476results about How to "Improves ablation resistance" patented technology

The invention relates to an ultra-high temperature resistant ceramic-based composite and a preparation method, which adopts carbon or boron nitride fabric cloth as reinforcing phases, ceramic powders of high melting point or high-temperature resistant metal powders as the stuffing, and carbon/silicon carbide as the base. Through the blending and ball milling of the adhesives and the powder stuffing, the sizing agent thus acquired is coated on the reinforcing phase fabric cloth, and then overlapping, molding, cross-bonding, high-temperature pyrolysis, and repeated densification are carried out in preparing the composite. The ultra-high temperature resistant ceramic composite has the advantages of excellent thermal shock resistance, low density, and low ablating rate under ultra-high temperature.

The invention discloses a C/C composite material superhigh temperature ceramic coating, and a preparation method thereof. The C/C composite material superhigh temperature ceramic coating is composed of an anti-oxidation SiC transition internal layer and a superhigh temperature ablation-resistant ceramic external layer; the superhigh temperature ablation-resistant ceramic external layer is composedof more than one ingredients selected from SiC, ZrC, HfC, TaC, TiC, ZrB2, HfB2, TaB2, and TiB2. The preparation method is suitable for industrialized production, is simple in equipment, is convenientin operation, is capable of controlling coating thickness, satisfying preparation requirements of large size C/C composite material superhigh temperature ceramic coating with complex shapes, and is asuperhigh temperature ceramic coating preparation method with excellent development potential.

The invention discloses a preparation method of boron modified phenolic resin, which comprises the following steps that: (1) phenol and formaldehyde in the molar ratio of 1.0:0.1 to 1.0 is added into a reactor, to be stirred under acid environment and reflux for 5 to 6 hours; (2) a reaction product prepared in step (1) is distilled and hydrated at normal pressure, until the water content is less than 10 weight percent; (3) the produce dehydrated in step (2) is added with a compound which contains boron hydroxyl, to have esterification; and the input of the compound which contains boron hydroxyl is 20 weight percent of that of the phenol at most. The synthesis method provided by the invention is simple and feasible, the prepared resin has stable performance and is beneficial to large-scaleindustrial production, and the prepared boron modified phenolic resin has excellent thermal oxidation and ablation resistant performance, and can be widely applied to high-temperature brake materials, ablation resistant materials, heat insulation materials and other fields.

Belonging to the technical field of lightning protection, the invention relates to an insulating and thermal conductive ablation resistant adhesive and application thereof in lightning protection. The adhesive is mainly prepared from the following raw materials: 20-100% and not up to 100% of a mixture of high temperature resistant resin and a curing agent, and 0-80% and greater than 0% of an insulating and thermal conductive ablation resistant inorganic filler. After curing, the electrical conductivity of the adhesive is in the range of 10<-8>-10<-20>S/m, the DC breakdown voltage in the air is in the range of 30-300kV/mm, the thermal conductivity is in the range of 0.2-3.0W/(m.K), and the ablation resistant temperature is up to 300DEG C. A certain thickness (30-250micrometer) of the insulating and thermal conductive ablation resistant adhesive is employed to stick a conductive film to the surface of a continuous carbon fiber laminated composite material part, thus preventing conduction of current to the continuous carbon fiber laminated composite material part and improving the lightning protection effect of the conductive film.

The invention discloses a method for making a super-high temperature resistant ceramic coating. The method adopts organic polymer as adhesive and mixed powder consisting of high melting metal powder, B powder, C powder and Si powder as raw materials; moreover, through adopting processes such as preparing slurry used in a coating, slurry coating, precoating curing, high-temperature reaction sintering, a super-high temperature resistant ceramic coating is finally made on the surface of a ceramic matrix composite material. The coating making process is simple and has low cost; the made coating has ideal bonding performance with a substrate and has excellent ablation resistance and antioxidation, thereby laying the foundation for the application of a ceramic matrix composite material in the super-high temperature resistant and antioxidation fields.

The invention discloses a method for molding a phenolic panel honeycomb sandwich structural member and belongs to the technical field of composite material molding. The phenolic panel honeycomb sandwich structural member comprises inner covering skin, outer covering skin, a frame, a honeycomb, a reinforcing fiber prepreg tape reinforcing layer, an inner glue film layer and an outer glue film layer. The method comprises preparing a phenolic resin prepreg cloth, preparing a mold having the honeycomb sandwich structure shape, pre-curing the inner covering skin and the frame, paving a reinforcing fiber prepreg tape through bonding the reinforcing fiber prepreg tape to the surface of the pre-molded inner covering skin to obtain the reinforcing fiber prepreg tape reinforcing layer, carrying out honeycomb installation and pre-curing, pre-curing the outer covering skin, assembling a product through paving the outer covering skin layer, integrally curing the assembled product and carrying out demolding. The method can mold a large-size honeycomb sandwich structure. The molded honeycomb sandwich structure does not deform, lose viscidity and produce bulge, has the size, weight and shape satisfying design requirements and has good ablation resistance.

The invention discloses boron modified phenolic resin and a preparation method thereof. The boron modified phenolic resin is made of, by weight, 80-90 parts of phenol, 55-65 parts of formaldehyde, 0.5-0.6 part of oxalic acid and 3-5 parts of boric acid by means of feeding, refluxing, emulsifying, primary dewatering, adding oxalic acid, secondary dewatering and discharging. The preparation method is simple, and the boron modified phenolic resin made by the method has high heat resistance, ablation resistance and mechanical performance, is wide in application range and has remarkable economic and social benefits.

The invention discloses special ceramic which is prepared from the following raw materials in parts by weight: 3-4 parts of wollastonite, 10-14 parts of feldspar, 5-7 parts of aluminum oxide, 20-25 parts of kaolin, 58-66 parts of quartz, 2-3 parts of nano-zinc oxide, 2-3 parts of oleic acid, 1-2 parts of oxidized paraffin, 12-15 parts of zirconium oxychloride, 3-4 parts of sodium zirconate, 3-4 parts of tetraethoxysilane, a proper amount of deionized water, 1-2 parts of potassium hydroxide, a proper amount of ethanol and 4-6 parts of an additive. The ceramic disclosed by the invention is relatively wide in temperature resistance, good in ablation resistance, good in mechanical property and large in strength, due to the addition of zirconium oxychloride and sodium zirconate, the wearing resistance and the temperature resistance of the ceramic are improved, the ceramic is not easy to break, resistant to vibration and long in service life, and due to the addition of the additive, the surface smoothness, wearing resistance and thermal resistance of the ceramic are improved.

The invention relates to a carbon/carbon fiber-silicon, boron, carbon and nitrogen ceramic composite material and a preparation method thereof. The invention relates to a short carbon fiber reinforced silicon, boron, carbon and nitrogen ceramic composite material and a preparation method thereof. The invention aims to solve the problem that the existing fiber reinforced silicon, boron, carbon and nitrogen ceramic composite material is complex in preparation process and high in cost, and the strengthening and toughening effect of the fibers is not remarkable due to over-strong interfacial adhesion. The product is prepared from short carbon fibers, phenolic resin, acetone and silicon, boron, carbon and nitrogen ceramic composite powder. The preparation method comprises the following steps: I, dissolving phenolic resin in acetone to prepare dipping liquor; II, putting the short carbon fibers in the dipping liquor to dip, and then splitting in an argon atmosphere to obtain carbon coating-coated short carbon fibers; III, putting silicon powder, graphite and hexagonal boron nitride in a ball mill to ball-mill and mix to obtain composite powder; and IV, after mixing the carbon coating-coated short carbon fibers with the composite powder, carrying out hot pressed sintering to obtain the carbon/carbon fiber-silicon, boron, carbon and nitrogen ceramic composite material.

The invention relates to a high-strength flame-retardant ablation-resistant coating and a preparation method thereof. the coating comprises the following ingredients (by weight): 40-60 parts of high-temperature-resistant resin, 20-40 parts of an ablation-resistant filler, 5-15 parts of a flame-retardant filler, 15-35 parts of reinforced fiber, 0.5-2 parts of an auxiliary agent and 10-40 parts of a solvent. When the coating is used, 20-30 parts by weight of a polyamide curing agent and 0.3-2 parts by weight of a phenols curing agent promoter are added. Through a method of blade coating, roller painting and spraying for coating the surface of a device, a film is formed. In comparison with the prior art, the film formed by the coating can be resistant to instant high temperature of 1500 DEG C and above, has excellent flame-retardant effect and high bonding strength, and has been successfully applied to parts of guided missile launcher, etc. to effectively solve the thermal protection problem of the surface during missile launching, can be resistant to multiple times of ablation and scouring, and has repairability.

The invention relates to a ceramic spiral fiber reinforced silicone rubber light ablation resistance thermal insulation coating and application of the ceramic spiral fiber reinforced silicone rubber light ablation resistance thermal insulation coating, the ceramic spiral fiber reinforced silicone rubber light ablation resistance thermal insulation coating is a double-layer composite coating systemand is compounded from a TI thermal insulation coating on the inner layer and a TA ablation resistance coating on the outer layer, the thickness ratio of the TI thermal insulation coating to the TA ablation resistance coating is (4-7):(2-5), a component B is added in a component A of the TI coating prepared according to the formula in the application, the mixture is blended by using a solvent inthe component A to the specified spraying viscosity and is blade-coated, roller-coated or sprayed to the thickness of 4-7 mm on the surface of a device; a component D is added in a component C of theTA coating prepared according to the formula, the mixture is blended by using a solvent in the component C to the specified spraying viscosity, is sprayed on the surface of a dried TI coating film, and is blade-coated or roller-coated to the thickness of 2-5 mm. Compared with the prior art, the bonding strength of a formed coating is high, and the coating can resist the instantaneous high temperature of more than 1500 DEG C, has an excellent heatproof effect, effectively protects a launcher against ablation damages, and is higher in strength.

The invention relates to an ablation-resistant protection technology for refractory metal materials and particularly relates to a Zr-based ceramic coating protection method for the surface of a refractory metal material. The method comprises the following steps of firstly, degreasing a refractory metal and grinding with sand paper; secondly, depositing Zr-based ceramic powder on the surface of the refractory metal to form a Zr-based ceramic powder pre-coated layer by virtue of an electrophoretic technology; and finally, cladding the Zr-based ceramic powder pre-coated layer on the surface of the refractory metal to obtain the Zr-based ceramic coating by virtue of a laser cladding technology. According to the method, in order to solve the problem of relatively low application temperature of the silicide protective coating applied in the refractory metal, the Zr-based ceramic coating is adopted to solve the application limitation of the refractory metal so that the ablation resistance of the refractory metal matrix at above 2000 DEG C is effectively increased.

The invention provides a Cf/HfC-TaC-C composite material and a preparation method thereof, wherein a carbon fiber preform as a skeleton is immersed in a precursor solution containing a hafnium-tantalum precursor copolymer, and curing and cracking are performed to obtain the Cf/HfC-TaC-C composite material. According to the present invention, the process is simple, and the preparation period is short; and the prepared ultra-high temperature ceramic matrix composite material has advantages of excellent high-temperature resistance, excellent oxidation resistance and excellent ablation resistance,can be used as the high temperature thermal structure material of highly-hypersonic aircrafts and rocket propulsion systems, and has wide application prospect.

The invention relates to a preparation method of a Cf/SiC-ZrC-ZrB2 ultrahigh-temperature ceramic-based composite material. The preparation method comprises the following steps: (1) preparing a sol solution containing H3BO3 and polyvinyl alcohol; (2) introducing the sol solution into a carbon fiber preform by utilizing vacuum impregnation, and performing gelatinization to obtain Cf/polyethyl borate; (3) cracking the Cf/polyethyl borate in the presence of an inert gas to obtain Cf/B2O3-C; (4) performing a carbothermal reduction reaction on the obtained Cf/B2O3-C in the presence of the inert gas to obtain Cf/B4C-C; and (5) infiltrating fused ZrSi2 into the Cf/B4C-C to perform an infiltration reaction to generate SiC, ZrC, ZrB2 in situ, thereby obtaining the Cf/SiC-ZrC-ZrB2 ultrahigh-temperature ceramic-based composite material. The method provided by the invention is simple and feasible, the prepared Cf/SiC-ZrC-ZrB2 has high contents of ultrahigh-temperature phases (ZrC and ZrB2) and is uniformly distributed, and the method significantly improves ablation resistance, oxidation resistance and mechanical properties of the material.

The invention relate to high-residual-carbon thermosetting boron-containing phenolic resin as well as a preparation method and application thereof. In the prior art, The reaction condition of thermosetting phenolic resin needs base catalysis, NaOH is difficult to remove from the final phenolic resin product and can be neutralized with some acidic substances at most to become sodium salt existing in resin; therefore, a sodium atomic ionization potential is low and wake flow can be generated easily to interrupt communication; meanwhile, the oxidation resistance of the material is reduced. The preparation method of the high-residual-carbon thermosetting boron-containing phenolic resin comprises an esterification phase, a cooling phase, a low-molecular-weight phenolic resin synthesis phase and an evacuation phase. The high-residual-carbon thermosetting boron-containing phenolic resin can be used for manufacturing various composite materials, functional coatings and special adhesives which are resistant to high temperature, resistant to ablation, and clean and flame-retardant, also can be used as a multifunctional curing agent for epoxy resin for improving the heat resistance, flame retardance and ablation resistance of epoxy resin simultaneously, and can be used as a multifunctional modifying agent for other resins and rubbers.

The invention discloses a polyhedral oligomeric silsesquioxane (POSS) filled ablation-resistant ethylene-propylene-diene monomer (EPDM) rubber heat-insulating layer. The POSS filled ablation-resistantEPDM rubber heat-insulating layer comprises the following components in parts by mass: 60 to 85 parts of EPDM rubber, 15 to 40 parts of neoprene, 15 to 25 parts of a reinforcing agent, 6 to 15 partsof organic fiber, 20 to 30 parts of high-temperature-resistant resin, 25 to 35 parts of high-temperature-resistant POSS, 8 to 40 parts of a modifier, 5 to 8 parts of a metal oxide, 4 parts of a vulcanizing agent and 2 parts of stearic acid. Grafting modification of the POSS on the EPDM rubber base material is realized by utilizing the POSS modifier; the POSS with excellent high-temperature resistance, the reinforcing agent, the resin and the organic fiber are added, so that the ablation resistance of the EPDM heat-insulating layer is obviously improved, and the product has excellent ablation resistance, is suitable for the thermal protection field which requires high-temperature-resistant ablation, and is particularly suitable for the thermal protection field of a solid rocket engine.

The invention relates to a sprayable silicone rubber-based lightweight ablation-resistant thermal insulation coating and an application thereof. The coating is prepared from a component A and a component B according to a mass ratio of 100:0.5 to 100:3, the component A is prepared from, by weight, 80-110 parts of room temperature-vulcanized silicone rubber, 40-50 parts of a flame-retardant filler,3-5 parts of a chopped carbon fiber filler, 10-12 parts of a silicon-based reinforcing filler, 0.5-1 part of a dispersing aid, 5-10 parts of a coupling agent and 100-150 parts of a solvent, and the component B is prepared from a cross-linking agent tetraethyl orthosilicate or hydrogen-containing silicone oil and a catalyst dibutyltin dilaurate or tetrabutyl titanate according to a mass part ratioof 7:3. Compared with coatings in the prior art, the coating in the invention has a higher bonding strength with the coating layer of a metal substrate; the chopped carbon fibers form a strong honeycomb structure in a residual carbon layer, so that the coating layer has excellent erosion resistance, and can effectively protect the surfaces of rockets and other aeronautics and astronautics devicesfrom being ablated and damaged; and the ablation products of the coating mainly comprise CO2 and SiO2, so the coating is green and non-polluting.

The invention relates to a carbon fiber composite fabric or a carbon-copper compound material and the method thereof. The invention takes a porous carbon body prepared by the carbon fiber composite fabric densification as the prefabricated part, and the copper alloy is infiltrated in the pore of the prefabricated part. By adoption the method of no-pressure melt infiltration, the invention features the simple process, low cost, and easy realization of the industrialization, and is capable to prepare the carbon fiber composite fabric or the carbon-copper compound material with high electrical conductivity, outstanding self lubrication wear resistance performance, excellent hot-proof and anti-vibration and ablation resistance performance.