A radiation high temperature determination method for aircraft interior parts

Abstract

The present invention provides a method for radiative pyrometry of aircraft interior components, relating to the technical field of aircraft interior component testing. The method includes establishing a radiative heat source system comprising multiple radiative heat source devices with adjustable wavelength and radiation intensity. These radiative heat source devices simulate the radiative heat environment of an aircraft during different flight phases, and automatically adjust the wavelength and radiation intensity of the radiation sources to simulate the actual radiative heat source environment during flight. This method integrates multi-dimensional thermal monitoring, thermal deformation and stress monitoring, automated visual analysis, and artificial intelligence data analysis to accurately capture the thermal response, stress changes, and surface damage of components in radiative high-temperature environments.

Description

Technical Field

[0001] The present invention relates to the technical field of aircraft interior component testing, and in particular to a radiation high temperature measurement method for aircraft interior component. Background Art

[0002] With the continuous improvement of aircraft design and flight requirements, the performance requirements for aircraft interior components are becoming more and more stringent. In order to ensure the safety and comfort of passengers, the materials and components inside the aircraft need to withstand a variety of extreme environmental conditions including high temperature radiation and mechanical pressure during flight. Especially in high temperature environments, aircraft interior components are easily affected by high temperature radiation, causing 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. At present, the thermal stability evaluation of aircraft interior components mainly relies on laboratory testing. During the test process, high temperature environments are usually simulated through heating furnaces, thermal radiation sources and other equipment. Existing high temperature testing methods mostly use hot air heating, infrared radiation heating and other methods.

[0003] However, these methods have limitations. Existing testing methods lack the precision to simulate radiant heat sources, making it difficult to replicate the actual radiant heat environment encountered during flight. Traditional high-temperature testing methods typically focus solely on temperature measurement, ignoring the long-term effects of thermal radiation on component surface materials, making it impossible to fully assess the material's thermal stability and high-temperature resistance.

[0004] Therefore, a more accurate and comprehensive radiation high-temperature testing method for aircraft interior components is urgently needed to better evaluate the long-term performance of materials in high-temperature radiation environments and ensure the safety and reliability of aircraft. Summary of the Invention

[0005] In response to the shortcomings of the existing technology, the present invention provides a method for radiant high temperature measurement of aircraft interior components. The technical problem to be solved by this invention is: how to achieve accurate 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 implemented through the following technical solutions: A method for measuring the high temperature of aircraft interior components by radiation, comprising:

[0007] S1. Setting up a radiant heat source system, wherein the radiant heat source system includes multiple radiant heat source devices with adjustable wavelength and radiation intensity. The radiant heat source devices simulate the radiant heat environment of an aircraft at different flight stages and automatically adjust the wavelength and radiation intensity of the radiation source to simulate the actual radiant heat source environment during flight;

[0008] S2. Place the aircraft interior component to be tested on the test platform in front of the radiant heat source, ensuring that the distance between the component surface and the radiant heat source is set to 1 to 20 cm, simulating the actual environment in which the component is directly exposed to the radiant heat source during flight;

[0009] S3. Use an integrated multi-dimensional thermal monitoring and surface material analysis system to monitor the thermal response and surface changes of the components under test in real time;

[0010] S4. Based on the real-time monitoring data, using a deep learning analysis model, evaluate the thermal stability, high-temperature resistance, thermal deformation, and crack growth of components under different high-temperature radiation environments, and generate a detailed thermal response analysis report, including an assessment of material thermal degradation;

[0011] S5. Generate a complete test report that includes the component's thermal aging trends, material property changes, crack development, deformation characteristics, and overall reliability assessment. Combined with actual thermal radiation conditions during flight, the report provides data support for design optimization and improvement of interior components.

[0012] Preferably, the radiation heat source device includes a plurality of infrared radiation modules and ultraviolet radiation modules, the wavelength range of the infrared radiation module is 1-15 μm, and the wavelength range of the ultraviolet radiation module is 200-400 nm.

[0013] Preferably, the multi-dimensional thermal monitoring and surface material analysis system includes:

[0014] Multi-dimensional thermal monitoring: Use thermal infrared imaging systems and surface temperature sensors to obtain full-surface temperature distribution images of components;

[0015] Thermal deformation and stress monitoring: Use fiber optic sensor networks to monitor the thermal deformation and stress distribution on the surface and inside of components in real time;

[0016] Automated visual analysis: Combining high-resolution microscopy imaging with computer vision technology, this system automatically detects thermal aging phenomena such as microcracks, discoloration, and bubbles on component surfaces caused by high radiation temperatures. The system can automatically identify and quantify the degree of thermal damage under various radiation conditions, generating a thermal damage distribution map.

[0017] Artificial Intelligence Data Analysis: The system combines artificial intelligence algorithms to automatically process real-time acquired thermal response data and surface damage data to analyze the material's thermal aging trends and potential failure risks.

[0018] Preferably, the thermal infrared imaging system has a resolution of ≤0.1 mm and a time resolution of ≤0.1 second, and can accurately capture the transient thermal response of components under different radiation intensities.

[0019] Preferably, the surface temperature sensor includes a thermocouple and a thermal resistance sensor, which is used to detect the temperature change and thermal diffusion characteristics inside the component, and the optical fiber sensor is arranged on the surface and inside the component.

[0020] Preferably, the thermal response analysis report includes a step of evaluating the thermal degradation of the material, including the following sub-steps:

[0021] S5.1 Use a 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 changes of the material, combined with the principles of thermodynamics, to quantitatively evaluate the degradation mechanism of the material under different high temperature environments;

[0022] S5.2 Analyze the thermal degradation characteristics of different materials by integrating experimental data from thermomechanical analysis, differential scanning calorimetry, and thermogravimetric analysis;

[0023] S5.3 Combine real-time data from temperature sensors, strain sensors, and heat flow sensors to analyze the thermal expansion behavior, thermal stress, and physical changes of materials under the action of radiant heat sources;

[0024] S5.4 automatically generates a material degradation report based on the thermal degradation analysis results. The report includes the material's thermal aging rate, thermal expansion changes, surface crack growth and its impact on structural integrity, and gives the possible failure modes of the material in a long-term high-temperature environment.

[0025] Preferably, the thermal aging trend analysis describes the thermal degradation rate of the material under different radiation heat sources through a mathematical model, and the thermal aging model describes the degradation process of the material based on the equation:

[0026] ;

[0027] in, is the material degradation rate constant, is the frequency factor, is the activation energy, is the gas constant, is the test temperature.

[0028] Preferably, the surface crack propagation is predicted using a fracture mechanics model:

[0029] ;

[0030] in, is the crack growth rate, is the material constant, is the stress intensity factor range, is the material index.

[0031] The present invention provides a method for radiant high temperature determination of aircraft interior components. It has the following beneficial effects:

[0032] This radiation-induced high-temperature determination method for aircraft interior components integrates multi-dimensional thermal monitoring, thermal deformation and stress monitoring, automated visual analysis, and artificial intelligence data analysis to accurately capture the thermal response, stress changes, and surface damage of components exposed to radiant high-temperature environments. This data comprehensively reflects the thermal stability, crack growth, and thermal aging trends of materials during different flight phases, providing a scientific basis for component design optimization. In particular, the use of a high-resolution infrared imaging system and high-precision sensor network enables more precise real-time monitoring of temperature, stress, and deformation, providing higher data accuracy and reliability for long-term reliability and safety.

[0033] By combining thermal degradation models, crack growth prediction models, and artificial intelligence algorithms, a multi-dimensional analysis of materials is achieved. The application of deep learning technology enables the system to automatically analyze and process data from various sensors, identifying thermal aging trends, crack growth, and potential failure risks. BRIEF DESCRIPTION OF THE DRAWINGS

[0034] Figure 1 The present invention is a flowchart for implementing the present invention. DETAILED DESCRIPTION

[0035] The following will clearly and completely describe the technical solutions in the embodiments of the present invention in conjunction with the accompanying drawings. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without making creative efforts are within the scope of protection of the present invention.

[0036] Example 1, as Figure 1As shown, an embodiment of the present invention provides a method for radiant high temperature measurement of aircraft interior components, comprising: S1. Setting a radiant heat source system. The radiant heat source system includes multiple radiant heat source devices with adjustable wavelength and radiation intensity. The radiant heat source devices simulate the radiant heat environment of an aircraft during different flight phases and automatically adjust the wavelength and radiation intensity of the radiation sources to simulate the actual radiant heat source environment during flight. The radiant heat source devices include multiple infrared radiation modules and ultraviolet radiation modules. The infrared radiation modules have a wavelength range of 1-15μm, and the ultraviolet radiation modules have a wavelength range of 200-400nm. These modules can simulate the various radiation environments encountered by an aircraft during different flight phases. When simulating the aircraft's cruising phase, the radiation intensity can be set to 800 W / m² to reproduce the radiant heat environment generated by the difference between solar radiation and atmospheric temperature during high-altitude flight. During the landing phase, a higher radiation intensity, such as 1200 W / m², is set to simulate the higher temperature environment during descent. During the aircraft's cruising phase, the ultraviolet radiation intensity can be adjusted to 0.15 W / m², which 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 radiation intensity through the control system during the test to adapt to the actual needs of different flight phases.

[0037] S2. Place the aircraft interior component to be tested on a test platform in front of the radiant heat source. During simulated flight, the test platform's support frame adjusts the distance between the component and the radiation source according to the flight phase. During the cruise phase, the distance between the component and the radiation source is maintained at 10 cm. During takeoff and landing, the support frame automatically adjusts to 5 cm to simulate the stronger radiation environment at the beginning of flight and during landing.

[0038] S3. An integrated multi-dimensional thermal monitoring and surface material analysis system is used to monitor the thermal response and surface changes of the components under test in real time. The multi-dimensional thermal monitoring and surface material analysis system includes:

[0039] Multi-dimensional thermal monitoring: Use thermal infrared imaging systems and surface temperature sensors to obtain full-surface temperature distribution images of components.

[0040] Thermal deformation and stress monitoring: A fiber optic sensor network is used to monitor the thermal deformation and stress distribution on the surface and inside of components in real time.

[0041] Automated visual analysis: Combining high-resolution microscopy imaging with computer vision technology, this system automatically detects thermal aging phenomena such as microcracks, discoloration, and bubbles on component surfaces caused by high radiation temperatures. The system can automatically identify and quantify the degree of thermal damage under various radiation conditions and generate a thermal damage distribution map.

[0042] Artificial Intelligence Data Analysis: The system combines artificial intelligence algorithms to automatically process real-time acquired thermal response data and surface damage data to analyze the material's thermal aging trends and potential failure risks.

[0043] The thermal infrared imaging system has a resolution of ≤0.1mm and a temporal resolution of ≤0.1 second, enabling it to accurately capture the transient thermal response of components under varying radiation intensities. Surface temperature sensors, including thermocouples and thermistor sensors, are used to detect internal temperature changes and thermal diffusion characteristics of components. Fiber optic sensors, deployed on and within the components, can accurately detect stress changes, minor deformations, and crack development caused by thermal radiation. Under simulated high-temperature conditions, the fiber optic sensors can monitor the thermal expansion rate and surface stress distribution of components in real time. Test data showed that at 100°C, the surface stress of the component changed by 0.05 MPa, while at 200°C, the stress changed by 0.2 MPa, indicating a potential risk of thermal cracking. During testing, the computer vision system automatically identified a surface crack of 0.1 mm in length and marked it as minor thermal damage. Further analysis revealed that the discoloration area of ​​the component reached 2%, demonstrating the degree of thermal aging of the material in the high-temperature environment.

[0044] S4. Based on real-time monitoring data, a deep learning analysis model is used to evaluate the thermal stability, high temperature resistance, thermal deformation, and crack propagation of components in different high-temperature radiation environments. A detailed thermal response analysis report is generated, which includes an assessment of material thermal degradation.

[0045] S5. Generate a complete test report that includes component thermal aging trends, material property changes, crack development, deformation characteristics, and overall reliability assessment. Combined with actual thermal radiation conditions during flight, this report provides data support for design optimization and improvement of interior components. Thermal aging trend analysis uses mathematical models to describe the thermal degradation rate of materials under different radiant heat sources. The thermal aging model describes the material degradation process based on the following equation:

[0046] ;

[0047] in, is the material degradation rate constant, is the frequency factor, is the activation energy, is the gas constant, The test temperature is the temperature at which the component is tested. Based on this model, combined with the radiant heat and temperature changes under different flight conditions, the thermal aging trend of the component is evaluated, and a basis for material selection and design optimization is provided. The surface crack propagation is predicted using the fracture mechanics model:

[0048] ;

[0049] in, is the crack growth rate, is the material constant, is the stress intensity factor range, It is a material index that, combined with test data, evaluates the crack growth trend and its impact on the structural reliability of components. The report will provide the crack growth rate and, combined with the thermal stress changes during flight, predict the failure mode that may result from long-term use. The thermal response analysis report includes the steps for evaluating material thermal degradation, including the following sub-steps:

[0050] S5.1 uses a thermal degradation model to analyze the material degradation rate of components under different radiation intensities. Based on the thermal activation process and the physical and chemical changes of the material, combined with thermodynamic principles, the thermal degradation model quantitatively evaluates the degradation mechanism of materials under different high-temperature environments. The model considers factors such as structural changes, molecular chain breakage, and chemical reaction rates caused by thermal aging, and can accurately predict the thermal degradation process of materials under high-temperature radiation environments.

[0051] S5.2 Analyzes the thermal degradation characteristics of different materials by integrating thermomechanical analysis, differential scanning calorimetry, and thermogravimetric analysis experimental data.

[0052] S5.3 combines real-time data from temperature sensors, strain sensors, and heat flow sensors to analyze the thermal expansion behavior, thermal stress, and physical changes of materials under the action of radiant heat sources.

[0053] S5.4 automatically generates a material degradation report based on the thermal degradation analysis results. The report includes the material's thermal aging rate, thermal expansion changes, surface crack growth and its impact on structural integrity, and gives the possible failure modes of the material in a long-term high-temperature environment.

[0054] The second embodiment is different from the first embodiment in that the specific implementation is as follows:

[0055] 1. Thermal aging trend analysis and model application

[0056] During the test, a thermal degradation model is used to analyze the material degradation rate of components under different radiant heat sources. The prediction of thermal aging trends is based on the following mathematical model:

[0057] ;

[0058] in: is the material degradation rate constant, is the frequency factor, is the activation energy, is the gas constant , is the test temperature in Kelvin.

[0059] Implementation data: For example, assuming the activation energy of the material is , the frequency factor is ,exist Thermal aging experiments were conducted under the following conditions. By using this formula, the degradation rate of the material can be calculated as , and combined with different radiant heat source intensities (such as and ) to evaluate its thermal aging trend.

[0060] 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.

[0061] 2. Surface crack growth prediction and fracture mechanics model

[0062] The analysis of surface crack growth uses a fracture mechanics model to predict the crack growth rate:

[0063] ;

[0064] in: is the crack growth rate, is the material constant, is the stress intensity factor range, is the material index.

[0065] Implementation data: For example, assuming material constants for , stress intensity factor range for , Material Index for Under this condition, the crack growth 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 expansion trend and its impact on the structural reliability of components.

[0066] 3. Thermal degradation analysis and experimental data integration

[0067] In thermal degradation analysis, a variety of experimental methods (thermomechanical analysis, differential scanning calorimetry, and thermogravimetric analysis) are combined to comprehensively evaluate the thermal degradation characteristics of different materials.

[0068] Implementation data:

[0069] Thermomechanical analysis: Evaluates the thermal expansion characteristics of a material by measuring its dimensional changes at different temperatures. Assuming the thermal expansion coefficient of the test material is ,exist The length change of the material is 0.03mm.

[0070] Differential Scanning Calorimetry: Used to evaluate the glass transition temperature and melting point of a material. Assuming the Tg of the material is , under different radiation intensities, its melting point varies from Change to .

[0071] Thermogravimetric analysis: measures the change in mass of a material when it is heated. For example, test results show that the material Time Lost The quality of Time Lost The quality of the material indicates its durability and thermal stability in high temperature environments.

[0072] Combined with these experimental data, the system can comprehensively evaluate the thermal degradation characteristics of different materials, thereby providing data support for material selection and long-term use evaluation.

[0073] Example 3. This example is based on the specific implementation method of step S4 and 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 based on real-time monitoring data, and generate a detailed thermal response analysis report, including an assessment of material thermal degradation.

[0074] Step 1: Real-time monitoring data collection

[0075] Installation and deployment of multi-dimensional monitoring system:

[0076] Temperature sensors, strain sensors, and heat flow sensors are installed on the surface of components and at key locations. Temperature sensors, including thermocouples and RTDs, monitor surface and internal temperature changes of components. Strain sensors monitor deformation and stress changes of components under the influence of radiant heat sources, while heat flow sensors monitor the heat transfer characteristics of materials in real time.

[0077] The infrared imaging system is used to capture thermal images of components in real time, generate temperature distribution maps, and monitor the thermal response characteristics of components in real time.

[0078] Real-time data collection:

[0079] Assume that during the experiment, the surface temperature of a component gradually increases from 50°C to 200°C, while the internal temperature increases from 30°C to 180°C. Simultaneously, a strain sensor monitors the slight deformation of the material surface. At 150°C, the surface strain is 0.05%, increasing to 0.15% at 200°C.

[0080] Step 2: Deep Learning Analysis Model

[0081] Data preprocessing and model training:

[0082] Multidimensional data acquired from various sensors is collected and organized, and data preprocessing, such as denoising and normalization, is performed to ensure data quality. This data is then fed into a deep learning model for training. The deep learning algorithms used are convolutional neural networks and long short-term memory networks. CNNs are used to process image data, while LSTMs are used to process time series data.

[0083] Training Data: The model's training dataset includes historical experimental data, simulated flight data, and actual component test data. Assume that components made of different materials are tested at 800W / m² and 1200W / m² over multiple test cycles, covering the temperature variations of various flight environments.

[0084] Model analysis:

[0085] The deep learning model automatically assesses a component's thermal stability, high-temperature resistance, thermal deformation, and crack growth trends by studying its thermal response patterns under varying heat radiation conditions. Combining thermodynamic principles, materials theory, and experimental data, the model can predict material aging rates, thermal stress concentrations, and crack growth under varying flight conditions.

[0086] For example, through model analysis, it was found that the material Under the heat radiation environment of 1 hour, the thermal aging rate is , under higher radiation intensity conditions, the crack growth rate is , showing the fatigue life and failure risk of materials in extreme thermal environments.

[0087] Step 3: Generate Thermal Response Analysis Report

[0088] 1. Report generation and content:

[0089] Based on the results of deep learning analysis, the system automatically generates a thermal response analysis report, which lists in detail important information such as the thermal aging trend, high temperature resistance, thermal deformation, crack propagation and structural reliability assessment of components.

[0090] Thermal aging assessment: The report calculates the thermal degradation rate of components under different radiation intensities based on equations, and combines the impact of high temperature environment on materials to predict the degradation trend in long-term use. Assuming that the degradation rate of the material under high temperature conditions is , the surface hardness and tensile strength of the parts will gradually decrease over time, and it is expected to lose strength.

[0091] Crack Growth Assessment: Using fracture mechanics models, the report predicts the crack growth rate and failure mode of components during long-term use. Simulation data shows that during the cruise phase, the crack growth rate is , while at higher temperatures, the crack growth rate will accelerate, increasing the risk of failure.

[0092] Thermal stress and deformation: Combined with real-time monitoring of strain data, the report analyzes the thermal stress distribution and deformation of components under different radiant heat sources. The report points out that the material The stress is 0.05MPa, while When the thermal stress increases to 0.2MPa, it indicates that the material may experience stress concentration and cause the formation of microcracks under high temperature conditions.

[0093] While embodiments of the present invention have been shown and described, it will be appreciated by those skilled in the art that various changes, modifications, substitutions, and variations may be made to these embodiments without departing from the principles and spirit of the invention, and that the scope of the invention is defined by the appended claims and their equivalents.

Claims

1. A method for radiant high temperature determination of aircraft interior components, characterized in that: include: S1. Setting up a radiant heat source system, wherein the radiant heat source system includes multiple radiant heat source devices with adjustable wavelength and radiation intensity. The radiant heat source devices simulate the radiant heat environment of an aircraft at different flight stages and automatically adjust the wavelength and radiation intensity of the radiation source to simulate the actual radiant heat source environment during flight; S2. Place the aircraft interior component to be tested on the test platform in front of the radiant heat source, ensuring that the distance between the component surface and the radiant heat source is set to 1 to 20 cm, simulating the actual environment in which the component is directly exposed to the radiant 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 components under test in real time; S4. Based on the real-time monitoring data, using a deep learning analysis model, evaluate the thermal stability, high-temperature resistance, thermal deformation, and crack growth of components under different high-temperature radiation environments, and generate a detailed thermal response analysis report, including an assessment of material thermal degradation; S5. Generate a complete test report that includes the component's thermal aging trends, material property changes, crack development, deformation characteristics, and overall reliability assessment. Combined with actual thermal radiation conditions during flight, the report provides data support for design optimization and improvement of interior components.

2. The method for radiant high temperature determination of aircraft interior components according to claim 1, characterized in that: The radiation heat source device includes a plurality of infrared radiation modules and ultraviolet radiation modules. The wavelength range of the infrared radiation module is 1-15 μm, and the wavelength range of the ultraviolet radiation module is 200-400 nm.

3. The method for radiant high temperature determination of aircraft interior components according to claim 1, characterized in that: The multi-dimensional thermal monitoring and surface material analysis system includes: Multi-dimensional thermal monitoring: Use thermal infrared imaging systems and surface temperature sensors to obtain full-surface temperature distribution images of components; Thermal deformation and stress monitoring: Use fiber optic sensor networks to monitor the thermal deformation and stress distribution on the surface and inside of components in real time; Automated visual analysis: Combining high-resolution microscopy imaging with computer vision technology, this system automatically detects thermal aging phenomena such as microcracks, discoloration, and bubbles on component surfaces caused by high radiation temperatures. The system can automatically identify and quantify the degree of thermal damage under various radiation conditions, generating a thermal damage distribution map. Artificial Intelligence Data Analysis: The system combines artificial intelligence algorithms to automatically process real-time acquired thermal response data and surface damage data to analyze the material's thermal aging trends and potential failure risks.

4. The method for radiant high temperature determination of aircraft interior components according to claim 3, characterized in that: The thermal infrared imaging system has a resolution of ≤0.1 mm and a time resolution of ≤0.1 second.

5. The method for radiant high temperature determination of aircraft interior components according to claim 4, characterized in that: The surface temperature sensor includes a thermocouple and a thermal resistance sensor, and the optical fiber sensor is arranged on the surface and inside of the component.

6. The method for radiant high temperature determination of aircraft interior components according to claim 1, characterized in that: The thermal response analysis report includes the steps of evaluating the thermal degradation of the material, including the following sub-steps: S5.1 Use a 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 changes of the material, combined with the principles of thermodynamics, to quantitatively evaluate the degradation mechanism of the material under 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 Combine real-time data from temperature sensors, strain sensors, and heat flow sensors to analyze the thermal expansion behavior, thermal stress, and physical changes of materials under the action of radiant heat sources; S5.4 automatically generates a material degradation report based on the thermal degradation analysis results. The report includes the material's thermal aging rate, thermal expansion changes, surface crack growth and its impact on structural integrity, and gives the possible failure modes of the material in a long-term high-temperature environment.

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

8. The method for radiant high temperature determination of aircraft interior components according to claim 7, characterized in that: The surface crack propagation is predicted using a fracture mechanics model: ； in, is the crack growth rate, is the material constant, is the stress intensity factor range, is the material index.

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