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

The invention discloses the structure and application of a heat protection coating material for steel structure surface. The thermal protective coating material of the invention is composed of three layers of materials: an organic bottom layer, a refractory brick and an inorganic surface layer. Among them, the organic bottom layer is composed of epoxy resin, curing agent polyamide and toughening agent liquid rubber. The refractory brick is made of clay refractory brick, and the inorganic surface layer is composed of water glass, curing agent sodium fluorosilicate, sand, cement and refractory aggregate. The heat protection coating material of the invention can withstand the scouring of simulated rocket gas flow, the temperature of the metal back does not exceed 150 DEG C, and the coating has good heat insulation performance.

A detachable multi-lobed cabin section butt heat-proof structure, the docking frames of the two cabin sections to be docked are radially connected, and the outer ring at the radial connection is equipped with a multi-petal heat-proof ring. The heat ring is in clearance fit with the outer heat-proof structure of the above-mentioned butt joint two compartments. The present invention aims at the docking structure between the cabin sections that require repeated disassembly and assembly, and proposes that the docking place adopts a multi-lobed heat-proof ring that is easy to disassemble to prevent heat at the docking part—that is, the cabin section docking still uses countersunk head screws in the radial direction The docking form is just to install the multi-lobed heat-proof ring by screwing after the docking. The multi-lobed heat-proof ring covers all the docking screws and the docking parts to protect the heat, and can be disassembled and operated repeatedly. It is simple and meets the requirements of rapid maintenance response.

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 relates to a surface-protection-type conductive composite material and a preparation method thereof. The composite material is prepared by carrying out compounding and mould pressing ona resin-based composite material, an adhesive layer, a conductive layer, a reinforcing layer and a protective layer, wherein the adhesive layer is an inorganic or organic adhesive, the conductive layer is a pure conductive metal mesh or a high-molecular resin conductive adhesive film or a high-molecular resin insulating adhesive film / conductive metal mesh composite adhesive film or a high-molecular resin conductive adhesive film / conductive metal mesh composite adhesive film, the reinforcing layer is made of a fabric, and the protective layer is made of a rubber material. The preparation methodcomprises the following steps: firstly, cutting a prepreg, the adhesive layer, the conductive layer, the reinforcing layer and the protective layer in a layer-by-layer mode according to the shape andsize of the composite material product, and then carrying out integral curing and forming on the conductive layer with the resin-based composite material, then preparing the resin-based composite material with the adhesive layer, the reinforcing layer and the protective layer into blanks, and finally carrying out compression molding.

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.

A triangular surface type dovetail groove type composite material rudder base plate and its installation method, the lower surface of the rudder base plate is in the same shape as the profile of the cabin shell where it is installed; the lower surface is provided with a dovetail groove, and the central surface of the dovetail groove is used as the whole The center plane of the rudder base plate; the center of the upper surface is a triangular plane, and the two end faces of the upper surface are parallel to the central plane; a smooth transition between the triangular plane and the above-mentioned two end faces; the lower surface of the triangular plane relative to the rudder base plate is inclined and The apex of the triangular plane is located on the outer heat-resistant surface of the cabin shell. The invention improves the thermal environment around the rudder base plate by adopting the aerodynamic shape of the smooth triangular surface structure; it is installed on the surface of the aircraft through the trapezoidal dovetail groove of the rudder base plate and the dovetail block of the metal shell, simplifying the traditional heat-proof plug and multi-thread connection interface structure, Reduce the grinding process and improve the operability of production assembly.

The invention specifically discloses an environmentally friendly and degradable aromatic polyurethane foaming material, which is formed by mixing and foaming components A and B, wherein: component B is aliphatic isocyanate, and component A includes the following parts by weight Components: 80-100 parts of complex polyol, 4-8 parts of foaming agent, 0.5-0.8 parts of catalyst, 0-1 part of cross-linking agent, 0.5-1 part of foam stabilizer and 15-25 parts Parts of modified lavender particles, wherein the complex polyol is composed of vegetable oil-based polyether polyol, polypropylene oxide ether and polyurethane insole alcoholysis product. The invention adopts modified lavender granules, which can effectively control the volatilization of lavender aroma components, achieve long-lasting aroma effect and cover up peculiar smell, and at the same time enhance the antibacterial performance of foam materials and products, and have the functions of deodorization, breathability, refreshing, and aromatherapy. The advantages of repelling insects can improve the utilization rate of lavender, reduce the waste of waste and improve the degree of degradation, which is green and environmentally friendly.

The invention discloses the structure and application of a high-temperature-resistant coating material for metal surfaces. The high temperature resistant coating material of the invention is composed of two layers of materials, an organic bottom layer and an inorganic surface layer. Among them, the organic bottom layer is composed of epoxy resin, curing agent polyamide and toughening agent liquid rubber. The inorganic surface consists of pyrite, cordierite, aluminate cement and silica fume. The high-temperature-resistant coating material of the invention has strong adhesion, can withstand the scouring of simulated rocket gas flow, the temperature of the metal back does not exceed 120°C, and the coating has good high-temperature gas-flow scouring performance and heat insulation performance.

The invention discloses a high temperature resistant coating material for a rocket launch platform. The high temperature resistant coating material of the invention is composed of two layers of materials, an organic bottom layer and an inorganic surface layer. Among them, the organic bottom layer is composed of epoxy resin, curing agent polyamide and toughening agent liquid rubber. The inorganic surface layer consists of mullite, cordierite, aluminate cement and silica fume. The high-temperature-resistant coating material of the invention has strong adhesion, can withstand the scouring of simulated rocket gas flow, the temperature of the metal back does not exceed 100°C, and the coating has good high-temperature gas-flow-resistant scouring performance and heat insulation performance.