Radiation high-temperature measuring method for aircraft interior parts

Abstract

The invention provides a radiation pyrometry method for aircraft interior parts, and relates to the technical field of aircraft interior part testing, which comprises the following steps: setting a radiation heat source system which comprises a plurality of radiation heat source devices with adjustable wavelengths and radiation intensities, the radiation heat source device simulates radiation heat environments of an airplane in different flight stages, and simulates a real radiation heat source environment in the flight process by automatically adjusting the wavelength and radiation intensity of a radiation source. According to the radiation high-temperature measurement method for the aircraft interior part, by integrating multi-dimensional thermal monitoring, thermal deformation and stress monitoring, automatic visual analysis and artificial intelligence data analysis, thermal response, stress change and surface damage of the part in a radiation high-temperature environment can be accurately captured.

Description

Technical Field

[0001] The present invention relates to the technical field of interior component testing for aircraft, and particularly to a method for measuring the radiant high temperature of aircraft interior components. Background Art

[0002] With the continuous improvement of aircraft design and flight requirements, the performance requirements for aircraft interior components are becoming increasingly strict. To ensure the safety and comfort of passengers, the materials and components inside the aircraft need to withstand various extreme environmental conditions during flight, including high-temperature radiation, mechanical pressure, etc. Especially in a high-temperature environment, aircraft interior components are easily affected by high-temperature radiation, leading to material aging, deformation, and even failure. Therefore, how to accurately evaluate the performance of interior components under high-temperature radiation has become an important issue in the aviation industry. Currently, the thermal stability evaluation of aircraft interior components mainly relies on laboratory tests. During the test process, high-temperature environments are usually simulated through equipment such as heating furnaces and thermal radiation sources. Existing high-temperature test methods mostly use hot air heating, infrared radiation heating, etc.

[0003] However, these methods have certain limitations. The existing test methods do not accurately simulate the radiation heat source, and it is difficult to reproduce the real radiation heat environment encountered during actual flight. Traditional high-temperature test methods usually only focus on temperature measurement, while ignoring the long-term impact of thermal radiation on the surface materials of components, and cannot comprehensively evaluate the thermal stability and high-temperature resistance of materials.

[0004] Therefore, there is an urgent need for a more accurate and comprehensive method for measuring the radiant high temperature of aircraft interior components, in order to better evaluate the long-term use performance of materials in a high-temperature radiation environment and ensure the safety and reliability of aircraft. Summary of the Invention

[0005] Aiming at the deficiencies of the prior art, the present invention provides a method for measuring the radiant high temperature of aircraft interior components. The technical problem to be solved by this invention is: how to achieve the precise thermal response of aircraft interior components in a radiant high-temperature environment by integrating multi-dimensional thermal monitoring and thermal degradation models.

[0006] To achieve the above objectives, the present invention is realized through the following technical solutions: A method for measuring the radiant high temperature of aircraft interior components, including: S1. Set a radiation heat source system. The radiation heat source system includes multiple radiation heat source devices with adjustable wavelengths and radiation intensities. The radiation heat source devices simulate the radiation heat environment of the aircraft at different flight stages, and automatically adjust the wavelength and radiation intensity of the radiation source to simulate the real radiation heat source environment during flight; S2. Place the aircraft interior parts to be tested on the test platform in front of the radiation heat source device, ensuring that the distance between the surface of the parts and the radiation heat source is set to 1 to 20 cm, simulating the real environment where the parts directly suffer from the radiation heat source during flight; S3. Use an integrated multi-dimensional thermal monitoring and surface material analysis system to monitor the thermal response and surface changes of the parts to be tested in real time; S4. According to the real-time monitoring data, through a deep learning analysis model, evaluate the thermal stability, high-temperature resistance, thermal deformation and crack propagation of the parts in different high-temperature radiation environments, and generate a detailed thermal response analysis report, which includes an assessment of material thermal degradation; S5. Generate a complete test report, which includes the thermal aging trend, material property changes, crack development, deformation characteristics and overall reliability assessment of the parts, and combined with the actual thermal radiation conditions during flight, provide data support for the design optimization and improvement of the interior parts.

[0007] Preferably, the radiation heat source device includes a plurality of infrared radiation modules and ultraviolet radiation modules, the wavelength range of the infrared radiation modules is 1 - 15 μm, and the wavelength range of the ultraviolet radiation modules is 200 - 400 nm.

[0008] Preferably, the multi-dimensional thermal monitoring and surface material analysis system includes: Multi-dimensional thermal monitoring: Use a thermal infrared imaging system and surface temperature sensors to obtain the full-surface temperature distribution image of the parts; Thermal deformation and stress monitoring: Use a fiber optic sensor network to monitor the thermal deformation and stress distribution on the surface and inside of the parts in real time; Automated visual analysis: Combine high-resolution microscope imaging and computer vision technology to automatically detect thermal aging phenomena such as microcracks, color changes, and bubbles on the surface of the parts caused by radiation high temperature. The system can automatically identify and quantify the degree of thermal damage under various radiation conditions and generate a thermal damage distribution map; Artificial intelligence data analysis: The system combines artificial intelligence algorithms to automatically process the real-time obtained thermal response data and surface damage data, and analyze the thermal aging trend and potential failure risks of the material.

[0009] Preferably, the resolution of the thermal infrared imaging system is ≤0.1 mm, and the time resolution is ≤0.1 second, which can accurately capture the transient thermal response of the parts under different radiation intensities.

[0010] Preferably, the surface temperature sensors include thermocouples and resistance temperature sensors, which are used to detect the internal temperature changes and thermal diffusion characteristics of the parts, and the fiber optic sensors are arranged on the surface and inside of the parts.

[0011] Preferably, the thermal response analysis report includes steps for evaluating the thermal degradation of materials, including the following sub-steps: S5.1 Analyze the material degradation rate of components under different radiation intensities using a thermal degradation model. The thermal degradation model is based on the thermal activation process and the physical and chemical change laws of materials, combined with the principles of thermodynamics, to quantitatively evaluate the degradation mechanism of materials in different high-temperature environments; S5.2 Analyze the thermal degradation characteristics of different materials by integrating experimental data from thermomechanical analysis, differential scanning calorimetry, and thermogravimetric analysis; S5.3 Analyze the thermal expansion behavior, thermal stress, and physical changes of materials under the action of a radiation heat source by combining real-time data from temperature sensors, strain sensors, and heat flux sensors; S5.4 Automatically generate a material degradation report based on the thermal degradation analysis results. The report includes the thermal aging rate of the material, thermal expansion changes, surface crack propagation, and its impact on structural integrity, and gives the possible failure modes of the material in a long-term high-temperature environment.

[0012] Preferably, the trend analysis of thermal aging describes the thermal degradation rate of materials under the action of different radiation heat sources through a mathematical model. The thermal aging model is based on an equation to describe the degradation process of materials: ; wherein, is the degradation rate constant of the material, is the frequency factor, is the activation energy, is the gas constant, is the test temperature.

[0013] Preferably, the surface crack propagation uses a fracture mechanics model to predict crack propagation: ; wherein, is the crack propagation rate, is the material constant, is the stress intensity factor range, is the material index.

[0014] The present invention provides a method for measuring the radiation high temperature of aircraft interior components. It has the following beneficial effects: The method for measuring the radiant high temperature of aircraft interior components can accurately capture the thermal response, stress changes, and surface damage of components in a radiant high temperature environment by integrating multi-dimensional thermal monitoring, thermal deformation and stress monitoring, automated visual analysis, and artificial intelligence data analysis. These data can comprehensively reflect the thermal stability, crack propagation, and thermal aging trend of materials under different flight stages, providing a scientific basis for the design optimization of components. In particular, the high-resolution infrared imaging system and high-precision sensor network adopted enable more refined real-time monitoring of temperature, stress, and deformation, thus providing higher data accuracy and reliability for long-term reliability and safety.

[0015] By combining the thermal degradation model, crack propagation prediction model, and artificial intelligence algorithm, multi-dimensional analysis of materials is achieved. The application of deep learning technology enables the system to automatically analyze and process data from different sensors, identify thermal aging trends, crack propagation, and potential failure risks. Brief Description of the Drawings

[0016] Figure 1 It is a schematic flow diagram for implementing the invention. Detailed Embodiments

[0017] Next, the technical solutions in the embodiments of the present invention will be clearly and completely described in conjunction with the accompanying drawings in the embodiments of the present invention. Obviously, the described embodiments are only a part of the embodiments of the present invention, rather than all of the embodiments. All other embodiments obtained by those of ordinary skill in the art based on the embodiments of the present invention without creative efforts shall fall within the protection scope of the present invention.

[0018] Embodiment 1, as Figure 1As shown in the figure, an embodiment of the present invention provides a method for measuring the radiant high temperature of aircraft interior components, including: S1. Set up a radiant heat source system. The radiant heat source system includes multiple radiant heat source devices that can adjust the wavelength and radiant intensity. The radiant heat source devices simulate the radiant heat environment of the aircraft at different flight stages, and by automatically adjusting the wavelength and radiant intensity of the radiation source, the real radiant heat source environment during the flight process is simulated. The radiant heat source devices include multiple infrared radiation modules and ultraviolet radiation modules. The wavelength range of the infrared radiation modules is 1 - 15 μm, and the wavelength range of the ultraviolet radiation modules is 200 - 400 nm, which can simulate various radiation environments encountered by the aircraft at different flight stages. When simulating the cruise stage of the aircraft, the radiant intensity can be set to 800 W / m² to reproduce the radiant heat environment generated by solar radiation and atmospheric temperature differences during high-altitude flight. During the landing stage, a higher radiant intensity, such as 1200 W / m², is set to simulate the environment with a higher temperature during the aircraft's landing process. During the cruise stage of the aircraft, the intensity of ultraviolet radiation can be adjusted to 0.15 W / m², and this intensity can simulate the ultraviolet intensity in the upper atmosphere during flight. To ensure the accuracy of the simulation, the ultraviolet radiation module can dynamically adjust the radiant intensity through the control system during the test process to adapt to the actual requirements of different flight stages.

[0019] S2. Place the aircraft interior component to be tested on the test platform in front of the radiant heat source device. During the simulated flight process, the support frame of the test platform can adjust the distance between the component and the radiation source according to different flight stages. During the cruise stage, the distance between the component and the radiation source is maintained at 10 cm, while during the takeoff or landing stage, the support frame can automatically adjust to 5 cm to simulate the stronger radiation environment during the initial stage of flight and landing.

[0020] S3. Adopt an integrated multi-dimensional thermal monitoring and surface material analysis system to monitor the thermal response and surface changes of the component to be tested in real time. The multi-dimensional thermal monitoring and surface material analysis system includes: Multi-dimensional thermal monitoring: Use a thermal infrared imaging system and a surface temperature sensor to obtain the full-surface temperature distribution image of the component.

[0021] Thermal deformation and stress monitoring: Use a fiber optic sensor network to monitor the thermal deformation and stress distribution on the surface and inside of the component in real time.

[0022] Automated visual analysis: Combine high-resolution microscope imaging and computer vision technology to automatically detect thermal aging phenomena such as microcracks, discoloration, and bubbles on the surface of the component caused by radiant high temperature. The system can automatically identify and quantify the degree of thermal damage under various radiation conditions and generate a thermal damage distribution map.

[0023] Artificial Intelligence Data Analysis: The system combines artificial intelligence algorithms to automatically process the thermo-response data and surface damage data obtained in real time, and analyze the thermal aging trend and potential failure risks of the material.

[0024] The resolution of the thermal infrared imaging system is ≤0.1 mm and the time resolution is ≤0.1 second. It can accurately capture the transient thermo-response of components under different radiation intensities. The surface temperature sensors include thermocouples and resistance temperature sensors, which are used to detect the internal temperature changes and heat diffusion characteristics of components. The fiber optic sensors are arranged on the surface and inside of components, and can accurately detect the stress changes, micro-deformations and crack developments caused by thermal radiation. Under the simulated high-temperature environment, the fiber optic sensors can monitor the thermal expansion rate and surface stress distribution of components in real time. The test data shows that at 100 °C, the surface stress change of the component is 0.05 MPa, while at 200 °C, the stress change is 0.2 MPa, indicating a potential thermal crack risk. During the test, the computer vision system automatically identified that the surface crack length of the component was 0.1 mm and marked it as a minor thermal damage. Further analysis showed that the discolored area of the component reached 2%, indicating the degree of thermal aging of the material in the high-temperature environment.

[0025] S4. According to the real-time monitoring data, through the deep learning analysis model, evaluate the thermal stability, high-temperature resistance performance, thermal deformation and crack propagation of components under different high-temperature radiation environments, and generate a detailed thermo-response analysis report. The thermo-response analysis report includes the evaluation of material thermal degradation.

[0026] S5. Generate a complete test report. The test report includes the thermal aging trend of components, material property changes, crack developments, deformation characteristics and overall reliability assessment, and combines the actual thermal radiation conditions during flight to provide data support for the design optimization and improvement of interior components. The trend analysis of thermal aging describes the thermal degradation rate of the material under the action of different radiation heat sources through a mathematical model. The thermal aging model is based on an equation to describe the degradation process of the material: ; where, is the degradation rate constant of the material, is the frequency factor, is the activation energy, is the gas constant, is the test temperature. According to this model, combined with the radiation heat and temperature changes under different flight conditions, evaluate the thermal aging trend of components, and provide a basis for material selection and design optimization. The surface crack propagation uses the fracture mechanics model to predict crack propagation: ; where, is the crack propagation rate, is a material constant, is the stress intensity factor range, is the material index. Combining with the test data, it evaluates the crack propagation trend and its impact on the structural reliability of components. The crack propagation rate will be given in the report. Combining with the thermal stress changes during flight, it predicts the possible failure modes during long-term use. The thermal response analysis report includes the steps for evaluating material thermal degradation, including the following sub-steps: S5.1 Use the thermal degradation model to analyze the material degradation rate of components under different radiation intensities. The thermal degradation model is based on the thermal activation process and the physical and chemical change laws of materials. Combining with the principles of thermodynamics, it quantitatively evaluates the degradation mechanism of materials in different high-temperature environments. The model considers factors such as the structural changes of materials, molecular chain breakage, and chemical reaction rate caused by thermal aging, and can accurately predict the thermal degradation process of materials in high-temperature radiation environments.

[0027] S5.2 Analyze the thermal degradation characteristics of different materials by integrating the experimental data of thermomechanical analysis, differential scanning calorimetry, and thermogravimetric analysis.

[0028] S5.3 Combine the real-time data of temperature sensors, strain sensors, and heat flux sensors to analyze the thermal expansion behavior, thermal stress, and physical changes of materials under the action of radiation heat sources.

[0029] S5.4 Automatically generate a material degradation report based on the results of thermal degradation analysis. The report includes the thermal aging rate of materials, thermal expansion changes, surface crack propagation, and its impact on structural integrity, and gives the possible failure modes of materials in long-term high-temperature environments.

[0030] Example 2, different from Example 1, the specific implementation method is as follows: 1. Thermal aging trend analysis and model application During the test, use the thermal degradation model to analyze the material degradation rate of components under the action of different radiation heat sources. The prediction of the thermal aging trend is based on the following mathematical model: ; Where: is the degradation rate constant of the material, is the frequency factor, is the activation energy, is the gas constant , is the test temperature (in Kelvin).

[0031] Implementation data: For example, assume that the activation energy of the material is , and the frequency factor is , at Perform a thermal aging experiment. By using this formula, the degradation rate of the material can be calculated as , and combined with different radiation heat source intensities (such as and ) to evaluate its thermal aging trend.

[0032] Through this model, combined with the radiation heat and temperature changes under different flight conditions, the thermal aging rate of components can be accurately predicted, providing a scientific basis for material selection and design optimization.

[0033] 2. Prediction of Surface Crack Propagation and Fracture Mechanics Model The analysis of surface crack propagation uses a fracture mechanics model to predict the crack propagation rate: ; Where: is the crack propagation rate, is the material constant, is the stress intensity factor range, is the material index.

[0034] Implementation data: For example, assume that the material constant is , the stress intensity factor range is , and the material index is . Under this condition, the crack propagation rate can be calculated as , and further combined with actual test data, such as temperature changes, radiation intensity, stress changes, etc., to evaluate the crack propagation trend and its impact on the structural reliability of components.

[0035] 3. Integration of Thermal Degradation Analysis and Experimental Data In thermal degradation analysis, combined with various experimental methods (thermomechanical analysis, differential scanning calorimetry, thermogravimetric analysis), the thermal degradation characteristics of different materials are comprehensively evaluated.

[0036] Implementation data: Thermomechanical analysis: Evaluate the thermal expansion characteristics of materials by measuring the dimensional changes of materials at different temperatures. Assume that the thermal expansion coefficient of the test material is , and the length change of the material is 0.03 mm at .

[0037] Differential scanning calorimetry: Used to evaluate the glass transition temperature and melting point changes of materials. Assume that the Tg of the material is , and its melting point changes from to under different radiation intensities.

[0038] Thermogravimetric analysis: Measuring the mass change of materials during heating. For example, the test results show that the material loses of its mass at , and loses of its mass at , indicating the durability and thermal stability of the material in a high-temperature environment.

[0039] Combining these experimental data, the system can comprehensively evaluate the thermal degradation characteristics of different materials, providing data support for material selection and long-term use evaluation.

[0040] Example 3: Based on the specific implementation of step S4, this example demonstrates how to evaluate the thermal stability, high-temperature resistance, thermal deformation, and crack propagation of components in different high-temperature radiation environments through a deep learning analysis model according to real-time monitoring data, and generate a detailed thermal response analysis report, including an assessment of material thermal degradation.

[0041] Step 1: Real-time monitoring data collection Installation and deployment of a multi-dimensional monitoring system: Install temperature sensors, strain sensors, and heat flux sensors on the surface and key positions of the component. The temperature sensors include thermocouples and resistance temperature detectors, which are used to monitor the surface and internal temperature changes of the component. The strain sensor monitors the deformation and stress changes of the component under the action of a radiation heat source, and the heat flux sensor real-time monitors the heat transfer characteristics of the material.

[0042] Real-time capture of the thermal image of the component through an infrared imaging system, generate a temperature distribution map, and real-time monitor the thermal response characteristics of the component.

[0043] Real-time data collection: Assume that during the experiment, the surface temperature of the component gradually increases from 50°C to 200°C, while the internal temperature increases from 30°C to 180°C. At the same time, it is monitored by the strain sensor that there is a slight deformation on the surface of the material. At 150°C, the surface strain is 0.05%, and at 200°C, the strain increases to 0.15%.

[0044] Step 2: Deep learning analysis model Data preprocessing and model training: Collect and organize multi-dimensional data obtained from different sensors, perform data preprocessing such as denoising and normalization to ensure data quality. Then, input this data into a deep learning model for training. The deep learning algorithms used are convolutional neural networks and long short-term memory networks, where CNN is used to process image data and LSTM is used to process time series data.

[0045] Training Data: The training data set of the model includes historical experimental data, simulated flight data, and actual test data of components. Assume that through multiple test cycles, components of different materials are tested at 800W / m² and 1200W / m², covering temperature variations in a variety of different flight environments.

[0046] Model Analysis: The deep learning model automatically evaluates the thermal stability, high-temperature resistance, thermal deformation, and crack propagation trend of components by learning the thermal response patterns of components under different thermal radiation conditions. Combining thermodynamics principles, materials science theories, and experimental data, the model can predict the aging rate of materials, the concentration of thermal stress, and crack propagation under different flight conditions.

[0047] For example, through model analysis, it is found that in the hour thermal radiation environment, the thermal aging rate of the material is , and under conditions of higher radiation intensity, the crack propagation rate is , showing the fatigue life and failure risk of the material in extreme thermal environments.

[0048] Step 3: Generate a Thermal Response Analysis Report 1. Report Generation and Content: Based on the deep learning analysis results, the system automatically generates a thermal response analysis report, which details important information such as the thermal aging trend, high-temperature resistance, thermal deformation, crack propagation, and structural reliability assessment of components.

[0049] Thermal Aging Assessment: The report calculates the thermal degradation rate of components under different radiation intensities based on an equation, and combines the impact of high-temperature environments on materials to predict the degradation trend during long-term use. Assume that the degradation rate of the material under high-temperature conditions is , then the surface hardness and tensile strength of the component will gradually decrease over time, and it is expected to lose of its strength within 200 hours.

[0050] Crack Propagation Assessment: Through a fracture mechanics model, the report predicts the crack propagation rate on the surface of components and the failure mode during long-term use. Simulation data shows that during the cruise phase, the crack propagation rate is , and at higher temperatures, the crack propagation rate will accelerate, increasing the risk of failure.

[0051] Thermal Stress and Deformation: Combining the strain data monitored in real time, the report analyzes the thermal stress distribution and deformation of components under the action of different radiation heat sources. The report points out that the stress of the material is 0.05MPa at , while at When the temperature reaches [specific value], the thermal stress increases to 0.2 MPa, indicating that stress concentration may occur in this material under high-temperature conditions, leading to the generation of microcracks.

[0052] Although the embodiments of the present invention have been shown and described, those of ordinary skill in the art can understand that various changes, modifications, substitutions, and variations can be made to these embodiments without departing from the principles and spirit of the present invention. The scope of the present invention is defined by the appended claims and their equivalents.

Claims

1. A method for measuring the radiant high temperature of aircraft interior components, characterized in that, Including: S1. Set up a radiation heat source system, which includes multiple radiation heat source devices that can adjust the wavelength and radiation intensity. The radiation heat source devices simulate the radiation heat environment of an aircraft at different flight stages, and automatically adjust the wavelength and radiation intensity of the radiation source to simulate the real radiation heat source environment during flight; S2. Place the aircraft interior parts to be tested on the test platform in front of the radiation heat source device, and ensure that the distance between the surface of the parts and the radiation heat source is set to 1 to 20 cm to simulate the real environment where the parts are directly exposed to the radiation heat source during flight; S3. Adopt an integrated multi-dimensional heat monitoring and surface material analysis system to monitor the heat response and surface changes of the parts to be tested in real time; S4. According to the real-time monitoring data, through a deep learning analysis model, evaluate the thermal stability, high-temperature resistance, thermal deformation and crack propagation of the parts in different high-temperature radiation environments, and generate a detailed heat response analysis report. The heat response analysis report includes an assessment of material thermal degradation; S5. Generate a complete test report, which includes the thermal aging trend, material property changes, crack development, deformation characteristics and overall reliability assessment of the parts, and provides data support for the design optimization and improvement of the interior parts in combination with the actual heat radiation conditions during flight.

2. The method for measuring the radiant high temperature of an aircraft interior component according to claim 1, wherein: The radiation heat source device includes multiple infrared radiation modules and ultraviolet radiation modules. The wavelength range of the infrared radiation modules is 1 - 15 μm, and the wavelength range of the ultraviolet radiation modules is 200 - 400 nm.

3. A method for measuring the radiant high temperature of an aircraft interior component according to claim 1, characterized in that: The multi-dimensional heat monitoring and surface material analysis system includes: Multi-dimensional heat monitoring: Use a thermal infrared imaging system and surface temperature sensors to obtain the full-surface temperature distribution image of the parts; Thermal deformation and stress monitoring: Use a fiber optic sensor network to monitor the thermal deformation and stress distribution on the surface and inside of the parts in real time; Automated visual analysis: Combine high-resolution microscope imaging and computer vision technology to automatically detect thermal aging phenomena such as microcracks, color changes, and bubbles on the surface of the parts caused by radiation high temperature. The system can automatically identify and quantify the degree of thermal damage under various radiation conditions and generate a thermal damage distribution map; Artificial intelligence data analysis: The system combines artificial intelligence algorithms to automatically process the real-time obtained heat response data and surface damage data, and analyze the thermal aging trend and potential failure risks of the material.

4. A method for measuring the radiant high temperature of an aircraft interior component according to claim 3, characterized in that: The resolution of the thermal infrared imaging system is ≤0.1 mm, and the time resolution is ≤0.1 second.

5. A method for measuring the radiant high temperature of an aircraft interior component according to claim 4, characterized in that: The surface temperature sensors include thermocouples and resistance temperature sensors, and the fiber optic sensors are arranged on the surface and inside of the parts.

6. A method for measuring the radiant high temperature of an aircraft interior component according to claim 1, characterized in that: The steps for the heat response analysis report to include an assessment of material thermal degradation include the following sub-steps: S5.1 Use a thermal degradation model to analyze the material degradation rate of the parts under different radiation intensities. The thermal degradation model is based on the thermal activation process and the physical and chemical change laws of the material, and combines thermodynamic principles to quantitatively evaluate the degradation mechanism of the material in different high-temperature environments; S5.2 Analyze the thermal degradation characteristics of different materials by integrating thermomechanical analysis, differential scanning calorimetry, and thermogravimetric analysis experimental data. S5.3 Analyze the thermal expansion behavior, thermal stress, and physical changes of the material under the action of a radiation heat source by combining the real-time data of the temperature sensor, strain sensor, and heat flux sensor; S5.4 Automatically generate a material degradation report based on the results of the thermal degradation analysis. The report includes the thermal aging rate of the material, thermal expansion changes, surface crack propagation, and its impact on structural integrity, and gives the possible failure modes of the material in a long-term high-temperature environment.

7. A method for measuring the radiant high temperature of an aircraft interior component according to claim 6, characterized in that: The trend analysis of the thermal aging describes the thermal degradation rate of the material under the action of different radiation heat sources through a mathematical model, and the model of the thermal aging is based on an equation to describe the degradation process of the material: ； Among them, is the degradation rate constant of the material, is the frequency factor, is the activation energy, is the gas constant, is the test temperature.

8. A method for measuring the radiant high temperature of an aircraft interior component according to claim 7, characterized in that: The surface crack propagation uses a fracture mechanics model to predict crack propagation: ； Among them, is the crack growth rate, is the material constant, is the stress intensity factor range, is the material index.

Images