151 results about "Thermal protection" patented technology

The application discloses a kind of thermal protector detection devices, it is related to thermal protector detection technical field, including workbench, workbench is provided with driving piece one, driving piece one output end is provided with rotating plate, rotating plate circumference is provided with several placing plates, placing plate is provided with several clamping grooves, several connecting rods are arranged at intervals in clamping groove;Workbench is provided with heating box, the top surface of heating box is provided with opening, and several heating rods are arranged in heating box;Heating box is provided with support, support is provided with driving piece two, and the output end of driving piece two is provided with detection plate, and several indicator lights are provided with detection plate corresponding clamping groove, and several pressing plates that can be in contact with thermal protector in clamping groove are provided with detection plate;Driving piece two drives detection plate to move down, indicator light contacts thermal protector to complete temperature trigger on-off function test, while pressing plate carries out pressure resistance test to thermal protector, so that temperature trigger on-off function test and pressure resistance test are completed in the same device, greatly improve detection efficiency.

The application discloses a thermal protector with a mounting structure and belongs to the technical field of electrical elements. Mainly comprising a thermal protector body, an installation ear which is installed on the thermal protector body, an installation hole is formed in the installation ear, an installation assembly which is installed on the installation ear, the installation assembly comprises a connecting seat, the connecting seat is installed on an external heat generator, a limiting groove is formed in the upper end of the connecting seat, the connecting seat is penetrated and installed on the installation hole, an installation sleeve which is installed on the installation ear, and installation seats are installed on the two sides of the installation sleeve. The thermal protector with the mounting structure can be quickly installed through the cooperation of the connecting seat and the installation sleeve in the installation assembly and the clamping of the limiting block on the locking rod and the limiting groove of the connecting seat, the step of screwing a bolt is omitted, and the problem that it is relatively inconvenient to install the thermal protector by using a bolt is solved.

A thermal-protective transient voltage suppressor (TVS) includes a TVS assembly, a housing, a frame, a cover plate, and a pin, where the TVS assembly is provided in the frame; the TVS assembly is electrically connected to the pin; the housing and the cover plate form an accommodation chamber for accommodating the frame; the pin extends out of the accommodation chamber, and an extended part of the pin is provided with a mounting portion for surface mount soldering; a spacing limit post is provided on the cover plate; and the frame abuts against the spacing limit post, such that the mounting portion of the pin and the TVS assembly are spaced apart by a preset distance. The spacing limit post on the cover plate of the thermal-protective TVS limits the frame provided with the TVS assembly, thereby increasing a distance between the mounting portion of the pin and the TVS assembly.

The application belongs to the field of aero-engine product thermal protection design calculation, and particularly relates to a thermal protection design calculation method for an aero-engine signal control box. When carrying out product thermal insulation design, the thermal insulation material in the thermal insulation layer is laid flat on the inner surface of the product shell, the heat conduction rate of the flat wall of the product shell at different temperatures is calculated based on the thermal conductivity of the thermal insulation material; the heat dissipation layer is designed based on the heat conduction rate; the selected heat dissipation material is determined, and the heat dissipation assembly is designed; the mass of the heat dissipation material is determined according to the density and volume of the selected heat dissipation material; the total heat absorbed by the heat dissipation assembly is calculated according to the mass of the heat dissipation material; the temperature rise time of the control box is calculated according to the heat conduction rate of the thermal insulation material and the heat absorbed by the heat dissipation assembly, and the design is completed when the temperature rise time meets the design requirements. The application has the characteristics of small space, light weight, good reliability and maintainability, low cost and good use effect.

FIELD: rocket science.SUBSTANCE: invention concerns the design of a ramjet engine. The ramjet engine body is a structure consisting of several layers, including: an internal heat-protection layer made of a composite material based on a thread frame of heat-resistant fibers impregnated with an elastic polymer binder, a power body based on a high-temperature polymer composite material and an external heat-protection layer made of a composite material based on an elastic polymer binder and a finely dispersed mineral filler. Thanks to the use of layers of external and internal thermal protection, it becomes possible to use a polymer composite material for the power casing.EFFECT: reducing the labor intensity of manufacturing and weight of the product and increased energy-mass perfection of the propulsion system.1 cl, 2 dwg

The application discloses an online identification method for pyrolysis and ablation interface evolution of carbonized ablation material based on X-ray image fusion enhancement. In the ground thermal test of the carbonized ablation material, a plurality of groups of images of the carbonized ablation material at different moments are obtained through X-ray imaging, an image fusion enhancement algorithm is adopted to improve the image quality, the local features of the pyrolysis and ablation interface are enhanced, the image noise is reduced through local sliding window averaging, and the pyrolysis and ablation interface is identified in real time based on a gradient algorithm. The application can realize real-time automatic measurement of the ablation amount, the interface between the pyrolysis layer and the carbonization layer, and the interface between the pyrolysis layer and the original layer in the ground thermal test of the carbonized ablation material, overcome the problems that the traditional measurement method is difficult to identify the interface between the pyrolysis layer and has low accuracy, and improve the measurement technical level of the ground thermal test of the thermal protection material, thereby providing support for the design of the ablation thermal protection system.

The application discloses a nano-structure thermal protection coating for hydrogen fuel gas turbine and a preparation method thereof. The nano-structure thermal protection coating takes high-temperature alloy as a substrate, and sequentially deposits a bonding bottom layer, a yttrium stabilized zirconium oxide or zirconate intermediate layer and a silicate top layer on the surface of the substrate. The application starts from the design of the coating structure, and aims at the problems of low service temperature and poor water-oxygen corrosion resistance of the existing thermal protection coating for gas turbine. The water-oxygen corrosion resistance function of the silicate material is superimposed on the thermal protection coating for gas turbine, and the coating structure is optimized to form a new thermal protection coating structure resistant to high-temperature corrosion. The new thermal protection coating structure can not only meet more extreme service environments, but also resist water-oxygen corrosion at high temperature. The new thermal protection coating structure is suitable for hydrogen fuel power generation gas turbine, and is also suitable for hydrogen fuel or hydrogen mixed marine engines, hydrogen fuel rocket engines and other hydrogen fuel gas turbines.

The application relates to a high-temperature-resistant high-entropy ceramic battery shell and a preparation method thereof. The battery shell comprises a battery shell base material and a high-entropy oxide ceramic coating attached to the surface. The coating comprises an organic-inorganic hybrid cross-linked network and a nano ceramic powder; the powder has a single cubic phase fluorite structure, and a general chemical formula is AB2O4, wherein a rare earth element is a positive trivalent element not containing cerium. The powder particle size distribution satisfies D50 / D90 < 2.5, and a coating and a base material interface form a covalent bond. During preparation, a nano slurry is obtained through high-temperature calcination and sand milling, a bonding system is constructed by combining a silane coupling agent and an inorganic sol, and a high-adhesion coating is generated in situ through coating and low-temperature curing. The application solves the thermal mismatch combination problem of high-entropy ceramics and a metal base material, and significantly improves the limit thermal protection performance of the battery shell under a transient working condition of more than 1600 DEG C.

A multi-layered thermal protection structure for hypersonic vehicles and its fabrication method are disclosed, relating to the field of hypersonic vehicle thermal protection technology. The structure comprises, from the outside in, a C / SiC composite material layer, a vacuum buffer layer, a white calcium carbonate layer, a solar cell module, and a thermoelectric generator. Through a five-layer synergistic design, multi-dimensional protection is achieved: the C / SiC composite material layer directly resists extreme high temperatures and ablation; the vacuum buffer layer blocks solid-state heat conduction, reducing heat transfer inwards; the white calcium carbonate layer reflects radiant heat, reducing heat input; and the solar cell module and thermoelectric generator convert residual heat into electrical energy, actively consuming heat. This integrated "blocking-reflection-conversion" design improves thermal protection efficiency by more than 40%, enabling the internal structure temperature to be controlled within a safe range of ≤100℃ even in extreme environments of 2000℃-3000℃. This invention achieves a comprehensive balance of high-temperature resistance, ablation resistance, low thermal conductivity, and high toughness.

A high-temperature resistant lightweight composite material, its preparation method, and its applications are disclosed, relating to the field of composite material technology. This invention solves the problems of existing materials where it is difficult to simultaneously achieve high temperature resistance and lightweight, low structural efficiency due to the separation of heat protection and load-bearing design, insufficient temperature resistance and toughness of the sandwich layer, and difficulties and high costs associated with large-size molding. The material comprises an integrated co-cured outer heat-resistant layer, an intermediate transition layer, and an inner load-bearing layer. The outer heat-resistant layer uses a modified epoxy / cyanate copolymer resin as the matrix and a high-silica glass fiber and carbon fiber blended fabric as reinforcement, with fumed silica and carbon nanotube fillers incorporated into the matrix resin. The intermediate transition layer is polymethacrylamide foam. The inner load-bearing layer uses an epoxy-modified cyanate ester resin as the matrix and a carbon fiber biaxial plain weave fabric as reinforcement. This invention can be used in rocket fairings, hypersonic vehicle skins, spacecraft reentry capsule thermal protection structures, hypersonic missile shells, aircraft engine nacelles, or high-speed train front fairings.

This invention provides a system for thermal protection in power distribution equipment. [Solution] The power distribution system 100 includes a first silicon-controlled rectifier (SCR) 106A and a second SCR 106B connected to a heat sink. A first temperature sensor 105A senses the temperature of the first SCR, and a second temperature sensor 105B senses the temperature of the second SCR. While the second SCR is disconnected from the load, the control unit compares the temperature from the first temperature sensor with a plurality of temperature thresholds, and in response that the temperature reading from the first temperature sensor exceeds a first threshold but not a second threshold, generates a first warning, and further, in response that the temperature reading from the first temperature sensor exceeds a second threshold, it may disconnect the first SCR from the load and connect the second SCR to the load.

This application belongs to the field of aero-engine technology, and specifically relates to a double-layer structure afterburner heat insulation plate. The heat insulation plate is installed between the inner cone and the rear bearing cavity, isolating the rear bearing cavity from the inner cone's internal cavity. The heat insulation plate includes an inner layer, an outer layer, a skin, and a mounting edge. The mounting edge is located at the circumferential outer edge of the inner layer and has multiple circumferentially distributed through holes. The mounting edge is installed on the mounting edge of the bottom surface of the inner cone through these through holes. The outer layer is attached to the surface of the inner layer near the inner cone. The inner layer includes a spherical surface protruding into the inner cone's internal cavity. The afterburner heat insulation plate has a double-layer structure, and the cavity height is maintained by fixed supports and rivets. Heat insulation cotton is added to the double-layer cavity to enhance the heat insulation effect of the heat insulation plate.

The utility model relates to metal smelting hoisting equipment technical field, in view of the problem of the existing metal smelting hoisting high temperature flue gas and spatter easy to damage the sling, the existing protective measures are insufficient, provide a kind of sling heat insulation protective device. The device includes the heat insulation plate of being arranged in the recess of the beam both sides of sling, heat insulation plate is composed of semicircular plate and rectangle plate, rectangle plate is fixed in recess, semicircular plate bottom surface is equipped with deflector;Deflector main part is triangle heat-resistant steel plate, outer surface is bonded fiberboard through inorganic high temperature adhesive, semicircular plate bottom surface is also bonded fiberboard. Fiberboard is multiple L-shaped plate parts, and deflector installation groove is formed by the interval between adjacent plate parts. The device can effectively block high temperature, change high temperature flue gas flow direction, reduce equipment damage and downtime loss by special structure design and high temperature resistant material application, has the advantages such as compact structure, high safety, good heat insulation effect, low maintenance cost, is applicable to the high temperature liquid metal hoisting operation of metal smelting industry.

The utility model discloses a new energy automobile cooling fan is with brush holder assembly for assembling, through change the structure of compression spring, reduce the space of compression spring, increase the length of brush, improve the life of brush, adopt the split type inductance to the inductance one, and in the middle with soldering tin fixed, through the angle of inductance and soldering tin's tin content to control inductance fusing time, when motor block rotation, heat protection inductance disconnects first, forms open circuit, effectively prevents motor combustion risk.

This invention discloses a porous rectifying structure for the afterburner of a variable cycle engine, comprising a rectifying orifice plate installed in an annular channel between the turbine outlet and the flame stabilizer. The orifice plate is symmetrically arranged along its radial central axis, with the clogging area facing the turbine inflow and axially aligned with the heat shield inlet. The orifice plate height is 2 / 3 of the channel height between the central cone and the heat shield. The plate has uniformly distributed pores with an equivalent diameter of 10-20 mm along the radial direction, with a clogging ratio of 5%-25%. This invention forms a multi-stage mixing interface through the radially gradient porosity pore arrangement, promoting shear mixing of the high-temperature internal combustion gas and the external bypass gas. Simultaneously, the static pressure difference across the orifice plate drives the external bypass gas flow into the heat shield cooling channel, increasing the cooling flow rate, improving the uniformity of the upstream velocity field of the flame stabilizer, eliminating the recirculation zone inside the heat shield, reducing the thermal load on the casing wall, and controlling the total pressure loss to within 3%, achieving high-stability combustion and reliable thermal protection under a wide bypass ratio.

The present application belongs to the technical field of thermal protection coating of aero-engine and gas turbine, and relates to an environmental barrier coating for resisting high-temperature water-oxygen corrosion of SiC-based ceramic or composite material and a preparation method thereof. With SiC or SiC-based composite material as a substrate, MoSi2 powder is first sprayed on the surface of the substrate by atmospheric plasma spraying, so that the Si element in MoSi2 is selectively volatilized to form a composite coating mainly composed of MoSi2 and Mo5Si3; then HfO2 powder is sprayed on the surface of the composite coating by atmospheric plasma spraying to form an HfO2 layer; and then the substrate after spraying the HfO2 layer is placed in an oxygen-containing gas atmosphere, heated to 1200-1500 DEG C for high-temperature oxygen-containing heat treatment to obtain a coating structure with three-layer structure of sacrificial layer, oxygen barrier layer and water barrier layer. The environmental barrier coating prepared by the present application has higher stability in high-temperature water-oxygen environment and higher comprehensive performance.

The application discloses an anti-thermal shock alumina fiber reinforced phosphate high-temperature-resistant composite material and a preparation method thereof, and belongs to the technical field of ceramic matrix composites. The material is composed of gradient modified alumina fiber reinforcement, composite phosphate matrix and multi-scale composite filler. The fiber surface is provided with a nano yttrium oxide-yttrium phosphate gradient interface layer, and the matrix is an aluminum phosphate-zirconium phosphate-yttrium oxide composite system. The preparation method comprises fiber degumming, gradient interface modification, slurry preparation, impregnation and curing and microwave sintering. Through gradient interface regulation and composite matrix design, the application solves the problems of poor thermal shock resistance and insufficient high-temperature stability of the existing materials. Tests show that the material has no macroscopic cracking after 10 times of water cooling at 1300 DEG C, the strength retention rate is greater than or equal to 88%, the room temperature bending strength is greater than or equal to 280 MPa, and the material has excellent high-temperature mechanical properties and thermal shock stability, and is suitable for aerospace thermal protection and high-temperature structural parts.

This invention discloses a method for manufacturing an outer nozzle of a baffle nozzle with a sweating cooling function. The method uses high-temperature alloy powder as raw material and performs selective laser melting forming according to a preset laser scanning path and laser selective melting forming parameters to obtain the outer nozzle of the baffle nozzle with a sweating cooling function. The laser scanning path is determined based on a three-dimensional model, which is a ring-shaped periodic porous structure with sweating cooling. This invention utilizes the concept of sweating cooling in the outer nozzle of a liquid rocket engine baffle nozzle, using fuel as the cooling medium. As the fuel flows through the outer nozzle, it undergoes strong convective heat transfer with the nozzle. Simultaneously, a liquid film forms on the surface of the outer nozzle, hindering heat transfer between the outer nozzle and the high-temperature mainstream, thus achieving thermal protection of the outer nozzle and preventing ablation damage.

The invention provides a preparation method of composite aerogel, the composite aerogel, a thermal management system and a battery, and relates to the technical field of batteries. According to the specific technical scheme, fiber gel and organic sol are provided, wherein the fiber gel comprises silicon-based gel and a fiber matrix; coating the organic sol on the outer surface of the fiber gel body to obtain a composite gel body; drying the composite gel to obtain a composite material, forming silicon-based aerogel from the silicon-based gel, and forming fiber aerogel from the fiber gel; finally, carbonizing the composite material to obtain composite aerogel, and forming carbon aerogel from the organic sol; the composite aerogel prepared by the method not only has synergistic heat insulation and heat conduction functions, but also has a relatively stable structure, and can be applied to a battery as a thermal protection material so as to improve the overall safety of the battery.

The application belongs to the technical field of thermal protection coating materials, and discloses a bonding layer material for thermal barrier / environment barrier coating, a preparation method of the bonding layer material, a thermal barrier / environment barrier coating and an engine. 13 The bonding layer material for the thermal barrier / environment barrier coating comprises xSiC*yAl6Si2O 13 zHfSiO4*(1-x-y-z)HfO2, wherein x, y and z are volume percentages, x=0%~70%, y=0%~70%, z=0%~70%, and 30%≤x+y+z≤70%. The bonding layer material for the thermal barrier / environment barrier coating can improve the use temperature of a substrate, and has the advantages of high melting point, low thermal expansion coefficient and high fracture toughness.

In electric vehicles, this invention aims to achieve both thermal protection of the drive motor, which is the power source, and energy savings in the cooling system that cools the drive motor. [Solution] The information processing device according to this embodiment determines the output of the radiator fan and water pump using pre-prepared table information from a target combination which is a combination of the detected temperature of the drive motor, the estimated road surface gradient angle of the travel path, and the calculated vehicle speed of the electric vehicle.

The application discloses an ion source ceramic discharge channel support and inner heat shield integrated structure, and belongs to the Hall ion source field.The integrated structure comprises a ceramic support and an inner heat shield which are welded and fixed as an integrated piece; the ceramic support comprises a bottom plate and an outward-flanged cylinder, the outward-flanged cylinder comprises, from bottom to top, a mounting and positioning section, an outward-expanding section, a radiation heat transfer section and an outer magnetic pole mounting outward-flanged section, and the inner heat shield is in a cylindrical structure, and the bottom side outer side is fixedly connected with the inner ring end face of the bottom plate.The ceramic support is fixed to the outer magnetic pole of the Hall ion source through the outer magnetic pole mounting outward-flanged section, and a gap is kept between the ceramic discharge channel outlet section and the ceramic discharge channel, so that the heat conduction between the ceramic support and the ceramic discharge channel is changed into mainly radiation heat exchange; the inner heat shield keeps a radial gap with the ceramic discharge channel and the inner magnetic screen, and a low-radiation-rate surface is adopted to reduce the heat transfer of the ceramic discharge channel to the inner magnetic circuit.The application can reduce the heat transfer to the inner and outer magnetic circuits while realizing the support and positioning of the ceramic discharge channel, improve the thermal protection effect of the Hall ion source, and improve the working reliability and service life of the magnetic circuit and the ceramic discharge channel.

This invention discloses a method and apparatus for measuring steady-state thermal conductivity with self-calibrated thermal loss. Combining the theory of self-calibrated thermal loss, it utilizes a layered thermal barrier of high and low thermal conductivity materials to achieve quasi-one-dimensional heat conduction. This invention eliminates the need for additional thermal loss calibration, using easily measurable physical quantities to account for thermal loss and calculate the accurate thermal conductivity and thermal resistance of the sample. Compared to traditional quasi-steady-state testing methods, this invention is applicable to measuring the thermal conductivity and contact thermal resistance of both extremely high thermal conductivity thin films and extremely low thermal conductivity materials under wide temperature ranges and varying pressure conditions. This invention eliminates the need for additional thermal protection and thermal loss calibration; the accurate thermal conductivity can be directly calculated from the measurement data, simplifying the steady-state measurement process and improving the repeatability and accuracy of the measurement. It can be used to measure the thermal conductivity and thermal resistance of samples under different temperatures and pressures.

The application discloses a high-temperature environment magnetic suspension motor heat protection method, obtains the armature winding loss, excitation winding loss and core loss of the magnetic suspension motor under the rated working condition; based on the component loss and the corresponding volume, calculates the heat generation rate of each component, and establishes a temperature field mathematical model containing the heat conduction coefficient and the convective heat transfer coefficient; according to the temperature field mathematical model, the node temperature set of the whole magnetic suspension motor is determined, and the node temperature set is divided into temperature intervals; when the highest temperature is higher than the preset safety threshold, the arrangement parameters of the cooling channel are adjusted, and the simulation and adjustment are repeatedly executed until the highest temperature is below the preset safety threshold, and the heat protection is completed. The application verifies the highest temperature through the temperature field simulation, if the highest temperature exceeds the preset safety threshold, the arrangement parameters of the cooling channel are dynamically adjusted and iteratively optimized until the temperature control requirement is met, so that the key components of the motor are effectively prevented from over-temperature under the high-temperature environment.

The application belongs to the field of advanced ceramic materials, and relates to a high-entropy polyacetylacetone compound precursor and a preparation method of high-entropy ceramic nanofiber aerogel, which solves the problems of easy grain growth and crystallization pulverization of traditional ceramic aerogel at high temperature. The preparation steps are as follows: synthesizing high-entropy polyacetylacetone compound precursor powder, preparing a spinning solution and adding a phase stabilizer and a polymer spinning aid, obtaining precursor fibers through far-field electrospinning, and obtaining high-entropy ceramic nanofiber aerogel with a fiber diameter of 200-2000 nm through gradient high-temperature annealing treatment. The material has good flexibility and thermal stability, and is suitable for efficient heat insulation scenes in extreme environments such as aerospace thermal protection.

This invention relates to a method for preparing ultra-high temperature ceramic materials using low-temperature, pressureless, and rapid prototyping, belonging to the field of ultra-high temperature ceramic technology. The method involves dispersing polyzirconium dihydrogen phosphate powder in a mixed solvent of ethanol and water, adding an equal mass of F44 phenolic epoxy resin, and concentrating the solution to obtain an adhesive. Subsequently, hafnium carbide powder of different particle sizes is compounded into the adhesive, and boron powder and silicon powder may be selectively added. After uniform mixing, the solvent is removed, the mixture is ground and shaped, and then cured pressureless in air to obtain the ultra-high temperature ceramic material. This invention uses polyzirconium dihydrogen phosphate as a novel curing agent, solving the problems of high porosity and poor heat and ablation resistance in traditional epoxy systems, while retaining its high adhesive strength. The proposed process is low-temperature, pressureless, simple to operate, and rapid in molding, yielding ultra-high temperature ceramic materials with high heat and ablation resistance, suitable for thermal protection in extreme thermal environments such as aerospace.

This invention discloses a composite thermal protection aerodynamic rudder for aircraft and its manufacturing method, aiming to solve the problems of high manufacturing cost, poor thermal insulation, and poor overall mechanical performance in existing structures. The composite thermal protection aerodynamic rudder of this invention includes a metal frame, lightweight filler, and a composite material thermal protection structure arranged sequentially from the inside out. The metal frame includes a rudder shaft and a rudder surface, which are integrally formed. The rudder surface has an internal frame rib structure forming an internal cavity, which is filled with lightweight filler. The composite material thermal protection structure covers the outside of the rudder surface and the lightweight filler, forming the aerodynamic shape of the aerodynamic rudder. Through the frame rib structure design of the metal frame, the amount of material used is significantly reduced while ensuring load-bearing capacity, achieving lightweighting, which is beneficial to improving the thrust-to-weight ratio and maneuverability of the aircraft. Optimizing the rib layout according to the load path achieves efficient material utilization.

This invention relates to the field of thermal insulation materials, specifically to a gradient-structured ceramic fiber composite felt and its preparation method. From bottom to top, the felt consists of a surface layer A1, a core layer B, and a surface layer A2, with gradient transition interfaces between each layer. The slurry A of surface layers A1 and A2 is composed of water, long ceramic fibers, glass microspheres, and a composite adhesive. The slurry B of the core layer B is composed of water, SiO2 aerogel, inorganic functional fillers, short ceramic fibers, a composite light-blocking agent, and a flocculant. This invention, through a gradient structure design, organically combines a high-strength, wear-resistant surface layer with an ultra-low thermal conductivity, highly protective core layer. By introducing inorganic functional fillers into the core layer, a unique active thermal protection system is constructed. When exposed to high temperatures, the material not only passively insulates with the low thermal conductivity of the aerogel but also actively dissipates heat and blocks heat conduction through the endothermic decomposition of the fillers and the in-situ self-generation of a secondary ceramic insulation layer.