65 results about "Aerospace materials" patented technology

The present invention provides a rubber member having excellent corrosion resistance and a semiconductor manufacturing–related device using the same. Provided is a rubber member that includes an olefin-based rubber, the rubber member being at least one member selected from the group consisting of building material members, mobility members, aerospace members, semiconductor members, and information communication members, and the rubber member coming into contact with a corrosive substance.

The invention discloses a method and device for predicting abrasive particle impact damage on the surface of a carbon fiber plate, relates to the field of aerospace material performance research, and can solve the problem that the evolution process of damage to the carbon fiber plate caused by micro-scale abrasive material impact cannot be directly observed and obtained in real time at the present stage, and the method comprises the steps that a gas-solid two-phase flow field model in a nozzle is established; setting a discrete phase injection source in CFD simulation software, and determining abrasive particle motion data according to the gas-solid two-phase flow field model in the nozzle after grid division; establishing a three-dimensional model of the abrasive particles in finite element modeling simulation software and carrying out grid division; a carbon fiber plate model is established in explicit dynamics simulation software, the abrasive particle three-dimensional model obtained after grid division is imported into the carbon fiber plate model, the initial impact speed of the abrasive particles on the carbon fiber plate model is set according to abrasive particle motion data obtained through calculation of CFD software, and the damage result of the carbon fiber plate is determined through impact simulation calculation of the abrasive particles on the carbon fiber plate. The method is used for simulating and predicting the damage caused by impact of the microscale abrasive on the carbon fiber plate.

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 application provides a thermal control-wave absorbing integrated composite material, a preparation method thereof, and a spacecraft, which relates to the field of aerospace materials technology. The thermal control-wave absorbing integrated composite material comprises a composite ceramic core and a porous coating layer; the porous coating layer covers the composite ceramic core; the chemical formula of the composite ceramic core is La 1‑x Sr x MnO3 / Al2O3, 0.1≤x≤0.3; the porous coating layer includes Al2O3. By introducing Al2O3 into the composite ceramic core, the thermal radiation phase transition temperature can be controlled. The Al2O3 coating layer acts as a shell component to ensure the strength of the thermal control and wave absorbing integrated composite material. The porous structure of the porous coating layer allows radar waves to be absorbed through multiple reflections within the pores, effectively increasing the thermal control and wave absorbing integrated composite material's radar absorption.

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.

The utility model discloses an aerospace material conveying device which is applied to the technical field of aerospace material conveying and comprises a moving trolley, a lifting frame and a material frame, the lifting frame is fixed to the top of the moving trolley, the material frame is fixed to the top of the lifting frame, and the lifting frame is used for adjusting the height of the material frame in a lifting mode. The material rack is used for placing materials to be conveyed; the material frame comprises a base, a front side plate, a rear side plate, a left side plate, a fixing frame, a right side plate, two connecting rod sets and a supporting frame. A plurality of sets of material boxes, transverse moving assemblies and longitudinal moving assemblies are arranged on the material frame, and four sets of universal wheels are fixedly connected to the bottoms of the material boxes. The transverse moving assembly comprises a motor, a frame and a plurality of rollers, and the distance between the two sets of longitudinal universal wheels at the bottom of the material box is larger than the longitudinal length of the frame.

This invention discloses a honeycomb-filled multifunctional thermal protection structure and its construction method, belonging to the technical field of aerospace materials. It includes a load-bearing heat dissipation layer and a load-bearing heat insulation layer, both of which have macroscopic and mesoscopic structures. The load-bearing heat dissipation layer is a thin layer of high thermal conductivity C / C composite material, and its mesoscopic structure is a three-dimensional woven structure. The load-bearing heat insulation layer is composed of low thermal conductivity C / C honeycomb and porous insulation material, and its mesoscopic structure is a plain weave structure. The invention includes the following steps: First, a dual-scale geometric model is established using 3D modeling software; second, a high-fidelity dual-scale mathematical model is established based on the actual usage environment and conditions; then, the heat protection, heat insulation, and mechanical properties of the honeycomb-filled multifunctional thermal protection structure are simulated using finite element software; finally, the final design is determined by comprehensively evaluating the heat protection, heat insulation, mechanical properties, and lightweight level of the honeycomb-filled multifunctional thermal protection structure.

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 invention relates to the technical field of aerospace material detection, in particular to an aerospace material small-size sample detection device. Comprising a base, a supporting rod is installed on the base, an upper cross beam is arranged on the supporting rod, lead screw motors are further symmetrically installed on the base, a lower cross beam is arranged between lead screws of the two lead screw motors in a threaded mode, electric chucks are arranged in the upper cross beam and the lower cross beam, a pressing block is installed at the bottom of the lower cross beam, and an adjusting mechanism is arranged on the base. A connecting frame is arranged on the adjusting mechanism, and the adjusting mechanism is used for adjusting the orientation of the connecting frame. By arranging the adjusting mechanism, the clamping block, the pressure applying mechanism and the translation mechanism, the orientation of the sample can be automatically adjusted, and different stress surfaces of the sample are clamped and limited, so that the multi-surface mechanical property detection of the small-size sample of the aerospace material is realized, the sample does not need to be manually overturned and fixed again, the detection efficiency is greatly improved, and the detection cost is reduced. And the labor intensity of operators is reduced.

The purpose of the present invention is to provide a member excellent in chemical resistance, a method for manufacturing the same, and a semiconductor manufacturing-related device. The present disclosure is of a member in which at least a part of the surface of a material (a) is laminated with an insulating material, wherein the member is at least one selected from the group consisting of a building material member, a mobility member, an aerospace member, a semiconductor member, and an information communication member.

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 present invention belongs to the technical field of aerospace material preparation, and specifically relates to a heat treatment method for an aluminum-lithium alloy and a ribbed cylindrical shell. The aluminum-lithium alloy is heated in stages to 400-440°C, maintained at this temperature, then placed at 500-510°C, maintained at this temperature, and cooled to room temperature. During the staged heating, the heating rate of the aluminum-lithium alloy is controlled to be no more than 1°C / min. The staged heating is divided into at least three stages, and the temperature is maintained after each heating is completed. The temperature difference between the insulation temperatures of each stage is 50-70°C, and the insulation temperature after the first heating is 230-250°C. The present invention significantly reduces grain size while improving product strength and elongation.

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.

The invention discloses a design method and equipment for a radiation shielding lightweight material of an aerospace electronic component, and a readable storage medium, and relates to the field of aerospace materials. The design method comprises the following steps: determining that the radiation shielding material is of a multi-layer composite structure; the total mass thickness of the radiation shielding material is designed to be lower than the equivalent mass thickness of an Al plate under the same shielding performance; designing a spacecraft equivalent model; gradually adjusting the number of layers of the designed radiation shielding material, the atomic number of each layer, the occupied mass thickness and the stacking sequence, and performing numerical simulation by adopting a Monte Carlo method; the average energy deposition of the silicon balls in the equivalent model of the spacecraft and the cumulative total dose of the total radiation quantity in 10 years are simulated and calculated, and then a radiation shielding material is selected according to the anti-radiation requirement. According to the shielding material designed through the method, the shielding efficiency is improved, and the quality of the shielding material is controlled; and electronic components in the spacecraft can be protected from being subjected to less accumulated dose in the on-orbit working time.

The invention provides an imidazole ring diamine monomer and a preparation method thereof, a black polyimide material and a preparation method and application thereof, and relates to the field of polymers. The invention provides a novel imidazole ring diamine monomer, and a synthesis method of the novel imidazole ring diamine monomer comprises the step of carrying out one-pot reaction on terephthalaldehyde, 1, 2-bis (3-hydroxyphenyl) ethane-1, 2-diketone, 1, 4-phenylenediamine and ammonium acetate in a solvent environment and protective gas at 70-90 DEG C to generate the imidazole ring diamine monomer. A novel imidazole ring diamine monomer is introduced into a polyimide material, stable, uniform and deep intrinsic blackening can be realized on the premise of keeping inherent excellent performances such as thermal performance, mechanical performance and chemical stability of polyimide, an important candidate system is provided for high-end electronic information product packaging and aerospace materials, and the application prospect is broad. The method can be applied to brand new scenes such as deep space exploration, 6G communication and brain-computer interfaces.

The application relates to the field of aerospace material solid lubricating materials, and particularly discloses a low-orbit space radiation resistant self-adaptive molybdenum disulfide-based multilayer composite film and a preparation method. The closed field non-equilibrium magnetron sputtering technology is adopted to deposit a bonding layer (Ti), a gradient transition layer (MoS2 / Ti), a functional layer (MoS2 / Ti), a transition layer (MoS2-Ti-C) and a functional layer (MoS2-C) on a metal material to form a multilayer composite lubricating film. The prepared lubricating film can reliably serve in a low-orbit space environment, can effectively reduce the mechanical wear of a space mechanical friction moving part, and can still maintain stable tribological properties under long-time radiation in the low-orbit space, and is particularly suitable for bearings, gears and other long-time moving parts of a new generation of low-orbit serving space vehicles.

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.

The invention relates to the technical field of aerospace material surface cleaning, in particular to a cleaning method for an A sandwich structure ceramic 3D printing product. According to the cleaning method for the A sandwich structure ceramic 3D printing product, a combined cleaning scheme of ultrasonic cavitation cleaning, pulse airflow purging and negative pressure flash evaporation drying is adopted, and design of technical parameters such as ultrasonic frequency, pulse frequency, nano bubble nucleus particle size, gas core components, fluid Reynolds number and negative pressure drying pressure is matched; the A sandwich structure product is effectively cleaned on the premise that the product structure and material are not damaged, the performance and reliability of the A sandwich structure missile head cover body are guaranteed, and a solution is provided for effective cleaning of other complex honeycomb structure products.

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.