32 results about "Posterior composites" patented technology

The invention discloses a high-temperature damage in-situ characterization method for a composite material for a molten salt reactor based on an acoustic emission technology, and relates to the field of damage characterization of the composite material for the molten salt reactor, and the method comprises the following steps: preparing a C / C composite material under an approximate molten salt reactor working condition; stretching the prepared C / C composite material to obtain a time-stress curve in the stretching process; controlling a laser spot to completely cover the stretching section, and collecting the change condition of an acoustic emission signal; and after the change condition of the acoustic emission signal is correlated with the time-stress curve, judging and representing the change of the internal microstructure of the C / C composite material before and after molten salt infiltration according to a correlation result. According to the method, the internal damage of composite material components with different scales and different shapes in the performance evaluation stage before service under the working condition of the molten salt reactor can be effectively monitored, and the change of the internal microstructure of the material can be analyzed by combining the change of the characteristic frequency of the acoustic emission signal with the tensile curve, so that the method has important engineering practical significance.

The invention discloses a quantitative evaluation method for a composite material patching and cementing maintenance surface water film test, and relates to the technical field of maintenance surface water films, and the quantitative evaluation method comprises the steps of 1, test preparation, 2, contact angle measurement and 3, maintenance surface evaluation. In the first step of test preparation, the defects of scratches, hole pitches and eroded damaged surfaces of the surfaces of the metal components of the airplane are found in time, then corresponding matched patches can be screened in time, the surface repairing problem of the airplane is solved, the service life of the airplane is prolonged, and the operation risk and maintenance cost of the airplane are reduced. In the step 2, in contact angle measurement, the number of broken water films is reduced, the cleanliness of the surface of the patch is improved, the problem that the adhesion force is reduced is solved, then the quality and reliability of the repaired composite material component are improved, the safety risk caused by inaccurate cleanliness is reduced, and the safety of an aircraft structure is improved.

The invention belongs to the technical field of design and manufacturing of flexible printed circuit boards, and particularly relates to a bending deformation and bending stress calculation method and a reliability analysis method of a flexible printed circuit board. A flexible printed circuit board with a complex structure is reasonably simplified into a laminated plate structure model, and then a composite material stress calculation method and an ideal elastic compression bar deformation calculation method are applied to theoretical calculation of the flexible printed circuit board. The bending deformation and the bending stress of the flexible printed circuit board under the condition of large-deflection bending are theoretically solved, the workload of experiments or simulation is greatly reduced, and the reliability of the flexible printed circuit board can be quickly evaluated.

The application discloses a rubber-cement composite material surface modifier optimization method based on molecular simulation, which comprises the following steps: based on molecular dynamics simulation, a full-atom numerical model for characterizing the physicochemical properties of cement matrix, rubber and modifier material is constructed by using Materials Studio software; based on the full-atom numerical model, the Gibbs free energy of the material system is calculated by using a quantum mechanics method to predict whether chemical reaction or physical adsorption behavior occurs between the selected modifier and the two types of materials of rubber and cement, and finally a rubber-cement-based composite material system model before and after the treatment of the modifier is constructed; the free volume fraction and atomic concentration of the composite material system model before and after the modification are analyzed on a microscale to quantitatively evaluate the effect of the modifier on the material performance, and then the optimal surface modifier is determined. The application can construct a numerical model accurately reflecting the material properties and analyze and optimize the material surface / interface modifier.

The invention discloses a supporting device for aircraft part composite material processing, belongs to the technical field of aircraft part composite materials, and aims to solve the problems that in the use process of the composite material supporting device, after a composite material is fixed, the bottom of the composite material cannot be vacated, so that after the composite material is supported and fixed, the processing is limited, and the composite material cannot be damaged. The problems that in the prior art, the shielding position of a composite material and a table top cannot be conveniently machined, corresponding clamps cannot be replaced according to the shapes of different composite materials, and practicability is reduced are solved. Through cooperation of the supporting base, the supporting channel, the supporting plate, the fixing mechanism and other structures, a composite material can be placed on the surface of the supporting plate before being fixedly clamped, and after the composite material is tightly clamped, the supporting plate can be pulled out, and the space below the composite material is vacated; in this way, workers can conveniently machine and treat the composite material.

The application relates to the technical field of industrial material cutting, in particular to a laser cutting process method and equipment for composite materials, which comprises the following steps: running cutting software in a cutting equipment, and importing a cutting file into the cutting software; placing a composite material to be cut on a workbench of the cutting equipment; and cutting the composite material to be cut in a non-contact manner by using a laser on the workbench based on the cutting file. Since the laser is used to cut the composite material to be cut in a non-contact manner according to the method, compared with a traditional composite material cutting method, the laser cutting process method for the composite material provided by the application has small heat influence on the cut composite material, and the cut composite material has no burr on the edge, so that the deformation and poor precision of the composite material caused by the traditional physical contact (such as using a cutter wheel, a grinding wheel and the like) cutting method are avoided, and the quality of the cut composite material is improved.

This laminate film provides desired optical properties regardless of the luster or surface roughness of the adherend and exhibits excellent durability, even under high-humidity conditions. The film includes, in order, a protective film, a coating layer, a resin substrate, and an adhesive layer, with the protective film and the coating layer positioned adjacent to each other. When the protective film is peeled from the laminate at a specific rate, the surface roughness (Rac, Rap), surface free energy (γac, γap), and Martens hardness of the coating layer meet specific criteria. Additionally, the 60° gloss values (G(IL), G(IC)) of the laminate film, both alone and in combination with the adherend, satisfy certain equations. After damp heat testing, the 60° gloss (G(A)) of the composite and the 60° gloss (G(IC)) satisfy a specific equation.

The invention discloses a method for preparing a B4C / Ti6Al4V composite material through laser melting deposition and application of the B4C / Ti6Al4V composite material, and belongs to the technical field of additive manufacturing. According to the preparation method disclosed by the invention, the B4C / Ti6Al4V composite material synergistically enhanced by B4C, TiB and TiC is prepared from B4C powder of 65-73 microns and spherical Ti6Al4V alloy powder of 45-75 microns by adopting a laser melting deposition technology; the volume fraction of B4C in the B4C / Ti6Al4V composite material is 1 to 5 vol.%. The B4C powder is added into the Ti6Al4V alloy, so that TiB and TiC reinforced phases are generated in the composite material in situ, and undissolved B4C exists. After the B4C is added, beta-Ti and alpha-Ti grains in the composite material are refined. The C element is subjected to solid solution in a matrix, and TiB generated in situ plays a bearing role in the stretching process. And the laser melting deposition technology of the method adopts two paths of powder feeding, so that the uniformity of B4C in the composite material is improved. By adopting the method for preparing the B4C / Ti6A14V composite material, rapid forming can be realized, the subsequent processing time is shortened, and the cost is saved.

The invention discloses a preparation method of a high-densification and high-thermal-conductivity diamond copper-based composite material. The preparation method comprises the following steps: weighing the following components in percentage by mass: 15-49 wt% of diamond single crystal particle powder; 1 to 5 wt.% of silver powder; the preparation method comprises the following steps: mixing the components, putting the uniformly mixed diamond single crystal particle powder, copper powder and silver powder into a vacuum hot pressing sintering furnace, sintering at 962-1085 DEG C to obtain a composite material, and uniformly filling gaps in the composite material with semisolid copper and liquid silver in the sintering process; by adding a small amount of silver powder, the diamond and the copper matrix can be better fused, and improvement of the density of the composite material is facilitated; vacuum sintering is adopted, on one hand, the preparation speed of the composite material is increased, and on the other hand, the silver powder is melted through heating in an extremely short time, gaps are fully filled, and the density of the composite material is improved; as the thermal conductivity of silver is better than that of pure copper, the thermal conductivity of the composite material is further improved after pores are fully filled.

The present invention discloses a Co-BDC / MXene nanocomposite material, a preparation method and an application, which belong to the field of gas sensors. The present invention provides a Co-BDC / MXene nanocomposite material and an application. The Co-BDC / MXene-based sensor has good sensitivity to acetone gas, a low detection limit and a wide detection range. The stability of the Co-BDC / MXene composite material is also improved compared to the pure MXene material, so the stability of the Co-BDC / MXene-based acetone sensor will be better. At the same time, due to the good flexibility and plasticity of the MXene material, the Co-BDC / MXene composite material has the possibility of preparing a flexible wearable gas sensor. Finally, the conductivity of the Co-BDC / MXene composite material is significantly improved compared to traditional MOFs.

The application discloses a SiC f / SiC composite material containing a high-strength and high-modulus matrix and a preparation method and application thereof, and relates to the technical field of silicon carbide-based composite materials. The method comprises the following steps: preparing a CVI-BN interfacial phase in a SiC fiber preform by adopting a chemical vapor infiltration process, introducing SiC whiskers in the SiC fiber preform by adopting a gel injection molding process, and obtaining a porous composite material; placing the porous composite material in a first polycarbosilane slurry for multiple times of impregnation and pyrolysis, so as to obtain a semi-dense SiC f / SiC composite material; placing the semi-dense SiC f / SiC composite material in a second polycarbosilane slurry for multiple times of impregnation and pyrolysis, so as to obtain a dense SiC f / SiC composite material; the application promotes the formation of a continuous rigid load-carrying skeleton in the matrix by jointly modifying a PIP-SiC matrix by means of inert fillers SiC w and active fillers silicon powder, reduces the defect content of the matrix, improves the crystallinity, and purifies the components. The mechanical properties of the modified composite material are improved by more than 30%.

A cast cup can include a forward portion of a golf club head, including a hosel, a face portion, and forward portions of a crown, sole, heel and toe. A rear ring can be formed separately from the cast cup and coupled to heel and toe portions of the cast cup to form a metallic club head body, such that the club head body defines a hollow interior region, a crown opening, and a sole opening. The cast cup and rear ring can be cast of titanium alloys. Composite crown and sole inserts can then be coupled to the crown opening and sole opening. The face portion of the cast cup can have a desirably complex geometry. The rear surface of the face portion of the cast cup can be modified before the rear ring is attached.

The utility model discloses a high-ductility prepreg preparation device, which relates to the technical field of composite material preparation and comprises an operating platform, two groups of symmetrically arranged mounting plates are fixedly connected to the upper side of the operating platform, positioning mechanisms are mounted outside the mounting plates, and mounting strips are fixedly connected to two sides of the operating platform. Mounting grooves are formed in the inner sides of the two mounting strips, sliding grooves are formed in the outer portions of the mounting grooves, sliding blocks are slidably connected to the inner sides of the mounting grooves in a limiting mode, a translation mechanism is mounted in the operation table, a mounting frame is fixedly connected between the two sliding blocks, and a multi-point cutting assembly is mounted on the outer portion of the mounting frame. According to the device, fiber tows on the surface layer of the prepreg are accurately cut off in translational motion by adopting the rotary blades which are distributed in a staggered manner, the restraining force of a fiber network on resin is reduced by generating micro-incisions, and the ductility of a cured composite material is directly improved.

This invention relates to an epoxy resin adhesive, its preparation method, and its application. The adhesive comprises 100 parts by weight of epoxy resin, 1-10 parts by weight of dicyandiamide micronized curing agent, 3-20 parts by weight of metal micronized powder, and 10-30 parts by weight of thermoplastic acrylic resin. The adhesive preparation process of this invention does not use solvents, and the adhesive has no irritating odor, meeting environmental protection requirements. It is chemically stable at room temperature, and once used, there is a strong interaction between the adhesive and the composite material, making it difficult to detach. The bonding time is short, and it is easy to manufacture into various shapes, with good adaptability to the bonding site. The adhesive is in a solid state, can be stacked, and can be arbitrarily adapted to the bonding spacing of composite materials, facilitating the bonding process. The composite material bonded by the adhesive is resistant to high temperatures; after high-temperature use, there are no cracks or detachment at the bonding joints, and it still possesses good mechanical properties.

The application discloses a composite material and a preparation method and application thereof. The composite material is composed of a porous carbon material as a carrier and a metal organic compound as a precursor; wherein oxygen groups of the porous carbon material are connected with metal centers of the metal organic compound through coordination bonds. The composite material is prepared by using a heating reflux method, and the composite material of graphene oxide loaded MOFs with high water stability is prepared by taking graphene oxide as a functionalized carrier. After adding a small amount of GO, the composite material shows smaller aggregated particles compared with MOFs, which is attributed to the coordination between oxygen groups in graphene oxide layers and metal centers in MOFs, so as to prevent the aggregation of MOFs microcrystals and increase the dispersity of the microcrystals, more adsorption active sites can be provided to increase the adsorption performance, and the composite material can be used for efficient capture of CO2.

The utility model relates to the technical field of composite material processing, and discloses a mould pressing device for composite material processing, which comprises a base and a locking mechanism, the upper surface of the base is provided with a plurality of mounting grooves I, the upper surface of the base is fixedly provided with a lower module through the locking mechanism, and the top end of the lower module is provided with an inner groove. And a lower mold plate is clamped in the inner groove in a sliding manner. A composite material to be subjected to mold pressing is placed on the lower mold plate, the hydraulic rod drives the movable seat to press downwards, so that the upper mold plate completes mold pressing machining on the composite material, after machining is completed, the hydraulic rod drives the movable seat to move upwards to be opened, and at the moment, due to traction force of the movable seat, the movable frame is pulled through the hook rope to move upwards; and the moving frame moving upwards drives the ejector rod to move upwards, so that the lower mold plate is ejected out of the inner groove, the composite material subjected to mold pressing is convenient to take, the problem that the composite material subjected to mold pressing is difficult to take out through an existing device is solved, and application and popularization are facilitated.

The invention discloses a wide-temperature-range high-strength nickel-based self-lubricating composite material and a preparation method thereof. The wide-temperature-range high-strength nickel-based self-lubricating composite material comprises 50-95% of nickel-based alloy, 5-15% of Ag, 0-10% of Mo, 0-15% of MoS2 and 0-10% of Ti3SiC2. The method comprises the steps that S1, nickel-based alloy powder, Ag, Mo, MoS2 and Ti3SiC2 are mixed and subjected to ball milling, and then the ball-milled powder is placed in a discharge plasma sintering furnace provided with a graphite mold to be sintered; s2, after sintering is finished, the composite material is cooled to the room temperature along with the furnace, and then heat treatment is conducted in a muffle furnace; and S3, air cooling is conducted to the room temperature, and the wide-temperature-range high-strength nickel-based self-lubricating composite material is obtained. The prepared wide-temperature-range high-strength nickel-based self-lubricating composite material is good in organizational structure stability and excellent in mechanical property and tribological property, and has wide application prospects in the working conditions of high temperature, heavy load and difficult lubrication or maintenance as a self-lubricating material.

The application relates to a multi-scale feature fusion composite material damage mechanics behavior prediction method and system, and relates to the technical field of material damage prediction. An initial graph neural network is generated according to initial mapping data sets, variation data is obtained according to a preset inversion network and is updated to corresponding nodes in the initial graph neural network, topological adjustment instructions for the graph structure are obtained and an adaptive graph neural network is reconfigured and generated, the current damage index and the current residual strength of the composite material are obtained, the damage accumulation process thereof is iteratively simulated to generate a load adjustment suggestion, and the measured damage index of the composite material after the execution of the load adjustment suggestion is obtained, and the preset weight coefficient in the preset inversion network is updated in combination with the current damage index. The real-time performance, the accuracy and the active risk avoidance capability of the composite material damage prediction can be significantly improved.

The invention relates to the technical field of catalysts, in particular to a nickel-manganese oxide pompon structure composite material and a preparation method and application thereof.The preparation method comprises the following steps that a nickel chloride solution and a potassium permanganate solution are mixed and stirred, and then a mixture is obtained; and carrying out a hydrothermal reaction on the mixture, after the reaction is finished, filtering, taking a precipitate, washing, drying, and grinding to obtain the NiMn2O3 (OH) 4 composite material. According to the NiMn2O3 (OH) 4 composite material prepared by the method disclosed by the invention, the efficiency of degrading organic pollutants by potassium hydrogen persulfate can be remarkably improved; and Ni can remarkably reduce the leaching rate of metal ions in the NiMn2O3 (OH) 4 composite material, and secondary pollution to the environment caused by leaching of the metal ions is avoided. After four times of cycle experiments, the degradation efficiency of the NiMn2O3 (OH) 4 composite material for activating PMS to degrade organic pollutants is still up to 98% or above, and it is proved that the NiMn2O3 (OH) 4 composite material has good stability and reusability.

The application discloses a kind of UHMWPE fiber reinforced epoxy composite battery protection plate and preparation method and application, belong to high polymer composite material and battery safety protection technical field.The application is through "plasma surface activation-GA / PEI and its derivative synergistic co-deposition-metal ion secondary coordination crosslinking-epoxy resin impregnation pre-curing-composite layer / metal layer laminating molding" multistage interface enhancement route, solve the problem that UHMWPE fiber surface inertness is big, and weak with epoxy matrix bonding, and easy interlayer peeling under impact.Experimental results show that:O2 plasma treatment 320 s can significantly improve fiber interface reactivity;After continuous modification by GA / PEI and its derivatives and metal ions, the peel strength and bending strength of the composite material are significantly improved;Under the working condition of 300 J drop hammer, the protection plate can remain without penetration failure and improve the energy absorption capacity.The application has clear process window, raw materials are easy to obtain, and has good repeatability, and is suitable for the manufacture of lightweight high-safety protection structure of new energy vehicles and energy storage systems.

The present application provides a method for filling pinhole recesses on a carbon fiber composite honeycomb surface. The method comprises: preparing a repair adhesive for a composite structure; pouring an organic solvent into a spray bottle for spraying the organic solvent onto the marked areas of the pinholes and small recesses, wherein the spraying time of the organic solvent does not exceed 10 s each time, and finishing blade coating of the repair adhesive within 30 s after spraying; by means of the volatilization effect of volatile matter in the organic solvent, dripping the adhesive solution into the pinholes and the small recess areas for filling, so as to obtain a smooth and continuous part surface; after the blade coating of the repair adhesive is finished, placing the composite honeycomb part that has been subjected to blade coating in a curing furnace for curing; and after curing is finished, polishing the blade-coated area by using alumina water-resistant sandpaper to remove excessive adhesive solution on the surface of the part. Moreover, the present application further provides a verification method for the carbon fiber composite honeycomb surface. In the present application, pinholes and small recesses on the surface of the carbon fiber composite honeycomb part can be filled, and the composite honeycomb part meets the primer spraying requirement after an adhesive spraying method is adopted.

A rewinding and unwinding mechanism for prepreg sheets used in composite material patch repair, comprising a slideway and table units. The slideway is in a "Z" shape and includes a horizontal straight section, a first arc section, and a vertical straight section. One end of the horizontal straight section is a free end, the other end of the horizontal straight section is connected to one end of the first arc section, and the other end of the first arc section is connected to the lower end of the vertical straight section. The table units are slidably connected to the slideway. There are multiple table units arranged in a line, and adjacent two table units are rotatably connected. With the "Z" - shaped slideway design, during use, the table units slide to the horizontal straight section of the slideway, and when not in use, the table units slide to the vertical straight section of the slideway. Before and after use, the size of the composite material patch repair system will not increase, ensuring that its volume is small enough. A composite material patch repair system is also provided.

The application relates to a preparation method of a graphene / carbon nanotube / ferroferric oxide composite material for heat conduction and electromagnetic shielding. The graphene / carbon nanotube / ferroferric oxide composite material is prepared through two steps of hydrothermal reaction and heat treatment. In the hydrothermal reaction process, ferroferric oxide particles are generated, and graphene oxide is wrapped on the surface of the ferroferric oxide particles; carboxylated carbon nanotubes are connected to the surface of the graphene oxide through group reaction; meanwhile, reduction reactions of the graphene oxide and the carboxylated carbon nanotubes occur, and a core-shell multi-level structure is formed. In the drying process, compression molding is carried out, and the graphene / carbon nanotube / ferroferric oxide composite material is obtained; the internal structure is that graphene sheets are stacked to wrap the ferroferric oxide particles, and the carbon nanotubes are cross-linked to form a carbon nanotube network; after high-temperature heat treatment, the dielectric constant of the composite material is greatly improved, a complete shielding network and a heat conduction path are formed, and excellent comprehensive performance is exhibited.

The application relates to a multi-scale feature fusion composite material damage mechanics behavior prediction method and system, and relates to the technical field of material damage prediction. An initial graph neural network is generated according to initial mapping data sets, variation data is obtained according to a preset inversion network and is updated to corresponding nodes in the initial graph neural network, topological adjustment instructions for the graph structure are obtained and an adaptive graph neural network is reconfigured and generated, the current damage index and the current residual strength of the composite material are obtained, the damage accumulation process thereof is iteratively simulated to generate a load adjustment suggestion, and the measured damage index of the composite material after the execution of the load adjustment suggestion is obtained, and the preset weight coefficient in the preset inversion network is updated in combination with the current damage index. The real-time performance, the accuracy and the active risk avoidance capability of the composite material damage prediction can be significantly improved.

A method for repairing composite material structures using an I-shaped patch design includes the following steps: Step 1: After determining the number of layers to be removed from the damaged area, the damaged area is processed into an "I-shaped" structure; Step 2: Based on the patch repair layer with the smallest diameter or area, the lower patch with a larger diameter or area is cut into N (N≥2) parts according to the process separation surface; Step 3: Under pre-compaction temperature, the splicing area between the parts of the cut patch in Step 2 is pressed under high pressure to complete the overall splicing process of the patch; Step 4: After sequentially stacking the upper patches, the structure is sealed and cured to complete the repair process. This method can improve the mechanical properties of the composite material structure after damage repair and is applicable to the repair process of laminated structures such as composite skins and sandwich composite panels.

The invention belongs to the technical field of composite materials, and particularly relates to a high-heat-resistance recyclable epoxy carbon fiber composite material and a preparation method thereof. A degradable epoxy resin system is used as matrix resin, carbon fiber cloth is used as a reinforced base material, the carbon fiber cloth is impregnated through the degradable epoxy resin system to prepare prepreg, and the prepreg is obtained through hot press molding. The high-heat-resistance recyclable epoxy carbon fiber composite material disclosed by the invention has relatively high heat resistance, and complete degradation and recycling of each component can be realized in a relatively mild environment. Before degradation, the bending strength of the composite material is up to 900 MPa, the tensile strength is 700-800 MPa, the composite material has excellent high temperature resistance, and the mechanical strength retention rate of the composite material after aging treatment is 92% or above; the composite material can be rapidly degraded at the temperature of 100 DEG C, the carbon fiber cloth can be recycled for multiple times, the bending strength and tensile strength retention rate of the composite material are both 90% or above, and a solvent and degradation products in degradation liquid are easy to separate, recycle and reuse.

The application discloses an aluminum / carbon fiber / diamond composite material with a bonding layer generated in situ under turbulent impact, a heat dissipation sheet and a preparation method thereof, and belongs to the technical field of composite material preparation. The aluminum / carbon fiber / diamond composite material is prepared by the following steps: an AlTiSi / carbon fiber master alloy is prepared by stirring casting; the master alloy is melted and infiltrated into a mold filled with diamonds to obtain a composite material heat dissipation sheet; and high and low temperature heat treatment is carried out under atmosphere protection to obtain the final aluminum / carbon fiber / diamond composite material heat dissipation sheet. Under the combined action of in-situ reaction and turbulent impact, the carbon fiber is completely dispersed to form a uniform and fine heat conduction network. In the heat conduction network formed by the carbon material, the large-size diamond is used as the main body, and the micron-scale carbon fiber network is uniformly distributed in the gap of the diamond network. After the joint addition of Ti and Si, the interface reaction of the composite material is sufficient, the interface thermal resistance is small, and the bonding strength is high. Through the adjustment of the particle size and proportion of the diamond and the carbon fiber, a combination with better thermal conductivity and expansion coefficient can be obtained.

The application discloses a cross-linked PBT composite material suitable for lead-free welding, which comprises the following raw materials in parts by mass: PBT resin: 30-80 parts, inorganic fiber: 0-60 parts, cross-linking auxiliary master batch: 5-40 parts, halogen-free flame retardant: 5-25 parts, antioxidant: 0.1-1 part, and lubricant: 0.2-1 part. After high-energy ray radiation, three-dimensional network cross-linking structure is generated between internal macromolecular chains of the composite material, the temperature resistance of PBT is significantly improved, and PBT does not melt even at a temperature of more than 400 DEG C, so that the temperature resistance limit of traditional thermoplastic PBT can be broken, and the lead-free welding process at a higher temperature can be applied. In addition, the cross-linking is carried out after the material is injection molded into a product, and the easy processing and molding advantages of PBT are not changed, so that the cross-linked PBT composite material is convenient to apply to the production of electrical elements such as connectors and relays which need lead-free welding. Compared with special engineering plastics which are high in price and difficult to process, the cross-linked PBT composite material has the remarkable advantages of low cost and easy processing.

A method for preparing a non-uniform micro-nano SiCp hybrid reinforced aluminum matrix composite material is disclosed, relating to a method for preparing aluminum matrix composite materials. The aim is to address the problem of high strength but low plasticity in existing silicon carbide particle reinforced aluminum matrix composites. The micro-nano SiCp hybrid reinforced aluminum matrix composite material prepared by this invention has a non-uniform microstructure, wherein the nano-silicon carbide particles are embedded inside the aluminum matrix particles, hindering dislocation movement and having minimal impact on matrix deformation, thus maintaining high plasticity while improving material strength; the micron-sized silicon carbide particles are distributed on the surface of the aluminum matrix particles, hindering dislocation movement and matrix deformation, thereby improving the material's strength and stiffness. After extrusion treatment, the composite material exhibits a tensile strength up to 768 MPa, an elastic modulus exceeding 109 GPa, and an elongation exceeding 13.6%.

The invention discloses an assembly structure and an assembly method for a composite guide pipe and a stator of a pump-jet propeller. The assembly structure comprises a guide pipe and a stator, the guide pipe is divided into a small guide pipe end body and a large guide pipe end body along the middle of the pipe wall, the depth of the large guide pipe end body is smaller than that of the small guide pipe end body, and the stator is arranged in the large guide pipe end body after being of an integral structure composed of stator blades and a stator hub and connected with the large guide pipe end body to form a large guide pipe end combination structure. The assembly method comprises the following steps of: assembling the stator blades and the stator hub, assembling the guide pipe and the stator, and assembling the guide pipe large end body assembly and the guide pipe small end body to complete the assembly of the whole structure. According to the method, the assembling method of the stator blades and the stator hub is optimally designed, so that the overall precision of the assembled composite material stator can be ensured while the assembling process is ensured to be smoothly and efficiently completed; and through the assembly design of the conduit and the stator, the connection performance of the conduit and the stator is optimized, and the reliability of the structure and the convenience of installation and maintenance are ensured.