precise temperature control system, which can control the temperature at 120°C-140°C, a heat preservation timing device which can accurately control the heat preservation time to 2 hours-3 hours, and a function of providing a nitrogen atmosphere with a purity of more than 99.9%.