31results about How to "Act as thermal protection" patented technology

The invention discloses an aero-engine fuel nozzle structure. The fuel nozzle structure comprises a sleeve shell and an oil conveying part, wherein the oil conveying part comprises a first oil conveying part and a second oil conveying part, one end of the second oil conveying part is integrally connected with the first oil conveying part, and the other end of the second oil conveying part is connected with an auxiliary vortex device, the sleeve shell is integrally formed with the oil conveying part, a sleeve is arranged outside the second oil conveying part and is extended to the second oil conveying part from the boundary of the first oil conveying part and the second oil conveying part, a semi-closed air heat insulation cavity is provided with the radial space between the second oil conveying part and the sleeve, and elastic pieces which are in contact with the opposite side walls of the air heat insulation cavity are arranged on the open side of the air heat insulation cavity. The fuel nozzle structure has the advantages of stable and reliable structure, long service life and the like.

The invention provides a method for preparing an antibacterial epoxy resin pouring sealant. The method comprises the following steps: 1) drying ginkgo leaves, crushing the ginkgo leaves and sieving to obtain the ginkgo leaves powder, adding an ethyl alcohol solution, performing ultrasonic extraction, standing and filtering the material, concentrating the material to obtain a ginkgo leaves extract product; 2) adding diatomite and the ginkgo leaves extract product in a mixer, heating the materials and performing magnetic stirring, taking the product out and drying the product, grinding the product and sieving the product to obtain a composite antiseptic; 3) preparing a mixed liquor by the composite antiseptic, heating the mixed liquor, adding an aluminic acid ester coupling agent, stirring the materials, performing pumping filtration, drying the materials to obtain the modified composite antiseptic; 4) adding epoxy resin, a flexibilizer, a diluents, a filling material and the modified composite antiseptic in a stirred tank for stirring the above materials, performing vacuum defoaming to obtain a component A; 5) adding a curing agent and a promoter in the stirred tank for stirring the above materials, performing vacuum defoaming to obtain a component B; and 6) uniformly mixing the component A and the component B to obtain the antibacterial epoxy resin pouring sealant. The prepared antibacterial epoxy resin pouring sealant has good antibacterial property.

The invention relates to the technical field of EVA composite materials. The natural aromatic environment-friendly EVA composite foam material is prepared from the following components in parts by weight: 80-100 parts of a rubber and plastic base material, 4-8 parts of a foaming agent, 0.5-1 part of a cross-linking agent, 0.5-0.8 part of mineral oil, 0.5-1 part of stearic acid and 20-40 parts of modified lavender particles, and the rubber and plastic base material contains 40-100% of EVA. According to the invention, the modified lavender particles are adopted, volatilization of lavender aromacomponents can be effectively controlled, meanwhile, the antibacterial performance and deodorization of the foaming material and the product can be enhanced, the advantages of deodorizing, ventilating, refreshing, incensing, expelling parasites and the like are achieved, the utilization rate of lavender can be increased, waste and environmental pollution are reduced, and the lavender perfume is environmentally friendly and suitable for living goods and sports equipment such as soles, insoles, yoga mats and crawling mats.

The invention discloses a structure for a thermal protective coating of a rocket launching pad and an application thereof. The thermal protective coating is composed of materials in three layers, namely, an organic bottom layer, refractory bricks and an organic-inorganic compound surface layer, wherein the organic bottom layer is composed of epoxy resin, solidifying agent polyamide and flexibilizer liquid rubber; clay refractory bricks are adopted as the refractory bricks; the organic-inorganic compound surface layer is composed of organic rubber epoxy resin, polyurethane curing agent, sand and cement. The material of the thermal protective coating provided by the invention can endure the scouring of the simulated fuel gas flow of a rocket; the temperature on a metal rear surface is not above 200 DEG C; the coating has an excellent heat-insulating property.

The invention provides alpha-cyanoacrylate heat-conducting glue. The alpha-cyanoacrylate heat-conducting glue comprises the following components in parts by weight: 100 parts of alpha-cyanoacrylate, 2-5 parts of a thickening agent, 2-4 parts of a plasticizer, 0.1-0.4 parts of a stabilizing agent, 0.5-1 part of a polymerization inhibitor, 20-30 parts of a cross-linking agent, 3-6 parts of a fire retardant, 1-2 parts of pigment, 100-110 parts of a heat-conducting filling material, 10-14 parts of magnesium hydrogen phosphate, and 8-10 parts of liquid polyisobutylene. The invention also provides a preparation method of the alpha-cyanoacrylate heat-conducting glue. The alpha-cyanoacrylate heat-conducting glue has good impact-resistance performance and heat-resistance performance.

The invention discloses a structure of a thermal protective coating material for a metal surface and a use thereof. The structure of the thermal protective coating material is composed of an organic base layer, a fire refractory light aggregate and an inorganic surface layer. A part of the fire refractory light aggregate is embedded in the organic base layer and a part of the fire refractory light aggregate is embedded in the inorganic surface layer. The organic base layer is composed of epoxy resin, a curing agent polyamide and a toughening agent liquid rubber. The inorganic surface layer is composed of water glass, a curing agent sodium fluorosilicate, sand and cement. The thermal protective coating material can resist rocker simulated gas flow erosion, the metal backside temperature does not exceed 150 DEG C, and the coating has good heat insulation performances.

The invention discloses a high-temperature-resistant coating material for a rocket launching pad. The high-temperature-resistant coating material comprises two material layers, namely an organic bottom layer and an inorganic surface layer, wherein the organic bottom layer comprises epoxy resin, the curing agent of polyamide, and the toughening agent of liquid rubber; the inorganic surface layer comprises mullite, dichroite, aluminate cement and silica ash. The high-temperature-resistant coating material is high in adhesive force, and can bear rocket simulation gas stream impact; the temperature of metal back is lower than 100 DEG C, and the coating has excellent high-temperature gas stream impact resistance and heat-insulating performance.

The invention discloses a thermal protection coating material structure for a rocket launching pad and application of the structure. The thermal protection coating material is composed of a first organic layer, a refractory brick layer, a second organic layer and an unshaped refractory material layer, wherein the two organic layers are same in composition and are both composed of epoxy resin, curing agent modified polyamine and toughening agent liquid rubber, and the unshaped refractory material layer is composed of mullite, cordierite, aluminate cement and silica fume. The thermal protection coating material is high in adhesive force and can bear simulated combustion-gas flow scour of a rocket and greatly reduce thermal ablation and thermal shock of a metallic substrate; the thermal protection coating material has good high-temperature combustion-gas flow scour resistance and thermal insulating performance, the temperature of the back face of metal does not exceed 80 DEG C, and therefore an effective thermal protection effect on the rocket launching pad is achieved.

Provided is a triangular curved dovetail groove composite rudder substrate and an installation method thereof. The lower surface of the rudder substrate is conformed to the shape of a profile of an installation cabin shell; a dovetail groove is formed in the lower surface, and the center surface of the dovetail groove is used as a whole center surface of the rudder substrate; the center of the upper surface is a triangular plane, and both end surfaces of the upper surface are parallel to the center surface; smooth transition between the triangular plane and the both end surfaces is achieved; the triangular plane is inclined with respect to the lower surface of the rudder substrate, and the apex of the triangular plane is located on the outer heat prevention surface of the cabin shell. Thesubstrate improves the thermal environment around the rudder substrate by adopting the aerodynamic shape of a smooth triangular curved surface structure, and is mounted on the surface of an aircraft through the rudder substrate trapezoidal dovetail groove and a metal shell dovetail block inserting mode to simplify a traditional heat-proof plug and a multi-thread connection interface structure, thegrinding process is reduced and the production overall assembly operation is improved.

The invention particularly discloses an environment-friendly degradable aromatic polyurethane foaming material. The foaming material is formed by mixing and foaming a component A and a component B, wherein the component B is aliphatic isocyanate, and the component A comprises the following components in parts by weight: 80 to 100 parts of composite polyol, 4 to 8 parts of a foaming agent, 0.5-0.8parts of a catalyst, 0 to 1 part of a crosslinker, 0.5 to 1 part of a foam stabilizer and 15 to 25 parts of modified lavender particles; wherein the composite polyol consists of plant oil-based polyether polyol, polypropylene oxide ether and polyurethane insole alcoholysis product. According to the invention, the modified lavender particles are adopted; wherein the lavender antibacterial foam material can effectively control volatilization of lavender aroma components, so that the material achieves lasting aroma efficacy, covers peculiar smell, can enhance the antibacterial performance of thefoam material and products. The material has the advantages of odor removal, ventilation, refreshing, incense and insect expelling and the like, can improve the utilization rate of lavender, reduce waste and improve the degradation degree, and is green and environment-friendly.

The invention discloses a stage structure comprising a rocket body, a pneumatic reduction mechanism and a pneumatic anti-collision mechanism. The pneumatic reduction mechanism comprises a pneumatic head and an ablation resisting layer. The pneumatic head is a second gas bag capable of being shrunk and spread. The second gas bag covers the head of the rocket body. The pneumatic anti-collision mechanism is provided with a first gas bag capable of being shrunk and spread. The first air bag covers the tail of the rocket body. After being inflated, the second gas bag is of a symmetrical structureand has good pneumatic stability. The outer wall of the second gas bag is provided with an ablation resisting layer, so that the second gas bag cannot be burned during flying aloft at high temperature. The second gas bag can reduce the speed of the rocket body at high temperature in high altitude; besides, during landing in low altitude, the second gas bag can achieve a buffering function on the rocket body; the second gas bag has the foldable capacity, so that the occupied space on the rocket body and the weight of the second gas bag can be reduced. Meanwhile, the first gas bag can achieve the flexible buffering function on the tail when the tail of the rocket body lands, and therefore the rocket body is prevented from being damaged.

The invention provides a PET compound for a packaging bottle. The PET compound comprises the following components by weight part: 50-60 parts of PET resins, 0.6-1.1 parts of lubricating agents, 5-10 parts of fire retardants, 3-4 parts of flexibilizer, 0.5-1 part of dispersing agent, 1-2 parts of antistatic agents, 5-10 parts of reinforcing agents, 1-2 parts of low temperature-resisting modifying agents, 3-4 parts of compatilizer, 5-6 parts of epoxy resins, 7-8 parts of compound melanin capsules and 2 parts of nylon. The invention also provides a manufacturing method for the PET compound for the packaging bottle. The PET compound has higher radiation resistance.

The invention discloses a structure and applications of a high-temperature-resistant coating material for steel structure surface. The high-temperature-resistant coating material is composed of an organic layer, a shaped firebrick layer, an organic layer, and an amorphous refractory material layer. The two organic layers have the same components and are composed of epoxy resin, a polyamide curing agent, and a toughening agent (liquid rubber). The firebrick is clay-based firebrick. The amorphous refractory material is composed of flint clay, cordierite, aluminate cement, and silica fume. The adhesion force of the provided high-temperature-resistant coating material is strong, which can sustain the washing of rocket imitated combustion-gas stream. The metal backside temperature does not exceed 120 DEG C, and the coating has an excellent performance on resisting high-temperature combustion-gas stream brushing and thermal insulation property.

The invention discloses a high-temperature-resistant composite color steel tile. The high-temperature-resistant composite color steel tile comprises a high-temperature-resistant coating and a composite color steel tile body, wherein the surface of the composite color steel tile is coated with a layer of the high-temperature-resistant coating. The invention relates to the technical field of color steel tiles. According to the invention, the high-temperature-resistant coating is prepared by matching an organic silicon prepolymer and modified resin and adding an auxiliary agent; after the organic silicon prepolymer and the modified resin undergo a reaction, a large number of Si-O bonds are formed in a reaction product, and the Si-O bonds have high bond energy, so the reaction product has high heat resistance, and the coating prepared from the reaction product has high resistance to high temperature; and in addition, aluminum oxide powder, titanium dioxide powder and talcum powder are added into the coating to serve as auxiliary agents, the mechanical performance of the coating can be improved, silicon dioxide and aluminum oxide in the coating can generate a performance protection layer to achieve thermal protection effect, and the high-temperature-resistant performance of the composite color steel tile is further improved.