64 results about "Aeronautical industry" patented technology

The invention relates to the technical field of three-dimensional woven composite material detection, solves the technical problem that defects of carbon fiber yarns and woven preforms cannot be detected in real time in a three-dimensional weaving production line in a traditional method, and particularly relates to a defect detection method for an aero-engine fan blade preform. Comprising the steps of collecting an original image in real time and preprocessing the original image; performing feature extraction on the preprocessed image to obtain a multi-scale feature map containing global features and local features; and constructing a defect perception decoupling detection module for decomposing a defect detection task into two sub-tasks of position modeling and size estimation, and optimizing the initial candidate box to obtain a defect result set. According to the invention, real-time, high-precision and automatic detection of defects of carbon fiber yarns and woven preforms can be realized, the quality control capability of an aero-engine fan blade preform production line is remarkably improved, and the strict production standard of the aviation industry is met.

The invention discloses an aviation casting aluminum alloy bar internal defect ultrasonic detection method and a sensor assembly, and the method comprises the following steps: adjusting water distance through three water immersion focusing probes to realize focusing of different depth areas, which are respectively a near surface depth of 2mm, a 1 / 4 bar radius depth and a 3 / 4 bar radius depth, and carrying out ultrasonic C scanning imaging; the probe forms water coupling with the surface of a workpiece through a water jacket, so that high-precision layered focusing detection is ensured. The collected ultrasonic signals are subjected to noise reduction processing through a wavelet decomposition technology, a threshold function is improved, wavelet coefficients are screened, the signals are reconstructed, and a C scanning image is reconstructed. The method has the advantages that the detection sensitivity and accuracy of the internal defects of the aluminum alloy bar are improved, the method is particularly suitable for quality detection of the aluminum alloy bar in the aviation industry, and the method has the characteristics of full coverage, accuracy and high efficiency.

The invention discloses a preparation method of a titanium alloy cast ingot containing a copper element, and relates to the technical field of smelting. And selecting a titanium-copper intermediate alloy and / or a titanium-copper-aluminum intermediate alloy according to the raw material proportioning value of the copper-containing titanium alloy cast ingot. And uniformly mixing the sponge titanium and the intermediate alloy to prepare the consumable electrode. And the consumable electrode is prepared into a copper-containing titanium alloy cast ingot through vacuum consumable arc melting. On one hand, a titanium-copper intermediate alloy and / or a titanium-copper-aluminum intermediate alloy is selected as an adding mode of a copper element. And on the other hand, inert gas is introduced into the water-cooled copper crucible for vacuum consumable arc melting, so that the reduction of a molten pool is promoted. Under the combined action of the two aspects, the uniformity of the Cu element in the cast ingot is improved, the problem that the titanium alloy cast ingot has the beta spot defect in the hot working process due to copper element segregation is solved, and the application range of the titanium alloy material in the petrochemical industry, the aviation industry, the nuclear power generation industry, the hydrogen storage industry and the military industry is widened.

The invention discloses a preparation method of a Ti60 high-temperature titanium alloy cast ingot, and relates to the technical field of titanium alloys. According to the target component range of the Ti60 high-temperature titanium alloy cast ingot, the matching range of all alloy elements in the Ti60 high-temperature titanium alloy cast ingot is determined as follows: 5.8-7.2% of Al and 3.2-4.3% of Sn; zr: 2.7 to 3.8%; 0.3% to 0.9% of Mo; 0.3 to 0.5 percent of Si; 0.3% to 0.6% of Nb; 0.8 to 1.4 percent of Ta; and C: 0.05 to 0.07%. By determining the reasonable matching range of all alloy elements, all the elements of the Ti60 titanium alloy are synchronously melted and evenly distributed within the limited smelting time, element composition segregation of the Ti60 titanium alloy is restrained, and the composition uniformity of all the elements of the Ti60 titanium alloy is improved. Besides, the high energy density and good refining capacity of the electron beam cold bed furnace are utilized firstly, then the components and the structure are further adjusted through the vacuum consumable electrode arc furnace, and the component uniformity and purity of the Ti60 high-temperature titanium alloy cast ingot are effectively improved; and the application of the titanium alloy material in the fields of petrochemical industry, aviation industry, nuclear power generation, hydrogen storage industry, military industry and the like is expanded.

The invention relates to a particle-reinforced Poly Ether Ether Ketone (PEEK) matrix composite material which exhibits superior wear resistance and mechanical qualities, and its method of preparation. This composite material offers superior mechanical and tribological qualities, as well as an extended service life, in comparison to PEEK-based composites utilized in the contemporary medical and aviation industries.

The invention discloses a preparation method of a Ti65 titanium alloy cast ingot, and relates to the technical field of titanium alloys. According to the target component range of the Ti65 titanium alloy cast ingot, the proportion range of each alloy element is determined as follows: 6.0-7.2% of Al; 3.2 to 4.3 percent of Sn; 3.2% to 4.8% of Zr; 0.3% to 0.9% of Mo; 0.25 to 0.45 percent of Si; 0.3% to 0.6% of Nb; 0.7 to 2.3 percent of Ta; 0.4 to 1.1 percent of W; and 0.03 to 0.07 percent of C. The raw materials to be smelted are subjected to primary smelting through the electron beam cold bed furnace, and primary cast ingots are subjected to secondary smelting through the vacuum consumable electrode arc furnace. Alloy elements are preliminarily homogenized and part of impurities are removed by using the high energy density and good refining capacity of the electron beam cold bed furnace, and then the components are further adjusted through the vacuum consumable electric arc furnace, so that the component uniformity of the Ti65 titanium alloy cast ingot is effectively improved, and the quality of the Ti65 titanium alloy cast ingot is improved. The application of the titanium alloy material in the fields of petrochemical industry, aviation industry, nuclear power generation, hydrogen storage industry, military industry and the like is expanded.

Composite plate (10), particularly for the aeronautical industry, this composite plate (10) having a sandwich structure and comprising: - a first layer (12) comprising non-woven carbon fiber scraps (14) and a thermoplastic binder ensuring the bonding of the fiber scraps together, - a second layer (16) comprising non-woven carbon fiber scraps (14) and a thermoplastic binder ensuring the bonding of the fiber scraps together, and - a foam layer (18) sandwiched between the first and second layers (12, 16), this foam layer (18) being made of thermoplastic, the layers (12, 16, 18) of the composite plate (10) being bonded together by fusion of their respective thermoplastic materials at the interfaces between the layers. Figure for the abbreviation: Figure 1

The application discloses a method for three-dimensional reconstruction of two-dimensional infrared images of an aero-engine blade under single visual angle, and relates to the technical field of computer vision, wherein the conversion from a two-dimensional temperature field to a three-dimensional temperature field is realized by means of a spatial position mapping algorithm for infrared temperature images under single visual angle on the premise of three-dimensional modeling of an aero-engine. The application has the characteristics of high efficiency, precision and low cost without providing multiple visual angle infrared images; the spatial position mapping of infrared images is combined with a three-dimensional model of a measured object for the first time to realize three-dimensional temperature field reconstruction of the measured object, which provides a new solution for temperature measurement and control of aero-engine blades and has a positive significance for promoting the development of the aviation industry.

The invention provides an objectification-based resource collaborative management implementation method, which relates to the technical field of aviation industry, and comprises the following steps: S1, data objectification, S2, product data object template definition: configuring an attribute field of a business data object, configuring a coding rule of the business object, and defining a template of the product data object based on the configured attribute field, s3, resource management: creating a personal workspace based on the selected product, and creating a folder in the workspace, and S4, creating a product data object. According to the objectification-based resource collaborative management implementation method, complicated data types of the aviation industry are abstracted to form object resource data stored in a bottom layer, collaborative design and development of product data and classification and management of the product data according to modules are facilitated in an object resource collaborative management mode, and the implementation efficiency of collaborative design and development of the product data is improved. The problems that product data are too dispersed and collaborative design and development are inconvenient are solved.

The invention relates to a composite plate (10), in particular for the aeronautical industry, this composite plate (10) having a sandwich structure and comprising: - a first layer (12) comprising non-woven carbon fiber scraps (14) and a thermoplastic binder bonding the fiber scraps to one another; - a second layer (16) comprising non-woven carbon fiber scraps (14) and a thermoplastic binder bonding the fiber scraps to one another; and - a foam layer (18) positioned between the first and second layers (12, 16), this foam layer (18) being made of thermoplastic, the layers (12, 16, 18) of the composite plate (10) being bonded together by fusion of their respective thermoplastic materials at the interfaces between the layers.

The present invention relates to a thermoplastic release film for molding composite material parts, particularly in the aeronautical industry. The film of the invention is very easy to use, environmentally friendly and can be recycled.

The application belongs to the technical field of liquid cooling forced convection heat dissipation of high-power-density electronic equipment in the aviation industry, and is a liquid cooling cabinet device for an airborne high-power motor controller based on liquid cooling forced convection heat dissipation technology, comprising a cabinet main body, the top of which has a mounting chamber, the bottom of which is formed with a liquid cooling flow channel in a multi-channel serpentine structure, and the side surface of the cabinet main body is provided with a cooling liquid inlet and a cooling liquid outlet in communication with the liquid cooling flow channel; a liquid cooling flow channel cover plate is fixedly arranged on the bottom surface of the cabinet main body with the liquid cooling flow channel, and is used for sealing the liquid cooling flow channel. The liquid cooling cabinet has the characteristics of good temperature uniformity, good heat dissipation performance, light weight, small flow resistance, wide universality and the like. An effective solution is provided for the temperature thermal management of the airborne high-power motor controller.

The application relates to the technical field of the aviation industry, and provides an intelligent regulation and control multi-flame combustion chamber, an aero-engine and a control method.The multi-flame combustion chamber comprises a combustion unit, an intelligent temperature control valve assembly and a plurality of main combustion stage fuel supply components, the combustion unit comprises a combustion chamber body and a plurality of main combustion stage assemblies arranged on the combustion chamber body, the main combustion stage assemblies comprise at least one main combustion stage base element component, the plurality of main combustion stage fuel supply components are connected in one-to-one correspondence with the plurality of main combustion stage assemblies, and the intelligent temperature control valve assembly is provided with a medium inlet and a plurality of medium outlets, the plurality of medium outlets are connected in one-to-one correspondence with the plurality of main combustion stage fuel supply components.The application senses the temperature change of the incoming medium through the intelligent temperature control valve assembly, intelligently controls the connection and disconnection of the at least one medium outlet and the medium inlet, realizes the on-off control of the plurality of main combustion stage fuel supply components, and further realizes the intelligent regulation and control of the combustion chamber outlet temperature distribution and NOx emission, so that the outlet temperature distribution is more uniform, the NOx emission is lower, and the aero-engine is more environmentally friendly. X X ​​

The present invention relates to a sandwich panel comprising an upper top layer (UTL) comprising a polyarylene ether sulfone polymer and a fibrous reinforcing agent, a foam core layer (FCL) comprising a polyarylene ether sulfone polymer and a lower top layer (LTL) comprising a polyarylene ether sulfone polymer and a fibrous reinforcing agent, wherein the upper top layer (UTL) is joined to the foam core layer (FCL) via a first film (F1) comprising a blend of a polyarylene ether sulfone polymer and a further polymer, and wherein the lower top layer (LTL) is joined to the foam core layer (FCL) via a second film (F2) comprising a blend of a polyarylene ether sulfone polymer and a further polymer. A further aspect of the invention is a method for producing a sandwich panel and the use of a sandwich panel as a construction part for the aeronautical industry and as a rotor blade for constructing a wind turbine. Yet another aspect of the invention is a method for reusing a sandwich panel.

The invention discloses an aviation primer and a preparation method thereof, and belongs to the technical field of aviation paint preparation. The aviation primer comprises a component A and a component B. The component A comprises bisphenol A type epoxy resin, bisphenol F type epoxy resin, a reactive diluent, hollow glass microspheres, surface fluorosilicone modified hollow silicon dioxide nanoparticles, a shape memory polyurethane modifier, a pH sensitive epoxy repairing agent microcapsule and various functional aids. The component B comprises a modified polyamide curing agent and a microcapsule coated imidazole accelerant. According to the preparation method, uniform dispersion of nano components is realized by adopting a high-shear dispersion and ultrasonic synergistic dispersion process, the breakage rate of the microspheres is reduced by adding the hollow glass microspheres with different particle sizes in batches, and ordered distribution of functional components is accurately regulated and controlled by adopting a three-section temperature control curing process. The light weight, super-hydrophobic and self-repairing functions of the aviation primer are achieved, and the requirements of the modern aviation industry for high performance, long service life and light weight of a coating are met.

The invention belongs to the technical field of aviation industry, and discloses a cementing verification device and method based on a contact array. The device comprises a contact working system, wherein the contact working system comprises a contact unit, a contact grid, a contact locking device and a contact support; the contact locking device comprises a locking mechanism and a locking knob; the base supporting system comprises a contact base, a pin and a device supporting leg; the contact unit penetrates through the contact grid and penetrates through the contact support, the tail end of the contact unit is in contact with the gluing piece, the contact grid is further provided with a locking mechanism used for limiting movement of the contact unit, and the locking mechanism is provided with a locking knob used for driving the locking mechanism to limit movement of the contact unit; and the locking knob is arranged on the side wall of the contact support. According to the invention, rigid contact displacement acquisition and three-dimensional data modeling are used for replacing flexible verification film physical imprinting, and accurate detection of gaps and quantitative filling of adhesive films are realized through a digital means.

The invention belongs to the technical field of composite material I-shaped beams, and particularly discloses a sandwich structure composite material wing I-shaped beam and a preparation method thereof. Through the five-layer alternate sandwich structure of the carbon fiber fabric and the sisal fiber tows and by combining and optimizing the fiber proportion, the laying layer design and the preparation method, the mechanical property of the I-beam is improved, the I-beam has high strength and high toughness, the maximum bending strength of the I-beam reaches 489.30 MPa, the maximum impact energy of the I-beam reaches 94.65 KJ / m < 2 >, and the I-beam can effectively bear the bending load and the impact load borne by a wing and can be widely applied to the field of airfoils. The flight safety redundancy is obviously improved; the self-weight of the wings can be reduced, so that the energy consumption of the aircraft can be optimized. Meanwhile, the material cost is reduced by introducing the sisal fibers, the product consistency and stability are guaranteed by a standardized process, and large-scale production is facilitated; and the application of natural fibers improves the environmental protection property and sustainability of the material, and accords with the development trend of aviation industry.

The application discloses a kind of TC4 alloy surface wear-resistant CrZrN solid solution ceramic coating and preparation method thereof, belong to TC4 alloy surface treatment field, the coating is prepared CrZrN ceramic coating using double-glow plasma surface metallurgy technology for TC4 alloy surface, the coating includes deposition layer and diffusion layer, Cr, Zr, N, Ti content in diffusion layer gradient change, alleviate the failure of coating caused by composition mutation and property difference;Compared with CrN binary coating, the CrZrN ceramic coating prepared by the application has the advantages of realizing solid solution strengthening, refining the grain and realizing metallurgical bonding between the coating and the substrate, which can effectively improve the service life of TC4 alloy substrate and can be applied to wear-resistant parts protection in the fields of aviation industry and shipbuilding industry.

The invention relates to the technical field of aviation industry, and provides an operation data driven turbine full-life intelligent design method, computer equipment and a computer storage medium, and the method comprises the steps: S1, obtaining basic parameters of new turbine design and basic parameters of mature turbine design; s2, standardizing the basic parameters by using a parameter extractor to obtain a standardized parameter database; s3, constructing and training a Transform intelligent prediction model by using the standardized data of the mature turbine, inputting the standardized parameters of the new turbine design into the Transform intelligent prediction model, and comprehensively evaluating the design scheme to generate a prediction result; and S4, according to a prediction result of the Transform intelligent prediction model, carrying out intelligent decision making, generating an optimization design scheme, and obtaining a design result. According to the method, multi-head learning is carried out on real operation data through the constructed Transform model, the efficiency attenuation curve and the expected life of the turbine in the whole life cycle are predicted, and the predicted efficiency attenuation confidence coefficient reaches 95% or above.

Systems and methods are provided for dynamically modeling and depicting overall emissions of the aviation industry and changes thereto when taking into account, for example, traffic growth and introduction of sustainability strategies, such as new and / or improved technologies, an increase in operational efficiency, and carbon offsets. Using the dynamic tool described herein, users can define scenarios on how to reduce emissions through the introduction of different sustainability strategies, both statically and over time, analyze the impact of those strategies on emissions, and understand the dependencies between select strategies.

The present invention belongs to the technical field of material preparation, and aims to solve the problem that the preparation process of the existing metal ceramic material is difficult to accurately control the distribution and grain size of each phase in the metal ceramic matrix, resulting in uneven microstructure of the material, thereby affecting the comprehensive performance of the material. To this end, the present invention provides a method for preparing a fiber-reinforced metal ceramic material, comprising: pre-treating silicon carbide fiber; mixing and grinding titanium metal powder and silicon carbide ceramic powder according to a predetermined ratio; then adding silicon carbide fiber particles and placing them in an ultrasonic mixer; adding a dispersant and a binder and mixing them again; the mixture is sequentially cold isostatically pressed and hot pressed; the obtained blank is sequentially pre-sintered, high-temperature sintered, cut and surface treated. The metal ceramic material prepared by the present invention is significantly improved in strength, toughness, hardness, high temperature resistance, wear resistance and corrosion resistance, can better meet the high performance requirements in the aviation field, and provide strong support for the aviation industry.

The application belongs to the technical field of aviation industry, and discloses a kind of based on contact array's cementation checking device and method.The device includes contact working system, including contact unit, contact grid, contact locking device and contact support;Contact locking device includes: locking mechanism and locking knob;Base support system includes contact base, pin, device support leg;Contact unit is through on contact grid, and is through contact support, the end of contact unit is in contact with cementing piece, locking mechanism for limiting the movement of contact unit is also provided on contact grid, locking mechanism is installed with locking knob for driving locking mechanism to limit the movement of contact unit;Locking knob is installed in the side wall of contact support.The present application uses rigid contact displacement collection, three-dimensional data modeling to replace flexible verification film physical imprint, and realizes accurate detection of gap and quantitative filling of adhesive film through digital means.

The utility model belongs to the technical field of roller coating of carbon fiber cloth in the aviation industry, and particularly provides an automatic coating device for a composite material. Comprising a frame, a feeding box, a storage box, a discharging port, a rolling brush, a control device, a lower bottom plate, a power source, an upper bottom plate, a motor and rolling wheels. The frame is of a double-layer structure and comprises a lower bottom plate and an upper bottom plate, and the lower bottom plate and the upper bottom plate are stably connected through four mounting columns. A power system is arranged on the lower bottom plate, the power system is composed of four motors, the four motors drive the rolling wheels to operate respectively, and the rotating speed and the direction of the motors can be manually regulated and controlled through a control system; a power supply module and a control system are also arranged; wherein the rolling brush is fixed at the front end of the lower bottom plate; and the feeding box and the storage box form a communicating structure. And a row of discharge ports are designed at the bottom of the storage box. The composite material gluing device is simple in structural design, low in processing and assembling process requirements of parts, free of complex processing equipment or high-precision technology, easy to maintain and capable of achieving automatic composite material gluing.

This invention relates to the field of thermoplastic composite material preparation technology, and discloses a thermoplastic resin-based composite material, its preparation method, and its application. The preparation method includes: mixing molten resin with a fabric in a flowing state for a first contact impregnation, followed by a second contact impregnation under pressure; calendering the impregnated material to obtain a prepreg; and then molding the prepreg to obtain the composite material; wherein, based on the total weight of the impregnated material, the resin content is 30-40 wt%; and the temperature of the second contact impregnation is 10-25°C higher than that of the first contact impregnation. The composite material prepared by the method of this invention has a uniform resin distribution, low porosity, a resin content dispersion value of <4%, and a porosity of <0.05%, making it particularly suitable for use in high-performance thermoplastic composite material parts in the aerospace industry.

The invention discloses a design method of a Co-Cr-Ni-Ti-Al-V series eutectic high-entropy alloy with light weight and high temperature resistance performance. An aero-engine case is in an extreme working environment, the requirement for the performance of a workpiece material is harsh, and currently used nickel-based superalloy (such as Inconel 625 superalloy) is large in material density and does not meet the development target of the modern aviation industry. In recent years, development of the high-entropy alloy provides a direction for research and development of novel engine case materials, and meanwhile, the Co-Cr-Ni-Ti-Al-V series eutectic high-entropy alloy with light weight and high temperature resistance is designed in consideration of the problems of poor castability, high brittleness and the like of the alloy. According to the method in the claim 1, the density of the manufactured alloy ranges from 5.5 g / cm < 3 > to 6.8 g / cm < 3 > and is 19%-35% lower than the density of nickel-based high-temperature alloy (for example, the material density of Inconel 625 high-temperature alloy is 8.4 g / cm < 3 >). According to the method in the claim 1, the high-temperature mechanical property of the material is tested, it is found that continuous strengthening after yield is observed in the alloy manufactured within the service temperature range of the Inconel 625 nickel-based high-temperature alloy at 650-1100 DEG C, and the compressive strength exceeds 1000-1300 MPa; the compressive strength (for example, the compressive strength of Inconel 625 high-temperature alloy at the service temperature of 850 DEG C is about 700 MPa) of the nickel-based high-temperature alloy is 43%-86% higher than that of the nickel-based high-temperature alloy; no obvious crack is observed in the compressed sample. As the test temperature rises to 850-1300 DEG C (for example, the compressive strength of the Inconel 625 high-temperature alloy at the temperature of 1100 DEG C is about 400 MPa), the load on a stress-strain curve is reduced, and the strength is reduced to about 800-1000 MPa. According to the method in the claim 1, the high-temperature oxidation resistance of the material is tested, and after the material is oxidized for 200 hours at the temperature of 650-1100 DEG C, the thickness of an oxide layer of the manufactured alloy is measured to be about 3-5 microns and is 45%-67% lower than the thickness of an oxide layer of a nickel-based high-temperature alloy (for example, the thickness of an oxide layer measured after an Inconel 625 high-temperature alloy is oxidized for 200 hours at the temperature of 850 DEG C is measured to be about 9 microns). Compared with a nickel-based high-temperature alloy, the material designed by the invention has the advantages in material density, high-temperature mechanical property and high-temperature oxidation resistance, has a good development prospect in application materials of aero-engines, and also has very important reference value for subsequent design and application of eutectic high-entropy alloys.

The utility model relates to the technical field of aviation industry, in particular to a positioning tool for punching of a special-shaped connector, which is used for clamping the special-shaped connector and comprises a base, a positioning groove is formed in the base, and the positioning groove is matched with the special-shaped connector in appearance; and the pressing plate is used for being tightly pressed on the special-shaped connector, and the pressing plate is detachably connected with the base. In the using process, the special-shaped connector is assembled into the positioning groove, then the pressing plate is pressed on the special-shaped connector and connected with the base, the pressing plate tightly presses the special-shaped connector on the base, positioning of the special-shaped connector is achieved, and then the two ends of the special-shaped connector are punched. The positioning tool is specially used for positioning the special-shaped connector, due to the fact that the positioning groove is matched with the special-shaped connector in appearance, the special-shaped connector can be clamped and positioned more accurately, and clamping and positioning are more convenient.

The utility model discloses an axial static type PTFE packing cup rotary sealing performance testing device, and belongs to the technical field of sealing tests. The driving mechanism is fixed on the bottom plate, two frame bodies are fixed on the bottom plate, a cavity is formed between the two frame bodies, the output end of the driving mechanism is coaxially and fixedly connected with the shell with the U-shaped section, the PTFE leather cup to be verified is pressed on the inner wall of the shell in an interference fit mode, the inner side of the PTFE leather cup is tightly attached to the test shaft, the rubber leather cup is pressed on the test shaft in an interference fit mode, and the rubber leather cup is fixedly connected with the shell. The inner side of the rubber cup is tightly attached to the outer wall of the shell, the test shaft is arranged in the cavity, and the outer end of the test shaft is fixedly connected with the cavity. According to the utility model, the driving mechanism drives the shell and the PTFE packing cup in the shell to rotate, and the test shaft is kept static, so that the sealing performance of the PTFE packing cup in a rotating state is accurately tested, and the test mode is closer to an actual application scene, therefore, the test result has higher reference value, and the test requirements in special application scenes such as aviation industry and the like are met.

The invention discloses an aviation industry Internet data extraction method and system based on feature recognition and a medium, and relates to the technical field of data extraction, and the method comprises the steps: searching data related to the aviation industry in the Internet through employing a web crawler technology; preprocessing the network aviation data to obtain aviation source data; performing calibration processing on industrial data in the aviation source data by using a data calibration method; performing classification based on the data type of the standard aviation industrial data; the method is used for solving the problem that the extracted data is doped with data irrelevant to the aviation industry or contains parameter error data due to the lack of an effective screening method in the aspects of data checking and picture analysis for the extracted data in the aspect of the aviation industry in the prior art.

The present invention relates to the technical field of three-dimensional braided composite material detection, and solves the technical problem that traditional methods cannot perform real-time detection of carbon fiber yarn and woven preform defects in a three-dimensional weaving production line. In particular, it relates to a method for detecting defects in a preform of an aeroengine fan blade, which includes collecting original images in real time and preprocessing the original images; extracting features from the preprocessed images to obtain a multi-scale feature map containing global features and local features; constructing a defect-aware decoupled detection module for decomposing the defect detection task into two subtasks of position modeling and size estimation, and optimizing the initial candidate boxes to obtain a set of defect results. The present invention can realize real-time, high-precision, and automated detection of carbon fiber yarn and woven preform defects, significantly improve the quality control ability of the production line of aeroengine fan blade preforms, and meet the strict production standards of the aviation industry.