91results about How to "Good heat protection" patented technology

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 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 discloses a method for preparing a double-layer wave-permeable heat proofing and insulating composite structural part. The structural part comprises an inner heat insulation material and an outer heat-proof +material. The method includes steps of preparation of the outer heat-proof material, preparation of silicon oxide hollow microspheres, preparation of chopped fiber reinforced silicon oxide hollow microsphere slurry, casting of the chopped fiber reinforced silicon oxide hollow microsphere slurry and thermal treatment of a structural part blank material. Quartz fiber reinforced quartz composite ceramic serves as the outer heat-proof material, chopped fiber reinforced silicon oxide hollow microsphere ceramic serves as the inner heat insulation material, compact combination of the inner and outer materials is realized by means of slurry casting and high-temperature sintering moulding, and integration of advantageous performances of high temperature resistance, heat proofing, heat insulation, wave permeability and the like is realized.

The invention discloses a design method for reusable sky-earth aircraft configuration. According to the method, an up-down contour control line and a left-right width contour line of a fuselage are determined, a quadratic curve and a CST method based on a type function and a shape function are adopted to generate a corresponding section shape, and therefore a key stance shape of the whole fuselage is obtained; the shape of the whole fuselage is obtained through a surface lofting technology; a numerical computation method is adopted to compute a flow field; matching design is performed on a control plane; and aerodynamic configuration is optimized. Compared with the prior art, the method has the advantages that high supersonic velocity lift-to-drag ratio characteristics and sub-cross-ultralow velocity entrance characteristics are comprehensively considered, the reusable sky-earth aircraft configuration with all velocity domains meeting design demands is designed, and an aircraft obtained through optimization has excellent aerodynamic performance and good heat resistance as well as good practicability.

The curing agent consists of two parts: water solution preparation and powder preparation. The water solution preparation is compounded with saturated solution of sodium chloride, sodium carbonate, magnesium chloride, sodium silicate, potassium chloride, sodium hydroxide, calcium chloride and ammonium chloride; and the powder preparation is prepared through mixing iron ore slag, silica, magnesia, calcium sulfate, magnesium chloride and coal powder. The cured matter formed with the curing agent has high water tightness, low water absorption, low water penetration, powerful waterproof performance, high freeze-thaw resistance, high heat resistance and sustained compression strength enhancement. The curing agent of the present invention may be used in road environment, water engineering, building engineering, environment protection engineering, etc.

The invention discloses a fully-protected flexible unfolding re-entry aeroshell comprising a load capsule main body. A rigid thermal protection blunt nose is connected to the lower end of the load capsule main body. A sliding connecting frame is installed at the upper end of the load capsule main body. A head cover is arranged at the top of the sliding connecting frame. Hinged seats and threaded hole bearings are arranged at the connection between the load capsule main body and the rigid thermal protection blunt nose. The hinged seats are connected with the lower parts of lower support bars. The upper parts of the lower support bars are connected with the lower parts of upper support bars. The upper parts of the upper support bars is connected with the sliding connecting frame. A leeward side flexible thermal protection structure and a windward side flexible thermal protection structure are respectively connected to the upper support bars and the lower support bars. The fully-protected flexible unfolding reentry aeroshell uses a connecting-bar unfolding mechanism and adds the leeward side flexible thermal protection structure, thereby not only reducing the requirement of the fairing envelope of a launch vehicle and avoiding the impact of the inflow/shock wave on the rear-end of the aeroshell, but also improving the flight environment and increasing the loading volume to provide a technological path for the entrance, deceleration and landing of future load extraterrestrial asters.

The invention provides a heat-resistant coating as well as a preparation method and application thereof. The heat-resistant coating is used for heat-resistant protection of the surfaces of rockets, guided missiles and other aircrafts and a variety of equipment. The heat-resistant coating consists of the following components in percentage by mass: 30 to 40 percent of room temperature silicon sulfide rubber, 0.7 to 1.5 percent of accelerating agent 109, 7 to 10 percent of vermiculite, 7 to 10 percent of silsesquioxane, 10 to 25 percent of hollow glass beads, 15 to 20 percent of APP (Ammonium Polyphosphate) and 5 to 10 percent of melamine. According to the heat-resistant coating, the silsesquioxane with high silicon content is selected instead of carbon fiber, so that the coating is low in granularity and suitable for pneumatic coating. The coating with the thickness of 2.0mm can resist the high temperature of 1,800 DEG C for 100 seconds, and the heat-resistant requirements of space flight and aviation products can be met.

The invention discloses a high property solid propellant rocket engine with a laterally arranged nozzle. The high property solid propellant rocket engine with the laterally arranged nozzle comprises a charging combustion chamber, an ignition device and the nozzle, wherein a combustion chamber shell body of the charging combustion chamber is a hollow cylinder. The high property solid propellant rocket engine with the laterally arranged nozzle is characterized in that the nozzle is fixedly mounted at the opening of the outer side of the combustion chamber shell body in a sealed mode, the included angle between the axis of the nozzle and the axis of the cylinder of the combustion chamber shell body is 10-90 degrees. By arranging the nozzle laterally, the requirements for high thrust and high total impulse of the solid propellant rocket engine in a small using structural space are met; by designing a special-shaped nozzle shell body, the problem of sealed mounting of the laterally arranged nozzle is solved; by designing special-shaped nozzle throats, the problem that fuel gas in the charging combustion chamber flows along the wall caused by the nozzle arranged laterally is solved, and ablation and erosion on the position of the sealed mounting structure of the nozzle are substantially improved, the reliability of heat proof, load-carrying capability and connection sealing design on the position of the sealed mounting structure of the nozzle are improved, the integration of the engine work structure and the uniformity of internal ballistic property are guaranteed.

The invention relates to a ceramic high carbon polymer matrix composite and a preparation method thereof. The composite comprises the following components according to parts by weight: 15-50 parts of high thermoset carbon resin, 5-10 parts of eutecticevaporate mixture, 20-50 parts of clay stratified structure mineral powder, and 0.1-1.5 parts of molding additives. The preparation method comprises the following steps of hot melting and mixing the components according to the proportion, heating and fusing the mixture for vacuum defoamation, casting in a die, and thermocuring for molding at the temperature, so as to obtain the ceramic high carbon polymer matrix composite. The ceramic component of the polymer is characterized in that the ceramic component can be converted into ceramic material containing carbon in high temperature aerobic environment, the temperature for ceramic conversion is controllable, the ceramic conversion rate is high in high temperature aerobic environment, and the ceramic bovine component can be used in the field of antiflaming and fireproofing and thermal protection.

The invention belongs to gloves braiding technology field, discloses an anti-cutting cladding yarn and a preparation method and a purpose; the curling coefficient of the anti-cutting cladding yarn is 99.8; the preparation of the anti-cutting cladding yarn comprises the following steps: spandex filament is used as the core, and cladding yarn after wire contacting, nylon wire or polyvinyl filament or polypropylene fiber filament are used to clad the core; when the core is claded, the cladding yarn twist is 470-520, and the twisting direction is S-shaped; the twist of nylon wire or polyvinyl filament or polypropylene fiber filament is 209-231 and twisting direction is Z-shaped; the rabbi of the spandex filament is between 1.4-3.5 times; by weight percentage, the prepared anti-cutting cladding yarn comprises the cladding yarn 35-45%, nylon wire or polyvinyl filament or polypropylene fiber filament 45-60% and spandex filament 5-15%. The gloves made by the cladding yarn provided by the invention have the advantages of highly improved anti-cutting performance, thermal contact performance, wear resistant performance, anti tear performance and anti-puncture performance.

The invention discloses an active and passive radar seeker radome and an aircraft and relates to the field of an aircraft radome. The radome comprises a radome body, a shell, a heat insulation shieldand a heat insulation layer, wherein the shell is fixed at an interior of the radome body; the shell comprises a front frame and a rear frame which are disposed at intervals; a cabin section for fixing a passive antenna is disposed between the front frame and the rear frame; the heat insulation shield is disposed in the radome body and fixed on the front frame; and the heat insulation layer is attached between an inner side of the radome body and an outer side of the shell. According to the active and passive radar seeker radome provided by the invention, heat shielding, wave transmission, conformal installation of an antenna array and the radome, and vibration-damping installation of an active seeker can be implemented.

The invention discloses a carbon fiber-enhanced high-temperature-resistance high-strength light hybrid ceramic-resin composite material pipe. A ceramic-based composite material is used as a shell, a resin-based composite material is used as an inner shell, the outer shell and the inner shell are mutually nested to form a composite structure, the surfaces of inner and outer walls are smooth, the ceramic component in the composite material is distributed in a graded mode in the pipe wall thickness direction and is gradually reduced from the outer surface to the interior of the pipe, the high temperature resistance is good, and long-time application can be achieved at 600 DEG C; and compared with traditional aluminum alloy shells, the heat conductivity coefficient is lower, and high-temperature-resistance anti-heating performance is better. The resin component is also distributed in a graded mode in the pipe wall thickness direction and is gradually reduced from the inner surface to exterior of the pipe and filled with a certain amount of filler, the high temperature resistance and impact resistance of the resin-based material are improved, and therefore the resin-based material has the vibration reduction characteristics. The ceramic-based component and the resin-based component are integrally formed, and the light hybrid ceramic-resin composite material pipe integrating heat temperature resistance, heat prevention, heat insulation, bearing and vibration reduction is prepared.

The invention discloses a new energy resource charging pile with a plug-in type charging gun and a use method of the new energy resource charging pile. The new energy resource charging pile comprisesan outer pile body and a gun body. A pile door is installed on one side of the outer pile body in a rotating manner. An inner box body is arranged in an inner cavity of the outer pile body. Four connection columns are symmetrically installed on the outer walls of the two sides of the inner box body. A lead screw is arranged between every two adjacent connection columns. Nuts are arranged on the peripheral face of each lead screw in a rotating manner and are fixedly installed on a water baffle. By means of the inner and outer two-layer design of the outer pile body and the inner box body, the waterproof and heat-proof effects of the whole charging pile can be better; meanwhile, the inner box body is connected with the inner wall of the outer pile body through the connection columns, and therefore a sufficient cooling space can be formed between the inner box body and the outer pile body, and the cooling effect of the whole charging pile can be better; the lead screws are driven by output shafts of drive motors to rotate, the lead screws are used in cooperation with the nuts to drive the water baffles to fall, rod sleeves on the water baffles slide downwards along stand rods, the water baffles slide downwards to one sides of cooling fins on the outer pile body, and then rainwater can be prevented from entering the outer pile body through the cooling fins when it rains.

The invention provides a special-shaped fuel tank for an aircraft. The special-shaped fuel tank comprises a plate-shaped component, an annular cabin, a first end frame and a second end frame and is characterized in that the annular cabin is provided with a first accommodating cavity used for accommodating an engine, the structure of the first accommodating cavity is matched with the shape of the engine, the plate-shaped component is fixedly arranged on the annular cabin along the length direction of the annular cabin to form a combined part, and the shape of combined part is matched with the shape of the aircraft; the first end frame is fixedly arranged at one ends of the plate-shaped component and the annular cabin, the second end frame is fixedly arranged at the other ends of the plate-shaped component and the annular cabin, the first end frame, the second end frame, the plate-shaped component and the annular cabin jointly form a second accommodating cavity in an enclosed manner, andthe second accommodating cavity is used for accommodating fuel. By the special-shaped fuel tank, the technical problems that a cylindrical fuel tank in the prior art is low in fuel capacity and poorin adaptability are solved.

The invention discloses a halogen-free flame-retardant polyethylene material and preparation method and application thereof. The halogen-free flame-retardant polyethylene material is prepared from, bymass, 80-95 parts of LDPE, 5-15 parts of a halogen-free phosphate ester flame retardant, 1-5 parts of a nitrogen flame retardant, 0.2-0.8 part of an antioxidant, 0.1-0.5 part of diffusion oil and 0.3-0.7 part of a lubricant. The invention also discloses the preparation method of the halogen-free flame-retardant polyethylene material, and also discloses the application of the halogen-free flame-retardant polyethylene material. The halogen-free flame-retardant polyethylene material has the advantages that the flame-retardant and mechanical properties are excellent, the flexibility of a workpiece is good, the material does not prick the hand when touched by hand, the rebound resilience is good, the material can be recycled, environmentally friendly and nontoxic, the flame resistance can reach UL94 V-2, the self-extinguishment is good, the preparation method is simple, the production cost is low, industrial large-scale production is easy, and the material is suitable for preparing simulation decorations and plug inner membranes.

The invention relates to a conveying manipulator and a handling device used for carrying a large area baseplate. The conveying manipulator comprises a load-bearing arm and a heat protection shell positioned on the surface of the load-bearing arm, wherein the thickness range of the heat protection shell is 0.001mm-0.3mm; and preferably, the surface of the load-bearing arm or a surface at which the heat protection shell is contacted with the load-bearing arm is provided with one or more protruding parts. The invention also provides the handling device which comprises the conveying manipulator. The conveying manipulator provided by the invention adopts the heat protection shell, the conveying manipulator still can exactly operate under a hot environment, even if the conveying manipulator is positioned in the hot environment for a long time, and the conveying manipulator can not transform; and in addition, the thickness of the heat protection shell is 0.001mm-0.3mm, further the weight of the conveying manipulator is reduced, the volume of the conveying manipulator is reduced, and the conveying cost is reduced.

The invention discloses a heat preservation nomadism tent which mainly comprises a frame and a tent cover arranged on the frame, wherein, a skylight hole and a side window hole are arranged on the tent cover, the area ratio of the skylight hole to the tent cover ranges from 0.01 to 0.03, and the area ratio of the side window hole to the tent cover ranges from 0.05 to 0.15; and the tent cloth on the outermost layer of the tent is made of pure white or light offwhite organo-fluorine waterproof breathable fabrics with the heat conductivity ranging from 0.042 to 0.055 W/m DEG C. The invention realizes the fundamental improvement on heat shielding, ventilation, smoke discharge and the like of the heat preservation tent by the scientific and reasonable design of the tent cover; and based on scientific experiments, the invention reasonably chooses the heat-conducting property and the color of the fabrics of the outer tent cloth, reduces the greenhouse effect and the cold room effect of the heat preservation tent, and increases the heat insulation property and the heat preservation property of the tent, thereby improving the quality of life and habitation of herdsmen during nomadism.

The invention discloses a heat resistance warning cone for a heating pipeline repair well opening. The heat resistance warning cone comprises a warning cone body and a support seat, wherein the support seat comprises a first support ring and a second support ring, the first support ring and the second support ring are connected through a plurality of connecting rods, a first support rod and a second support rod are arranged in the first support ring, the two ends of the first support rod and those of the second support rod are respectively connected with the inner wall of the first support ring, the lower end surfaces of the first support rod and the second support rod are in contact with the ground, the upper end surface of the second support ring is provided with an annular convex edge, the cross section of the annular convex edge is in a round shape, a plurality of clamp buckles are arranged on the lower end surface of the warning cone body, each clamp buckle comprises a first connecting sheet and a second connecting sheet, a gap allowing the annular convex edge to pass is formed between each first connecting sheet and the corresponding second connecting sheet, and the first support ring, the second support ring, the connecting rods, the first support rod and the second support rod are respectively made of metal materials. The heat resistance warning cone for the heating pipeline repair well opening can be used for a long time on high-temperature well covers for warning passing pedestrians, and the occurrence of injury accidents can be reduced.