15 results about "Aerospace manufacturing" patented technology

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.

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 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.

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.

This invention provides a processing apparatus for aerospace parts, relating to the field of aerospace manufacturing technology. It includes: a worktable, an extrusion mechanism mounted on the worktable, a shaping mechanism located on the top working surface of the worktable, and a feeding device connected to the shaping mechanism. A support plate is provided at the top of the worktable, and a mounting seat is provided on the bottom working surface of the support plate, the mounting seat being embedded in the worktable. A drive mechanism is provided on the support plate, and the output end of the drive mechanism is connected to the extrusion mechanism. The shaping mechanism is located directly below the extrusion mechanism and can be tightly connected to it. A control terminal is provided on one side of the support plate, and the control terminal is used to control the working status of each component. This invention ensures precise guidance of the pressure plate during the extrusion process, making the extrusion action more stable and accurate. Furthermore, the sealing ring increases the sealing performance of the extrusion operation, ensuring the quality and precision of the formed parts.

This application discloses a blind hole machining device for aerospace components, comprising: a bracket with a rectangular frame structure for providing support; a fixed plate with its first end fixedly connected to the end of the bracket; a pin detachably connected to the second end of the fixed plate; a movable plate with its first end slidingly engaged with the inner side of the fixed plate; a guide plate detachably connected to the second end of the movable plate, having a guide hole in its center, and the guide hole being coaxial with the pin; a guide post with both ends fixedly connected to the bracket, the movable plate having through holes for the guide post to pass through, the guide post being configured to guide the movement of the movable plate; and a positioning unit capable of securing the first end of the movable plate. This application overcomes the industry challenge of coaxiality control in blind hole machining of aerospace components through innovative designs such as cross-side guidance and modular adaptation, combining high precision, high versatility, and ease of operation, providing efficient and reliable process equipment support for aerospace manufacturing.

This invention relates to the field of aerospace manufacturing technology, specifically to a processing equipment for integrated molding of aerospace shells. The equipment includes a base and a mounting base, with the mounting base fixedly mounted on the base. Multiple piston holes are formed on the upper surface of the mounting base, and a punch is coaxially mounted in each piston hole. The upper end of the punch extends beyond the piston hole. A flexible pad is provided on the upper side of the mounting base, with its lower end face fitting against the upper end face of the punch. The flexible pad has through holes matching the number of punches. A spherical groove is coaxially formed on the upper surface of the punch, and a ball bearing is rolled within the spherical groove. This invention, by using a flexible pad, avoids direct contact between the punch's sharp corner and the sheet metal, preventing localized plastic deformation of the sheet metal. Simultaneously, the flexible pad provides elastic support to the sheet metal, preventing gaps between adjacent punches from easily forming micro-wrinkles in the sheet metal, thus improving the molding quality of the aerospace shell.

This invention discloses a single-point micro-area metallurgical riveting device and method based on vacuum electron beam melting and die casting densification, belonging to the field of advanced aerospace manufacturing and material joining technology. The single-point micro-area metallurgical riveting device includes a motion positioning module, a vacuum melting injection module, a die casting densification module, a tray module, and a vision inspection module. A first station is formed below the vacuum melting injection module, and a second station is formed below the die casting densification module. The motion positioning module drives pre-made grooves on the workpiece to switch between the two stations. The tray module is movable and provides support and cooling for the workpiece. This invention achieves sequential completion of molten metal injection and die casting densification through multi-station collaboration, forming a metallurgically bonded riveting structure within the pre-made grooves, obtaining high-density, high-strength connection points, suitable for high-performance automated connections of thin-plate structures.

This application relates to the field of aerospace manufacturing process equipment technology, specifically to a flexible paperclip winding machine for anodizing aerospace aluminum alloys, and particularly to a specialized tooling with adjustable dimensions for the efficient manufacture of paperclip fixtures. The positioning block is adjustable, allowing for rapid adaptation to the manufacturing needs of paperclip fixtures of different specifications; the guiding system ensures the straightness of the aluminum wire, and mechanical forming guarantees product consistency; manual operation is simple, reducing the skill requirements for operators; it can handle aluminum wire materials of different diameters and is suitable for various aerospace aluminum alloy materials; the winding machine adopts a modular design, allowing for quick replacement of key components, reducing equipment maintenance time and costs.

This invention belongs to the field of aerospace manufacturing technology, and specifically relates to a method for precision machining of small holes in the steel ball seat of an electromagnetic valve. This invention utilizes electrical discharge machining (EDM) for rough machining to obtain a pre-hole, and then uses femtosecond laser machining (FLM) for finishing machining to obtain the final small hole. This solves the problems of existing machining technologies, such as the inability to guarantee the dimensional accuracy and roundness of the small hole, the inability to guarantee the quality of the sharp edge of the small hole opening, and the presence of surface defects such as remelted layers and microcracks on the hole wall surface. At the same time, it avoids the high processing costs and low production efficiency associated with using only femtosecond laser machining.

This invention proposes a low-density polyurethane composite material for aircraft skin brackets and its preparation method, belonging to the field of aerospace manufacturing technology. The composite material is obtained by mixing component A and component B and then curing them. Component A, by mass percentage, includes: 50%-80% polyether polyol mixture, 10%-30% hollow glass microspheres, and 1%-10% additives; component B includes an isocyanate mixture. The preparation method includes steps such as preparing component A, preparing component B, mixing and casting, curing and molding, CNC machining, and surface treatment. This invention achieves a material density comparable to wood (0.60-0.70 g / cm³) through the composite of hollow glass microspheres and a polyurethane matrix. 3 This invention also possesses excellent dimensional stability, corrosion resistance, flame retardancy, and recyclability, completely solving the technical problems of traditional wooden brackets such as easy deformation and cracking, short service life, and poor fire resistance. The bracket prepared by this invention can be widely used in processes such as painting, assembly, storage, and transportation of aircraft skin, and has significant economic benefits and environmental value.

This application provides a method, apparatus, and system for high-precision assembly quality control of aerospace composite materials, relating to the fields of aerospace manufacturing assembly and intelligent control technology. The method includes: acquiring the initial shape deviation between the current shape of the section to be assembled and the target shape; controlling each actuator in the actuator array to apply test loads in a preset order, recording the displacement data of each actuator, and identifying the local response matrix between the actuators; inputting the local response matrix into a pre-constructed joint Bayesian prior model to calculate the global response matrix of the section to be assembled, and calculating the optimal actuator control force vector based on the initial shape deviation and the global response matrix. The method, apparatus, and system for high-precision assembly quality control of aerospace composite materials provided by this application can fully utilize the sensing function of the actuators to quickly identify the stiffness characteristics of each section without adding additional external measurements, thereby achieving efficient and high-precision shape control.

This invention discloses a laser processing system for aerospace composite materials, relating to the field of aerospace manufacturing technology. The system includes a processing table, an adjustment mechanism, a processing mechanism, and an ultrasonic vibration mechanism. The processing table includes a worktable for providing space for material placement. The invention provides a mounting position for the ultrasonic vibrator via a mounting sleeve, and a telescopic assembly is symmetrically mounted on the mounting sleeve. A telescopic plate is telescopically connected to the inner side of the telescopic assembly, and a vibration ring is mounted at the bottom. This facilitates the generation of high-frequency vibration by the ultrasonic vibrator, which is then transmitted through the mounting sleeve, telescopic assembly, and telescopic plate to the vibration ring. The vibration ring fits snugly against the processing location, allowing for simultaneous high-frequency vibration operation during processing. This helps reduce the material's hardness and viscosity, promotes the removal of slag and fumes, reduces heat accumulation, and improves processing quality and efficiency.

This application provides a multi-level control method and system for workpiece grinding in the aerospace field, belonging to the field of aerospace manufacturing technology. The method includes: determining a first control strategy for the grinding equipment based on the material properties of the target workpiece and the grinding task requirements; acquiring physical state signals of the grinding area of ​​the target workpiece when the grinding equipment is controlled based on the first control strategy; the physical state signals include one or more of grinding force, grinding temperature, vibration signals, acoustic emission signals, and workpiece surface morphology; selecting a control strategy generation mode based on the deviation index between the physical state signals and a preset target state of the target workpiece; generating a target control strategy based on the control strategy generation mode; and controlling the grinding equipment to grind the target workpiece based on the target control strategy. The multi-level control method and system for workpiece grinding in the aerospace field provided by this application achieves precise control of the aerospace workpiece grinding process.

This invention relates to the field of aerospace manufacturing technology, addressing the technical problems of limited measurement range, insufficient ability to capture details of complex curved surfaces, and susceptibility to environmental factors inherent in single measuring devices. Specifically, it relates to a method and apparatus for three-dimensional measurement of the overall shape of a large aircraft based on multi-component collaboration. The method includes acquiring and registering the shape contour point cloud to obtain local shape contour point clouds of the entire aircraft from different local perspectives; registering the local shape contour point clouds and constructing a sparse pose map; and registering the local shape contour point clouds acquired from different local perspectives based on the sparse pose map to generate a complete overall shape contour point cloud of the large aircraft. This invention can register high-precision local point cloud data of the aircraft acquired by the measuring device, automatically generating point cloud data for the surface of large aircraft, thereby achieving high-precision and high-efficiency measurement of large and complex shapes, and further improving the manufacturing and assembly quality of aircraft.