317results about How to "Improve thermal protection performance" patented technology

The present invention relates to an electronic cigarette with prolonged heating protection and a protection method of the same. The electronic cigarette can avoid generating peculiar smell due to long time heating processes, and can also avoid scald injuries and fire accidents caused by too high temperatures.

The invention provides a room-temperature curing high-temperature-resistant organic silicon rubber coating as well as a preparations method and application of the room-temperature curing high-temperature-resistant organic silicon rubber coating. The organic silicon rubber coating is prepared from an organic silicon rubber material; and the organic silicon rubber material is characterized in that amatching system of a hydroxy-terminated polysiloxane polymer containing different functional groups, modified white carbon black reinforced filler, high-temperature-resistant and antioxidant filler,high-temperature-resistant and ablation-resistant filler and fibers is designed and used and is matched with a proper polysilazane curing agent based on a mechanism of an interaction among an organicsilicon polymer chain, the reinforced filler, the high-temperature-resistant and antioxidant filler, the high-temperature-resistant and ablation-resistant filler and the fibers in order to meet the harsh requirement for excellent comprehensive performances such as room temperature curing, high temperature resistance and high mechanical properties required in the use of the high-temperature-resistant organic silicon thermal protection coating, so that the formula design of a high-temperature-resistant elastic coating is simplified, and the use of a char forming agent capable of generating hugeinfluences to the mechanical properties is reduced.

The invention provides a self-catapulting launching device for a guided missile. The self-catapulting launching device comprises a flow-guiding cone, a limiting mechanism, a buffering device, a long guide rail, a short guide rail and adaptors; the flow-guiding cone is fixedly connected to the bottom end of a launching cylinder, the buffering device is fixedly connected to the outlet of the launching cylinder, the long guide rail and the short guide rail are fixed to the inner wall of the launching cylinder in the axis direction of the launching cylinder and are staggered and evenly distributed in the launching cylinder, grooves of the adaptors are slidingly matched with the long guide rail, gaps between two adjacent adaptors are slidingly matched with the short guide rail, the limiting mechanism is fixedly connected to the inner wall of the launching cylinder, the adaptors are limited to move to the interior of the cylinder in the axis direction of the launching cylinder, and after guided missile is filled, a closed space is defined by the bottoms of the adaptors, the bottom of the guided missile, the end face of the bottom of the long guide rail and the end face of the bottom of the short guide rail in the launching cylinder. The initial launching precision of the guided missile can be improved, and the manufacturing cost and the maintenance cost of the launching device are effectively lowered.

The invention discloses a hypersonic flight vehicle leading edge heat protection method based on a gradient porous material. A porous leading edge with gradient porosity is prepared from a high-temperature-resistant material, the porosity of a stationary point area of the porous leading edge is the maximum, and the porosity decreases backwards; a cooling pipeline is fixedly connected with the backpart of the porous leading edge, a coolant is injected into a cooling cavity through the cooling pipeline and sprayed out of the surface of the leading edge; the coolant is forced to perform heat convection when flowing through the porous leading edge, the temperature of the porous leading edge is decreased, meanwhile, the coolant is injected in a high-temperature mainstream through micropores inthe porous leading edge, and a thicker air film covering layer is formed in the stationary point area of the porous leading edge to isolate the porous leading edge from hot flows. A traditional sweatcooling mode is optimized by use of the gradient porous material, high-accuracy positioning and quantitative injection of the coolant are realized, and the ideal heat protection effect is realized.

The invention discloses a plastic motor case and bearing device installing method, where the bearing device comprises gland, oil containing bearing and oiled felt, and the method comprises the steps of: 1) firstly injection-moulding a plastic motor case with bearing cavity for reserving; and II) placing the oil-containing bearing and oiled felt in the bearing cavity, and then fixing the gland on the bearing room to fix them in the bearing cavity. And it has advantages of simple process, low manufacturing cost, coaxial matching, low operating heat and long service life.

The invention discloses a thermal barrier coating with thermal radiation property. The thermal barrier coating is a SiO2 plugging surface layer which is prepared by on the surface of a ZrO2 coating after sol-gel by using a dipping-pull method and is high in finishing degree and low in roughness. On one hand, a function of increasing the thermal radiation rate of the surface of the coating is achieved, on the other hand, a function of filling pores of the thermal resisting coating is achieved, and the pores in the surface of the coating are made up. The composite coating of a novel structure can be used for improving the thermal protection property of the surface of a titanium alloy at high temperature, and has important values on protection of high-speed aircraft shells.

The invention relates to the technical field of electric vehicles, in particular to a power battery box for an electric vehicle. The power battery box comprises a box cover and a box body, wherein a lining is connected to the inner wall of the box body and filled with a phase change material; and the box body is formed by extruding molding of an aluminium alloy material. The box body is small in density, lighter in weight, convenient to process and manufacture and low in processing cost; meanwhile, the lining is connected to the inner wall of the box body, and can enhance the integral rigidityand strength of the box body, play the role of vibration and energy absorption and improve the protective capability of the box body; and the lining is filled with the phase change material, and thephase change heat accumulation principle of the phase change material is utilized to assist a heat management system in temperature adjustment of the battery box, so that the temperature in the battery box can meet the requirements on the performance and the service life of a power battery, and the power battery can efficiently work at an appropriate temperature.

The invention provides a combustor fuel nozzle and a thermal protection structure thereof. The thermal protection structure can reduce possibility that the nozzle is liable to coke fuel during an actual use process. The thermal protection structure comprises a thermal protection pipe and a heat exchange structure, wherein the thermal protection pipe is used for surrounding an oil inlet pipe; the inner wall surface of the thermal protection pipe is used for forming a thermal protection space together with the outer wall surface of the oil inlet pipe; the thermal protection space is divided into an air inlet part and an air outlet part, which are separated and located on two sides of the oil inlet pipe; the air inlet part and the air outlet part are used for forming a cooling air channel together with a pipe-wall inner cavity of an outlet section of the nozzle; the heat exchange structure is arranged in the thermal protection space and comprises a plurality of transverse rib plates and a plurality of longitudinal rib plates; the transverse rib plates are perpendicular to the flowing direction of cooling air; the longitudinal rib plates are radially distributed by taking the oil inlet pipe as a center and intersect the transverse rib plates respectively; and each transverse rib plate is provided with a plurality of airflow holes for allowing the cooling air to flow through.

The invention discloses a direct-current cold-wall type engine combustor. The direct-current cold-wall type engine combustor comprises a combustor upper cover, a combustor linear section, a jet section and a spray pipe convergence and expansion section which are connected in sequence. An oxidizing agent liquid collection cavity, an oxidizing agent jet hole, a fuel liquid collection cavity and a fuel jet hole are formed in the outer wall of the jet section in the circumferential direction. An oxidizing agent enters the oxidizing agent liquid collection cavity via an oxidizing agent regenerativecooling channel and then flows out from the oxidizing agent jet hole to form a jet flow, fuel enters the fuel liquid collection cavity via a fuel regenerative cooling channel and then flows out fromthe fuel jet hole to form a jet flow, the jet flows are close to the inner wall of the combustor linear section but being not in contact with the wall, and the jet flows impact for atomization, mixingand combustion on the combustor upper cover, and are discharged out of the combustor through the spray pipe convergence and expansion section. By means of the combustor, the propellant combustion efficiency and the thermal protection capacity of the combustor can be improved, and the combustor is simple in overall structure and easy to machine and obtain.

A turbine cooling cascade with a vortex structure relates to a turbine cooling cascade. The invention settles the problems of flowing loss, blending loss and easy burning of blade leading edge and end wall surface of blade leading edge caused by the existence of horse shoe vortex structure in the prior blade cascade. According to the blade (2) of the invention, a pressure surface (2-2) next to the blade leading edge (2-1), a suction surface (2-3) of blade (2) next to the blade leading edge (2-1) and the blade leading edge (1-1) of wall (1) are respectively provided with a plurality of elongated slots (3) which are distributed in row. One side wall of each elongated slot (3) is provided with a plurality of cold air injection openings (4). Furthermore the positions of cold air injection opening (4) are next to the base of elongated slot (3). The turbine cooling cascade with vortex structure according to the invention reduces the flowing loss at the inner part of flow passage, reduces the bigger blending loss of air currents with different flowing velocities, provides better thermal protection function for the end wall of blade and the blade surface, effectively protects the end wall adjacent with the blade leading edge and the high-temperature area on the surface of blade, and increases the usage factor of cold air.

The invention discloses a linen fiber bleaching device for textile production and relates to the technical field of textile production. In order to solve the problem that the bleaching time is difficult to control and linen fibers are easy to damage when the linen fibers are soaked in a solution to be stirred, the linen fiber bleaching device specifically comprises a shell, a plurality of supporting frames are fixedly installed at the bottom of the shell, driving mechanisms are fixedly installed on the two sides of the top of the shell, a capping mechanism is fixedly installed between the topends of the two driving mechanisms, and bleaching sections extending downwards are arranged in the middle sections of the driving mechanisms. According to the linen fiber bleaching device for textileproduction, a bleaching solution is in contact with a heating mechanism when being sprayed out; the linen fibers are heated and cooked; the linen fiber bleaching efficiency is improved; the linen fibers are drained; a bleaching solution is recycled; the loss of the solution is reduced; the situation that the working environment is affected due to solution dripping is avoided; raw materials can becontinuously bleached due to the fact that the raw materials enter from one end and exit from the other end, and the linen fiber bleaching processing efficiency is improved.

The invention discloses a gas flow regulation device for a rotary spray pipe value of a solid rocket-ramjet engine. Each of a first fixed part and a rotating part is provided with one central hole andtwo arc-shaped holes in the axial direction; the front end of a transmission shell and an axial outlet section of a rear sealing head shell of a combustion chamber form a dynamic sealing structure; the tail end of the transmission shell and the head end of a spray pipe shell form a dynamic sealing structure; an outer ring of a thrust self-aligning roller bearing is mounted and fixed to the interior of a shell hole in the head end of the spray pipe shell; and the inner ring of the thrust self-aligning roller bearing is fixed to a shaft neck of the tail end of the transmission shell in a matched manner. A driving motor drives a driven gear to rotate to determine a corresponding angle of a transmission ratio, and finally, drives the rotating part to rotate at a corresponding angle relative to the first fixed part, so that the two arc-shaped holes of the rotating part and the fixed part are staggered and sheltered in the axial direction, thereby changing the effective outlet circulation area of the gas of the combustion chamber and realizing gas flow regulation with determined accuracy. The gas flow regulation device for the rotary spray pipe value of the solid rocket-ramjet engine isbetter in transmission mechanism thermal protection, more compact in structure and has higher work reliability, and can realize higher-precision and larger-range gas flow regulation.

The present invention provides a process and apparatus for producing container plants in a covered raised-based environment.

The invention relates to aerodynamic layout of an internal and external flow waverider aircraft and belongs to the technical field of aerodynamic design of aircrafts. The aircraft is divided into an upper part and a lower part in terms of aerodynamic layout design; the lower part of the aircraft is mainly used for providing high lift-drag ratio for unpowered gliding flight with high Mach number, and a flat waverider layout form is adopted; the upper part of the aircraft is mainly used for arranging an air suction type ramjet. According to the layout form, an engine flow channel and a waveriderplane are mutually independent and non-interfering, so that coupling effect of pneumatics and power is greatly reduced, particularly, resistance produced by an engine during unpowered flight with high Mach number can be obviously reduced, increase of the lift-drag ratio during unpowered flight with high Mach number is facilitated, and furthermore, thermal protection of the engine is facilitated.

The invention discloses a highly visible arc protective multilayer composite fabric which at least comprises a surface fabric and an inner fabric, wherein the surface fabric and the inner fabric are adhered by a flame retardant adhesive; the surface fabric is woven from two or more than two of vinyon N, Lenzing flame retardant viscose and flame retardant cotton; the inner fabric is blended from one or two yarns of silicon nitrogen series flame retardant viscose, para-aramid as well as polysulfonamide and polyimide; and the flame retardant adhesive is flame retardant polyurethane or flame retardant EVA (Ethylene-Vinyl Acetate). According to the manner, the fabric disclosed by the invention can achieve long-term and excellent flame retardant and arc protective effects, and the fabric has theeffects of being humidity-absorbing and breathable, comfortable to wear, antibacterial and healthy.

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 discloses a high-temperature fuel gas adjusting valve used for a rocket engine. The high-temperature fuel gas adjusting valve used for the rocket engine is composed of a valve body, an upper end cover, connection end covers, a motor shaft sleeve, a rotating shaft, a valve element and a valve element bracket. The motor is fixedly connected with the upper end cover; an output shaft of the motor is fixedly connected with the motor shaft sleeve which is connected with the rotating shaft and the valve element in a cooperative manner, and positioning and transmission are achieved; and the valve element is connected with the valve element bracket. Gas conveying pipe heat insulating pieces are installed at the two ends of the valve element bracket and fixedly connected with the connection end covers; the valve body is in threaded connection with the connection end covers and is fixedly connected with the upper end cover through bolts; and the connection end covers are connected with a fuel gas pipeline. The high-temperature fuel gas adjusting valve changes the circulating area by changing the rotating angle of the valve, and therefore thrust adjustment of a solid propellant engine, flow adjustment of a solid fuel gas generator or fuel gas flow adjustment of a primary fuel gas generator of the solid rocket ramjet engine can be achieved; and the high-temperature fuel gas adjusting valve is safe and reliable. The high-temperature fuel gas adjusting valve is simple in structure, convenient to install and operate and good in heat protection effect.