76 results about "Aerospace manufacturing" patented technology

The invention discloses an aerospace intelligent manufacturing large model construction method, which comprises the steps of collecting original data, performing preprocessing and data association, and constructing an aerospace intelligent manufacturing database; establishing a knowledge acquisition and structured conversion assembly line, a multi-dimensional associated domain knowledge graph, a knowledge quality control system and a dynamic updating mechanism, and constructing a professional knowledge base; aligning the cross-modal manufacturing data to generate a corpus; combining base general large model pre-training, injecting terminology semantics and multi-modal association capability, and completing knowledge migration; based on the pre-trained aerospace intelligent manufacturing large model, constructing an aerospace manufacturing cognitive agent, and forming a complex engineering problem solving framework; professional ability is optimized through a two-stage progressive multi-task training strategy, and dynamic adaptation of a production environment is realized in combination with an online learning and incremental updating mechanism. The intelligent level of aerospace intelligent manufacturing is remarkably improved.

The invention relates to the technical field of intelligent manufacturing equipment fault diagnosis, and particularly discloses a Meta-Transform driven multi-working-condition equipment bearing fault diagnosis method and system. The method aims at bearing fatigue damage risks caused by dynamic adjustment of technological parameters of a numerical control machine tool in the aerospace manufacturing process and challenges such as feature distribution offset and fault sample scarcity caused by variable working conditions. The diagnosis system is constructed through three core modules. The method comprises the following steps: firstly, reconstructing an original bearing signal into a multi-scale time-frequency feature space by adopting continuous wavelet transform; then designing a causal Transform architecture with a strict lower triangle attention mask, and realizing feature extraction and classification according to a physical causal law of fault propagation; and finally, integrating the mechanisms into a model-independent element learning framework, and realizing cross-working-condition rapid self-adaption through a self-adaption gradient pruning strategy. The bearing fault diagnosis accuracy under the condition of few samples is improved, the interpretability and generalization ability of the model are enhanced, and the industrial application practicability of bearing fault diagnosis is improved.

The invention relates to the technical field of rocket thrust chamber manufacturing, and discloses an additive forming part linear cutting and taking auxiliary system for a rocket thrust chamber. The system comprises a multi-source data acquisition module for acquiring geometrical morphology data of the additive forming part through various sensors; the cutting path planning module is used for generating a global cutting path sequence based on an improved genetic algorithm; the dynamic deformation compensation module is used for compensating thermal deformation and vibration interference in real time by using a fuzzy adaptive observer; and the multi-axis cooperative control module is used for constructing a distributed constraint optimization model to realize accurate control of multi-axis motion. The system can accurately collect data, reasonably plan a cutting path, effectively compensate deformation, ensure multi-axis cooperative work, remarkably improve the quality and efficiency of linear cutting and taking of the rocket thrust chamber additive forming part, reduce the production cost and provide powerful technical support for spaceflight manufacturing.

The invention relates to the technical field of aerospace manufacturing and intelligent welding control, and solves the technical problems of insufficient single-mode perception, limited quality prediction precision, lagging parameter regulation and control and weak model adaptive capacity in traditional welding process monitoring. In particular to a spaceflight structure friction stir welding multi-modal sensing and intelligent quality control method, which combines multi-modal real-time sensing and reinforcement learning by introducing a body intelligent body thought, so that a system can autonomously understand a welding state, predict a quality trend and actively adjust process parameters in a welding process; and adaptive optimization control with quality as constraint is realized. According to the method, the limitation of traditional off-line modeling and manual adjustment is broken through, an intelligent control framework with self-learning and self-evolution capacity is provided for spaceflight-level friction stir welding, and a new technical approach is provided for achieving high-consistency and high-reliability welding seams. The intelligent level of friction stir welding of the spaceflight structural part and the welding seam consistency level are remarkably improved.

The invention discloses a titanium alloy skin processing compensation method based on a digital twinning residual stress prediction model, particularly relates to the field of aeronautical manufacturing, and aims to solve the problems that local resilience is difficult to prejudge and a compensation result is unstable due to inconsistent stress release time sequences and dispersed compensation basis in a subunit cutting process of a titanium alloy skin. A unit stress release state is constructed by collecting a unit contour offset and a unit cutting sequence, same-chain deduction is carried out by combining preorder unit residual stress mapping to generate a unit compensation candidate quantity, and execution judgment and a closed-loop updating parameter layer are formed based on playback and re-scanning consistency analysis. According to the method, compensation decision traceability, processing deviation convergence and continuous inheritance between working steps are achieved, the manual repeated trial cutting and parameter adjustment cost is reduced, and the transition smoothness of adjacent units and the forming consistency of the whole skin are improved.

The invention relates to an aircraft component intelligent assembly data management system based on compliance verification, and belongs to the technical field of aerospace manufacturing. In order to solve the problems of data dispersion, low verification efficiency and difficulty in quality tracing in the aircraft component assembly process, the system comprises a standard process library construction unit used for constructing an aircraft component assembly standard process library which is clear in classification and contains detailed specifications; the assembly information acquisition unit is used for collecting assembly data in multiple channels and processing the assembly data into a structured data set; the data management system unit is used for integrating multi-source data and analyzing historical data and verification results to form a trend table so as to realize overall management; and the qualification checking unit is used for checking real-time data in multiple dimensions, generating a report and performing synchronous early warning. According to the system, intelligent management of the aircraft component assembly process is realized, the data processing efficiency and accuracy are improved, and the assembly quality and the safety and reliability of an aircraft are guaranteed.

The invention discloses an aviation transmission part fretting friction wear test device and method, and belongs to the field of aerospace manufacturing, and the device comprises a supporting assembly, an axial force loading assembly, a transverse vibration assembly, a first test piece and a second test piece; the supporting assembly comprises a vibration platform, a first support and a second support, the first support is fixed on the vibration platform, the axial force loading assembly comprises a sliding plate, a servo motor, a lead screw and a nut, the sliding plate is in sliding connection with the vibration platform, the servo motor is connected with the lead screw, the nut is fixedly connected with the sliding plate, and the second support is fixed on the sliding plate; the transverse vibration assembly comprises a variable frequency motor, an eccentric wheel, a connecting rod, a vibration rod and a limiting plate, the variable frequency motor is fixed to the sliding plate, the eccentric wheel comprises a rotating shaft and an eccentric shaft, the variable frequency motor is in transmission connection with the rotating shaft, and one end of the connecting rod is rotationally connected with the eccentric shaft while the other end is rotationally connected with the vibration rod; therefore, the working condition of the aviation transmission part in a transverse vibration environment can be simulated.

The present invention discloses a micro-friction and wear testing device and method for aviation transmission components, which belongs to the field of aerospace manufacturing. The device comprises a support assembly, an axial force loading assembly, a lateral vibration assembly, a first test piece and a second test piece. The support assembly comprises a vibration platform, a first support and a second support, the first support is fixed on the vibration platform, the axial force loading assembly comprises a sliding plate, a servo motor, a lead screw and a nut, the sliding plate is slidably connected to the vibration platform, the servo motor is connected to the lead screw, the nut is fixedly connected to the sliding plate, and the second support is fixed on the sliding plate; the lateral vibration assembly comprises a variable frequency motor, an eccentric wheel, a connecting rod, a vibration rod and a limit plate, the variable frequency motor is fixed on the sliding plate, the eccentric wheel comprises a rotating shaft and an eccentric shaft, the variable frequency motor is transmission-connected to the rotating shaft, one end of the connecting rod is rotationally connected to the eccentric shaft, and the other end is rotationally connected to the vibration rod, thereby simulating the working condition of the aviation transmission component in a lateral vibration environment.

The invention discloses a skin riveting quality monitoring method and system based on machine vision, and relates to the technical field of aerospace manufacturing engineering quality inspection, and the method comprises the steps: comprehensively obtaining the form, texture and temperature information of a rivet region through multi-modal data synchronous collection of a coaxial structured light three-dimensional sensor, an industrial camera and a thermal infrared imager; projecting the three-dimensional point cloud data to a radial grid by adopting a polar coordinate system, generating a height measurement function and calculating a morphology difference function; extracting morphology energy characteristics by combining a weighted p-norm integration method, extracting fractal dimensions, texture characteristics and temperature rise indexes of rivet contours at the same time, constructing a rivet distribution diagram structure, and defining adjacent weights through Euclidean distances between nodes and stress transfer paths; and outputting a riveting defect analysis result by dynamically adjusting an adjacent weight based on a graph convolutional network containing a morphology gating mechanism. Therefore, the accuracy of riveting defect detection is improved.

This invention discloses a method, system, medium, and equipment for planning manufacturing process routes for aerospace product components, belonging to the technical field of intelligent aerospace manufacturing. It establishes a knowledge model of process division of labor and a digital model of process division of labor feature retrieval and identification; collects data to establish a basic database for process division of labor reasoning; determines the type of parts based on the EBOM database, classifies and labels the parts, and outputs the master manufacturing unit and cooperating units of the parts; retrieves process division of labor feature information from the digital model of components to determine the component type and outputs the master manufacturing unit and cooperating units of the components; retrieves process division of labor feature information from the digital model of assemblies to output the user units of the assemblies and their sub-components. Finally, it integrates and outputs the process route of the materials. This invention effectively improves the efficiency and quality of process route design.

A hot spinning forming manufacturing method for a titanium alloy large-length cylindrical part belongs to the technical field of spaceflight manufacturing and comprises the following steps: welding a titanium alloy circular blank end socket at one end of a titanium alloy thick-wall cylindrical blank to form a thick-wall cylindrical part; the thick-wall cylindrical part with one end sealed is installed on a core mold of the spinning machine and fixed, then flame spray guns arranged in an array mode are used for heating the outer surface of the thick-wall cylindrical part, the heating process is intermittently stopped, and the temperature of the thick-wall cylindrical part is measured in real time; when the temperature of the thick-wall cylindrical part reaches the spinning temperature, multi-pass spinning is carried out, and the flame heating intensity is adjusted according to the measured temperature of the thick-wall cylindrical part in the spinning process; and when the wall thickness of the thick-wall cylindrical part meets the requirement, spinning and demolding are stopped, the thick-wall cylindrical part is taken down at the preset temperature, after the room temperature is reached, the round blank with the welded end is cut off, and the large-length cylindrical part is obtained. The method can improve the product temperature uniformity in the hot spinning process, improve the spinning process stability and improve the product forming quality.

The invention relates to a ceramic-based composite material connecting hole ultrasonic / water-guided laser combined machining device, in particular to a ceramic-based composite material hole characteristic water-guided laser and ultrasonic-assisted vibration combined machining device which is used for machining connection holes, special-shaped holes and butt joint boundaries of material fasteners such as ceramic-based composite materials / high-temperature alloy in aircraft assembly. Belongs to the field of aeronautical manufacturing engineering / aircraft assembly. And the requirement for high-precision and rapid machining of the thermal adaptation connecting holes of ceramic material flat-plate type (or near-flat-plate) small parts is met. A combined machining mode is adopted, the advantages of ultrasonic-assisted vibration and water-guided laser are fully played, machining modes are convenient to convert, the machining difficulty of high-hardness and high-brittleness materials is remarkably reduced, meanwhile, the defects that laser machining aperture precision is not high, and a heat affected zone exists are overcome, the machining efficiency and precision are both considered, parts are clamped and positioned at a time, and machining precision is high. And assembly in-situ machining of various types of connecting holes can be completed.

The invention provides a fork lug type connector butt joint tolerance distribution method, belongs to the technical field of aeronautical manufacturing, and particularly comprises the steps that an assembly mathematical model of a fork lug type connector is imported into simulation analysis software, and then the assembly state of the fork lug type connector and the assembly state of a support lug type connector are integrally separated; the machining precision of butt joint holes of the fork lug type connector and the support lug type connector is input; performing rotation assembly iteration and translation assembly iteration on the model data generated by each simulation analysis software in sequence, and setting rotation assembly iteration times and translation assembly iteration times; rotation assembly iteration times and translation assembly iteration are carried out; after simulation is finished, a simulation result is output, data of the simulation result comprises a minimum containing value data set of each piece of model data, and the number of minimum containing values of each data set is equal to the number of the fork ear type connectors. By means of the processing scheme, the assembling quality and efficiency of the plug-in type connector are improved.

The present invention relates to the field of rocket thrust chamber manufacturing technology, and discloses a wire cutting and picking auxiliary system for additively molded parts for rocket thrust chambers. The system includes a multi-source data acquisition module, which collects geometric morphology data of additively molded parts through multiple sensors; a cutting path planning module, which generates a global cutting path sequence based on an improved genetic algorithm; a dynamic deformation compensation module, which uses a fuzzy adaptive observer to compensate for thermal deformation and vibration interference in real time; and a multi-axis collaborative control module, which constructs a distributed constraint optimization model to achieve precise control of multi-axis motion. The system can accurately collect data, reasonably plan cutting paths, effectively compensate for deformation, and ensure multi-axis collaborative work, significantly improving the quality and efficiency of wire cutting and picking of additively molded parts for rocket thrust chambers, reducing production costs, and providing strong technical support for aerospace manufacturing.

The present invention relates to an oil storage wing / rudder wing supported by a combination of plate columns and trusses, and belongs to the field of aerospace manufacturing technology. The present invention aims to solve the problems of insufficient high-stress bearing capacity and poor heat insulation ability at high temperatures in existing oil storage wings and rudder wings in complex aerospace environments. The oil storage wing / rudder wing supported by a combination of plate columns and trusses consists of vertical thick plates, multiple rows of side trusses, a perforated oil tank, multiple intermediate oblique columns, a wing shell, and heat insulation filling. The present invention is used for oil storage wings / rudder wings supported by a combination of plate columns and trusses.

The invention provides a hot sizing tool for an aircraft airfoil structure welding part, and relates to the technical field of welding. The thermal correction tool for the aircraft airfoil structure welding part comprises a positioning module and a pair of load loading modules, the positioning module comprises a positioning assembly, the positioning assembly is located in an installation area, the positioning assembly is used for bearing an airfoil structure, and the positioning assembly can be in positioning fit with the airfoil structure; the pair of load loading modules are symmetrically arranged on the base, and a mounting area is defined between the pair of load loading modules; the load loading module comprises a plurality of load loading assemblies, the load loading assemblies are distributed on the corresponding sides of the airfoil structure, each load loading assembly comprises a driving part and an extrusion part, the driving parts are connected with the extrusion parts, and the driving parts are used for driving the extrusion parts to be close to or away from the airfoil structure. According to the method, high-precision, universal and low-cost airfoil structure deformation correction can be realized, so that the strict requirements of modern aerospace manufacturing on light-weight and high-reliability structures are met.

The invention relates to a machining method of an aviation flywheel, and relates to the technical field of aerospace manufacturing, the machining method comprises the following steps: S1, a 5000-ton press is used for pre-forging, and a 9-meter ring forging machine is used for rolling to prepare a drum wheel rim; a rim and a hub are preprocessed; s2, preheating to 250 + / -10 DEG C in a 9-meter well type electric furnace, performing full penetration welding by adopting a gas shield welding wire, and performing heat preservation and slow cooling after welding; performing UT and MT detection on each welding seam, heating to 500 DEG C at the speed of less than or equal to 50 DEG C / h, tempering, preserving heat for 8 hours, cooling to 250 DEG C or below along with the furnace, and discharging; in the machining process of the aviation flywheel, the temperature of the temperature measuring point is monitored in real time through the temperature measuring gun during welding, the structure is homogenized during tempering, welding residual stress is eliminated, deformation and cracking in the subsequent machining or using process are prevented, the size precision is stabilized, and the accuracy in the subsequent machining process is ensured.

The invention discloses a spaceflight core process digital asset uplink right confirmation and transaction method based on expert process data, and relates to the technical field of spaceflight manufacturing and digital assets, in particular to the spaceflight core process digital asset uplink right confirmation and transaction method based on the expert process data. According to the method, multi-modal process data of an expert is collected in real time through wearable equipment, a process fingerprint is generated by using a processing model based on a world model architecture, and rare digital assets are judged by calculating a uniqueness score and an emotional value score; the process fingerprints of the rare assets are subjected to homomorphic encryption uplink to generate NFT, ownership completely belongs to experts, and transaction income is automatically distributed according to a preset proportion; and meanwhile, a hardware fusing protection mechanism for illegal operation is arranged. According to the invention, security right confirmation, capitalized transaction and value sharing of expert process data are realized, and inheritance and innovation of a spaceflight core technology are effectively promoted.

The utility model provides a different-plane-angle auxiliary forming tool for an aircraft waste water and grey water pipeline, which relates to the technical field of aerospace manufacturing and comprises a core mold, a clamping mechanism, a pointer arm, an angle scale and a positioning mechanism. Axial scale marks are arranged on the core mold; the clamping mechanism is slidably arranged on the core mold in a sleeving manner, is provided with a clamping space and is used for clamping a pipeline; the positioning mechanism is slidably arranged on the core mold in a sleeving mode, the first end face of the positioning mechanism is connected with the angle scale, and the second end face abuts against the clamping mechanism and the pipeline; the pointer arm is hinged to the clamping mechanism and used for pointing to angle scale lines of the angle scale. Through the synergistic effect of the core mold, the clamping mechanism, the pointer arm, the angle scale and the positioning mechanism, a universal and efficient auxiliary bending tool is formed in a combined mode, the auxiliary bending tool is matched with a common pipe bending machine to conduct multi-dimensional and high-precision different-plane-angle manufacturing operation, and the high-standard manufacturing requirement of aircraft waste water and grey water pipelines is met.

The invention belongs to the field of single-machine products in the aerospace manufacturing industry, and discloses an online visual detection system and method for single-machine products, and the system comprises an optical system, an image capturing module, an image digitization module, a digital image processing module, and an intelligent interpretation decision module. The optical system comprises at least one light source and a light source controller matched with the light source, and is used for adjusting the light source irradiating the to-be-detected object; the image capturing module is used for collecting a detection image of a to-be-detected object; the image digitization module is used for discretizing the detection image acquired by the image capture module in space; the digital image processing module is used for analyzing and processing the discretized detection image to obtain an image processing result; and the intelligent interpretation and decision-making module is used for carrying out analysis and decision-making on the image processing result transmitted by the digital image processing module, building a machine vision single-machine detection system, replacing part of manual detection contents, improving the detection efficiency and reducing manual missed judgment and misjudged judgment.

The application relates to the field of aerospace manufacturing technology and discloses a forming stress roll bending correction method and device for an F-shaped profile frame part for aerospace. The method is characterized in that a vertical correction roller correction device is installed on parallel support frames on both sides of a numerical control three-axis profile roll bending machine, an F-shaped profile frame part is placed at a detection platform detection bottom plate upwarp gap position, the part is rolled into the roll bending machine, and the vertical correction roller is in rolling contact with the annular rib plate; when there is a gap on the arc-shaped outer side of the bottom plate, the parallel support frames are lowered; and when there is a gap on the arc-shaped inner side of the bottom plate, the parallel support frames are raised, so that a vertical correction force is applied to the annular rib plate and overall roll bending correction is carried out. The scheme can correct the bottom plate upwarp and the verticality deviation of the vertical plate, and improves the correction efficiency and forming quality of the F-shaped profile frame part.

A kind of multi-module series oil tank for light heat-insulated oil storage wing / aileron, the present application belongs to the technical field of aerospace manufacturing.The present application solves the problem that the high-temperature service environment of the existing light-weight hypersonic aircraft wing / aileron fuel tank is prone to overheating, stress concentration, and some fuel tanks belong to flow dead zone, which causes the region to break through the thermal protection to form a thermal bridge, seriously affecting the service life of the fuel tank.The multi-module series oil tank is composed of n oil tanks connected by oil pipeline, and is left-right symmetrical structure along the center line L;The side of the oil tank along the height direction is composed of two symmetrical inclined planes.The present application is a multi-module series oil tank for light heat-insulated oil storage wing / aileron.

The utility model discloses a connecting and fixing device, which belongs to the technical field of aeronautical manufacturing and maintenance, and comprises a connecting piece A and a connecting piece B which have the same structure, fixing bases of the connecting piece A and the connecting piece B are used for being fixed on materials needing to be connected, and fastening parts in a hollow triangular prism shape are fixed on the lower parts of the fixing bases of the connecting piece A and the connecting piece B; the difference is that the size of the fastening part of the connecting piece B is smaller than that of the connecting piece A, so that the connecting piece B can be sleeved in the connecting piece A and then is fixedly connected through a fastening screw. According to the utility model, the situation that a common angle section needs to be fixed at a fixed angle in advance is avoided, the effective utilization of the space in the operation process is improved, and the connection mode has no limitation requirement on the space of the two materials.

The invention discloses a spaceflight core process digital asset uplink right confirmation and transaction method based on expert process data, and relates to the technical field of spaceflight manufacturing and digital assets, in particular to the spaceflight core process digital asset uplink right confirmation and transaction method based on the expert process data. According to the method, multi-modal process data of an expert is collected in real time through wearable equipment, a process fingerprint is generated by using a processing model based on a world model architecture, and rare digital assets are judged by calculating a uniqueness score and an emotional value score; the process fingerprints of the rare assets are subjected to homomorphic encryption uplink to generate NFT, ownership completely belongs to experts, and transaction income is automatically distributed according to a preset proportion; and meanwhile, a hardware fusing protection mechanism for illegal operation is arranged. According to the invention, security right confirmation, capitalized transaction and value sharing of expert process data are realized, and inheritance and innovation of a spaceflight core technology are effectively promoted.

This invention belongs to the field of aerospace manufacturing technology and discloses an apparatus and method for preparing ultra-wide equiaxed fine-grained thin plates. The apparatus includes a worktable, a rotary table, a motor, a support arm, and a movable pressurizing mechanism fixed to the support arm. The motor drives the rotary table to rotate synchronously with the original billet. High-speed rotation, high-frequency vibration, and ball stirring, along with thickness extrusion of the rotating billet, induce a point-to-point kneading effect on both sides of the hot semi-solid, semi-viscous material, resulting in grain breakage, dynamic recrystallization, and superplastic thinning to obtain ultra-wide equiaxed fine-grained thin plate billets. This invention overcomes the technical difficulty of preparing ultra-wide plates using existing thin-plate rolling processes. Ultra-large billet preparation can be achieved with minimal equipment tonnage, making it highly applicable and versatile in engineering applications. The billet preparation process involves recrystallization and softening, eliminating the need for separate heat treatment, resulting in a simple process and low cost.

The invention belongs to the technical field of aerospace manufacturing, and provides a narrow and small space reverse hole guiding device which comprises an outer plate, an inner plate, an inner plate and a guide rod. The inner plate is opposite to the outer plate, a movable guide column is arranged at one end of the inner plate, the other end of the inner plate is fixedly connected with the other end of the outer plate, and a certain distance is formed between the outer plate and the inner plate; and the tightening bolt is mounted on the inner plate and is used for fixing a part. The technical problem that reverse hole guiding is difficult in an existing narrow space is solved, and reverse hole guiding operation in a narrow operation space is achieved.

The utility model discloses a screw taking-out device, which belongs to the technical field of aeronautical manufacturing and maintenance and comprises a sleeve, a locking ring, a cylindrical rolling shaft and the like, the cross section of an inner hole of the sleeve is a triangle-like shape formed by connecting three linear sections and three arc sections at intervals, the locking ring is provided with three strip-shaped cylindrical rolling grooves, and the cylindrical rolling shaft is arranged in the cylindrical rolling grooves. And the two are combined and then placed and limited in the inner hole of the sleeve. During use, the screw rod is inserted among the three cylindrical rolling shafts in the locking ring, the outer sides of the cylindrical rolling shafts are adjacent to the arc section of the inner hole in a non-extrusion state, the sleeve is rotated, the cylindrical rolling shafts slide to the linear section of the inner hole under the friction force action of threads of the screw rod, the screw rod is clamped by the cylindrical rolling shafts, and the sleeve is continuously rotated to screw out the screw rod. When the screw rod is disassembled, torque applied to the screw rod acts on the axis of the screw rod, the screw rod is prevented from being broken in the rotating and taking-out process, the quality of a product fastened by a bolt is guaranteed, and meanwhile the disassembling work efficiency is not affected.

The application belongs to the technical field of aerospace manufacturing, and discloses a high-performance ceramic matrix composite functional surface for hypersonic transition regulation and control. Based on a numerical simulation method, a hypersonic cone transition process of a microstructure functional surface with different microstructure parameters is predicted, and the influence of the microstructure parameters on the transition position and aerodynamic drag is obtained. The microstructure functional surface design is completed by comprehensively considering the ceramic matrix material manufacturing constraints. The corrugated wall microstructure is manufactured by ultrasonic vibration assisted grinding, and the micro-hole array is processed by femtosecond laser. According to the segmented integrated manufacturing concept, a plurality of simulation cone sample pieces with the microstructure functional surface are processed. The simulation cone sample pieces with the microstructure functional surface are tested in a wide speed range in a hypersonic wind tunnel. According to the wind tunnel test data and the results of the numerical simulation, a high-fidelity data set and a low-fidelity data set are established, a multi-fidelity surrogate model is constructed, the microstructure parameters are subjected to multi-objective optimization, and an optimal solution set is obtained.

The invention discloses a novel forming process method for an aviation flaring guide pipe, and relates to the technical field of aerospace manufacturing. According to the method, the problem of leakage of the guide pipe in service due to introduction of residual stress in a traditional single-time spinning forming process is solved; the method comprises the following steps: performing first flaring pre-forming on the end part of the guide pipe to form a primary flaring conical surface; the formed guide pipe flaring section is subjected to residual stress aging treatment so as to release and homogenize harmful residual stress; secondary spinning finishing is conducted on the flaring section subjected to stress treatment, so that microscopic deformation is corrected, and the final geometric accuracy is obtained; comprehensive detection including performance is carried out on the finished conduit; through a closed-loop process chain of forming, stress relief and finishing, the residual stress state and geometric accuracy of the flaring guide pipe are actively controlled and optimized, and the sealing reliability and long-term service stability of the flaring guide pipe are remarkably improved.

This invention relates to the field of aerospace manufacturing, specifically to an intelligent defect detection method for automated fiber placement of composite materials, comprising the following steps: S1: Obtain a training dataset, divide the training dataset into a training set, a test set, and a validation set according to a preset ratio, and obtain the constructed composite material fiber placement defect detection model; S2: Using the training dataset, train the composite material fiber placement defect detection model with the FM-IoU loss function as the optimization objective; S3: Evaluate the performance of the trained composite material fiber placement defect detection model on the validation set, and perform hyperparameter tuning or model fine-tuning based on the evaluation results; S4: Test the trained composite material fiber placement defect detection model and output the defect detection results; thereby improving the accuracy and engineering applicability of fiber placement defect detection.