51 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 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 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 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 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.

Device for channeling aerodynamic flow and recovering wind energy generated by the car. Project description: Moving freely and quickly wherever you want in the world is man's greatest innovation. But how can you move around on a dead planet? Without a major revolution in the automotive sector, our earth is increasingly in danger. The electrification of vehicles has started this revolution, but it is not enough. The use of immense quantities of rare earths greatly mitigates the true ecological goal of the electric car. My patent aims to respond to a real challenge of decarbonizing the car in an efficient and sustainable manner. It is therefore based on a 100% electric vehicle base with a profound modification of the front space (under the hood). Indeed, instead of the air coming into contact with the grille frontally, it is channeled through a tunnel.It is designed to disturb the aerodynamic flow as little as possible and to lower the overall drag of the car as much as possible. In the middle of the hood, the two openings will converge to form a large central passage. These openings are not there by chance, their purpose is to house the blower-generators on the one hand and secondly to reduce drag as much as possible. To return to the blowers, they constitute the basis of my invention and are inspired by the aeronautical industry. They were designed to be as compact as possible but also as efficient as possible by integrating the alternator within it. Their purpose is to recharge the car with only the force of the wind it produces while driving.Thanks to this technology, our cars of tomorrow equipped with this system could therefore travel hundreds of kilometers without recharging, but the real feat is that this is done with a very small battery and a cost of use per 100 km of the symbolic order. Despite this, the blowers do not work at all speeds and start to become effective from 50 km / h and become truly active above 100 km / h, in short where the EV is currently in the most difficulty. The system can be deployed in two different ways, the first via the retrofit of already existing electric cars and the second with the design of a car designed around Thoréole. In short, we can easily define my innovation as a wind range extender.

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 provides a co-bonding forming preparation method for improving profile precision of a composite cabin door. The surface precision and structural performance of an aircraft cabin door assembly (6) are improved by optimizing a manufacturing process. According to the independent symmetrical laying layer design, the cabin door body (5) and the reinforcing base plate (4) are manufactured separately and then assembled together in a precise assembly mode. The independent manufacturing technology can reduce skin surface deformation and residual stress, allows manufacturing flexibility of respective components, reduces manufacturing errors, improves the surface precision of the cabin door component (6) and prolongs the service life of the cabin door component (6). In addition, independent manufacturing and precise assembly can be carried out through the partition layering design, the profile precision and the structural integrity of the aircraft cabin door are remarkably improved, and the development of composite materials in the aviation industry can be further promoted by combining an intelligent manufacturing technology and advanced materials subsequently.