76 results about "Material repair" patented technology

The invention discloses an ultrasonic-annular water cooling synergetic thermosetting composite material repairing method and equipment, on the basis of coaxial annular water cooling, an annular cooling cavity with a variable contour and a structural design of a closed ring with a plane contour which can be circular, elliptical, waist-circular or polygonal are introduced, so that the inner side contour of a cooling ring can be more attached to a welding area. For a large-size or irregularly-shaped thermosetting matrix component repaired by adopting ultrasonic local fusion welding, the cooling zone can be tightly attached to the outline of a welding interface in the circumferential direction through the design, heat is effectively prevented from overflowing along a complex boundary, compared with a fixed circular or linear cooling structure, the range of a heat affected zone can be further narrowed, and the service life of the component is prolonged. And a high-temperature area in the thermosetting matrix is more limited near a welding interface, so that the overall temperature of the thermosetting matrix is always lower than the glass-transition temperature while sufficient melting and flowing of the thermoplastic patch are ensured, and resin degradation and interface strength attenuation caused by local overheating are avoided.

The invention relates to the technical field of material repair, and discloses a wave-absorbing foaming adhesive film and a preparation method thereof.The wave-absorbing foaming adhesive film comprises a fiber layer, a first surface and a second surface, and the fiber layer is provided with the first surface and the second surface opposite to each other in the first direction; the first adhesive layer is arranged on the first surface; the second adhesive layer is arranged on the second surface; the first backing layer is arranged on the surface, far away from the fiber layer, of the first adhesive layer; the second backing layer is arranged on the surface, far away from the fiber layer, of the second adhesive layer; wherein the wave absorbing intensity of the first adhesive layer and the wave absorbing intensity of the second adhesive layer are gradually changed in the second direction, and the second direction is perpendicular to the first direction. Different areas in the wave-absorbing foaming adhesive film are different in wave-absorbing strength, the wave-absorbing foaming adhesive film has flexible wave-absorbing performance strength distribution, and the wave-absorbing foaming adhesive film has a foaming function and is particularly suitable for repairing functional structures such as wave-absorbing honeycombs and the like.

The invention discloses an evaluation method, device and equipment for composite material repair consumables and a medium, and relates to the technical field of composite material structure maintenance. A series of controllable disturbance factors are introduced around reference process parameters to simulate actual fluctuation, and the system tests the performance of the repair consumables under non-ideal process conditions, so that the safety boundary of qualified products produced by the repair consumables is determined, and a more comprehensive and practical evaluation system is provided. A process window volume is introduced as an objective and comparable robustness quantitative index, and a process space boundary is efficiently predicted by means of a Gaussian process regression model, so that the problems of high cost and low efficiency of a traditional exhaustion test method are avoided. According to the method, the process robustness for determining the stability of the repair consumables in the actual maintenance environment is converted into the quantifiable and comparable equivalent curing process window and the measurement value thereof, scientific screening of the repair consumables is realized, and the quality risk in actual maintenance operation is remarkably reduced.

The utility model, which relates to the technical field of circuit board repairing, discloses a folding and pressing damage repairing device comprising a machine table provided with a material carrying table, a fixing mechanism, a conveying mechanism, a repairing mechanism and an adjusting mechanism. When the material repairing device is used, a material to be repaired is placed on the material carrying table and fixed through the fixing mechanism, then the position of the repairing pressing head is adjusted through the adjusting mechanism, the bottom of the repairing pressing head is flush with the top face of the material, and then the conveying mechanism drives the material carrying table to move under the repairing pressing head. And when passing through the repairing pressure head, warped edges or bumps on the material are flattened by the repairing pressure head, so that the material is repaired by folding and pressing damage, manual repairing is not needed, and the repairing efficiency is improved.

This invention belongs to the technical field of thermal insulation material repair in water conservancy projects. Specifically, it discloses an embedded permanent thermal insulation template anchoring and repair structure and method for dam surfaces. The structure includes a broken bridge support structure located inside the thermal insulation template. One inner end of the broken bridge support structure is connected and fixed to the concrete dam body via an anchoring device. A connecting screw is installed inside the outer end of the broken bridge support structure. The outer end of the connecting screw has a threaded hole, and a pressure plate is installed at the outer end of the connecting screw. The threaded end of the screw passes through the central hole of the pressure plate and connects and is fixed to the threaded hole of the connecting screw, so that the pressure plate abuts against the outer protective layer of the thermal insulation template. This allows the original broken bridge support structure to be used to fix the newly replaced outer protective layer, achieving the repair of the thermal insulation template.

The application discloses a kind of quick repair methods of ternary lithium material, it is related to battery material repair field.The method includes that ternary pole piece is broken, screening is mixed with white carbon black, carries out primary roasting in inert gas atmosphere, removes white carbon black by separation, removes suspended substance by washing with water, after material drying, ball milling, carries out secondary roasting in inert gas atmosphere, obtains repaired ternary lithium pole piece powder.The application carries out repair processing to the pole piece of electric performance drop, adds white carbon black in the process of roasting and removing organic matter, utilizes white carbon black and the reaction of HF generated by pyrolysis, avoids the reaction of HF and ternary lithium crystal, guarantees the integrity of ternary crystal structure, significantly improves the electric performance repair effect of pole piece powder, after being applied to the preparation battery, capacity, charging efficiency and electric cycle stability are significantly improved, avoid the ecological pollution caused by irregular discharge of waste ternary lithium material to environment, with economy and sustainable development.

The present disclosure provides an aviation composite material repair digital twin and intelligent repair method, system and device, wherein the method comprises: transmitting the repair elements of the aviation composite material repair entity collected in real time to the aviation composite material repair digital twin; the digital twin establishes an initial visual digital model of the repair entity according to the structure parameters and damage parameters of the repair entity; the digital twin searches the design space according to the repair process parameters, predicts the key performance of different repair process parameter combinations, and obtains the target repair process parameters required for the repaired repair entity to achieve the key performance; the digital twin predicts the full-field distribution information of the key performance of the repair entity according to the repair process parameters and the initial visual digital model, and displays and analyzes; and transmitting the received target repair process parameters to the repair tool; setting the repair process according to the target repair process parameters through the repair tool, and implementing intelligent repair of the repair entity.

The utility model relates to building waterproof technical field, a kind of anti-seepage anti-cracking type underground engineering composite waterproof layer structure, base layer further include: the first waterproof layer of playing primary waterproof function, set in the top of the base layer, the top of the first waterproof layer is provided with the second waterproof layer of playing the waterproof effect of reinforcement;The utility model is through the fourfold block of "base layer anti-seepage+coating closed+coiled material barrier+self-repairing concrete", realizes above P12 anti-seepage grade;HPT-X nuclear material inhibits crack generation, non-solidified coating buffering deformation stress, YX-H material repairs microcrack, forms full-cycle anti-cracking system;Polymer coiled material anti-aging, drainage system reduces water pressure, ensure that waterproof layer long-term effective, the structure is through material synergy and system design, solved the problems, such as traditional waterproof layer easy cracking, easy aging, maintenance difficult, applicable to high water level, geologically complex area's underground engineering.

A construction material repair device designed for filling, repairing, and restoring defects in construction materials comprising right-handed female tapered helical thread to aid insertion and adhesively secured into the construction material to cosmetically repair and structurally restore the defect in minimal steps, time, and cost. The device is manufactured in a variety of materials to match or complement the construction material requiring repair.

The utility model discloses an environment-friendly material repairing device based on indoor decoration, which comprises a front support frame, a rear support frame and a repairing main machine, the bottom of the repairing main machine is communicated with a repairing mechanism arranged between the two support frames, the repairing main machine is fixedly connected with the tops of the two support frames, and an adsorption assembly is arranged below the two support frames; the repairing mechanism comprises a left sliding rail and a right sliding rail, the two sliding rails are fixedly installed between the front supporting frame and the rear supporting frame, and a lead screw is rotationally connected between the front face and the back face of the inner wall of each sliding rail. According to the environment-friendly material repairing device based on indoor decoration, a repairing material is sprayed to a local damaged area through the repairing spray head, and the repairing material is evenly smeared through the repairing roller, so that rapid repairing of a decorative plate is achieved; and through cooperation of the elastic pressure assemblies, the repairing rolling wheels can make good contact with the surface of the decorative plate.

The invention relates to the field of airplane composite material maintenance, and particularly discloses a composite material layering damage in-situ prefabrication method based on chemical reaction, which comprises the following steps: cutting prepregs, and obtaining the prepregs with corresponding quantity and angle; calculating the volume V and the mole number n of the required gas; calculating the mass of the required chemical reagent according to the mole number n of the required gas; laying a predetermined number of layers of prepregs, and then spreading a chemical reagent at the laying position on the prepregs; a preset number of layers of prepregs are laid on the upper portion where the chemical reagent is laid; and the laid composite laminated plate is heated and pressurized to be cured, and gas generated by decomposition forms a cavity in the composite laminated plate after curing is completed. In the paving and manufacturing process of the composite material, a small amount of chemical reagent capable of generating gas through thermal decomposition is arranged between prepreg paving layers, in the heating and curing process of the composite material, the chemical reagent is decomposed to generate gas, and then layering damage can be prefabricated in the composite material.

The application discloses a kind of carbon fiber composite material defect repair equipment and repair method, it is related to gas cylinder repair equipment field, technical scheme is, including chassis, the middle part of chassis is set through passage, the lower portion of passage is set for supporting the support mechanism of carbon fiber gas cylinder, the upper surface of chassis one side parallelly arranged two slide rails, each slide rail is slidably connected with a slider, the clamping mechanism for clamping carbon fiber gas cylinder is fixedly arranged on slider, the middle part of clamping mechanism is set inflation passage, the inflation passage is coaxial with the axis of carbon fiber gas cylinder with gas inlet;The side of chassis is fixedly set main push rod;It further includes the guide rail fixedly set in the side of chassis, the repair mechanism for carbon fiber composite material repair is slidably arranged on guide rail.The beneficial effects of the application are: simple structure, convenient to use, fast repair speed, effectively shorten the repair time of carbon fiber gas cylinder, improve repair efficiency, reduce manpower and material cost.

This invention provides an active material repair patch, comprising non-woven fabric and release paper. The release paper is formed on the lower end face of the non-woven fabric. A wrapping bag is disposed between the non-woven fabric and the release paper. Specifically, the wrapping bag consists of two sets of wrapping films sealed on all four sides. An air bag I and an air bag II are disposed inside the wrapping bag. Two sets of soluble microneedles are disposed on the other side of the wrapping film adjacent to the non-woven fabric. An active repair material is applied to the corresponding position of the wrapping film adjacent to the release paper. This invention involves applying the non-woven fabric to the affected area, and then pressing the repair patch to puncture the lower wrapping film through the soluble microneedles. The active repair material is then applied to the affected area through the puncture holes. Due to the adhesive properties of the repair material, the gas inside the air bags, released through the puncture holes, accumulates around the applied patch, preventing the non-woven fabric from sticking to the surrounding area and causing pain when the patch is removed for dressing changes.

The application relates to a composite material repairing assembly and a composite material repairing method, wherein the composite material repairing assembly comprises: a pretreatment layer, which can be laid on a wind power blade and covers a to-be-repaired area; a pouring auxiliary material layer, which is arranged on one side of the pretreatment layer in a thickness direction of the composite material repairing assembly; a first vacuum layer, which is arranged on a side of the pouring auxiliary material layer away from the pretreatment layer, and covers the pouring auxiliary material layer; and a second vacuum layer, which is arranged on a side of the first vacuum layer away from the pretreatment layer, and has an area greater than that of the first vacuum layer. The composite material repairing assembly can improve repairing efficiency and convenience.

The utility model relates to the technical field of material repair, and discloses a welding gun water cooling device of an electric spark surfacing repair machine, which comprises a repair machine main machine and a welding gun, the repair machine main machine is connected with the welding gun through a connecting line, and the side wall of the welding gun is respectively provided with a liquid outlet and a liquid inlet. One side of the repairing machine main machine is sequentially provided with a guiding and returning water pump, a cooling box and a guiding-out water pump, the input end of the guiding-out water pump is connected with the welding gun through flow guiding pipes, and the two flow guiding pipes are connected with the liquid outlet and the liquid inlet through hoops. According to the utility model, the heat dissipation area is increased through the annular spiral cooling channel, and the cooling efficiency is improved; the flexible pipeline is in buckle type surrounding clamping connection, rapid disassembly and assembly are facilitated, the operation flexibility is improved, and the burden of a welding gun is relieved; a filtering device is additionally arranged in a cooling liquid circulation path, blocking is effectively prevented, and the stability and durability of the system are improved.

The present application relates to the technical field of composite material repair, and particularly relates to a composite material rapid repair method based on chopped carbon fiber technology, comprising the following steps: chopped carbon fiber pretreatment; resin matrix preparation; spray slurry preparation; laser cleaning of the damaged area; scanning of the unmanned aerial vehicle; layered synchronous curing; evaluation of the coating quality; the chopped fiber spraying technology is used in the aspect of composite material damage repair, the repair time is reduced, the cost is reduced, the interface bonding strength and the fiber orientation are optimized, the problem that the interlayer peeling or the fiber orientation mismatching is prone to occur in the repair area, and the mechanical property recovery rate of the repaired material is low is solved, the thickness of the bubble defect can be rapidly detected, the method is suitable for efficient, accurate and lightweight repair of carbon fiber reinforced composite material (CFRP) damage, and is particularly suitable for on-site rapid repair scene.

The application belongs to the technical field of ceramic matrix composite material repair, and relates to a SiC / SiC composite material suture repair method and application. The method can repair the overall defect in the thickness direction of the SiC / SiC composite material by designing a matched suture interface, using a repair body and a suture line made of the same material as the body and being fixed, and combining a densification and reinforcement process, and can ensure that there is a continuous fiber connection between the repaired part and the body, thereby expanding the application range of the SiC / SiC composite material repair, significantly improving the mechanical properties of the composite material after repair, enhancing the reliability and service life of the composite material, and meeting the needs of related fields for high-performance ceramic matrix composite material repair.

A method for lifting and turning steel structures without welded lifting lugs involves CNC-controlled or manual drilling of permanent openings in the vertical plates or webs of T-beams of the steel structure, with the positions and number matching the crane's lifting points. Permanent reinforcing plates are welded around these openings for reinforcement. The opening dimensions must meet the pin assembly requirements of the turning connection device, and the reinforcing plate dimensions must meet the assembly requirements of the lifting and turning device and comply with safety regulations. After the tooling is connected to the permanent openings in the structure, during lifting and turning at 180°, the load-bearing connecting plate and the free edge of the T-beam are in line contact, facilitating the bearing of line load pressure and thus optimizing the overall stress distribution of the tooling. This method completely eliminates lengthy and high-risk additional processes such as lifting lug installation, flaw detection, cutting, grinding, and base material repair. Preparation time before lifting and turning and post-turning processing time are reduced by more than 80%, significantly improving production line efficiency.

The invention discloses a masonry hole rapid layering repairing composite material and method based on solid waste, and belongs to the technical field of building material repairing and solid waste recycling. The composite material is composed of 10-30 parts of alpha-ethyl cyanoacrylate (ECA) and 1-30 parts of alkaline solid waste powder, such as combustion ash powder CAP and alkaline residue powder SRP. The repairing method comprises the steps that after holes are cleaned, a layering process is adopted, an alkaline powder layer with the thickness of 2-3 mm is firstly filled, then ECA is poured to infiltrate the holes and initiate second-level curing, and operation is cycled till the holes are filled. According to the invention, high alkalinity of industrial solid waste is utilized to initiate rapid polymerization of ECA, and the solid waste is used as a reinforcing filler; by optimizing the layering thickness, the technical problems of incomplete internal curing, concentrated heat release, generation of pores and layering and the like during large-volume repair are effectively solved, and ultra-rapid forming, high early strength, excellent interface bonding performance and overall compactness of the prosthesis are realized. The method is simple in process, green, economical, high in field adaptability and particularly suitable for rapid in-situ repair of cement-based materials and red brick masonry.

A wind power blade core material repairing device and a method thereof, comprising a moving device, the moving device sequentially sets a glue applying device, a bonding device and a heating device from front to back along a moving direction; the glue applying device comprises a glue applying device and a glue applying box arranged on the moving device, a glue nozzle of the glue applying device is inserted into the glue applying box, rotating plates are arranged on both sides of the glue applying box, and a positioning plate for inserting into a core material gap is arranged at the bottom of the rotating plate; the bonding device comprises a reel I for winding a hot melt cloth, and a reel III for leading out the hot melt cloth and sticking the hot melt cloth to the core material; and the heating device comprises a hot air gun, and an air outlet of the hot air gun faces downward. The device of the application is used to replace manual operation, greatly improves the maintenance efficiency, reduces the maintenance difficulty, ensures the quality of the core material gap filling, improves the core material repairing efficiency and the core material laying process efficiency, and shortens the blade forming time.

The present application relates to a kind of surface pretreatment-repairing method of composite material, belong to the technical field of composite material surface treatment, for solving the existing composite material bonding repair process The mechanical removal of easy to cause secondary damage to the surface of composite material, the interfacial bonding strength of repaired composite material is lower;Bonding repair process long curing time Problem.It includes: using ultraviolet laser scanning the damage site of composite material, remove the damage site of composite material;The composite material treated in step 1 is cleaned;Adhesive interface is activated using low-temperature plasma;Lay adhesive film, scrape flat;Then lay patch, scrape flat and compact, then package;Heat curing, curing stage is assisted by ultrasonic radiation;After heating and curing, the repaired area is polished.The interfacial tensile shear strength of the composite material repaired by the surface pretreatment-repairing method of composite material of the present application is significantly improved;And shorten the curing time.

The application relates to a composite material repairing method, belonging to the technical field of composite material surface treatment, and solving the problems of low interface bonding strength of the repaired composite material and low repairing efficiency of the adhesive repairing process. The method comprises the following steps: removing the damaged part of the composite material by a mechanical removal method; scanning the interface after removal by an ultraviolet laser for multiple times to remove the mechanical damage layer generated due to the mechanical removal; cleaning the composite material after the step 2 treatment; activating the adhesive interface by a low-temperature plasma; laying and pasting an adhesive film and scraping; then laying and pasting a patch, scraping, compacting, and then packaging; heating and curing, and adopting ultrasonic radiation for auxiliary curing in the curing stage; and polishing the repaired area after heating and curing. The interface tensile shear strength of the composite material repaired by the method is increased by 38% compared with the strength of the existing single sandpaper polishing, the repairing quality is improved, and the curing time is shortened.

This invention belongs to the fields of chemical engineering, hydrometallurgy, and materials preparation technology, specifically relating to a subcritical hydrothermal system based on a circulating tubular reactor group. This subcritical hydrothermal system includes a feeding unit, a closed-loop reaction unit, and a product separation unit. The closed-loop reaction unit consists of a high-temperature shielded circulating pump, a gas-liquid mixer, a parallel multi-channel tubular reactor group, and a high-pressure gas-liquid separator. The core of this system lies in using a forced circulation loop and an "online detection-selective extraction" control strategy to ensure that the material circulates and reacts within the system until the target is reached. The average residence time h is determined by the total system volume V and the target product flow rate F. out Precise control. This invention solves the problems of solid-phase deposition, uneven gas-liquid mixing, and inaccurate reaction time control in subcritical hydrothermal processes, and realizes the enhancement and precise programming control of the reaction process. It is particularly suitable for complex gas-liquid-solid multiphase reaction systems such as waste catalyst resource utilization and battery material repair.

The invention belongs to the technical field of aviation composite material repairing, and particularly relates to a composite material blade front edge coated iron debonding repairing method. Comprising the following steps: preparing a de-bonding area of the coated iron at the front edge of the blade before repairing; verifying the molded surface of the to-be-bonded front edge clad iron by using a first shape clamping plate, and selecting the to-be-bonded front edge clad iron conforming to the theoretical shape; checking whether the mounting position of the blade front edge clad iron is deformed or not by using a second shape clamping plate, and if so, repairing the mounting position into a theoretical shape; a prepreg and an adhesive film are paved at the mounting position of the blade front edge cladding iron; the to-be-bonded leading edge clad iron conforming to the theoretical appearance is placed on the adhesive film, and a repairing and pressurizing tool is used for pressurizing the mounting position of the blade leading edge clad iron; a thermal insulation tool is used for conducting thermal insulation protection on the parts, except for the coated iron debonding area, of the paddle; and the paddle in the sixth step is cured, the thermal insulation tool is removed after curing is completed, and the repaired paddle is obtained.

The application belongs to the field of polymer material repair and relates to a preparation method of a composite preparation for repairing aged asphalt, which comprises the following steps: mixing 15-35 parts by weight of a bio-based ester softening component, 5-12 parts by weight of a polarity inducing component and 3-8 parts by weight of an emulsifying aid to construct an oil phase base material with a polarity gradient; dispersing the oil phase base material in water and a stabilizing component by high shear to obtain an oil-in-water kinetic stable microemulsion with a droplet particle size of 50-150 nm; and adding 1-4 parts by weight of an ionic strength triggering component to obtain the composite preparation. The application utilizes the interface in-situ nonlinear phase inversion mechanism triggered by ionic strength to drive the repair component to actively penetrate into the deep micropores of the matrix to be repaired, realizes the molecular-level eutectic melting of the repair component and the aged matrix, restores the sol-gel balance in the matrix, solves the technical problem that the activation is insufficient due to the limited penetration capacity of the conventional preparation, and improves the viscoelastic properties of the regenerated material.

This invention relates to a rapid repair method for assembled composite materials, comprising: S1, fabrication of a composite laminate; S2, cutting of the composite laminate; S3, drilling holes in hexagonal composite patch units; S4, obtaining a large number of hexagonal composite patch units; S5, bonding of alkali-free glass fiber cloth; S6, drilling holes in aluminum alloy sheets; S7, cutting of aluminum alloy sheets; S8, obtaining a large number of aluminum alloy connecting units; S9, assembling the repair patches; S10, adjusting the curved surface shape of the assembled structure; and S11, installing the assembled structure. By prefabricating and splicing a large number of hexagonal composite patch units and aluminum alloy connecting units, the manufacturing time for large-scale composite material repair is shortened, and the repair speed is improved. By changing the number of hexagonal composite patch units and aluminum alloy connecting units used, rapid repair of different damaged areas can be effectively achieved. By changing the bending shape of the aluminum alloy connecting units, rapid repair of composite material damage with different curvatures can be effectively achieved.

The invention discloses a system for evaluating an aircraft composite material outfield in-situ maintenance deviation factor, which relates to the field of outfield in-situ maintenance and comprises an aircraft repair coordinate evaluation module, an aircraft repair personnel evaluation module, an aircraft repair material evaluation module, an aircraft repair environment evaluation module and an aircraft maintenance deviation evaluation module. The method comprises the following steps: firstly analyzing maintenance consumption data of each coordinate to obtain a coordinate maintenance offset degree, secondly analyzing staff maintenance data to obtain a staff maintenance offset degree, then analyzing material maintenance data to obtain a material maintenance offset degree, then analyzing environment maintenance data to obtain an environment maintenance offset degree, and finally summarizing and analyzing. According to the method, corresponding early warning is made according to the analysis result, so that measures are taken to reduce loss in the maintenance process, the maintenance cost and the maintenance risk are reduced, meanwhile, the influence of external field in-situ maintenance deviation factors is reduced through multi-aspect analysis, and the reliability and the accuracy of the analysis result are improved.

The invention belongs to the technical field of composite material repairing, and particularly relates to a low-cost single-time repairing method for surface defects of a composite material interlayer part. Comprising the following steps: 1, preparing before surface defect repair, and determining a repair area; secondly, surface treatment is conducted on the repair area; thirdly, the acetone solution coating area is coated with an adhesive to form an adhesive coating area; fourthly, a glue absorbing material is laid in the repairing area, and first-time vacuumizing compaction is carried out; fifthly, vacuum bag pasting operation is conducted on the repairing area, and redundant adhesive is removed; and sixthly, the vacuum bag and the glue absorbing material are removed, a layer of composite material interlayer piece surface film is laid on the repairing area, and the missing film in the repairing area is repaired.

The invention relates to the technical field of composite material repair and intelligent monitoring, in particular to a composite material patching repair interface temperature field estimation method based on Kalman filtering, which comprises the following steps: step 1, constructing an airplane composite material patching repair curing heat transfer control equation; step 2, establishing a one-dimensional space model of the patching, repairing and curing heat transfer state, establishing a node every delta z in the thickness direction, obtaining a discrete heat control equation, and giving boundary conditions; and step 3, establishing a patching repair curing heat transfer nonlinear Kalman filtering model, deducing to obtain a Kalman filtering coefficient K, inputting an initial state value, and estimating the temperature of the cementing interface. According to the method, the state estimation and noise suppression technologies are introduced, multi-point temperature acquisition data are effectively fused, and the patch bonding interface temperature is accurately estimated on line in real time, so that a reliable temperature control basis is provided for a temperature control system of a hot patching instrument, and the problem of inaccurate temperature control in the prior art is solved.

This invention belongs to the field of composite material repair technology, and relates to an in-situ braided repair method and application for SiC / SiC composite materials. This repair method is used for in-situ braided repair of SiC / SiC composite materials with overall thickness defects, and includes: removing the damaged portion of the SiC / SiC composite material to obtain the SiC / SiC composite material body to be repaired; determining the yarn hanging hole array, diameter, and overlapping area based on the fiber preform structure, stress characteristics of the damaged area, and repair shape requirements; processing the yarn hanging holes and overlapping area; fabricating SiC fiber yarns; fixing one end of the SiC fiber yarn to the yarn hanging hole, and completing the in-situ braided repair according to a preset braiding path and braiding angle; wherein the preset braiding path and braiding angle are determined by the fiber preform structure; performing in-situ densification treatment on the composite material with the braided repair; and finally performing surface treatment, including geometric dimension finishing and coating. This method can effectively repair SiC / SiC composite materials, restoring their mechanical properties and reliability.