Aircraft windshield glass service reliability test method, system and medium

Abstract

The embodiment of the invention provides an airplane windshield glass service reliability test method and system and a medium, and the method comprises the steps: carrying out the coupling simulation of a test environment based on a plurality of environmental factors, and building a plurality of environmental factor cooperative control test modes; performing an impact test on the aircraft windshield based on the collaborative test mode to generate damage monitoring data; analyzing the damage monitoring data based on the damage mechanical model, and generating damage acceleration state data; inputting the damage monitoring data and the damage acceleration state data into a life prediction model, and outputting residual life prediction data; analyzing the damage acceleration state data and the residual life prediction data based on the reliability standard information to obtain a reliability test result, and transmitting the reliability test result to the terminal in real time; the mode testing environment is carried out through multiple environmental factors, so that impact testing of different environments is carried out on the aircraft windshield glass, the testing diversity is improved, damage monitoring is carried out on the glass, and the reliability testing precision of the glass is improved.

Description

Technical Field

[0001] The present application relates to the field of glass testing technology, and in particular to a method, system, and medium for testing the service reliability of aircraft windshields. Background Art

[0002] Aircraft windshields are subjected to a variety of external loads during flight, including aerodynamic pressure, temperature fluctuations, and mechanical stress. Performance evaluation and lifespan monitoring of windshields are crucial to ensure flight safety and passenger comfort. Existing technologies primarily rely on visual inspections and periodic maintenance, lacking methods for real-time monitoring and condition assessment.

[0003] Patent 202411869744.7 proposes an experimental device and experimental method for verifying the instantaneous breakage safety of windshields, which mainly targets instantaneous impacts of foreign objects. Instead of considering the damage accumulation behavior of the aircraft in the process of responding to pressurization and release cycles during the flight cycle. It also does not consider the accumulation of scratch damage caused by weak wind and sand cavitation on the surface, which leads to windshield rupture. Patent 202320195663.8 also proposes a breakage safety experimental device, both of which evaluate the breakage safety margin of the windshield through external impact loads. This method examines whether the aircraft windshield has structural failure caused by the external load acting on the outer anti-collision layer glass and the middle layer structural layer glass. The relevant patent is an initial airworthiness test conducted for external damage, which evaluates the static strength margin of the aircraft windshield.

[0004] With the continuous emergence of new aircraft, windshields are becoming larger and larger, and the internal residual stresses caused by the curved structural design are becoming increasingly complex. Due to the process of increasing the inner side of the cockpit, the windshield may bulge outward. The local support structure is affected by the pressure difference between the inside and outside of the large windshield, resulting in an increase in the local load at the windshield restraint position. This situation can cause the inner structural layer to crack, which is more harmful. In addition, after installation, the aircraft windshield is subjected to continuous sand and dust attacks. Micro-area scratches will not cause the windshield to break instantly. However, after long-term service, these micro-damages accumulate and experience the pressure difference cycle inside and outside the aircraft, which may cause the glass to break in subsequent service.

[0005] In addition, since the aircraft windshield is large and has a curved distribution feature, the damage behavior caused by the tension of the fasteners under the action of internal pressure difference cannot be underestimated.

[0006] The existing technology has the following defects:

[0007] The environmental simulation is insufficient and difficult to reflect the actual service conditions.

[0008] Traditional test chambers can only simulate a single environmental factor (such as temperature or humidity), lack the comprehensive testing capabilities of multi-physical field coupling (pressure, temperature, ultraviolet light, mechanical load, etc.), and cannot accurately reproduce the complex working conditions of high-altitude and high-speed flight.

[0009] Pressure cycle testing usually uses simple sinusoidal loading, which fails to match the actual flight envelope (such as dynamic pressure changes during takeoff-cruise-landing phases), resulting in deviations in fatigue life assessment.

[0010] Damage monitoring methods are limited and data reliability is low.

[0011] Relying on manual visual inspection or point strain gauges cannot achieve full-surface, high-precision real-time monitoring (such as micron-level crack initiation process).

[0012] Acoustic emission (AE) sensors are sparsely arranged and have large positioning errors (>10 mm), making it difficult to correlate damage locations with stress field distribution.

[0013] The fatigue test acceleration method is single and cannot reflect the real aging law.

[0014] Traditional accelerated tests only shorten the test period by increasing the number of cycles (such as high-frequency fatigue tests), but ignore the differentiated impact of pressure amplitude changes on material damage mechanisms, resulting in significant deviations between test results and actual service behavior. Summary of the Invention

[0015] The purpose of the embodiments of the present application is to provide a method, system and medium for testing the service reliability of aircraft windshields, which uses multiple environmental factors to perform a model test environment, thereby performing impact tests on aircraft windshields in different environments, improving the diversity of the tests, and monitoring the damage of the glass to improve the accuracy of glass reliability testing.

[0016] The present application also provides a method for testing the service reliability of an aircraft windshield, including:

[0017] Based on multiple environmental factors, a coupled simulation test environment is established, and a test mode with collaborative control of multiple environmental factors is established;

[0018] Conduct impact tests on aircraft windshields based on collaborative testing mode to generate damage monitoring data;

[0019] Analyze damage monitoring data based on damage mechanics models to generate damage acceleration state data of aircraft windshields;

[0020] Construct a life prediction model, input damage monitoring data and damage acceleration state data into the life prediction model, and output remaining life prediction data;

[0021] Based on the reliability standard information, the damage acceleration state data and the remaining life prediction data are analyzed to obtain the reliability test results of the aircraft windshield, and the reliability test results are transmitted to the terminal in real time.

[0022] Optionally, in the aircraft windshield service reliability testing method described in the embodiment of the present application, a test environment is simulated based on coupling of multiple environmental factors, and a test mode for collaborative control of multiple environmental factors is established, specifically including:

[0023] Acquiring multiple environmental factors, wherein the multiple environmental factors include temperature factors, pressure factors, and humidity factors;

[0024] Based on the test focus, the temperature factor, pressure factor and humidity factor are matched with weights to obtain the corresponding weight coefficients;

[0025] Generate a number of pairing combinations based on the weight coefficients, and generate a number of simulation test environments based on the number of pairing combinations;

[0026] Based on the simulation test environment, the synergy ratios between different environmental factors are analyzed to obtain multiple synergy patterns;

[0027] Multiple collaborative test modes of the aircraft windshield are generated based on the multiple collaborative modes.

[0028] Optionally, in the aircraft windshield service reliability testing method described in the embodiment of the present application, performing an impact test on the aircraft windshield based on the collaborative testing mode to generate damage monitoring data specifically includes:

[0029] Obtain paired combinations based on collaborative test patterns and generate corresponding temperature, pressure, and humidity data;

[0030] Generate a test environment based on temperature, pressure, and humidity data, perform an impact test on the aircraft windshield based on the test environment, and obtain a stress curve of the aircraft windshield;

[0031] Analyze the stress data of aircraft windshield at different time points based on the stress curve of aircraft windshield;

[0032] Compare the aircraft windshield stress data with the set glass standard data to generate damage difference values;

[0033] The damage status information of the aircraft windshield is analyzed based on the damage difference value to obtain damage monitoring data.

[0034] Optionally, in the aircraft windshield service reliability testing method described in the embodiment of the present application, analyzing damage monitoring data based on a damage mechanics model to generate damage acceleration state data of the aircraft windshield specifically includes:

[0035] Establish a data set based on historical damage data, iteratively train the initial model based on the data set, and obtain training results;

[0036] Determine whether the training results converge;

[0037] If converged, a damage mechanics model is generated, and stress data at different positions of the glass are analyzed based on the damage mechanics model. Damage monitoring data is obtained based on the stress data at different positions.

[0038] Analyze the damage status information at different time nodes based on damage monitoring data, and analyze the damage acceleration status data of the aircraft windshield based on the damage status information at different time nodes;

[0039] If it does not converge, adjust the model parameters.

[0040] Optionally, in the aircraft windshield service reliability testing method described in the embodiment of the present application, a life prediction model is constructed, damage monitoring data and damage acceleration state data are input into the life prediction model, and remaining life prediction data is output, specifically including:

[0041] Obtain historical prediction data based on big data, and build a lifespan prediction model based on the historical prediction data;

[0042] Analyze the damage stress data and damage acceleration state data of aircraft windshields based on the life prediction model;

[0043] Analyze the aging status of aircraft windshields based on damage acceleration data;

[0044] Based on the aging status information of the aircraft windshield, the remaining life of the glass is analyzed to obtain the remaining life prediction data.

[0045] Optionally, in the aircraft windshield service reliability testing method described in the embodiment of the present application, analyzing the damage acceleration state data and the remaining service life prediction data based on the reliability standard information to obtain the aircraft windshield reliability test results specifically includes:

[0046] Obtain damage acceleration status data and remaining life prediction data of aircraft windshields under different collaborative test modes;

[0047] Clean the damage acceleration status data and remaining life prediction data to remove outliers, erroneous data and duplicate data;

[0048] Analyze the damage acceleration state data to analyze the damage types of the aircraft windshield, including crack propagation, surface wear and delamination;

[0049] Analyze damage changes over time or in collaborative test modes based on statistical methods;

[0050] The remaining life prediction data is analyzed based on the damage change state information to obtain the reliability test results of the aircraft windshield.

[0051] In a second aspect, an embodiment of the present application provides an aircraft windshield service reliability testing system, comprising: a memory and a processor, wherein the memory includes a program for a method for testing the service reliability of an aircraft windshield, and when the program is executed by the processor, the following steps are implemented:

[0052] Based on multiple environmental factors, a coupled simulation test environment is established, and a test mode with collaborative control of multiple environmental factors is established;

[0053] Conduct impact tests on aircraft windshields based on collaborative testing mode to generate damage monitoring data;

[0054] Analyze damage monitoring data based on damage mechanics models to generate damage acceleration state data of aircraft windshields;

[0055] Construct a life prediction model, input damage monitoring data and damage acceleration state data into the life prediction model, and output remaining life prediction data;

[0056] Based on the reliability standard information, the damage acceleration state data and the remaining life prediction data are analyzed to obtain the reliability test results of the aircraft windshield, and the reliability test results are transmitted to the terminal in real time.

[0057] Optionally, in the aircraft windshield service reliability testing system described in the embodiment of the present application, a test environment is simulated based on coupling of multiple environmental factors, and a test mode for collaborative control of multiple environmental factors is established, specifically including:

[0058] Acquiring multiple environmental factors, wherein the multiple environmental factors include temperature factors, pressure factors, and humidity factors;

[0059] Based on the test focus, the temperature factor, pressure factor and humidity factor are matched with weights to obtain the corresponding weight coefficients;

[0060] Generate a number of pairing combinations based on the weight coefficients, and generate a number of simulation test environments based on the number of pairing combinations;

[0061] Based on the simulation test environment, the synergy ratios between different environmental factors are analyzed to obtain multiple synergy patterns;

[0062] Generate multiple test patterns of aircraft windshields based on multiple collaborative patterns.

[0063] Optionally, in the aircraft windshield service reliability testing system described in the embodiment of the present application, performing an impact test on the aircraft windshield based on the collaborative testing mode to generate damage monitoring data specifically includes:

[0064] Obtain paired combinations based on collaborative test patterns and generate corresponding temperature, pressure, and humidity data;

[0065] Generate a test environment based on temperature, pressure, and humidity data, perform an impact test on the aircraft windshield based on the test environment, and obtain a stress curve of the aircraft windshield;

[0066] Analyze the stress data of aircraft windshield at different time points based on the stress curve of aircraft windshield;

[0067] Compare the aircraft windshield stress data with the set glass standard data to generate damage difference values;

[0068] The damage status information of the aircraft windshield is analyzed based on the damage difference value to obtain damage monitoring data.

[0069] In a third aspect, an embodiment of the present application further provides a computer-readable storage medium, wherein the computer-readable storage medium includes an aircraft windshield service reliability test method program. When the aircraft windshield service reliability test method program is executed by a processor, the steps of the aircraft windshield service reliability test method as described in any one of the above items are implemented.

[0070] As can be seen from the above, the embodiments of the present application provide a method, system and medium for testing the service reliability of an aircraft windshield, which couples a simulated test environment based on multiple environmental factors and establishes a test mode for collaborative control of multiple environmental factors; performs impact testing on the aircraft windshield based on the collaborative test mode to generate damage monitoring data; analyzes the damage monitoring data based on a damage mechanics model to generate damage acceleration state data of the aircraft windshield; constructs a life prediction model, inputs the damage monitoring data and the damage acceleration state data into the life prediction model, and outputs remaining life prediction data; analyzes the damage acceleration state data and the remaining life prediction data based on reliability standard information to obtain reliability test results of the aircraft windshield, and transmits the reliability test results to the terminal in real time; performs a model test environment through multiple environmental factors, thereby performing impact tests on the aircraft windshield in different environments, improving the diversity of the test, and monitoring the damage of the glass to improve the accuracy of the glass reliability test. BRIEF DESCRIPTION OF THE DRAWINGS

[0071] In order to more clearly illustrate the technical solutions of the embodiments of the present application, the following is a brief introduction to the drawings required for use in the embodiments of the present application. It should be understood that the following drawings only show certain embodiments of the present application and therefore should not be regarded as limiting the scope. For ordinary technicians in this field, other relevant drawings can be obtained based on these drawings without creative work.

[0072] Figure 1 A flow chart of a method for testing the service reliability of an aircraft windshield provided in an embodiment of the present application;

[0073] Figure 2 A flow chart of a method for generating a collaborative control test pattern for an aircraft windshield service reliability test method provided in an embodiment of the present application;

[0074] Figure 3 This is a block diagram of the aircraft windshield service reliability testing system provided in an embodiment of the present application. DETAILED DESCRIPTION

[0075] The technical solutions in the embodiments of the present application will be clearly and completely described below in conjunction with the drawings in the embodiments of the present application. Obviously, the described embodiments are only a part of the embodiments of the present application, rather than all of the embodiments. The components of the embodiments of the present application generally described and shown in the drawings here can be arranged and designed in various different configurations. Therefore, the following detailed description of the embodiments of the present application provided in the drawings is not intended to limit the scope of the application for protection, but merely represents the selected embodiments of the present application. Based on the embodiments of the present application, all other embodiments obtained by those skilled in the art without making creative work fall within the scope of protection of the present application.

[0076] It should be noted that similar reference numerals and letters represent similar items in the following drawings. Therefore, once an item is defined in one drawing, it does not need to be further defined or explained in subsequent drawings. At the same time, in the description of this application, the terms "first", "second", etc. are only used to distinguish the description and should not be understood as indicating or implying relative importance.

[0077] Please refer to Figure 1 , Figure 1 This is a flow chart of a method for testing the service reliability of an aircraft windshield in some embodiments of the present application. The aircraft windshield service reliability testing method is used in a terminal device and includes the following steps:

[0078] S101, coupling a simulated test environment based on multiple environmental factors, and establishing a collaborative control test mode for multiple environmental factors;

[0079] S102, performing an impact test on the aircraft windshield based on the collaborative test mode to generate damage monitoring data;

[0080] S103, analyzing the damage monitoring data based on the damage mechanics model to generate damage acceleration state data of the aircraft windshield;

[0081] S104, constructing a life prediction model, inputting damage monitoring data and damage acceleration state data into the life prediction model, and outputting remaining life prediction data;

[0082] S105 , analyzing the damage acceleration state data and the remaining life prediction data based on the reliability standard information to obtain a reliability test result of the aircraft windshield, and transmitting the reliability test result to the terminal in real time.

[0083] It should be noted that the multi-factor coupled environmental simulation realistically reproduces the service conditions, realizes the coordinated control of dynamic pressure-temperature-humidity, adopts dynamic air pressure difference control and temperature and humidity adjustment control, accurately simulates the 0.25-0.75atm cyclic pressure, and matches the real flight envelope.

[0084] Among them, the environmental coupling SN curve equation

[0085] The SN curve is a load-life curve, where S refers to stress and N is the number of cycles. Therefore, the SN curve is a life curve under different stresses.

[0086] Windshield service life, SN curve considering temperature influence

[0087]

[0088] where N f is the fatigue life prediction value of the windshield structure, A represents the benchmark fatigue constant of the overall structure, B represents the pressure sensitivity coefficient, C represents the temperature coefficient, T represents the temperature, T0 represents the reference temperature, which is 298K, and △P represents the pressure difference between the inside and outside of the windshield, which is also the pressure difference between the inside and outside of the cockpit.

[0089] For different design schemes, extreme fatigue tests are carried out, which can achieve extreme load tests, that is, increasing the pressure to 0.75-3atm. For large curved windshields, the design scheme of the window frame structure is evaluated to determine its reliability under extreme conditions.

[0090] Please refer to Figure 2 , Figure 2 This is a flow chart of a method for generating a collaborative control test mode for an aircraft windshield service reliability test method in some embodiments of the present application. According to an embodiment of the present invention, a multiple environmental factor coupled simulated test environment is established, and a multiple environmental factor collaborative control test mode is established, specifically including:

[0091] S201, obtaining multiple environmental factors, including temperature factors, pressure factors, and humidity factors;

[0092] S202, matching weights of temperature factors, pressure factors, and humidity factors based on the test focus to obtain corresponding weight coefficients;

[0093] S203, generating a plurality of pairing combinations based on the weight coefficients, and generating a plurality of simulation test environments based on the plurality of pairing combinations;

[0094] S204, analyzing synergy ratios between different environmental factors based on the simulated test environment to obtain multiple synergy patterns;

[0095] S205 , generating multiple collaborative test modes for the aircraft windshield based on the multiple collaborative modes.

[0096] It should be noted that by setting different weights for multiple environmental factors, a pairing combination of multiple environmental factors is obtained, and multiple simulation test environments are obtained. Different simulation test environments correspond to different environmental factors. Different collaborative modes are obtained according to different simulation test environments to improve test accuracy.

[0097] According to an embodiment of the present invention, an impact test is performed on an aircraft windshield based on a collaborative test mode to generate damage monitoring data, specifically including:

[0098] Obtain paired combinations based on collaborative test patterns and generate corresponding temperature, pressure, and humidity data;

[0099] Generate a test environment based on temperature, pressure, and humidity data, perform an impact test on the aircraft windshield based on the test environment, and obtain a stress curve of the aircraft windshield;

[0100] Analyze the stress data of aircraft windshield at different time points based on the stress curve of aircraft windshield;

[0101] Compare the aircraft windshield stress data with the set glass standard data to generate damage difference values;

[0102] The damage status information of the aircraft windshield is analyzed based on the damage difference value to obtain damage monitoring data.

[0103] Specifically, fiber Bragg grating (FBG) sensors are used for distributed fiber sensing (3D-DIC) full-field strain measurement. FBG sensors are spaced 10 mm apart, providing real-time monitoring of stress concentration areas along the windshield edge (with an accuracy of ±0.01% strain). Fiber Bragg grating (FBG) or strain gauges are used to monitor micro-deformations of the windshield frame structure.

[0104] When using strain gauges, due to the multi-layer structure, strain can be monitored on both the inside and outside of the structural glass.

[0105] According to an embodiment of the present invention, damage monitoring data is analyzed based on a damage mechanics model to generate damage acceleration state data of an aircraft windshield, specifically including:

[0106] Establish a data set based on historical damage data, iteratively train the initial model based on the data set, and obtain training results;

[0107] Determine whether the training results converge;

[0108] If converged, a damage mechanics model is generated, and stress data at different positions of the glass are analyzed based on the damage mechanics model. Damage monitoring data is obtained based on the stress data at different positions.

[0109] Analyze the damage status information at different time nodes based on damage monitoring data, and analyze the damage acceleration status data of the aircraft windshield based on the damage status information at different time nodes;

[0110] If it does not converge, adjust the model parameters.

[0111] It should be noted that the model is continuously trained through historical damage data to make the output results of the model closer to the actual results and improve the output accuracy of the model.

[0112] The equivalence of the accelerated test is verified by the damage mechanics model (such as Chaboche nonlinear cumulative damage theory), and the calculation formula is as follows

[0113]

[0114] Where (N i (ΔP i )) is the number of failure cycles under different pressure differences to ensure that the test results are consistent with the actual service damage.

[0115] N i (ΔP i ) is the life (number of failure cycles) under different pressure differences. This data is obtained by fitting the SN curve. i Under the pressure difference condition △P i For example, an actual aircraft can experience 10,000 cycles under a pressure difference of 0.8 atmospheres, while in actual flight, under a pressure difference of 0.8 atmospheres, it can serve for 5,000 cycles and its life is 50% left. n is the number of different pressure difference conditions, D acc Equivalent cumulative damage parameter, D 实际飞行, is the cumulative damage in actual flight. This formula describes the equivalence between the working history of different damage conditions in accelerated testing and the damage accumulation in actual flight.

[0116] According to an embodiment of the present invention, a life prediction model is constructed, damage monitoring data and damage acceleration state data are input into the life prediction model, and remaining life prediction data is output, specifically including:

[0117] Obtain historical prediction data based on big data, and build a lifespan prediction model based on the historical prediction data;

[0118] Analyze the damage stress data and damage acceleration state data of aircraft windshields based on the life prediction model;

[0119] Analyze the aging status of aircraft windshields based on damage acceleration data;

[0120] Based on the aging status information of the aircraft windshield, the remaining life of the glass is analyzed to obtain the remaining life prediction data.

[0121] It should be noted that an acceleration factor (αe^(βt)) is introduced to describe the nonlinear attenuation law of material properties, and Monte Carlo simulation + LSTM timing analysis is performed. The reliability curve is calculated through 106 iterations to quantify the uncertainty. The LSTM network processes multi-sensor timing data and reduces the error in predicting the remaining life.

[0122] According to an embodiment of the present invention, damage acceleration state data and remaining life prediction data are analyzed based on reliability standard information to obtain reliability test results of aircraft windshields, specifically including:

[0123] Obtain damage acceleration status data and remaining life prediction data of aircraft windshields under different collaborative test modes;

[0124] Clean the damage acceleration status data and remaining life prediction data to remove outliers, erroneous data and duplicate data;

[0125] Analyze damage acceleration data to identify damage types on aircraft windshields, including crack growth, surface wear, and delamination.

[0126] Analyze damage changes over time or in collaborative test modes based on statistical methods;

[0127] The remaining life prediction data is analyzed based on the damage change state information to obtain the reliability test results of the aircraft windshield.

[0128] like Figure 3As shown, in a second aspect, an embodiment of the present application provides an aircraft windshield service reliability testing system, the system comprising: a memory and a processor, the memory comprising a program for a method for testing the service reliability of an aircraft windshield, and when the program is executed by the processor, the following steps are implemented:

[0129] Based on multiple environmental factors, a coupled simulation test environment is established, and a test mode with collaborative control of multiple environmental factors is established;

[0130] Conduct impact tests on aircraft windshields based on collaborative testing mode to generate damage monitoring data;

[0131] Analyze damage monitoring data based on damage mechanics models to generate damage acceleration state data of aircraft windshields;

[0132] Construct a life prediction model, input damage monitoring data and damage acceleration state data into the life prediction model, and output remaining life prediction data;

[0133] Based on the reliability standard information, the damage acceleration state data and the remaining life prediction data are analyzed to obtain the reliability test results of the aircraft windshield, and the reliability test results are transmitted to the terminal in real time.

[0134] It should be noted that the test box structure design of this application is as follows:

[0135] Main frame:

[0136] The frame is made of 6061-T6 aviation aluminum alloy with a profile section of 50×50mm (wall thickness 5mm), and is assembled into a special-shaped structure that matches the windshield shape through high-strength bolts (grade 8.8).

[0137] Built-in double-layer sealing system:

[0138] Primary seal: Fluorine rubber strip (hardness 70 Shore A), compression 30%

[0139] Secondary seal: In-situ cured silicone (Dow Corning 732) forms a continuous seal Transparent viewing panel:

[0140] The top and side walls are installed with 12mm thick tempered borosilicate glass (transmittance ≥ 92%), and the surface is coated with AR anti-reflective coating

[0141] A removable inspection door (size 600×400mm) is provided at the bottom with a quick-release locking mechanism (Camlock system)

[0142] The pressure channel system includes: an air intake module, which adopts a dual-path air supply design and consists of the following components:

[0143] Main air supply line: centrifugal compressor (flow rate 30m 3 / min, pressure 0-1.2MPa adjustable)

[0144] Backup gas line: high-pressure gas cylinder set (40L×6, pre-filled with nitrogen to 15MPa)

[0145] Gas processing unit:

[0146] Three-stage filtration (5μm+1μm+0.1μm particle filter)

[0147] Dryer with dew point control <-40℃

[0148] Exhaust Control Module:

[0149] Proportional control valve (SMC PVQ31-5G, response time 10ms)

[0150] Muffler (noise reduction of more than 25dB) and back pressure valve linkage control

[0151] Pressure control module:

[0152] Compressed air from the air tank passes through the pressure control unit, temperature and humidity control unit, and buffer tank inside the test chamber before entering the windshield test chamber. To provide compressed air to the test chamber, the control chamber's exhaust port is connected to the outside atmosphere via a pressure control valve. The pressure control valve is connected to the pressure control unit inside the test chamber via wiring. The internal pressure of the test chamber is then connected to the external pressure control unit via a pressure sensor installed inside the control chamber, forming a closed-loop control loop.

[0153] The temperature and humidity control module includes:

[0154] Controller: PLC or PID controller (such as Siemens S7-1200) Actuators include:

[0155] Heating module: electric heating tube (power 3kW, response time <30s);

[0156] Refrigeration module: semiconductor refrigeration chip (TEC1-12706, temperature range -40 ~ 85 ℃);

[0157] Humidification module: ultrasonic atomizer (frequency 1.7MHz, humidification capacity 0-5L / h adjustable);

[0158] Dehumidification module: rotary dehumidifier (dew point -40℃);

[0159] sensor:

[0160] Temperature sensor: PT100 platinum resistance (accuracy ±0.1℃);

[0161] Humidity sensor: capacitive humidity probe (Honeywell HIH-4000, accuracy ±2% RH);

[0162] A closed-loop control is formed through sensors, actuators and sensors.

[0163] Heating control computer (WHC):

[0164] The windshield heating control computer is an existing aircraft component that is used to simulate the normal working state of the windshield and heat the glass, thereby truly simulating the proportional working state of the aircraft windshield.

[0165] An internal stress or strain monitoring system installs strain gauges or fiber Bragg grating sensors on the outer and inner surfaces of the windshield to monitor the strain state of the windshield during the pressurization process. The strain gauges can be resistance strain gauges, fiber Bragg grating sensors, or other suitable strain sensors, capable of recording strain data in real time.

[0166] A simulated sandstorm or rain test system maintains pressure control, or temperature and humidity control, as well as a windshield heating control cycle. The system is placed in a simulated sandstorm environment, with varying sand content and wind speed. Starting from the maximum sandstorm rate, the cycle life of the windshield is evaluated within a normal pressure differential range under high sandstorm conditions. This allows the usable life of the windshield to be assessed under sandstorm conditions.

[0167] Control logic:

[0168] Initial stage: Rapid pressure increase to 0.9 atm within 30 seconds (simulating takeoff);

[0169] Cruise phase: maintain 0.9atm±0.02atm fluctuation (simulated altitude 12000m);

[0170] Depressurization stage: descend to 0.2 atm at a gradient of 0.1 atm / min (simulated landing);

[0171] Pressure amplitude enhancement: Extreme acceleration test to evaluate the damage reliability of windshield fasteners and windshield glass under higher pressure.

[0172] Damage equivalence verification: Real-time monitoring of crack growth rate through electronic speckle pattern interferometry (ESPI) to ensure that the da / dN ratio error before and after acceleration is <8%

[0173] According to an embodiment of the present invention, a test environment is simulated based on coupling of multiple environmental factors, and a test mode of collaborative control of multiple environmental factors is established, specifically including:

[0174] Acquire multiple environmental factors, including temperature, pressure, and humidity;

[0175] Based on the test focus, the temperature factor, pressure factor and humidity factor are matched with weights to obtain the corresponding weight coefficients;

[0176] Generate a number of pairing combinations based on the weight coefficients, and generate a number of simulation test environments based on the number of pairing combinations;

[0177] Based on the simulation test environment, the synergy ratios between different environmental factors are analyzed to obtain multiple synergy patterns;

[0178] Generate multiple test patterns of aircraft windshields based on multiple collaborative patterns.

[0179] It should be noted that by setting different weights for multiple environmental factors, a pairing combination of multiple environmental factors is obtained, and multiple simulation test environments are obtained. Different simulation test environments correspond to different environmental factors. Different collaborative modes are obtained according to different simulation test environments to improve test accuracy.

[0180] According to an embodiment of the present invention, an impact test is performed on an aircraft windshield based on a collaborative test mode to generate damage monitoring data, specifically including:

[0181] Obtain paired combinations based on collaborative test patterns and generate corresponding temperature, pressure, and humidity data;

[0182] Generate a test environment based on temperature, pressure, and humidity data, perform an impact test on the aircraft windshield based on the test environment, and obtain a stress curve of the aircraft windshield;

[0183] Analyze the stress data of aircraft windshield at different time points based on the stress curve of aircraft windshield;

[0184] Compare the aircraft windshield stress data with the set glass standard data to generate damage difference values;

[0185] The damage status information of the aircraft windshield is analyzed based on the damage difference value to obtain damage monitoring data.

[0186] Specifically, when using fiber Bragg grating sensors, distributed fiber sensing (FBG) + 3D-DIC full-field strain measurement: the FBG sensors are spaced 10 mm apart, and the stress concentration area at the edge of the windshield is monitored in real time (with an accuracy of ±0.01% strain).

[0187] When using strain gauges, due to the multi-layer structure, strain can be monitored on both the inside and outside of the structural glass.

[0188] According to an embodiment of the present invention, damage monitoring data is analyzed based on a damage mechanics model to generate damage acceleration state data of an aircraft windshield, specifically including:

[0189] Establish a data set based on historical damage data, iteratively train the initial model based on the data set, and obtain training results;

[0190] Determine whether the training results converge;

[0191] If converged, a damage mechanics model is generated, and stress data at different positions of the glass are analyzed based on the damage mechanics model. Damage monitoring data is obtained based on the stress data at different positions.

[0192] Analyze the damage status information at different time nodes based on damage monitoring data, and analyze the damage acceleration status data of the aircraft windshield based on the damage status information at different time nodes;

[0193] If it does not converge, adjust the model parameters.

[0194] It should be noted that the model is continuously trained through historical damage data to make the output results of the model closer to the actual results and improve the output accuracy of the model.

[0195] The equivalence of the accelerated test is verified by the damage mechanics model (such as Chaboche nonlinear cumulative damage theory), and the calculation formula is as follows

[0196]

[0197] Where (N i (ΔP i )) is the number of failure cycles under different pressure differences to ensure that the test results are consistent with the actual service damage.

[0198] According to an embodiment of the present invention, a life prediction model is constructed, damage monitoring data and damage acceleration state data are input into the life prediction model, and remaining life prediction data is output, specifically including:

[0199] Obtain historical prediction data based on big data, and build a lifespan prediction model based on the historical prediction data;

[0200] Analyze the damage stress data and damage acceleration state data of aircraft windshields based on the life prediction model;

[0201] Analyze the aging status of aircraft windshields based on damage acceleration data;

[0202] Based on the aging status information of the aircraft windshield, the remaining life of the glass is analyzed to obtain the remaining life prediction data.

[0203] It should be noted that an acceleration factor (αe^(βt)) is introduced to describe the nonlinear attenuation law of material properties, and Monte Carlo simulation + LSTM timing analysis is performed. The reliability curve is calculated through 106 iterations to quantify the uncertainty. The LSTM network processes multi-sensor timing data and reduces the error in predicting the remaining life.

[0204] According to an embodiment of the present invention, damage acceleration state data and remaining life prediction data are analyzed based on reliability standard information to obtain reliability test results of aircraft windshields, specifically including:

[0205] Obtain damage acceleration status data and remaining life prediction data of aircraft windshields under different collaborative test modes;

[0206] Clean the damage acceleration status data and remaining life prediction data to remove outliers, erroneous data and duplicate data;

[0207] Analyze damage acceleration data to identify damage types on aircraft windshields, including crack growth, surface wear, and delamination.

[0208] Analyze damage changes over time or in collaborative test modes based on statistical methods;

[0209] The remaining life prediction data is analyzed based on the damage change state information to obtain the reliability test results of the aircraft windshield.

[0210] A third aspect of the present invention provides a computer-readable storage medium, which includes a program for a method for testing the service reliability of an aircraft windshield. When the program for testing the service reliability of an aircraft windshield is executed by a processor, the steps of any of the above-mentioned methods for testing the service reliability of an aircraft windshield are implemented.

[0211] The present invention discloses a service reliability testing method, system and medium for aircraft windshields. The method comprises the following steps: coupling a simulated test environment based on multiple environmental factors, and establishing a test mode for collaborative control of multiple environmental factors; performing an impact test on the aircraft windshield based on the collaborative test mode to generate damage monitoring data; analyzing the damage monitoring data based on a damage mechanics model to generate damage acceleration state data of the aircraft windshield; constructing a life prediction model, inputting the damage monitoring data and the damage acceleration state data into the life prediction model, and outputting remaining life prediction data; analyzing the damage acceleration state data and the remaining life prediction data based on reliability standard information to obtain reliability test results of the aircraft windshield, and transmitting the reliability test results to a terminal in real time; performing a model test environment based on multiple environmental factors, thereby performing impact tests on the aircraft windshield in different environments, improving the diversity of the test, and performing damage monitoring on the glass to improve the accuracy of the glass reliability test.

[0212] In the several embodiments provided in this application, it should be understood that the disclosed devices and methods can be implemented in other ways. The device embodiments described above are merely schematic. For example, the division of units is merely a logical function division. In actual implementation, there may be other division methods, such as: multiple units or components can be combined, or can be integrated into another system, or some features can be ignored or not executed. In addition, the coupling, direct coupling, or communication connection between the components shown or discussed can be through some interfaces, and the indirect coupling or communication connection of devices or units can be electrical, mechanical or other forms.

[0213] The units described above as separate components may or may not be physically separated, and the components displayed as units may or may not be physical units; they may be located in one place or distributed across multiple network units; some or all of the units may be selected according to actual needs to achieve the purpose of the scheme of this embodiment.

[0214] In addition, all functional units in the embodiments of the present invention may be integrated into one processing unit, or each unit may be separately used as a unit, or two or more units may be integrated into one unit; the above-mentioned integrated units may be implemented in the form of hardware or in the form of hardware plus software functional units.

[0215] Those skilled in the art will appreciate that all or part of the steps of the above-mentioned method embodiments may be implemented by hardware associated with program instructions, and the aforementioned program may be stored in a readable storage medium. When the program is executed, the program executes the steps of the above-mentioned method embodiments. The aforementioned storage medium includes various media that can store program codes, such as mobile storage devices, read-only memories (ROMs), random access memories (RAMs), magnetic disks, or optical disks.

[0216] Alternatively, if the above-mentioned integrated unit of the present invention is implemented in the form of a software functional module and sold or used as an independent product, it can also be stored in a readable storage medium. Based on this understanding, the technical solution of the embodiment of the present invention, or the part that contributes to the existing technology, can be embodied in the form of a software product. The software product is stored in a storage medium and includes a number of instructions for enabling a computer device (which can be a personal computer, server, or network device, etc.) to execute all or part of the methods described in each embodiment of the present invention. The aforementioned storage medium includes: various media that can store program code, such as mobile storage devices, ROM, RAM, magnetic disks or optical disks.

Claims

1. A method for testing the service reliability of an aircraft windshield, characterized in that: include: Based on multiple environmental factors, a coupled simulation test environment is established, and a test mode with collaborative control of multiple environmental factors is established; Conduct impact tests on aircraft windshields based on collaborative testing mode to generate damage monitoring data; Analyze damage monitoring data based on damage mechanics models to generate damage acceleration state data of aircraft windshields; Construct a life prediction model, input damage monitoring data and damage acceleration state data into the life prediction model, and output remaining life prediction data; Based on the reliability standard information, the damage acceleration state data and the remaining life prediction data are analyzed to obtain the reliability test results of the aircraft windshield, and the reliability test results are transmitted to the terminal in real time.

2. The aircraft windshield service reliability testing method according to claim 1, characterized in that: Based on multiple environmental factors, a coupled simulation test environment is established, and a collaborative control test mode of multiple environmental factors is established, including: Acquiring multiple environmental factors, wherein the multiple environmental factors include temperature factors, pressure factors, and humidity factors; Based on the test focus, the temperature factor, pressure factor and humidity factor are matched with weights to obtain the corresponding weight coefficients; Generate a number of pairing combinations based on the weight coefficients, and generate a number of simulation test environments based on the number of pairing combinations; Based on the simulation test environment, the synergy ratios between different environmental factors are analyzed to obtain multiple synergy patterns; Multiple collaborative test modes of the aircraft windshield are generated based on the multiple collaborative modes.

3. The aircraft windshield service reliability testing method according to claim 2, characterized in that: Impact testing of aircraft windshields is performed based on the collaborative testing model to generate damage monitoring data, including: Obtain paired combinations based on collaborative test patterns and generate corresponding temperature, pressure, and humidity data; Generate a test environment based on temperature, pressure, and humidity data, perform an impact test on the aircraft windshield based on the test environment, and obtain a stress curve of the aircraft windshield; Analyze the stress data of aircraft windshield at different time points based on the stress curve of aircraft windshield; Compare the aircraft windshield stress data with the set glass standard data to generate damage difference values; The damage status information of the aircraft windshield is analyzed based on the damage difference value to obtain damage monitoring data.

4. The aircraft windshield service reliability testing method according to claim 3, characterized in that: The damage monitoring data is analyzed based on the damage mechanics model to generate damage acceleration state data of the aircraft windshield, including: Establish a data set based on historical damage data, iteratively train the initial model based on the data set, and obtain training results; Determine whether the training results converge; If converged, a damage mechanics model is generated, and stress data at different positions of the glass are analyzed based on the damage mechanics model. Damage monitoring data is obtained based on the stress data at different positions. Analyze the damage status information at different time nodes based on damage monitoring data, and analyze the damage acceleration status data of the aircraft windshield based on the damage status information at different time nodes; If it does not converge, adjust the model parameters.

5. The aircraft windshield service reliability testing method according to claim 4, characterized in that: Construct a life prediction model, input damage monitoring data and damage acceleration state data into the life prediction model, and output remaining life prediction data, specifically including: Obtain historical prediction data based on big data, and build a lifespan prediction model based on the historical prediction data; Analyze the damage stress data and damage acceleration state data of aircraft windshields based on the life prediction model; Analyze the aging status of aircraft windshields based on damage acceleration data; Based on the aging status information of the aircraft windshield, the remaining life of the glass is analyzed to obtain the remaining life prediction data.

6. The aircraft windshield service reliability testing method according to claim 5, characterized in that: Based on the reliability standard information, the damage acceleration state data and the remaining life prediction data were analyzed to obtain the reliability test results of the aircraft windshield, including: Obtain damage acceleration status data and remaining life prediction data of aircraft windshields under different collaborative test modes; Clean the damage acceleration status data and remaining life prediction data to remove outliers, erroneous data and duplicate data; Analyze the damage acceleration state data to analyze the damage types of the aircraft windshield, including crack propagation, surface wear and delamination; Analyze damage changes over time or in collaborative test modes based on statistical methods; The remaining life prediction data is analyzed based on the damage change state information to obtain the reliability test results of the aircraft windshield.

7. An aircraft windshield service reliability testing system, characterized in that: The system includes: a memory and a processor, wherein the memory includes a program for a method for testing the service reliability of an aircraft windshield. When the program is executed by the processor, the following steps are implemented: Based on multiple environmental factors, a coupled simulation test environment is established, and a test mode with collaborative control of multiple environmental factors is established; Conduct impact tests on aircraft windshields based on collaborative testing mode to generate damage monitoring data; Analyze damage monitoring data based on damage mechanics models to generate damage acceleration state data of aircraft windshields; Construct a life prediction model, input damage monitoring data and damage acceleration state data into the life prediction model, and output remaining life prediction data; Based on the reliability standard information, the damage acceleration state data and the remaining life prediction data are analyzed to obtain the reliability test results of the aircraft windshield, and the reliability test results are transmitted to the terminal in real time.

8. The aircraft windshield service reliability testing system according to claim 7, characterized in that: Based on multiple environmental factors, a coupled simulation test environment is established, and a collaborative control test mode of multiple environmental factors is established, including: Acquiring multiple environmental factors, wherein the multiple environmental factors include temperature factors, pressure factors, and humidity factors; Based on the test focus, the temperature factor, pressure factor and humidity factor are matched with weights to obtain the corresponding weight coefficients; Generate a number of pairing combinations based on the weight coefficients, and generate a number of simulation test environments based on the number of pairing combinations; Based on the simulation test environment, the synergy ratios between different environmental factors are analyzed to obtain multiple synergy patterns; Generate multiple test patterns of aircraft windshields based on multiple collaborative patterns.

9. The aircraft windshield service reliability testing system according to claim 8, characterized in that: Impact testing of aircraft windshields is performed based on the collaborative testing model to generate damage monitoring data, including: Obtain paired combinations based on collaborative test patterns and generate corresponding temperature, pressure, and humidity data; Generate a test environment based on temperature, pressure, and humidity data, perform an impact test on the aircraft windshield based on the test environment, and obtain a stress curve of the aircraft windshield; Analyze the stress data of aircraft windshield at different time points based on the stress curve of aircraft windshield; Compare the aircraft windshield stress data with the set glass standard data to generate damage difference values; The damage status information of the aircraft windshield is analyzed based on the damage difference value to obtain damage monitoring data.

10. A computer-readable storage medium, characterized in that The computer-readable storage medium includes an aircraft windshield service reliability testing method program, and when the aircraft windshield service reliability testing method program is executed by a processor, the steps of the aircraft windshield service reliability testing method according to any one of claims 1 to 6 are implemented.

Images