87 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 present invention relates to the field of aerospace materials, and in particular to a device for prestressed loading and irradiation testing of thin films; the device comprises a frame, a support block, an anvil, and a pressure gauge; the support block, the anvil and the pressure gauge can all move up and down inside the frame; the thin film material to be tested is fixed to the frame by a pressure plate, and the position of the anvil inside the frame can be changed by adjusting the support screws, thereby adjusting the size of the external force applied by the anvil; the present invention can provide forces of different sizes and directions to the thin film by replacing different anvils, and the external force applied to the thin film material to be tested is complex, changeable and detectable; at the same time, the cooperation between the frame, the support block and the screws is utilized to avoid the anvil from shifting during the irradiation process, resulting in changes in the applied external force and relaxation of the thin film material; the invention has the advantages of small size, simple operation, long-lasting and stable prestress, and is particularly suitable for irradiation tests in narrow irradiation spaces.

The invention relates to the technical field of aerospace materials, in particular to a rapid vibration fatigue specimen design method and device, and aims at solving the problems that in the prior art, vibration fatigue specimen design is long in period and high in cost, or the frequency of parts exceeds the excitation frequency range of a vibration test bed, or multi-round optimization and repeated design are needed. The method comprises the following steps: firstly, designing a reference sample, and rapidly designing a vibration fatigue sample which is simultaneously applicable to the geometrical characteristics of parts and the excitation frequency range of a vibration test bed by utilizing a dynamic similarity principle, namely determining the specific magnification or reduction multiple of the reference sample; according to the method, the vibration fatigue test sample which is simultaneously applicable to the geometrical characteristics of the parts and the excitation frequency range of the vibration test bed can be rapidly designed only according to the designed reference test sample, existing resources are well utilized, and compared with the best prior art, the design efficiency of the test sample is improved, and the method has the advantages of being high in speed and high in applicability.

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 invention relates to the technical field of aerospace material paint spraying, in particular to aerospace material paint spraying equipment which comprises a paint spraying base, a placing plate is installed above the paint spraying base, and the upper portion of the placing plate is used for placing aerospace materials to be painted; a first annular paint spraying pipe is arranged above the paint spraying base, a second annular paint spraying pipe is arranged above the paint spraying base and located on the inner side of the first annular paint spraying pipe, and the length of the first annular paint spraying pipe is larger than that of the second annular paint spraying pipe. Paint is sprayed to the outer wall and the inner wall of the shell type aerospace material through paint outlet grooves in the surfaces of the first annular paint spraying pipe and the second annular paint spraying pipe, paint spraying treatment on the outer wall and the inner wall at the same time is achieved, and through the action of a driving mechanism, the first annular paint spraying pipe and the shell type aerospace material can rotate; the spraying effect on the inner wall and the outer wall of the shell type aerospace material is improved, the problem that the inner wall of the shell type is difficult to spray is solved, and operation is convenient.

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 discloses an anti-leakage method for a special-shaped composite material storage tank, relates to the technical field of aerospace materials, fills the blank of an anti-leakage design method for the special-shaped composite material storage tank, and provides a solution for development of a novel sealing technology of the special-shaped composite material storage tank. The sealing coating technology is adopted to achieve leakage resistance of the special-shaped storage tank, and allowable opening displacement is used as a judgment basis for failure of the sealing coating. While the structural strength and rigidity of the composite material special-shaped storage tank are designed, the allowable opening displacement of the sealant layer is introduced into the structural design of the composite material special-shaped storage tank, and through systematic tests and simulation analysis, it is obtained that finite element simulation analysis is well matched with a pressurizing test; therefore, the opening displacement as failure judgment of the sealant layer can meet the anti-leakage design requirement of the storage tank. A feasible solution is provided for the sealing problem of the special-shaped storage tank, and the sealing performance and reliability of the special-shaped storage tank are remarkably improved.

The present invention provides a filament bundle reel winding and unwinding device for a feeding mechanism applied to an automatic fiber placement machine, which relates to the technical field of aerospace material production equipment and specifically includes: a driving assembly, a bearing assembly, and a limiting assembly; a bearing shaft penetrates into the inside of a filament bundle reel to hold the filament bundle reel, and a driving motor drives the bearing shaft to rotate through a driving shaft, realizing the transmission connection to the filament bundle reel, thereby precisely controlling the unwinding speed and the strip tension, ensuring a constant laying tension and a stable unwinding speed. Moreover, the top surface of the first limiting member abuts against the filament bundle reel, and the elastic limiting portion of the second limiting member abuts against the end of the filament bundle reel, preventing the filament bundle reel from loosening or shifting during the unwinding process. When the filament bundle reel needs to be disassembled, the elastic limiting portion can be pressed to make its top surface contract to be flush with the surface of the bearing shaft, and then the filament bundle reel is pulled out to complete the disassembly. The disassembly process is simple and time-consuming, and can reduce the production downtime during the replacement process, thereby improving the production efficiency.

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 invention relates to the technical field of aerospace material processing, and discloses a punching device for aerospace materials and a punching method of the punching device, a double-drilling-machine structure is adopted, two sets of hole positions can be formed and processed through one-time action, and compared with traditional single-drilling-machine equipment, the punching device has higher processing efficiency; the two sets of servo drilling machines are connected and installed through a servo rotary table and a pedestal structure, the servo drilling machine on one side is independently driven by a fifth motor in a lifting mode, and single-hole forming, equal-depth double-hole forming and non-equal-depth double-hole forming and machining can be conducted through the lifting driving control of the servo drilling machine on one side in cooperation with a midpoint positioning type machining method. The device is flexible to work, machining modes can be flexibly selected according to different aviation plates, and the device can meet machining requirements of various distributed hole sites in a plane due to the fact that the device is diversified in combination, and a double-CCD-camera visual positioning structure is adopted, and a protective partition plate is arranged at the position, close to a lens of the machining side, of the lower portion of the CCD camera. Effective dustproof shielding protection can be performed on the lens side of the CCD camera through sliding shielding protection.

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 discloses a hybrid fiber co-cured multifunctional composite airfoil structure, and belongs to the technical field of aerospace materials. In order to solve the problem that a traditional composite airfoil cannot have the bearing function and the detection function at the same time, a hybrid fiber co-curing process is mainly adopted, an insertion laying layer structure of same-layer butt joint and staggered-layer lap joint is combined, a hybrid fiber transition area is formed, the connection mode is optimized, interference of metal connection on the electrical performance of a functional area is avoided, and the service life of the composite airfoil is prolonged. And meanwhile, the overall rigidity and strength of the airfoil are improved. A traditional composite material airfoil structure is combined with the antenna to form an intelligent skin structure, a functional area is made of a wave-transparent fiber material and is conformal with the antenna, a bearing area is made of a carbon fiber material, and function partition cooperative work is achieved; the hybrid fiber co-curing process is adopted, so that the influence of metallization on the electrical performance of the antenna is eliminated, and the transformation from a traditional composite material structural part to a structural function integrated part is realized.

The present invention relates to the technical field of aerospace material preparation, and specifically relates to a short carbon fiber toughened ternary ultra-high temperature ceramic matrix composite material and a preparation method thereof. The preparation method provided by the present invention promotes the uniform dispersion of short carbon fibers and inhibits damage through the dispersion method of short carbon fibers blown by gas, removes excess oxides through the reaction of residual carbon and oxides after the cracking of the ball-milled coating resin to promote densification, and uses reaction hot pressing sintering without adding a second-phase sintering aid to prepare the material. The short carbon fiber toughened ternary ultra-high temperature ceramic matrix composite material prepared by the present invention has a low sintering temperature, uniform distribution of short carbon fibers, long length, high flexural strength and fracture toughness, and good densification degree.

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 discloses a molecular marker primer group for identifying or screening wax gourd spaceflight breeding materials and application of the molecular marker primer group. Six pairs of InDel marker primers capable of identifying the wax gourd aerospace material and the offspring thereof are developed and screened from 606959 InDel markers of the wax gourd aerospace breeding material, the primers can be used for identification in the seedling stage, the wax gourd aerospace material can be accurately bred according to the insertion / deletion size of the primers, the breeding period is shortened, and the breeding efficiency is improved. And the white gourd aerospace material and the offspring thereof can be bred quickly, accurately and efficiently. Meanwhile, when the InDel marker is applied to screening and offspring selection of aerospace breeding materials, the recognition and utilization efficiency of excellent variation in aerospace breeding can be remarkably improved, the offspring selection efficiency is optimized, and the breeding process of the aerospace breeding materials is accelerated. Compared with a traditional breeding identification method, the method is accurate and reliable, breeding target progenies can be screened in advance, the breeding cost is reduced, and more high-quality and efficient new white gourd varieties are provided for agricultural production.

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.