803 results about "Thermal protection" patented technology

The invention provides a spacecraft quartz powder heat insulation tile which is prepared by adopting high-purity quartz powder (SiO2) as a main raw material and combining a high-temperature-resistant ceramic fiber reinforcement and a nano aerogel heat insulation layer through a high-temperature sintering process. The heat insulation tile has the following advantages: 1, the heat insulation tile has excellent high temperature resistance, and can tolerate 1600 DEG C high temperature for a long time and tolerate 1800 DEG C instantaneous thermal shock for a short time; 2, repeated use: the structure is stable, and high strength is still kept after multiple thermal cycles; light weight: the density is low (less than or equal to 0.5 g / cm < 3 >), and the load of a spacecraft is reduced; and 4, the thermal conductivity is low (less than or equal to 0.05 W / m.K), and heat transfer is effectively isolated. The method is suitable for thermal protection systems (TPS) of spacecrafts, such as thermal insulation of reentry capsules and rocket engine nozzles.

The invention discloses a high-entropy alloy silicon carbide nanofiber composite material and a preparation method and application thereof, a high-entropy alloy is loaded on silicon carbide nanofibers, compared with a carbon fiber material carrier, SiC fibers can form a compact SiO2 protective layer in a high-temperature aerobic environment, further oxidation failure of the internal structure can be prevented, and the high-entropy alloy silicon carbide nanofiber composite material is prepared. And meanwhile, SiC also has relatively high high-temperature stability and weather resistance, so that the high-entropy alloy silicon carbide nanofiber composite material can stably work in an extreme high-temperature oxidation environment (such as a spacecraft thermal protection system and an engine tail gas pipeline) of over 1000 DEG C, and perfectly adapts to a high-temperature wave-absorbing scene.

According to the transition prediction method suitable for the wide Mach domain of the high-speed aircraft provided by the invention, temperature and Mach number coupling correction is performed on key parameters in time scale modeling of a second mode of a transition mode, and simplified processing of a flow compression effect and a heat transfer process by traditional single parameter association is broken through; the influence of an incoming flow disturbance effect is embedded in the mode, and dynamic association between test environment parameters and transition triggering criteria is achieved; according to the improved mode, accurate prediction results are obtained on a plurality of examples with the Mach number range of 4.7-14, the research results provide a more reliable theoretical tool for aerodynamic configuration optimization of a high-speed aircraft with a wider speed range, and the method has important engineering guiding significance for thermal protection system design of a new-generation reusable aircraft.

The invention discloses a preparation method of a toughening environmental barrier coating, and relates to a preparation method of a coating. The invention aims to solve the problem of poor fracture toughness of the existing environmental barrier coating. The method comprises the following steps: 1, pretreating a base material; 2, preparing a bonding layer; and 3, preparing the environmental barrier layer. The high-melting-point metal silicide prepared on the surface of the base material or the bonding layer compounded by the high-melting-point metal silicide and the rare earth silicate has excellent temperature resistance and good interface bonding strength, and due to the addition of the rare earth silicate, the expansion coefficient of the bonding layer is highly matched with that of the base material; according to the prepared yttrium oxide stabilized zirconia fiber, mullite fiber or silicon carbide fiber reinforced rare earth silicate environmental barrier layer, the fracture toughness of pure Yb2SiO5 is improved to 6.5 MPa.m < 1 / 2 >-8.0 MPa.m < 1 / 2 > from about 1.85 MPa.m < 1 / 2 >. The strengthening and toughening environmental barrier coating prepared by the invention has very important significance on development of thermal protection coatings of hot end parts of aircrafts with high thrust-weight ratios in China.

The invention discloses a high-strength heat-insulation aerogel structure with a dual multi-scale design and a preparation method thereof, relates to the technical field of thermal protection of spacecrafts, and in particular relates to the high-strength heat-insulation aerogel structure with the dual multi-scale design and the preparation method thereof. The invention aims to solve the problems of insufficient structural rigidity and poorer thermal protection property and thermal stability of the traditional spacecraft surface aerogel structure under the conditions of extreme high temperature and mechanical load. The structure is composed of an upper carbon-carbon composite material plate, a lower carbon-carbon composite material plate, an alloy skeleton and a filler. The method comprises the following steps: 1, preparing a multi-scale C / C composite material; 2, designing and preparing a titanium alloy honeycomb framework; 3, proportioning the multi-scale aerogel; 4, in-mold in-situ gelation; 5, drying and heat treatment; and 6, assembling and solidifying. The porosity of the aerogel is 85-98%, the structure has high rigidity and thermal protection performance, and the aerogel is applied to the field of aerospace thermal protection.

The invention discloses a normal-temperature curing ablation-resistant coating and a preparation method thereof, the normal-temperature curing ablation-resistant coating comprises a component A, a component B and a component C, the component A comprises the following raw materials by weight: 20-30 parts of epoxy resin, 30-40 parts of liquid nitrile rubber, 27-50 parts of an ablation-resistant filler, 10-20 parts of a heat-insulating functional filler, and 200-300 parts of toluene; the component B is a curing agent; and the component C is a curing accelerator. By selecting the high-performance polymer-based resin material and adding the ablation-resistant filler and the heat-insulating functional filler, the ablation-resistant and heat-insulating coating protection construction of the equipment under the normal-temperature curing condition is realized; the problems of ablation-resistant coating construction and thermal protection when a fragile cover, a launcher and the like in a launching system cannot use a high-temperature curing system ablation-resistant coating are solved. The coating can realize military technology and civil use, and can be widely applied to fire prevention and heat insulation construction of buildings.

The invention relates to a high-temperature-resistant temperature and vibration composite sensor applied to the field of measurement and testing, which comprises a composite sensor body and a composite circuit board arranged in the composite sensor body, and adopts the cooperation of a thermal insulation sleeve, a magnetic induction ring, a thermal insulation protection feedback unit and a ventilation regulation and control unit. According to the composite sensor, the adaptability of the composite sensor body to the environment is effectively promoted, the composite sensor body can be effectively isolated and protected under the high-temperature condition, and the situation that components in the composite sensor body are damaged due to continuous heat transfer is prevented, so that the durability of the composite sensor body is remarkably improved; meanwhile, heat exchange protection can be effectively carried out on the internal environment of the composite sensor body, the influence of heat on all components in the composite sensor body is further reduced, and the heat resistance of the composite sensor body is enhanced.

The invention provides a phase change enhanced ablation-resistant modified liquid silicone rubber material as well as a preparation method and application thereof, and belongs to the field of advanced materials. According to the invention, paraffin is adopted as a phase change filler, so that the ablation resistance and heat insulation performance of the expanded ceramic liquid silicone rubber material are remarkably improved, and the prepared silicone rubber composite material has the advantages of low density, low ablation surface temperature, strong carbon layer and high heat absorption capacity. The phase-change reinforced modified expanded ceramic flexible ablation-resistant material further improves the ablation resistance and high-temperature heat insulation performance of a liquid silicone rubber material, and has a good application prospect in the fields of aerospace thermal protection, building heat insulation and the like.

The invention discloses a chromium-doped indium oxide-based high-temperature heat flux sensor and a preparation method thereof, a screen printing technology is adopted, a slurry formula and printing process parameters are optimized, a thermopile structure is accurately formed on a high-temperature-resistant ceramic substrate, and then a thermopile and a thermal resistance layer are subjected to step-by-step high-temperature sintering treatment, so that the chromium-doped indium oxide-based high-temperature heat flux sensor is obtained. And firm combination between the thin film and the substrate and densification of a microstructure are ensured. The finally prepared sensor has excellent high-temperature oxidation resistance and long-term working stability, is stable and reliable in thermoelectric output signal, meets the strict requirements of aerospace, energy power and other fields on high-temperature heat flow measurement, is suitable for heat flow monitoring in high-temperature combustion environments, high-speed pneumatic heating and other scenes, and has wide application prospects. And a reliable test means is provided for design and performance evaluation of the thermal protection system in an extreme environment.

The invention relates to the technical field of textile materials, and particularly discloses a fabric capable of improving thermal protection performance and a preparation method and application of the fabric. Nano-scale aluminum oxide; polyethylene glycol diacrylate; a closed type waterborne polyurethane emulsion; a silane coupling agent containing a vinyl group; a photochromic dye; a thermochromic dye; the preparation method comprises the following steps: S1, preparing composite slurry; s2, applying the composite slurry to the surface of a fabric base material in a dot matrix form by adopting a screen printing process to form a coating; s3, the coating is irradiated with ultraviolet light; and S4, carrying out baking treatment on the fabric subjected to the ultraviolet light curing treatment at the temperature of 140-160 DEG C. According to the invention, the polyethylene glycol diacrylate, the closed waterborne polyurethane and the vinyl-containing silane coupling agent are adopted to form an interpenetrating polymer network structure in situ, so that when the obtained fabric is rubbed or washed and the like, the coating is not easy to crack and peel off.

The invention discloses a ceramic component gradient modified C / C-SiC-ZrC composite material and a preparation method thereof, and belongs to the technical field of carbon / carbon composite material matrix modification preparation, a carbon fiber preform and a heating element are placed in chemical liquid phase vaporization deposition equipment, a precursor solution is added until the carbon fiber preform is fully soaked, and a ceramic component gradient modified C / C-SiC-ZrC composite material is obtained; and carrying out chemical liquid phase vaporization deposition reaction to obtain the low-density C / C composite material with porosity in unidirectional gradient distribution. And putting the mixture into a graphite crucible with a carbon-rich area facing downwards and a carbon-less area facing upwards, completely putting the graphite crucible into the ceramic powder for modification, reacting and infiltrating, and cooling to room temperature to obtain the C / C-SiC-ZrC composite material with the gradient modified ceramic components. The end with high ceramic content endows the material with a high-temperature thermal protection function, the end with high pyrolytic carbon content can effectively conduct heat generated in a ceramic-rich area, and the end with low ceramic content can effectively conduct heat generated in a ceramic-rich area. Due to the gradient design from the ceramic-rich area to the carbon-rich area, the material has high-temperature oxidation resistance and ablation resistance and is light, and lightweight design of an aerospace thermal protection structure is facilitated.

Embodiments include thermal covers to help drain fluids away from dangerous environments, e.g., in an engine bay in a vehicle. Thermal covers can comprise a hat portion extending between two distal edges, support straps beneath the hat portion and extending between the distal edges, and thermal insulation disposed between the hat portion and the support straps. These can be coupled to the floor so as to allow space below for the flow of fluid. This allows the fluid to flow to holes in the floor of the engine bay, allowing the fluid (which could be flammable) to be drained away from potentially dangerous environments in the engine bay which may involve high temperatures.

The invention provides a graphene oxide and aramid nanofiber hybrid modified chopped fiber reinforced flexible polymer thermal protection material as well as a preparation method and application thereof, and belongs to the field of advanced materials. Aiming at the problems of huge modulus difference, poor interface compatibility and serious stress concentration between fibers and a flexible matrix, a hybrid interface phase composed of graphene oxide and aramid nanofibers is constructed, so that an inert surface microstructure of the chopped fibers is improved, and a multi-scale mechanical interlocking structure is promoted to be formed between the fibers and the flexible matrix; the modulus mismatch between the fiber and a rubber matrix is effectively relieved, and more uniform and efficient stress transfer of an interface area is realized. In the processes of tensile deformation, dynamic loading, high-temperature ablation and the like, the hybrid interface phase can keep tight interface combination between the fibers and the flexible matrix, the ablation anti-scouring performance and mechanical performance of the flexible composite material are remarkably improved, especially the flexible ablation performance in the high-dynamic and deformation state, and the flexible composite material has good application prospects.

The invention relates to the technical field of functional materials, in particular to phenolic aldehyde hybrid SiO2 mesoporous microspheres and application thereof. Mesopores with the pore diameter of 2-50 nm are formed in the surface and the interior of the phenolic aldehyde hybridized SiO2 mesoporous microsphere; the average diameter of the phenolic aldehyde hybrid SiO2 mesoporous microspheres is 10 to 100 microns; the phenolic hybrid SiO2 mesoporous microspheres can be applied to the fields of thermal protection, wave absorption, heat insulation and coatings. According to the phenolic hybrid SiO2 mesoporous microsphere disclosed by the invention, by virtue of a unique mesoporous structure and an organic-inorganic hybrid characteristic, excellent heat insulation performance and multifunctionality are realized, and meanwhile, the problems of insufficient protection performance, single function, poor processability, high cost and the like of an existing material are solved.

The invention relates to the technical field of bus duct thermal protection, in particular to a bus duct thermal protection method and system based on intelligent monitoring, and the method comprises the steps: obtaining a packet loss delay bandwidth generation state label, calling an unstable link collection path node congestion rate port number to generate a scheduling table, collecting a temperature rise rate displacement, calculating a thermal slope and combining field disturbance to obtain a trigger value, and comparing thermal triggering with thermal accumulation to identify a high-temperature-sensitive section mark, and calling the mark to compare a cutoff threshold value to generate a starting result. By collecting multi-dimensional data such as packet loss, delay and bandwidth for dynamic analysis, the state of a communication link can be evaluated in real time, an unstable link can be found, an accurate triggering boundary value is generated by combining parameters such as thermal load, electric field intensity and harmonic waves, cooling or power-off protection is started in time by matching with a heat flow trend before a high-temperature-sensitive area appears, and the reliability of the system is improved. Response lag of a traditional technology is avoided, an intelligent response mechanism is innovated to achieve accurate and flexible thermal protection, stable and safe operation of equipment is guaranteed, and overheating accidents are reduced.

The invention discloses a multi-scale bidirectional coupling sweating cooling simulation method which comprises the following steps: firstly, on a mesoscale, constructing a mesoscopic flow model, simulating flow of a coolant, and obtaining parameters such as porosity, permeability and inertia coefficient of a porous medium; introducing the obtained parameters into a porous medium panel area of a thrust chamber geometric model constructed under a macroscale to realize cross-scale parameter coupling; the flow and heat transfer process in the thrust chamber geometric model after cross-scale parameter coupling is simulated, and the speed, pressure, temperature and local heat flux density distribution of a combustion chamber and a porous medium panel area under the macroscale are obtained; and taking the local heat flow density as a new wall surface boundary condition, capturing the flow and heat transfer characteristics of a coolant in pores under a thermal state working condition based on the mesoscopic flow model, and further evaluating the overall cooling performance and the thermal protection effect of the porous medium panel. Through coupling calculation of the mesoscopic pores and the macroscopic combustion chamber, the accuracy and reliability of prediction of the cooling performance of the porous medium are improved.

The invention relates to the field of special polymer materials, in particular to polyimide foam with low thermal conductivity and high flame retardance and a preparation method thereof. According to the invention, hollow glass microspheres (HGM) are used as a carrier, and a novel three-stage coating structure of an inner layer (heat absorption dehydration), a middle layer (catalytic carbon formation) and an outer layer (smoke suppression hydrophobic) is constructed outside the hollow glass microspheres (HGM). The preparation method comprises the following steps: dispersing three-layer coated HGM (15-35%) in a foaming black material, mixing with a foaming white material to react to generate a foam intermediate, and carrying out gradient heating curing molding to obtain the foam with the density of 18-30kg / m < 3 >, the heat conductivity coefficient of less than or equal to 0.035 W / (m.K), the limit oxygen index of more than or equal to 41.5% and the smoke density Ds of less than 100. The problem that a traditional filler cannot consider low density, low heat conductivity, high flame retardance and processing compatibility at the same time is solved, and the filler is suitable for fire prevention and heat insulation of a spacecraft thermal protection layer and a new energy battery pack.

The invention discloses an anti-dusting ablation-resistant silicon dioxide aerogel composite material based on multi-phase synergistic reinforcement and a preparation method of the anti-dusting ablation-resistant silicon dioxide aerogel composite material. The inorganic vermiculite powder reinforcement is introduced into the aerogel in situ, the particle size of vermiculite is controlled to realize anchoring-bridging dual effects, a three-dimensional interpenetrating network is formed by co-gelling with the organosilicon precursor solution and the fibrofelt, and the powder falling rate of the finally prepared silicon dioxide aerogel composite material is 1t; mg and Fe elements contained in the vermiculite can promote generation of a glass phase at a high temperature, and cooperate with the fiber felt to resist 1200 DEG C ablation. The density of the product can be controlled to be 200-350kg / m < 3 >, the heat conductivity coefficient is 0.025-0.040 W / (m.K), and the product is suitable for the field of aerospace thermal protection.

The invention relates to a preparation method of a low-density boride aerogel material, and aims to solve the problems of high density, large pore diameter and poor heat insulation performance of the existing boride ceramic material with a porous structure, the method comprises the following steps: 1) preparing tannic acid-formaldehyde sol, and pre-gelling at a constant temperature; 2) preparing M / B precursor sol, and carrying out pregelation at a constant temperature; 3) mixing the tannic acid-formaldehyde sol and the M / B precursor sol, and fully and uniformly stirring to obtain mixed sol; 4) sealing and storing the mixed sol at a constant temperature to obtain boride precursor wet gel; (5) carrying out absolute ethyl alcohol replacement on the boride precursor wet gel, and drying at normal pressure to obtain boride precursor aerogel; and 6) carrying out high-temperature sintering on the boride precursor aerogel in a tubular furnace to obtain the pure-phase boride aerogel. The low-density boride aerogel material with a complete structure can be obtained, the material phase purity is high, the density and aperture are adjustable, the light absorption performance is excellent, the maximum porosity is-95%, and the low-density boride aerogel material has wide application prospects in the field of thermal protection of aircrafts as a light thermal insulation material.

The invention discloses an ultrathin rigid phenolic aerogel heat insulation sheet and a preparation method thereof, and belongs to the field of heat insulation materials. The preparation method comprises the following steps: firstly, impregnating a fibrofelt in a sodium silicate-based rigidifying solution, and carrying out mould pressing and drying to form a self-supporting rigid framework; then, the framework is soaked in a phenolic aerogel precursor solution, curing, washing and drying are carried out, and framework pores are filled with phenolic aerogel; and finally compounding the hot melt adhesive film. According to the preparation method, through the specific process sequence of first rigidifying and then compounding, the problems that a traditional aerogel material is poor in rigidity and prone to pulverization, and a silicon dioxide-based material is insufficient in ultra-high-temperature ablation resistance are successfully solved, and the thickness of the obtained heat resisting sheet is 0.1-5 mm; the composite material has excellent rigidity (the compression strength is greater than 2MPa when the deformation quantity is 5%), low heat conductivity coefficient (0.02-0.045 W / (m.K)) and excellent 1200 DEG C high-temperature flame ablation resistance, and is especially suitable for thermal protection in limited spaces such as new energy batteries and the like.

An aircraft engine has a flammable fluid containment assembly including a component containing a flammable fluid. A transfer tube is fluidly connected to the component. A sealing ring is provided at an interface between the aircraft engine component and the transfer tube. A first thermal barrier is provided between the sealing ring and a first one of the aircraft engine component and the flammable fluid inside the transfer tube. The first thermal barrier includes a first annular cavity filled with a first thermal insulation medium and axially spanning the sealing ring.

The present disclosure relates to the formation of thermal protection systems based on the formation of ceramic coatings. Such ceramic coatings may be derived from polymeric resins and may be applied over carbon-carbon (C / C) composites. The ceramic coatings may optionally contain a metal carbide coating.

The invention provides an anti-oxidation and ablation-resistant ceramic coating on the surface of a C / C composite material and a preparation method, and belongs to the technical field of thermal protection coatings. The anti-oxidation and ablation-resistant ceramic coating on the surface of the C / C composite material comprises a bottom bonding layer, a middle heat insulation layer and an external ablation-resistant layer, the bottom bonding layer is SiC-SiCf, the middle heat insulation layer is modified ZrO2, and the external ablation-resistant layer is HfC-ZrC-SiCf. According to the method, the SiC-SiCf / modified ZrO2 / HfC-ZrC-SiCf composite ceramic coating is prepared on the special-shaped part through dipping and brushing methods, the method is easy and convenient to operate, few in material consumption and low in cost, and the performance meets the specific use requirement.

The invention relates to the technical field of preparation of new materials and composite materials, and discloses a ceramifiable aramid nanofiber reinforced phenolic aerogel composite material and a preparation method thereof, the composite material is prepared from a hybrid aramid nanofiber preform and a matrix phenolic resin; wherein the preform is prepared by mixing aramid nano-fiber slurry, a silane coupling agent, a transition metal precursor and water-soluble phenolic resin and freeze-drying the mixture. The preparation method comprises the following steps: dipping a preform into a matrix phenolic resin solution, carrying out sol-gel reaction and drying to obtain the composite material, and further carrying out high-temperature carbonization treatment. Through a multi-scale synergistic enhancement strategy, the silane coupling agent is utilized to reinforce interface bonding, and the transition metal precursor is utilized to realize high-temperature in-situ ceramization, so that the mechanical strength, the structural integrity and the ablation-resistant thermal protection performance of the composite material are improved, and the problems of high brittleness and easy pulverization of the traditional phenolic aerogel are solved.

The invention discloses a variable-pore phase-change sweating cooling bionic structure based on fractal characteristics. The variable-pore phase-change sweating cooling bionic structure comprises a variable-pore porous sweating layer and a regulation and control unit, wherein the variable-pore porous sweating layer is composed of fractal flow equalizing plates which are sequentially arranged in a stacked mode in the heat flow direction; the fractal flow equalizing plate is of an N-stage bifurcated tree-shaped structure and is used for equally dividing one path of cooling working medium into 2N paths of cooling working medium, and N is an integer ranging from 4 to 6; the variable-pore porous sweating layer is divided into an upper-layer high-heat-flow area and a lower-layer low-heat-flow area in the thickness direction, the upper-layer high-heat-flow area is used for promoting phase change and efficient heat exchange of a cooling working medium, and the lower-layer low-heat-flow area is used for promoting liquid-phase permeation of the cooling working medium; and the regulation and control unit predicts the phase change leading edge position S (t) in real time based on a neural network, and dynamically regulates the cooling working medium flow Q (t) input into the inlet of the fractal flow equalizing plate according to the S (t). The invention further discloses a design method of the structure. By introducing the bionic variable porosity characteristic, coupling of flowing heat exchange is achieved, the cooling efficiency of thermal protection is improved, and consumption of a heat exchange working medium is reduced.

The invention discloses a preparation method of conductive ceramic as well as an obtained product and application of the conductive ceramic. The conductive ceramic is prepared by taking aluminum oxide powder, coal gangue powder, fly ash powder and an organic carbon source as matrix raw materials and polyvinyl alcohol as a binding agent and adopting a rapid hot-pressing high-temperature sintering carbon thermal reduction process. The method is simple in process, low in cost, low in energy consumption, high in production efficiency, good in environmental protection property and easy for industrial production. The obtained conductive ceramic is high in mechanical property, good in conductivity and low in resistance, and is a preferable material for the fields of indoor heaters, electromagnetic shielding devices, high-temperature sensors, aerospace thermal protection systems and aero-engines.

The invention discloses a spacecraft active thermal protection control method and device, equipment, a medium and a product, and relates to the technical field of spacecraft thermal management, and the method comprises the steps: obtaining real-time thermal environment data outside a spacecraft; based on the real-time thermal environment data, predicting a heat flow change trend of the exterior of the spacecraft in a preset time period; according to the heat flow change trend, a regulation and control instruction for a heat dissipation execution assembly arranged outside the spacecraft is generated; wherein the heat dissipation execution assembly comprises a porous zeolite matrix in which a liquid phase change working medium is stored, and the regulation and control instruction is used for controlling the transportation process of the liquid phase change working medium in the porous zeolite matrix and the vaporization process of the liquid phase change working medium on the surface layer of the porous zeolite matrix. The method can realize active control of thermal protection.

The utility model discloses a multi-temperature-control PTC heating structure which comprises a PTC heater, a temperature control box and a temperature detection assembly. The temperature detection assembly is arranged on the PTC heater and used for detecting the temperature of the PTC heater, and the corresponding end of the temperature detection assembly is further electrically connected with the corresponding end of the temperature control box and used for feeding back detected temperature information of the PTC heater to the temperature control box; the temperature control box is detachably arranged on the PTC heater, and a thermal protector and a thermal fuse are integrated in the temperature control box; the corresponding ends of the thermal protector and the temperature fuse are electrically connected with the corresponding end of the PTC heater; the thermal protector is used for automatically disconnecting a circuit to prevent overheating when the temperature of the PTC heater exceeds a preset safety threshold value. According to the utility model, the temperature of the PTC heater can be accurately controlled, the temperature requirements in different application scenes can be met, and the PTC heater has wide application prospects.

The invention provides a high-temperature static water oxygen corrosion simulation device and a stability evaluation method, and belongs to the technical field of surface coating thermal protection, the device comprises simulation equipment, a gas processor and an online monitoring device, the simulation equipment is internally provided with a simulation chamber for storing a sample to be tested and water vapor; the gas processor is used for eliminating flow field distortion, so that water vapor in the flowing process forms stable airflow; the on-line monitoring device is used for collecting parameters of water vapor and a simulation chamber environment; through cooperation of the pretreatment cabin and the simulation equipment, a high-temperature static environment can be formed in the simulation equipment, flowing mixed water vapor can be combed through arrangement of a first gas steady flow rectifier and a second gas steady flow rectifier, so that the mixed water vapor in the flowing process forms a stable gas flow, and the stability of the gas flow is improved. Flow field distortion and airflow instability caused by front-end atmosphere mixing are eliminated, system resistance is reduced, and stability and accuracy of water vapor concentration test data are improved.