1713 results about "Ceramic matrix composite" patented technology

A turbine shroud assembly adapted for use with a gas turbine engine includes a shroud segment. The shroud segment includes a heat shield, an attachment flange, and a multi-layer coating. The heat shield extends circumferentially partway around the axis to define a portion of gas path for the gas turbine engine. The attachment feature extends radially outward from the heat shield. The multi-layer coating is applied to different surfaces of the heat shield and the attachment feature of the shroud segment.

The invention relates to the technical field of carbon fiber reinforced ceramic matrix composites, in particular to a sintering process of a surface-modified short carbon fiber reinforced ceramic matrix composite, which comprises the following steps: surface modification treatment of short carbon fibers, preparation of a ceramic matrix material, mixing of the short carbon fibers and ceramic powder, compression molding and sintering. In the invention, the process is not only suitable for various ceramic matrixes such as aluminum oxide, silicon carbide, silicon nitride, zirconium oxide and the like, but also can flexibly adjust process parameters such as oxidizing agent types, coupling agent treatment time, ceramic powder particle size, forming pressure, sintering temperature and the like, so that customized preparation with different application requirements is realized; the prepared composite material has extremely high toughness, wear resistance and high-temperature resistance, and shows a wide application prospect.

The invention provides a preparation method of a high-temperature-resistant antioxidant chopped carbon fiber reinforced ceramic-based composite material, and relates to the field of ceramic-based composite material preparation, and the preparation method comprises the following steps: S1, selection and surface treatment of reinforced fibers: selecting chopped carbon fibers as a reinforced material, and carrying out surface modification treatment on the chopped carbon fibers to obtain the reinforced fibers; according to the present invention, the surface modification treatment is performed on the short carbon fiber, and particularly the SiC coating is coated on the fiber surface by using the chemical vapor deposition (CVD) method, such that the oxidation resistance of the carbon fiber under the high temperature condition is effectively improved. The coating enhances the stability of the fiber, reduces the oxidation loss of the fiber at high temperature, enhances the interface bonding force between the fiber and the ceramic matrix, and avoids stripping or interface failure in a high-temperature environment, thereby ensuring the overall stability and service life of the material.

The invention relates to a high-temperature ablation resistant ceramic matrix composite material and a preparation method thereof. The method comprises the following steps: preparing a rare earth acetylacetone complex from hexahydrate of rare earth chloride (rare earth nitrate) and acetylacetone; uniformly mixing the rare earth acetylacetone complex with poly (hafnium) oxane by using xylene to obtain a zirconium (hafnium)-rare earth ceramic precursor solution; densifying the porous carbon fiber preform by using a zirconium (hafnium)-rare earth ceramic precursor solution through a precursor impregnation and pyrolysis process to obtain a carbon fiber reinforced carbide ceramic-rare earth zirconium (hafnium) acid salt ceramic-based composite material; and densifying the carbon fiber reinforced carbide ceramic-rare earth zirconium (hafnium) acid salt ceramic-based composite material by using molybdenum chloride and silicon chloride through a chemical vapor infiltration method to prepare the high-temperature ablation resistant ceramic-based composite material. The prepared ceramic-based composite material has excellent high-temperature oxidation ablation resistance and excellent high-temperature mechanical properties at the temperature of 2000 DEG C or above.

The invention discloses an intelligent segmentation method and device for ceramic matrix composite CT image defects, and belongs to the technical field of image detection. The method comprises the following steps: inputting preprocessed CT image data into a preset double-branch collaborative segmentation model, and respectively outputting to obtain a local texture feature map and a global relation feature map; performing three-branch material perception fusion processing on the local texture feature map and the global relation feature map according to a preset perception fusion model to obtain a fusion feature map containing local detail accuracy and global consistency; sequentially carrying out progressive decoding and refined reconstruction processing on the fused feature graph to obtain a defect probability graph; and calculating a loss function of the defect probability graph and a manually pre-labeled real defect segmentation graph, and dynamically adjusting the loss weight of the initial model according to a calculation result to obtain a CT image defect segmentation model meeting a preset convergence condition. The method can meet the detection requirements of industrial scenes on the defects of the ceramic-based composite material.

The invention belongs to the field of aero-engines, relates to an engine main combustion chamber design technology, and provides a ceramic matrix composite material flame tube matching design method and system.The method comprises the steps that a flame tube wall temperature interval of a main working state point is obtained; determining the thermal-state radial dimensions of the feature points on the ceramic-based component and the metal component; converting the hot-state radial size into a cold-state radial size; carrying out two-dimensional cold-state flame tube profile design; and the cold-state radial size of the two-dimensional cold-state flame tube molded surface is converted into the hot-state size to obtain a two-dimensional hot-state flame tube molded surface, and a three-dimensional hot-state model is constructed and evaluated and iteratively optimized. According to the method, matching structure characteristic parameters of the ceramic-based component and the metal component are designed, and the molded surface of the flame tube made of the different materials is self-adaptively formed into smooth transition at main working state points, so that a backflow area is actively controlled, and the problems that the stability of a flow field of a main combustion chamber is influenced and pressure is lost due to different and relative displacement changes in the working process are solved.

The invention belongs to the field of aero-engine part clamping, and particularly relates to a combined clamping method for a ceramic matrix composite segmented cylindrical structure, which comprises the following steps of: firstly, clamping a workpiece, and connecting a lower rib plate of the workpiece with a positioning reference surface of a clamp by using two groups of positioning pins; then, the lower pressing plate, the workpiece lower rib plate and the clamp positioning datum plane are clamped and fixed through bolts, pointers of the two dial indicators abut against the inner wall face, between the workpiece upper rib plate and the workpiece lower rib plate, of the workpiece, and the initial reading of the dial indicators is zero; two sets of combined positioning pins penetrate through an upper pressing plate, a pin hole I in an upper rib plate of a workpiece and an upper supporting plate to be clamped and fixed, in the process, a supporting base is repeatedly adjusted to be connected with a bolt of the upper pressing plate, it is guaranteed that under the state that the workpiece is clamped, the change of the micrometer indication does not exceed the limiting value, and it is indicated that clamping of the workpiece is completed; and the steps are repeated to complete clamping of the whole cylindrical structure. Through the method, the machining deformation of the cylindrical structure is effectively relieved, and the machining precision is remarkably improved.

The invention provides a high-bearing-capacity double-cavity ceramic matrix composite material blade assembly, and belongs to the technical field of aero-engines, the ceramic matrix composite material blade assembly comprises a ceramic matrix composite material blade, the ceramic matrix composite material blade comprises a blade body with a cavity, a blade upper edge plate and a blade lower edge plate, and the blade upper edge plate and the blade lower edge plate are located on the two sides of the blade body; a partition rib is arranged in the cavity of the blade body and divides the cavity into a front cavity and a rear cavity; the front cavity metal framework is integrally connected with a metal lower edge plate, the rear cavity metal framework is integrally connected with a metal upper edge plate, the metal lower edge plate and the metal upper edge plate are connected with an engine bearing structure, the front cavity metal framework is arranged in a front cavity of the blade body, and the rear cavity metal framework is arranged in a rear cavity of the blade body. The rear cavity metal framework is arranged in a rear cavity of the blade body, the front cavity metal framework is connected with the upper metal edge plate through a connecting piece, and the rear cavity metal framework is connected with the lower metal edge plate through a connecting piece.

The invention relates to a high-temperature structure bearing / anti-ablation integrated ceramic matrix composite and a preparation method thereof.The preparation method of the composite comprises the steps that a pyrolytic carbon interface layer is deposited on the fiber surface of a carbon fiber preform through a chemical vapor deposition method, and a low-density C / C base material is obtained; the density of the carbon fiber preform is gradually increased from the surface to the inside; the preparation method comprises the following steps: carrying out first vacuum impregnation, first pressure impregnation, first curing and first cracking on a low-density C / C base material by adopting phenolic resin to obtain a porous C / C intermediate; carrying out reactive infiltration on the porous C / C intermediate by adopting an alloy infiltration agent to generate a multi-element ultra-high-temperature ceramic matrix, so as to obtain a multi-element ultra-high-temperature ceramic matrix composite material; and preparing an anti-oxidation ceramic protective layer on the near surface of the multi-element ultrahigh-temperature ceramic-based composite material to obtain the high-temperature structure bearing / anti-ablation integrated ceramic-based composite material. The ceramic-based composite material prepared by the preparation method has good high-temperature structure bearing performance and oxidation ablation resistance.

A method of forming a ceramic matrix composite component includes forming a fiber preform, the fiber preform including a plurality of ceramic fiber plies, a non-reduced fiber region having an areal weight, and a reduced fiber region characterized by a reduced areal weight less than the areal weight of the non-reduced fiber region by at least 5 percent. The method further includes selectively applying ceramic particles to the reduced fiber region in such manner as to avoid applying the ceramic particles to the non-reduced fiber region, and subsequently densifying the preform.

Disclosed is a collaborative design system and method for a thermophysical property gradient distribution and a braided structure of a CMC and a storage medium. The system comprises at least one storage medium and at least one processor. The at least one processor is configured to: generate a temperature field parameter of a surface of a CMC turbine blade under a non-uniform inflow condition based on a simulation analysis platform, and extract a convective heat transfer coefficient; partition the CMC turbine blade and import an extracted fluid-solid heat transfer boundary condition into an optimization platform; perform multi-objective optimization on the thermophysical property gradient distribution of the CMC turbine blade under the non-uniform inflow condition based on an optimization simulation tool; and generate C nanotube contents of different regions of the CMC turbine blade based on a correspondence function and values of material thermal conductivities of the different regions of the CMC turbine blade to realize the collaborative design of the thermophysical property gradient distribution and the braided structure of the CMC.

A method of manufacturing ceramic matrix composites includes producing chemical vapor deposition functionalized ceramic particles before injecting the functionalized ceramic particles into the CMC fabric. The functionalized ceramic particles are mixed with a binder solution and then dispensed into voids present between adjacent tows of the CMC fabric. Injecting the particles in the center of the voids reduces the size and volume fraction of the voids / defects, improving the homogeneity of surface texture, homogeneity of microstructure, and part model shape conformity.

The invention provides a deep V-shaped ceramic matrix composite component forming device and method. The forming device comprises a bottom die, an outer die and an inner die. The outer die is connected to the bottom die; the inner mold is connected to the bottom mold, and the bottom mold, the outer mold and the inner mold are encircled to form a cavity for forming the deep V-shaped ceramic matrix composite component; wherein the inner die comprises a V-shaped main body die and a plurality of small-section dies connected to the V-shaped main body die, the plurality of small-section dies are arranged in the narrow opening position and are sequentially connected in the length direction, and the plurality of small-section dies are provided with die drawing angles in the length direction. The deep V-shaped ceramic matrix composite component can be formed and prepared, and demolding is convenient.

The invention discloses a nanostructure thermal protection coating resistant to long-time high-temperature oxidation and a preparation method thereof.The nanostructure thermal protection coating takes a ceramic matrix composite material as a matrix, and a bonding layer and a composite component coating are sequentially sprayed to the surface of the matrix. Preparing a nano-structure self-healing additive / Re2Si2O7 spherical powder body; preparing a bonding layer on the surface of the ceramic-based composite material serving as a matrix; and 3, depositing the nano-structure self-healing additive / Re2Si2O7 spherical powder on the surface of the bonding layer to form the composite component coating. According to the preparation method, the self-healing additive / Re2Si2O7 is prepared into the nano-structure spherical powder suitable for thermal spraying for the first time, and a method is provided for implementation of the high-performance material on a thermal spraying nano-structure coating. The prepared coating is stable in phase structure at high temperature, phase change of powder is avoided in the spraying process, and the coating has good thermal expansion coefficient matching performance with a base body.

The invention discloses a method for patching and repairing a silicon carbide ceramic matrix composite part of an aero-engine, which comprises the following steps: using a CMC-SiC patch as a structure for patching and repairing part cracks, corrosion pits or fiber cracks, preparing surface textures on the contact surface of the CMC-SiC patch and the part by using pulse laser, coating brazing filler metal on the contact surface of the CMC-SiC patch and the part, and preparing the surface textures on the contact surface of the CMC-SiC patch and the part. And the CMC-SiC patch and the surface of the part are pressed tightly, and patching and repairing of the silicon carbide ceramic matrix composite part of the aero-engine are completed after vacuum brazing, polishing, cleaning and drying, environmental barrier coating recovery and annealing. According to the repairing method, a patching technology is adopted, a force transmission path at cracks, corrosion pits or fiber fractures is rebuilt, the strength of the part is recovered, and the repairing problem of relatively serious damage such as relatively wide cracks, corrosion pits or fiber fractures on the silicon carbide ceramic-based composite part is solved. In addition, specific textures and shapes are prepared on the binding face of the CMC-SiC patch and the part through pulse laser, and the optimal combination effect and joint strength of the brazing filler metal, the patch and part base metal are accurately achieved.

The invention provides a novel ceramic matrix composite material and metal material combined adjustable turbine blade, and belongs to the technical field of aerospace, the novel ceramic matrix composite material and metal material combined adjustable turbine blade specifically comprises a metal upper edge plate and a metal lower edge plate; the ceramic matrix composite material front edge assembly is fixedly installed between the metal upper edge plate and the metal lower edge plate, and the ceramic matrix composite material front edge assembly serves as a front edge area of the blade; the adjustable metal blade body is rotationally mounted between the metal upper edge plate and the metal lower edge plate; the rear end of the blade body part of the ceramic matrix composite material front edge assembly is in butt joint with the front end of the adjustable metal blade body to form a complete turbine blade body structure. Through the treatment scheme, the problem that in the prior art, cooling of the front edge of the metal blade consumes a large amount of cold air is solved, and the service life of the adjustable turbine blade is prolonged.

The invention provides a laser-induced composite material surface multi-scale micro-texture assisted brazing method which comprises the following steps: step 3, carrying out surface texturing treatment on a to-be-welded surface of a fiber reinforced ceramic matrix composite obtained in step 2 by using a laser in air, and in the laser texturing process, carrying out surface texturing treatment on the to-be-welded surface of the fiber reinforced ceramic matrix composite, the fiber-reinforced ceramic matrix composite material is placed in the center of a laser objective table, then laser with the defocusing amount being-5-5 mm, the laser power being 0-300 W and the laser scanning speed being 5-100 mm s <-1 > is adopted for vertical irradiation, and the textured fiber-reinforced ceramic matrix composite material is obtained; and fourthly, active brazing filler metal is placed between the textured fiber-reinforced ceramic matrix composite obtained in the third step and the to-be-welded face of metal, and brazing assembly is completed. According to the method, the original straight interface reaction layer is textured through a surface material reduction method, and compared with a surface material increase method which is complex in process, harsh in process condition and high in process cost, the economic cost and the labor cost of the process are greatly reduced through the method.

A method of preparing a ceramic fabric and ceramic matrix composite components constructed from the ceramic fabric include transforming ceramic tows, or ceramic fabrics, to varying degrees from a first tow geometry to a second tow geometry, thereby reducing a first dimension of the ceramic tows and increasing a second dimension of the ceramic tows orthogonal to the first dimension. Plies constructed with flattened tows, or as-received tows, have various inter-tow pore sizes that are arranged with increasing inter-tow pore size towards exterior surfaces of the preform structure.

The invention discloses a silicon nitride ceramic-based composite material and a preparation method thereof, and relates to the technical field of silicon nitride ceramics. The silicon nitride ceramic-based composite material is prepared from silicon dioxide coated modified boron nitride and resin composite phase change microcapsules, Si3N4-C coated Al2O3 core-shell fiber aerogel, nano yttrium oxide and polyvinyl butyral, the silicon dioxide coated modified boron nitride and resin composite phase change microcapsules are stably attached to the surface of the Si3N4-C coated Al2O3 core-shell fiber aerogel in a chemical bonding and mechanical interlocking mode, the interface bonding strength is enhanced, the risk of phase separation is reduced, the combination effect of the silicon dioxide coated modified boron nitride and resin composite phase change microcapsules and the Si3N4-C coated Al2O3 core-shell fiber aerogel is better exerted, and the composite phase change effect of the silicon dioxide coated modified boron nitride and resin composite phase change microcapsules is improved. According to the present invention, the fracture toughness can be improved through fiber toughening, aerogel pore and microcapsule stress dispersion, the high temperature resistance can be improved through the low thermal conductivity of the aerogel and the heat absorption effect of the microcapsule, the mechanical property of the silicon nitride can be significantly improved through multiple ways and multiple modes, and the high temperature resistance can be effectively enhanced.

The invention relates to a gradient carbon nanotube fiber needled preform heat dredging ceramic-based composite material and a preparation method thereof. The method includes; preparing a plurality of carbon nano tube fiber web tire layers and carbon nano tube fiber cloth layers which are alternately laminated with the carbon nano tube fiber web tire layers and are compounded by needling, wherein the carbon nano tube fiber web tire layers comprise carbon nano tube fibers and organic fibers, and the content of the organic fibers is gradually changed layer by layer along the thickness direction of the prefabricated body; forming a carbon interface layer by using a carbon source; decomposing the organic fibers through high-temperature treatment to form pores in gradient distribution; and carrying out impregnation and cracking by using a ceramic precursor to obtain the heat-conducting ceramic-based composite material. According to the pure carbon nanotube fiber needled preform prepared by the method, organic fibers are decomposed through high-temperature treatment, pores in gradient distribution are formed while the heat conductivity is improved, closed pores are avoided, carbon interface deposition and ceramic densification are facilitated, mechanics is improved, the preparation period is shortened, and the cost is reduced.

The invention relates to the technical field of ceramic matrix composite material forming, in particular to a forming die and method for a thin-wall R-arc reinforced structure composite material component, and the forming die comprises a bottom die, an outer die, an inner die and a top cover; the inner mold is located in an R-arc inner cavity of the thin-wall R-arc reinforced structure composite material component and connected to the bottom mold, the outer mold is connected to the bottom mold, the top cover is connected to the bottom mold and the outer mold, and a cavity used for forming the thin-wall R-arc reinforced structure composite material component is defined by the bottom mold, the outer mold, the inner mold and the top cover; a gasket used for enabling the R-arc outer molded surface of the component prefabricated body to be attached to the outer mold and the top cover is arranged at the position, making contact with the component prefabricated body, of the bottom mold, and a supporting cushion rope used for assisting in forming of the R-arc tip is arranged at the tip of the inner mold. The forming die and method of the thin-wall R-arc reinforced structure composite material component aim at solving the problem that the forming difficulty of the R-arc position of a thin-wall R-arc reinforced structure is large.

The invention discloses a milling cutter for processing a ceramic matrix composite material, a cutting edge comprises a wave-shaped cutting edge and a tooth-shaped cutting edge, the wave-shaped cutting edge and the tooth-shaped cutting edge are positioned on different edge sections and are alternately arranged, the waveform of the wave-shaped cutting edge is a sine curve waveform, and the sine curve waveform is periodically arranged along the axial direction of the milling cutter; chip separating grooves are periodically formed in the tooth-shaped cutting edge in the axial direction of the milling cutter at intervals, and the chip separating grooves correspond to wave crests and wave troughs of the sine curve waveform. The wave-shaped cutting edge is in a sine curve wave shape, so that the length of the cutting edge is increased, the load in unit length is reduced, the machining cutting force is effectively reduced, heat dissipation is accelerated, vibration and deformation are reduced, the tooth-shaped cutting edge is divided by the chip dividing grooves of the tooth-shaped cutting edge, and chip removal and heat dissipation are facilitated while cutting force distribution is optimized; and in the machining process, discontinuous parts are cut through the tooth-shaped cutting edges, machining is conducted through the wave crests or the wave troughs of the wave-shaped cutting edges, and the cutting service life of the cutter is long.

A method of fabricating a fibrous ceramic preform includes impregnating a plurality of individual ceramic tows (26) with a first polymer binder, incorporating the plurality of impregnated ceramic tows (26I) into a ceramic fabric (32), applying a solution comprising a second polymer binder and a second solvent to the ceramic fabric (32), and incorporating the ceramic fabric (32) into the preform. The first polymer binder is insoluble in the second solvent.

The invention discloses a method for testing interlayer tensile strength of a ceramic matrix composite material. Comprising the following steps: acquiring the geometric dimension of a sample, performing surface treatment on a test surface of the sample, marking a test section of the sample, acquiring the geometric dimension of a four-point bending clamp, determining a placement mode of the sample and a camera, and capturing a displacement field of the test surface of the sample by using the camera while performing a curved beam four-point bending test. Obtaining the load value and stroke of the first load drop, extracting the in-situ strain of the sample by using a camera, deducing a formula for calculating the interlayer radial and tangential modulus ratio of the sample, carrying out calculation, and calculating the interlayer tensile strength of the sample by using the existing formula. According to the method disclosed by the invention, the modulus ratio of the interlayer radial direction to the interlayer tangential direction is obtained by using in-situ strain, the problem that the interlayer radial modulus is difficult to accurately determine directly through the test is solved, and the accuracy of the interlayer tensile strength of the ceramic matrix composite material measured through the curved beam four-point bending test is improved.

The invention relates to the field of material performance evaluation, in particular to a resistance testing system and method in the slurry injection process, the testing system comprises a stress loading part and a testing clamp, and the testing clamp comprises an upper clamp, a lower clamp and an injector clamp; the upper clamp comprises a first connecting part and a first clamping assembly, and the position of the first clamping assembly relative to the first connecting part is adjustable up and down; the lower clamp comprises a second connecting part, an object carrying platform and a second clamping assembly, the position of the second clamping assembly relative to the object carrying platform is vertically adjustable, and the rotation angle of the lower clamp relative to the base is adjustable. According to the method, the mechanical property change in the injection process can be monitored in real time, the mechanical property of the slurry in the carbon fiber preform injection process can be accurately evaluated, the test accuracy and reliability are improved, an evaluation standard is provided for the applicability of a ceramic matrix composite prepared by an injection impregnation process, and the method is suitable for popularization and application. And an optimization basis is provided for improving the distribution uniformity of the components in the composite material.

A method of forming a ceramic matrix composite having a smooth surface includes laying up a plurality of plies, where some or all of the plies include an arrangement of spread tows comprising carbon fibers, thereby forming a fiber preform. Each spread tow has a height-to-width aspect ratio of less than about 0.1. The fiber preform is infiltrated with a ceramic matrix material and / or ceramic matrix precursor to embed the carbon fibers in a ceramic matrix. Thus, a ceramic matrix composite comprising a smooth and / or flat surface devoid of undulations from rounded tows is formed.

The invention relates to the technical field of aero-engine part machining, in particular to a machining method for a ceramic matrix composite turbine outer ring. The method specifically comprises the following steps: polishing a blank; blank detection; cutting the silicon shell; trimming is conducted; bonding is conducted; milling is conducted; repairing and cleaning by pincers; and inspecting. According to the method, a bonding clamping mode is adopted, a traditional pressing plate and bolt pressing structure is omitted, the structure of a tool clamp is simplified, the operation complexity of the clamp is reduced, and large machining and tool cost is saved; after the blank benchmark of the part is determined, the part is directly machined to the final size at a time, benchmark conversion is not needed, machining errors caused by clamping and benchmark conversion are reduced, the size precision and stability are guaranteed, and meanwhile the production efficiency is improved.

The invention discloses a morphology reconstruction method for a deposition layer of a ceramic matrix composite air film cooling structure, and belongs to the field of engineering thermophysics. According to the method, on the basis of traditional fluid-solid coupling heat transfer simulation, a track of dust particles on the surface of the ceramic-based composite material air film cooling structure is simulated in combination with a dispersed phase model, deposition layer thickness distribution characteristics are obtained, and after coordinate positions and normal vectors on surface grids are obtained through a user-defined function, the deposition layer thickness distribution characteristics are obtained. And directionally moving the coordinates at different positions of the component along the normal direction by the distance of the deposition thickness to obtain coordinate values of the surface of the sediment, and sequentially reconstructing the obtained coordinate point clouds into a polygonal mesh surface and a geometric model to obtain the geometric morphology of the reconstructed deposition layer. Therefore, the comprehensive cooling efficiency and attenuation characteristics of the ceramic-based composite material air film cooling structure under the influence of the deposited particles can be accurately calculated by simulating and analyzing the influence of the deposited layer on parameters such as flow characteristics and temperature distribution on the wall surface.

An airfoil includes an airfoil section that defines a trailing edge region that includes a trailing edge. The airfoil section is formed of a ceramic matrix composite that includes core fiber plies and skin fiber plies. The core fiber plies define a radial tube that has a radiused end in the trailing edge region. The skin fiber plies wrap around the core fiber plies and a filler element in the trailing edge region is aft of the internal cavity and is sandwiched between the skin fiber plies on the pressure side and the skin fiber plies on the suction side. There is at least one cooling passage that includes a first, inlet orifice section that opens to the internal cavity at a location forward of the radiused end and that extends through the core fiber plies, and a second, outlet orifice section that extends through the trailing edge.

The invention provides a multi-scale calculation method and system for mechanical properties of a unidirectional fiber reinforced ceramic matrix composite material. According to the method, a sequential multi-scale method is adopted, the surface energy of a matrix material is obtained through molecular dynamics on the nanoscale scale, and the molecular dynamics-discrete element coupled unidirectional fiber reinforced ceramic matrix composite material multi-scale calculation method and system are provided on the basis of the periodic damage characteristic of the material under the microscale. Compared with the prior art, the method has the advantages that the nanoscale damage behavior of the ceramic matrix composite matrix and the aggregation characteristic of the microcracks are fully considered, and the calculation precision of a microscopic result is remarkably improved. The method is suitable for component design, structure optimization and mechanical property prediction of the ceramic-based composite material in the aerospace field.