26 results about "Aeronautical industry" patented technology

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 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 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 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.

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.

FIELD: radio engineering industry; instrument engineering; aviation industry.SUBSTANCE: invention relates to lacquer protective compositions and can be used in the radio engineering industry, instrument engineering, aviation industry, and other sectors of the national economy for the anti-corrosion protection of aluminum, copper, iron, and their alloys. A lacquer composition is proposed, including 0.6-1.10 g / l of 50% butanolized melamine-formaldehyde resin K-421-02, 0.6-1.10 g / l pentaphthalic varnish “ПФ-060”, 0.78-1.05 g / l triethylamine, 15.8-16.5 g / l resin “BMA”-0120, which is a solution in isopropyl alcohol hydrolyzed a product consisting of a maleinated mixture of linseed and dehydrated castor oils, 0.025-0.03 g / l of manganese sulfate and water up to 1 liter.EFFECT: invention provides a protective composition capable of forming a corrosion-resistant transparent coating on the surface of metals, while reducing the amount of solvents in the composition.1 cl, 2 ex

The application discloses a preparation method of fine-grain low-noise GH4720Li alloy small-size rod, and specifically comprises the following steps: high-temperature homogenization treatment is conducted on a GH4720Li alloy ingot; air holes on a clean surface are turned, a risk area is cut off, upsetting and drawing are conducted, a blank rod is cut off at a rotten head, scale on a surface after bright forging is turned, surface defects are ground, the blank rod after grinding is cut, is sleeved, hot extrusion is conducted on the sleeved rod, roll straightening is conducted by using extrusion residual heat, a black skin rod is obtained, the black skin rod is subjected to light treatment by adopting abrasive belt polishing, surface defects are ground, and stainless steel component rotten heads at two ends of the rod are sawn off, and the method is completed.The prepared GH4720Li alloy small-size rod has a grain size between 8-10 levels, a flaw detection noise level between Phi 0.8-(9-18) dB, and an excellent surface quality, and is accurately controllable in diameter; and the GH4720Li alloy small-size rod has a good application prospect in the fields of aviation industry, energy and petrochemical industry.

The invention relates to the technical field of aviation industry, and provides a wide-working-condition turbine flow field prediction method of a physical constraint neural network, and the method comprises the steps: S1, constructing a wide-working-condition variable-blade-shape CFD simulation database; s2, preprocessing data, firstly normalizing each parameter, then disorganizing sample sorting, then converting a parameter format into a binary format, and dividing into a training set and a test set; s3, a neural network driven by data is constructed and pre-trained, mixed physical constraints are constructed, the mixed physical constraints comprise a correction Bernoulli equation representing non-viscous fluid and a turbulence model correction term representing viscous fluid, and total physical loss is obtained through weighted fusion; and then, a trained neural network is obtained through model training, a final physical constraint neural network is obtained, the physical constraint neural network is applied to wide-working-condition turbine flow field prediction, and a final prediction result is obtained. According to the method, high-precision, high-efficiency and high-physical interpretability flow field prediction is realized under the incoming flow condition of a wide working condition.

The invention discloses an integrated development method and system for civil aircraft multi-modal data, and the method comprises the steps: receiving a model file, carrying out the file format conversion, carrying out the quality verification of the converted model file, and storing the model file passing the quality verification in a target database; the method comprises the following steps: acquiring civil aircraft element data, selecting a corresponding data integration mode according to a data type to perform data acquisition, performing integrity verification on the acquired data, and storing the acquired data passing the verification into a target database; and converting the data table in the target database into a service interface for external service so as to be called by downstream software. According to the method, unified integrated development of file data in various data formats in aviation industrial software can be effectively processed, the data collaboration efficiency in cross-system collaboration operation is effectively improved, and the data utilization efficiency is enhanced.

The utility model relates to the technical field of aviation, in particular to an aircraft nose landing gear steering testing mechanism which comprises a box body, a top seat is arranged on the top end wall of the box body, a supporting column is rotatably connected to the middle portion of the inner bottom wall of the box body through a bearing, and the top end wall of the supporting column extends into the top seat and is provided with a top plate. A connecting plate is connected to the outer wall of the supporting column in an interference fit mode, a hydraulic oil cylinder is arranged on the inner bottom wall of the box body, an electromagnet is arranged on the driving top end wall of the hydraulic oil cylinder, a sensor is arranged on the outer wall of the hydraulic oil cylinder, a rail is arranged on the inner bottom wall of the box body, and a plurality of connecting rods are arranged on the bottom end wall of the top plate. And rollers are arranged on the bottom end walls of the connecting rods, and the rollers are connected to the rails in a sliding mode. According to the utility model, the rotation angle of the supporting column is recorded through the sensor, so that the data of the rotation angle of the nose landing gear of the airplane can be accurately obtained, an accurate quantitative index is provided for the evaluation of the steering performance of the nose landing gear of the airplane, and the requirement of the modern aviation industry on high-precision performance detection of airplane parts is met; the control precision of the aircraft sliding on the ground can be improved, and the flight safety is guaranteed.

The present application relates to the field of complex equipment development in the aviation industry, in particular to a SysML heterogeneous model integration method, aiming to solve the problems of data island and collaboration barriers caused by model heterogeneity. Based on a unified data management platform, the method realizes the normalization of multi-source SysML models, the unified integration and scheduling of heterogeneous models, the high-precision joint simulation of virtual and real systems, and the multi-dimensional intelligent analysis of simulation results through five core steps of intercommunication and synchronization, including SysML model analysis, functional unit conversion, multi-source heterogeneous model integration, virtual-real fusion test simulation, and comprehensive analysis and iterative optimization. The platform is equipped with four special function modules, which are compatible with multiple modeling tools and form a closed-loop design system through technologies such as full-factor mapping, middleware integration, gradient descent method parameter calibration, and three-dimensional visualization analysis. The method has been verified effective in the development of aircraft engines and airborne equipment, significantly improving model reuse rate and cross-disciplinary collaboration efficiency, shortening design optimization cycle, and providing replicable technical support for the implementation of MBSE in the aviation industry.

The application discloses a kind of wear test devices for actuating cylinder reciprocating dynamic seal, belong to the technical field of actuating cylinder sealing wear test equipment, including main frame body, and the test mechanism of movable connection on main frame body, one side of main frame body is provided with replaceable actuating cylinder structure to be measured, test mechanism includes moving rod, and the upper and lower ends of moving rod are respectively provided with limit component and counterweight component, connecting piece is provided on moving rod, and the one end of piston rod in connecting piece and actuating cylinder structure to be measured is hinged, by the application, the wear of actuating cylinder reciprocating dynamic seal can be tested, can satisfy the conventional movement of actuating cylinder output end under simulated static state and the non-axial force that actuating cylinder output end is subjected to under dynamic state, and the reliability of sealing ring in actual work can be comprehensively evaluated in combination, is verified from multiple dimensions, is favorable for discovering potential risk, and better meet the requirement of safety specification in aviation, industry and other fields.

The invention relates to the technical field of aviation industry, and provides a numerical simulation accelerated convergence method, system and device based on artificial intelligence prediction and a medium, and the method comprises the steps: S1, configuring a numerical simulation network and constructing a connection network; s2, constructing a prediction network, and constructing a U-Net main body network comprising an encoder and a decoder; integrating a space-time attention module in the U-Net to enable the network to learn a nonlinear mapping relation from the initial stage of calculation of oscillation to the later stage of convergence, thereby outputting a prediction flow field with a complete physical structure, and obtaining an optimized prediction network; s3, numerical simulation and calculation acceleration convergence are carried out, and a prediction result is obtained through the prediction network; and finally, the connection network writes the prediction result back to the numerical simulation network, covers the current state of the solver and guides the solver to restart iteration based on a high-quality initial field to realize accelerated convergence. According to the method, the prediction network is created, the artificial intelligence prediction network is used for replacing the convergence process of traditional numerical simulation calculation, and the convergence process of numerical simulation is remarkably accelerated.

The invention discloses a multi-modal data storage method and system based on aviation industry. The method comprises the following steps: receiving multi-source data through a data integration layer, identifying a file type through file header information, an extension name or a content sampling mode of the multi-source data, pre-extracting file basic metadata, and generating a temporary metadata record; generating a classification label by combining the data type, the business field, the access frequency and the security level of the multi-source data, and recording a classification log; carrying out analysis based on a predefined analysis strategy in unified data modeling; and the analyzed data is converted into a target data model according to a predefined mapping strategy in unified data modeling, data cleaning and verification are completed, a data entity conforming to unified data modeling specifications is created, and a storage medium is automatically selected according to a classification label. According to the method, storage management of cross-professional data in the aviation industry can be realized, and the data management capability in the aviation industry design and manufacturing process is comprehensively improved.

The invention provides a heat-resistant high-strength transparent polyamide material as well as a preparation method and application thereof. The preparation method of the heat-resistant high-strength transparent polyamide material comprises the following steps: mixing raw materials including diamine, binary acid, water and a catalyst, heating, and carrying out pre-polycondensation and final polycondensation to obtain the heat-resistant high-strength transparent polyamide material. According to the heat-resistant high-strength transparent polyamide material prepared by the invention, the mechanical strength and thermal performance of the material are improved while high transparency is maintained, the light transmittance is greater than or equal to 90%, the glass transition temperature is greater than or equal to 140 DEG C, the tensile strength is greater than or equal to 55 MPa, transparency can still be maintained at a higher use temperature, and the heat-resistant high-strength transparent polyamide material has relatively good comprehensive performance and is suitable for industrial production. The packaging film can be applied to the fields of aviation industry, automobile manufacturing, electric appliance industry, medical instruments and food packaging.

The utility model discloses a kind of measuring appliances of aero-engine guard plate, belong to the field of aeronautical industry manufacturing.The measuring appliance of the aero-engine guard plate includes the upper part and the lower part of mortise and tenon connection, lower part is set below upper part, the lower part is used to place aero-engine guard plate;Radially be equipped with a dovetail notch on the upper part, a blind groove is respectively equipped on the two sides groove wall of dovetail notch, the blind groove is as tolerance zone notch;The upper surface of lower part has a dovetail tenon above, the dovetail tenon and dovetail notch cooperate to form dovetail guide rail, upper part is along dovetail guide rail sliding to measure height.The device can save the measurement cost of guard plate class parts, to improve measurement efficiency and quality qualification rate.

The present disclosure provides an improved circular force generator having a housing configured to reduce vibrational forces transmitted to an aircraft structure. Additionally, the disclosed configuration provide the necessary safety redundancies required by the aviation industry. The circular force generator includes mounting point around the exterior of the CFG housing and a central mounting point thereby providing redundant mounting points.

The application relates to an automatic surface treatment and inspection method and system for an aviation high-pressure pipeline joint. An intelligent processing system is introduced, combined with data acquisition, processing, decision support, and automatic surface detection and maintenance of the high-pressure aviation joint. An intelligent algorithm and a mechanical arm and an industrial robot are combined to detect the surface of the high-pressure aviation joint, identify and analyze surface defects and other abnormalities, and construct corresponding abnormal alarm and defect part automatic maintenance schemes, replacing manual inspection work, batch inspection and maintenance, greatly improving the efficiency, quality and consistency of the surface treatment of the high-pressure aviation joint, reducing human error, and prolonging the service life of the joint. It is expected to be widely used in the aviation industry to improve the efficiency and reliability of maintenance and repair. The workshop terminal provides surface defect guidance for workers, visually displays surface abnormal images, guides workers to perform surface inspection, and realizes efficient surface maintenance and inspection.

The invention relates to the technical field of aviation industry, and provides a blade grid simulation grid intelligent generation method, system and device without operation of a user and a medium, and the method comprises the steps: S1, constructing a large language model; s2, obtaining a demand target; s3, decomposing the demand to obtain a grid demand parameter and a simulation demand parameter; s4, script generation and verification, including self-programming and verification; s5, performing grid generation and grid quality evaluation, and driving a grid generation tool to perform grid generation; after the initial grid is generated, according to a feedback grid quality report, the large language model gives a fine tuning instruction, and iteration is carried out until a preset quality standard is reached; s6, simulation execution and feedback modification are carried out, simulation calculation is started, and a simulation result file and a monitoring process file are obtained; and obtaining a final grid simulation result. According to the method, grids are generated according to requirements through a large language model, grid quality is optimized, simulation calculation is performed, grid quality optimization is fed back, and the problems that grid division depends on experiences of engineers, and consumed time is too long are solved.