43 results about "Aerospace materials" patented technology

The invention belongs to the technical field of aeronautical materials, and particularly relates to a PEI modified material containing a high-temperature composite dispersion system as well as a preparation method and application of the PEI modified material. The PEI modified material containing the high-temperature composite dispersion system provided by the invention is prepared from the following raw materials: polyetherimide resin, titanium dioxide, carbon black and dispersing agents (a coupling agent and polyamide wax). The PEI modified material containing the high-temperature composite dispersion system provided by the invention can realize efficient and uniform dispersion and color regulation and control of pigments in a high-viscosity and strong-polarity system, and has excellent heat resistance, mechanical property and flame retardant property, and interior structural parts prepared from the PEI modified material meet the comprehensive requirements on light weight, attractiveness and durability in the aviation field.

The invention discloses a thermal barrier coating temperature and thickness coupling measurement method, system and device and a storage medium, and relates to the technical field of aeronautical material testing. The method comprises the following steps: calibrating a mapping relation among parameters: preparing a series of standard samples with different thicknesses, collecting phosphorescence spectrums of the samples with the standard thicknesses at different temperatures, and calibrating the mapping relation among the parameters; the phosphorescence spectrum of the to-be-detected sample is collected, the phosphorescence intensity ratio of 457 nm to 483 nm is calculated, and the phosphorescence intensity of 586 nm is read; calculating the temperature of the to-be-measured sample: calculating the temperature of the to-be-measured sample according to the measured phosphorescence intensity ratio and the intensity ratio-temperature mapping relation; and calculating the thickness of the to-be-measured sample: determining a change curve of the phosphorescence intensity along with the thickness according to the calculated temperature of the to-be-measured sample, and calculating the thickness of the phosphorescence coating in combination with the measured phosphorescence intensity. The method and the system can realize non-contact synchronous online measurement of the temperature and the thickness of the thermal barrier coating.

The present invention provides a rubber component with excellent corrosion resistance, and semiconductor manufacturing-related equipment using the same. [Solution] A rubber member comprising a halogen-based rubber containing at least one selected from the group consisting of chlorine, bromine, and iodine, wherein the rubber member is at least one selected from the group consisting of building materials, mobility materials, aerospace materials, semiconductor materials, and information and communication materials, and is a rubber member that comes into contact with corrosive substances.

The invention relates to the technical field of aeronautical material detection, in particular to an aeronautical composite material physical property quality detection device which comprises a machine body, a lifting seat installed on the machine body, a lower clamp installed on the lifting seat and an upper clamp installed on the top of the machine body. Fixing blocks are fixedly connected to two workbenches of the bidirectional sliding table, and storage shells are fixedly connected to the upper ends of the two fixing blocks. When the aviation carbon fiber composite material is subjected to physical property quality detection through a tension testing machine, two ends of each sample can be automatically bonded with a metal sheet through glue, the operation is simple, time and labor are saved, meanwhile, the glue can be uniformly smeared on the metal sheet so as to ensure the bonding effect between the metal sheet and the sample, and the production efficiency is improved. And the glue can be accelerated to solidify through proper hot air heating, so that the detection efficiency and the detection effect of the aviation carbon fiber composite material are improved.

This utility model discloses a strength testing device for aerospace materials, including a testing frame, a testing table, a pressure testing machine, and an adjustment assembly. The testing table is rotatably mounted on the testing frame. The adjustment assembly is installed inside the upper part of the testing frame. The pressure testing machine is installed on the adjustment assembly and corresponds to the testing table. The adjustment assembly includes a forward / reverse motor, a lead screw, and a mounting base. The lead screw is rotatably mounted inside the upper part of the testing frame. The forward / reverse motor is installed on one side of the testing frame, and its output shaft is connected to one end of the lead screw. The mounting base is slidably mounted on the upper part of the testing frame and is threadedly connected to the lead screw. The pressure testing machine is installed on the mounting base. This utility model relates to the technical field of aerospace composite material testing equipment. This device allows for convenient and flexible adjustment of the material testing position and easy cleaning and collection of generated debris, improving the flexibility and convenience of the testing process.

The application discloses a laser speckle deformation thermodynamic displacement measurement method and system based on DL-SpeckleNet, and belongs to the cross technical field of optical measurement and deep learning. The method first constructs a multi-medium laser speckle image dataset under a temperature gradient of -50 DEG C to 800 DEG C and completes fine annotation, and after pretreatment such as gray scale conversion, joint denoising and data enhancement, a DL-SpeckleNet light-weight network is constructed by fusing a multi-scale feature extraction module and an attention enhancement unit; stress and strain reference data are generated by a MATLAB-ncorr algorithm, cross-validation is completed by a Python-ncorr algorithm, and the network is trained with the reference data as labels; a laser speckle interference experiment platform is built to collect measured data; finally, the pretreated speckle image to be measured is input into the optimized model, numerical output of thermodynamic displacement and visualization of stress and strain nephograms are realized, the environmental dependence of the ncorr algorithm is broken, high-precision and rapid measurement of material thermodynamic displacement in an extreme environment is realized, and the method is suitable for thermodynamic coupling deformation detection in the fields of aerospace and material science.

The application discloses a kind of laser cutting device for aerospace material processing, specifically relates to laser cutting technical field, including workbench, the top of the workbench is equipped with three-axis moving platform, laser cutting head is installed on the Z-axis of three-axis moving platform, the top of the workbench is close to laser cutting head one side and is equipped with smoke hood, the track of the X-axis of three-axis moving platform is connected with the smoke hood by connecting arm, the negative pressure chamber can form negative pressure by smoke inlet hose when fan is opened, and the negative pressure chamber is communicated with suction dust collection chamber by lower movable cylinder and annular filter screen, therefore, the flue gas on the workbench will pass through smoke inlet hole, smoke hood and through hole into dust collection box in turn, and then be extracted to fan by smoke inlet hose and be sprayed from smoke outlet hose, main guide tube, branch guide tube and V-shaped nozzle, to further aerate the water flow outside the radiator tube body, so as to quickly take away the heat of the radiator tube.

The invention provides a method, a device and equipment for constructing a salt mist sedimentation rate model of an aerospace material, and relates to the technical field of artificial intelligence, the model construction method comprises the following steps: inputting obtained salt mist sedimentation parameters into a preset initial model to obtain an initial sedimentation rate prediction result; obtaining a dynamic constraint result through dynamic constraint according to the growth rate coefficient, the inhibition coefficient, the maximum settlement rate and the initial settlement rate prediction result; according to the dynamic constraint result and the number of the sampling points, obtaining a stability constraint result through stability constraint; according to the dynamic constraint result and the stability constraint result, a settlement constraint matrix is obtained through automatic differentiation; generating updated parameters according to the settlement constraint matrix and the current parameters of the initial model, and updating the initial model according to the updated parameters to obtain a salt mist settlement rate model. According to the method, the accuracy of salt spray corrosion evaluation of the aerospace material is improved.

To provide a member excellent in chemical resistance, a method for manufacturing the same, and a semiconductor manufacturing-related device.SOLUTION: A member in which at least a part of the surface of the material (a) is laminated with a carbon material, wherein the member is at least one selected from the group consisting of a member for construction and decoration, a member for mobility, an aerospace member, a semiconductor member, and an information communication member.SELECTED DRAWING: None

The application discloses a kind of based on CA-MLL two segment reasoning aerospace material crack image detection method, comprising:1, using multi-scale adaptive feature extraction network to the image is handled, and the visual feature map of different scales is extracted;2, based on the visual feature map, generate multiple candidate defect regions with visual features;3, the crack data text prompt word is converted into text feature vector, the visual feature of candidate defect region is aligned with text feature vector across modal characteristics, and the semantic similarity of each candidate defect region and text prompt word is calculated;4, the defect region visual feature corresponding to the highest semantic similarity is input into multi-modal decision model, and the final crack category of candidate defect region is determined by multi-modal decision model, and crack classification result is output.The application improves the precision and accuracy of aerospace material crack detection, overcomes the characteristics that labeling is time-consuming and laborious in traditional defect detection, and model generalization ability is poor.

This utility model relates to the field of aerospace material molding die technology, and discloses a molding die for aerospace material processing, comprising an outer mold frame with a cavity inside; and an inner mold rotatably disposed within the cavity of the outer mold frame. A power drive component is provided on one side of the outer mold frame, which drives the inner mold to rotate within the cavity. The top and bottom sides of the inner mold both have molding cavities, which provide chambers for die casting of aerospace materials. In this utility model, when the outer upper mold downwards to die cast aerospace materials onto the inner mold, the upper mold abuts against the tops of the two vertical rods above the inner mold, causing the hollow cylinder to push downwards and eject the molded aerospace materials from the molding cavity below the inner mold, thus achieving demolding of the molded aerospace materials in the lower molding cavity. This allows for simultaneous die casting of aerospace materials and demolding of the previous aerospace material.

The application provides a salt mist deposition rate model construction method, device and equipment of aerospace materials, relates to the artificial intelligence technical field, and the model construction method comprises the following steps: inputting the obtained salt mist deposition parameter into a preset initial model to obtain an initial deposition rate prediction result; obtaining a kinetic constraint result through kinetic constraint according to a growth rate coefficient, an inhibition coefficient, a maximum deposition rate and the initial deposition rate prediction result; obtaining a stability constraint result through stability constraint according to the kinetic constraint result and the number of sampling points; obtaining a deposition constraint matrix through automatic differentiation according to the kinetic constraint result and the stability constraint result; generating an update parameter according to the deposition constraint matrix and the current parameter of the initial model, updating the initial model according to the update parameter, and obtaining a salt mist deposition rate model. The application improves the accuracy of the salt mist corrosion evaluation of aerospace materials.

Disclosed herein is a single piece, integrated, light weighted, cost-effective 3D printed engine for space vehicles. FIG. 5 illustrates an integrated engine that comprises a combustion chamber to burn the fuel, an injector plate (504) to inject the fuel to the combustion chamber, an igniter (502) to ignite the fuel mixture, a nozzle (506) to pass hot gas to produce thrust and cooling channels (508) for regenerative cooling, where all these components are fused to form a single piece integrated engine. The engine of the present invention eliminates the need of assembling the individual components. Further, the engine is additively manufactured with high grade aerospace materials.

The invention discloses a shielding copper mesh suitable for aerospace and a preparation process thereof, and relates to the technical field of aerospace materials, the shielding copper mesh is formed by stamping a high-strength, high-conductivity and corrosion-resistant copper foil as a raw material, the high-strength, high-conductivity and corrosion-resistant copper foil comprises, by mass, 0.3%-0.8% of Cr, 0.2%-0.6% of Ni, 0.01%-0.03% of Ce and the balance Cu, and the purity of Cu is larger than or equal to 99.9%; the surface of the shielding copper net is subjected to silver plating treatment, and the thickness of a plated layer of silver plating is 5-10 microns. According to the shielding copper net suitable for aerospace and the preparation process thereof, the tensile strength and corrosion resistance of a finished product prepared by the preparation formula and the preparation method are remarkably improved, meanwhile, high conductivity is maintained, the problem that strength and conductivity of pure copper foil are difficult to consider at the same time is solved, and the problems that a traditional shielding copper net made of pure copper foil is prone to cracking during punch forming, and the cost is low are solved. And moreover, the shielding effectiveness is stable in extreme environments such as high and low temperatures and salt mist, and the requirement for long service life of aerospace is met.

The invention relates to the technical field of spaceflight material ultra-high temperature performance testing, in particular to a sample clamp for spaceflight metal sheet ultra-high temperature tensile performance testing, which comprises a mounting back plate, a dismounting structure is arranged on the mounting back plate, and the side surface of the dismounting structure is connected with a clamping structure. A traction structure is connected between the dismounting and mounting structure and the mounting back plate, a guide structure is arranged on the clamping structure, a connecting structure is connected to the side face of the dismounting and mounting structure, and an adjusting structure is connected between the side face of the dismounting and mounting structure and the mounting back plate; the accuracy of the clamping position can be improved through the dismounting and mounting structure, different clamping modes can be adopted for different samples through the clamping structure, traction testing can be conveniently conducted on the fixed samples through the traction structure, and the accuracy of the sample fixing position can be further improved through the guide structure; and the situation of falling during clamping and fixing can be avoided through the connecting structure.

The invention discloses a method for cleaning oxide skins on the surfaces of titanium and titanium alloy blanks, and belongs to the technical field of surface treatment of titanium and titanium alloy materials. According to the method, the oxide skin on the surface of the titanium and titanium alloy blank is impacted and cleaned through cavitation jet flow, cavitation bubbles are collapsed near the material surface, transient micro jet flow and shock waves are generated, and the oxide skin can be effectively impacted, torn and stripped from the micro-level. In the process, energy is transmitted through a fluid medium, and non-contact cleaning is achieved; the strength and the toughness of the matrix material are far higher than those of the oxide skin, so that the damage to the alloy matrix is extremely small while the oxide skin can be efficiently removed. According to the method, the titanium alloy material yield can be increased, the production cost is reduced, and the cleanliness of the cleaned surface meets the quality standard of aerospace materials. In addition, the method does not need strong acid and strong alkali, has the advantages of being environmentally friendly, safe, free of pollution and the like, avoids dust harm generated by traditional grinding, and has important significance on cost reduction, efficiency improvement and green production of titanium alloy.

A material for forming an organic film, containing: (A) compound represented by formula (1A); and (B) organic solvent, where W1 represents n1-valent organic group, “n1” represents integer of 2 to 4, X1 represents group represented by formula (1B), “n2” represents 1 or 2, and R1 represents any group represented by formulae (1C). A compound for forming organic film that cures under film formation conditions in inert gas as well as in air, and makes it possible to form organic film that has heat resistance, properties of filling and planarizing pattern formed in substrate, and favorable film-formability on and adhesiveness to substrate; material for forming organic film, containing compound; substrate for manufacturing semiconductor device including material; method for forming organic film, using material; patterning process using material; and aromatic carboxylic anhydride having crosslinkable moiety, expected to be an industrially useful raw material such as electronic materials and aerospace materials.

The invention relates to the technical field of aerospace materials, in particular to a forming method of a honeycomb sandwich assembly and the assembly, the honeycomb sandwich assembly comprises an isolation plate, a sealing rubber strip and a bar, the bar is matched with a core grid on a honeycomb core in shape, the sealing rubber strip is used for sealing the position to be encapsulated on the honeycomb core, and the bar is used for sealing the position to be encapsulated on the honeycomb core. The sealing rubber strip is communicated with at least one vacuum nozzle, the isolation plate is provided with an air hole communicated with the bottom of a core grid at a to-be-encapsulated position, and the bottom of the isolation plate is transversely provided with an exhaust gap communicated with the air hole and the inner side of the sealing rubber strip; according to the invention, the homodromy of an exhaust path and filling power in the potting process is realized, the problem of bubble retention is solved, the compactness and uniformity of potting are obviously improved, and the defects of reduction of structural strength and fatigue life caused by potting bubbles are eliminated.

The invention discloses an ultra-high molecular weight polyethylene fiber as well as a preparation method, application and a material thereof, and belongs to the technical field of high polymer materials. The preparation method comprises the following steps: spinning ultra-high molecular weight polyethylene resin to obtain an ultra-high molecular weight polyethylene fiber aggregate; the ultra-high molecular weight polyethylene fiber aggregate contains a second component; and drafting the ultra-high molecular weight polyethylene fiber aggregate containing the second component to obtain the ultra-high molecular weight polyethylene fiber. The ultra-high molecular weight polyethylene fiber is prepared by the preparation method. The UHMWPE fiber can be applied to military protective materials, aerospace materials, medical materials and marine anchor ropes. The material is prepared from the ultra-high molecular weight polyethylene fiber and comprises a military protective material, an aerospace material, a medical material and a marine anchor rope. The cost can be reduced, static electricity is prevented from being generated by fibers, and broken filaments and floating filaments are reduced.

The invention provides a honeycomb core suitable for a special-shaped profile and a preparation method of the honeycomb core, and relates to the technical field of aerospace materials. The honeycomb core comprises a core body, an upper skin and a lower skin, wherein the upper skin and the lower skin are laid on the upper surface and the lower surface of the core body respectively, and the core body is provided with a special-shaped molded surface capable of being completely attached to the surface of a special-shaped tool. The preparation process of the core body comprises the steps that a cut semi-cured honeycomb core is laid and attached to the surface of a special-shaped tool mold with a specific molded surface, a vacuum bag film is used for coating, the vacuum bag film is vacuumized, and a laid part is obtained; and after curing treatment is conducted on the laid part, the vacuum bag film is removed, and demolding is conducted. By means of the method, the core body has complete hole lattice nodes and can be completely attached to the tool profile, the core is of the structure that honeycomb hole lattices are distributed perpendicular to the normal direction, and when the core is subjected to impact or pressure, stress can be effectively dispersed, and the overall strength and rigidity of materials can be enhanced.

The application discloses a kind of crimped basalt fiber composite material and its preparation method and application, belong to the field of automotive interior and exterior materials.The application is prepared by crimping basalt filament in the process of basalt fiber drawing by increasing rotating high-temperature rod to basalt filament, with a certain curvature basalt fiber, thereby avoiding the influence of high stiffness basalt fiber on the toughness of composite material, solve the problem of insufficient tensile strength and local fracture of fiber composite material in the process of large tensile deformation, with higher tensile strength and elongation at break, suitable for preparing the workpiece with large tensile deformation.Meanwhile, basalt fiber composite material also has excellent environmental protection and flame retardant performance, in addition to can be applied in automotive interior or exterior materials, also can be applied in building materials and aerospace materials, widen the application range of basalt fiber composite material, has very broad application prospect.

The present invention provides a rubber component with excellent corrosion resistance, and semiconductor manufacturing-related equipment using the same. [Solution] A rubber member comprising an olefin-based rubber, wherein the rubber member is at least one selected from the group consisting of building materials, mobility materials, aerospace materials, semiconductor materials, and information and communication materials, and is a rubber member that comes into contact with corrosive substances.

This invention relates to the field of chemical materials technology, specifically to an organosilicon compound functionalized with benzocyclobutene and its preparation method. The structure is shown in formula (I): where n is an integer from 2 to 8; R is one of the following: (a) a substituted or unsubstituted C1-C6 alkyl group; (b) a substituted or unsubstituted aryl group. The compound of this invention, or the polymer obtained by copolymerization with other compounds containing unsaturated bonds, possesses excellent thermal stability, mechanical properties, and dielectric properties, and can be used as a high-temperature resistant material, high-performance composite material, electronic packaging material, and aerospace material; applied to high-frequency PCB boards for 5G / 6G and interlayer packaging of chips, etc. The preparation method of this invention is simple, uses inexpensive and readily available raw materials, has high yield, low cost, and is easy to mass-produce and apply.

The invention belongs to the technical field of high-power power electronics, and discloses a high-power arc wind tunnel rectifying device based on redundant thyristor double-bridge series connection. According to the high-power arc wind tunnel rectifying device based on redundant thyristor double-bridge series connection, redundant backup is achieved through the double-bridge series connection design, and reliability is improved; the harmonic content is reduced through a 30-degree phase shift angle; and a multi-stage passive protection mechanism and an efficient water cooling design are adopted, so that the safety and stability of the system are ensured, and a reliable and efficient rectification solution is provided for the high-power arc wind tunnel. The high-power arc wind tunnel rectifying device based on redundant thyristor double-bridge series connection can be widely applied to high-power arc wind tunnel tests in the fields of aerospace, material science and the like, and has engineering practical value.

The application belongs to the technical field of aerospace material processing, and particularly relates to a heat treatment method for synergistically enhancing the strength and plasticity of TB8 titanium alloy, which comprises the following steps: step S1, solid solution treatment: the solid solution temperature is 780 DEG C to 820 DEG C, the holding time is 30 to 60 min, and cooling to room temperature; step S2, primary aging treatment: the aging temperature is 495 DEG C to 515 DEG C, the holding time is 450 to 540 min, and cooling to room temperature; step S3, secondary aging treatment: the aging temperature is 515 DEG C to 535 DEG C, the holding time is 450 to 540 min, and cooling to room temperature after the holding; wherein the temperature of the secondary aging treatment is higher than that of the primary aging treatment. The application overcomes the technical problem that the strength of TB8 titanium alloy is improved with the plasticity decreased during heat treatment, and realizes the synergistic optimization of TB8 titanium alloy in the three dimensions of high tensile strength, high shear strength and good plasticity.

A molding process for atomic oxygen-resistant composite materials. This invention belongs to the field of aerospace materials technology. This invention solves the problems of composite materials being susceptible to atomic oxygen in aerospace environments, and the tendency for debonding and air bubbles to form during bonding processes. This invention involves first coating an alloy material and a resin-based carbon fiber composite material separately with adhesive, and then bonding the alloy material and the resin-based carbon fiber composite material together to obtain an atomic oxygen-resistant composite material. The use of pressure rollers in this invention effectively ensures uniform adhesive layer thickness. A uniform adhesive layer allows for better adhesion of the metal protective layer to the surface of the resin-based carbon fiber composite material. The molding process of this invention ensures that the atomic oxygen-resistant composite material does not debond in aerospace environments, effectively extending the service life of aerospace equipment.

The application belongs to the technical field of aerospace materials, and provides a continuous boron fiber reinforced aluminum alloy matrix composite material, which is prepared by laying and hot isostatic pressing of boron fiber precursor filaments; the boron fiber precursor filaments comprise boron fiber filaments, a B4C layer, a Ti layer and an aluminum alloy layer which are sequentially deposited on the boron fiber filaments. The application introduces a B4C / Ti double coating layer on the boron fiber filaments, improves the interface bonding strength between the reinforcing boron fiber and the aluminum alloy matrix, and also maintains the integrity of the boron fiber; so that the interface bonding strength and the tensile strength of the continuous boron fiber reinforced aluminum alloy matrix composite material are significantly improved. f Compared with the interface bonding strength and the tensile strength of the B4C / Al matrix composite material without introducing the B4C / Ti double coating layer, the interface bonding strength and the tensile strength of the continuous boron fiber reinforced aluminum alloy matrix composite material are significantly improved, which has important significance for meeting the strong demand for lightweight high-strength materials in the field of aerospace.

The invention discloses a TB17 titanium alloy large-specification bar and a forging method thereof, and belongs to the field of titanium alloy material machining. Comprising the following steps that S1, a TB17 titanium alloy cast ingot is subjected to high-temperature homogenizing annealing and shaping; s2, multi-heating-number repeated upsetting and drawing forging and spheroidizing annealing in a single-phase region; s3, multi-heating-number repeated upsetting and drawing forging below the phase transformation point and forging into a flat square; s4, one heating number of upsetting and drawing forging above the phase transformation point is carried out, and a flat square is forged again; s5, recrystallization annealing; s6, multi-heating-number reversing pier pulling forging below the phase transformation point; and S7, finally forming and forging below the phase transformation point to obtain the bar with the target specification. According to the method, the steps of large deformation of a single-phase region, repeated upsetting and drawing, reversing upsetting and drawing, spheroidizing annealing, recrystallization annealing and the like are fully combined, the technical problems that a TB17 ultrahigh-toughness titanium alloy large-specification bar blank with the diameter being 300-500 mm is large in deformation resistance, the uniformity of the structure performance of all parts is poor, and a forging window is narrow are solved, the stability and the consistency of different-furnace batch forging processes are achieved, and the production cost is reduced. And the requirements of high specification and high performance of aerospace materials are met.

This invention discloses a pitch adjustment test platform device, belonging to the field of aerospace material processing technology. Developed to address the diverse sizes of products, the device includes a test platform, a platform support unit, a pitch observation function unit, a movable function unit, and a drive output unit. The pitch observation function unit, mounted on the platform support unit, indicates the pitch angle of the test platform. The movable function unit enables the movement of the test platform. The drive output unit provides power to the movable function unit. This device maintains the pitch angle of the test platform during automatic pitch adjustment, meeting the wide range of tilt angle requirements for products of different sizes. This invention enables rapid and accurate product positioning and testing, is easy to operate, ensures the accuracy of the pitch adjustment test process, improves product testing efficiency, and significantly reduces operating costs.

The invention discloses a preparation process of a novel aviation aluminum-lithium alloy containing a refining agent and Al-Ca-In-V compound addition, and belongs to the technical field of aerospace materials. According to the process, a multi-element alloy system is designed, and through vacuum melting, semi-continuous casting, homogenization, three-way forging, solid solution and double-stage aging treatment, the strength, the toughness and the corrosion resistance are synergistically improved. The method is suitable for key structural parts such as airplane bodies and wings, and has remarkable economic benefits and application value.