Aircraft bleed pressure fluctuation monitoring method, system, equipment and medium

Abstract

The invention discloses an aircraft bleed pressure fluctuation monitoring method, system and device and a medium. The method comprises the steps that aircraft bleed fluctuation value data, bleed pressure switch related data and left and right side bleed fluctuation abnormal value change amplitudes of all legs in aircraft QAR data are collected; according to the air entraining fluctuation value data, a fluctuation coefficient is obtained, and if the fluctuation coefficient exceeds a set threshold value, it is judged that the air entraining fluctuation value of the corresponding side is abnormal; according to relevant data of the bleed pressure switch, whether an electric switch of the bleed pressure control system is abnormal or not is analyzed by counting an abnormal value proportion; comparing the variation amplitudes of the air-entraining fluctuation abnormal values on the left side and the right side to judge an abnormal air-entraining pressure side; after an air-entraining fluctuation abnormal flight is found, comparing air-entraining fluctuation values on the left side and the right side to check whether a switch is abnormal, and if the switch is normal, positioning a fault abnormal side according to one side with a relatively large fluctuation coefficient; and the abnormal side of the flight with abnormal air entraining pressure fluctuation and the related abnormal fluctuation coefficient are transmitted to an aircraft crew in the form of an early warning message, and a 3D full-frame image is generated to display fault related conditions.

Description

Technical Field

[0001] The present invention relates to the technical field of fault analysis, and in particular to a method, system, equipment and medium for monitoring aircraft bleed air pressure fluctuations. Background Art

[0002] The stability of the bleed air system is crucial for daily aircraft operations. However, a variety of factors can cause bleed air system failures, leading to bleed air pressure fluctuations. Effective monitoring of this phenomenon can help promptly identify and address potential bleed air issues. Currently, troubleshooting abnormal bleed air pressure fluctuations is challenging, often accompanied by false alarms and missed alerts, causing considerable distress to maintenance personnel.

[0003] Of particular concern is the widespread pressure fluctuations in the A320's engine bleed air system. This unstable pressure condition can cause the bleed air temperature control system to fail, leading to a sharp rise in bleed air temperatures and even triggering overtemperature warnings. Due to the large number of tiny particles in the air, it's difficult to accurately determine the condition of the A320's air filters with the naked eye. Furthermore, when the bleed air temperature exceeds 220 degrees Celsius, the system issues a Level 3 fault alarm, posing a serious safety hazard. To ensure safe and stable flight and prevent ECAM warnings caused by bleed air issues from disrupting normal flight, it is necessary to monitor bleed air pressure fluctuations in real time and perform timely maintenance on related components. Proper temperature and pressure control ensures the bleed air system operates stably and meets flight requirements.

[0004] Currently, the market lacks mature technologies that can effectively detect abnormal bleed air fluctuation faults using fast-access recorder data. The lack of bleed air fluctuation abnormality warning technology hinders maintenance personnel from performing preventive maintenance on bleed air control devices, thereby increasing the possibility of failures and related operational risks. The traditional aircraft fault detection methods currently relied upon are not only costly, but also inefficient and have a high rate of missed reports. This results in many potential faults not being detected in the early stages, thereby increasing flight safety risks and maintenance costs. Abnormal bleed air pressure fluctuations may also occur due to factors such as flight segments and weather. The crew cannot simply determine whether there is a fault in the bleed air system based on a single indicator of bleed air pressure fluctuations, resulting in repeated maintenance and the inability to accurately locate the fault location of the bleed air component, wasting manpower. Summary of the Invention

[0005] The purpose of the present invention is to design a method, system, equipment and medium for monitoring aircraft bleed air pressure fluctuations, which solves the problem of the lack of fault warning technology in the current market, resulting in a high probability of fault occurrence and related operational risks; solves the problem that many potential faults cannot be detected in the early stages, thereby increasing the hidden dangers to flight safety and maintenance costs; and also solves the problem that the various causes of abnormal bleed air fluctuations lead to repetitive maintenance and the inability to accurately locate the fault position of the bleed air component.

[0006] The present invention provides a method for monitoring aircraft bleed air pressure fluctuations, comprising:

[0007] S1: Collect aircraft QAR data and extract the aircraft bleed air fluctuation value data of each flight segment, bleed air pressure switch related data and the change amplitude of the bleed air fluctuation abnormal values ​​on the left and right sides;

[0008] S2: Filter the bleed air fluctuation value data for the appropriate flight segment with the bleed air valve master switch open, obtain the maximum difference in bleed air fluctuation values ​​for each group, and determine if the bleed air fluctuation value on the corresponding side is abnormal;

[0009] S3: Based on the data related to the bleed air pressure switch in the QAR data, analyze whether there is any abnormality in the bleed air pressure control system switch by counting the proportion of abnormal values;

[0010] S4: Compare the change amplitude of the abnormal bleed air fluctuation values ​​on the left and right sides of the QAR data to determine the side with abnormal bleed air pressure;

[0011] S5: When an abnormal bleed air fluctuation is detected on a flight, compare the bleed air fluctuation values ​​on the left and right sides to check whether the switch is abnormal. If the switch is normal, locate the abnormal side based on the larger fluctuation coefficient.

[0012] S6: The abnormal side and related abnormal fluctuation coefficient of the flight with abnormal bleed air pressure fluctuation are transmitted to the maintenance personnel in the form of a warning message, and a 3D full-frame image is generated to display the relevant situation of the fault.

[0013] Preferably, in step S1, the parameters of the aircraft QAR data further include: left bleed air pressure value, right bleed air pressure value, PRV1 switch, PRV2 switch and flight segment.

[0014] Preferably, in step S2, the maximum difference of each group of bleed air fluctuations is obtained as follows:

[0015] Filter the bleed air fluctuation value data for the appropriate flight segment with the bleed air valve master switch open, divide it into sliding group data every 5 seconds, and calculate the maximum difference in bleed air fluctuation within each 5-second period, specifically:

[0016] D i =S i,tmax -S i,tmin

[0017] Among them, S i,tmax Indicates the maximum value of the bleed air fluctuation within 5 seconds; S i,tmin Indicates the minimum value of bleed air fluctuation within 5 seconds, D i Indicates the maximum difference in bleed air fluctuation within 5 seconds.

[0018] Preferably, the determination of the abnormality of the corresponding side air bleed fluctuation value is specifically as follows:

[0019] Filter out the bleed air difference value groups whose maximum bleed air fluctuation difference exceeds the first threshold, specifically:

[0020] There exists j such that |ij| <M且D j >Threshold, then D j Belongs to the difference group, Threshold is the first threshold, and the sum of all difference groups is obtained. D =∑ difference group D i ;

[0021] Calculate the sum of all differences greater than the first threshold and divide it by the total time length to obtain the fluctuation coefficient, specifically:

[0022]

[0023] When the fluctuation coefficient C exceeds the second threshold, the air induction wave value is judged to be abnormal.

[0024] Preferably, in step S3, the analyzing whether there is any abnormality in the switch of the bleed air pressure control system by counting the proportion of abnormal values ​​is specifically as follows:

[0025] When the bleed air main valve switch is closed for more than 10% of the total flight time, the bleed air valve component is determined to be faulty and is included in the bleed air pressure fluctuation fault troubleshooting scope.

[0026] Preferably, in step S4, the comparison of the change amplitudes of the abnormal bleed air fluctuation values ​​on the left and right sides of the QAR data to determine the abnormal bleed air pressure side is specifically as follows:

[0027] Filter the maximum bleed air pressure values, calculate the difference between the corresponding maximum values ​​on the left and right sides to form a new list, and analyze its mean and variance characteristics. If the minimum difference between the left and right bleed air pressures within the specified time exceeds the preset value, it is recorded as an anomaly point. The sum of the anomaly points divided by the total duration obtains the anomaly coefficient value. The anomaly coefficient value is used to determine whether the flight bleed air fluctuation value is abnormal.

[0028] Preferably, the determination of whether the flight air bleed fluctuation value is abnormal based on the abnormal coefficient value is specifically as follows:

[0029] Calculate the difference between the maximum and minimum values ​​within the corresponding time on the left and right sides to form two new lists. Calculate the mean and variance of the two lists. If the difference between the minimum values ​​of the left and right bleed air pressures within 8 seconds exceeds 5, it is recorded as an anomaly. The sum of the anomaly points divided by the total time is the anomaly coefficient value. If the anomaly coefficient value exceeds 0.75, the flight bleed air fluctuation value is determined to be abnormal.

[0030] Preferably, an aircraft bleed air pressure fluctuation monitoring system comprises:

[0031] The data acquisition module is used to collect aircraft QAR data and extract the aircraft bleed air fluctuation value data of each flight segment, the bleed air pressure switch related data and the change amplitude of the bleed air fluctuation abnormal values ​​on the left and right sides;

[0032] The fluctuation coefficient calculation module is used to screen the bleed air fluctuation value data for the appropriate flight segment and when the bleed air valve master switch is open, obtain the maximum difference in each group of bleed air fluctuations, and determine whether the bleed air fluctuation value on the corresponding side is abnormal;

[0033] The pressure switch troubleshooting module is used to extract data related to the bleed air pressure switch in the QAR data and analyze whether there are any abnormalities in the bleed air pressure control system switch by counting the proportion of abnormal values;

[0034] The two-side synchronous analysis module is used to compare the change amplitude of the abnormal bleed air fluctuation values ​​on the left and right sides of the QAR data to determine the side with abnormal bleed air pressure;

[0035] The fault location module is used to detect abnormal bleed air fluctuations on a flight and compare the bleed air fluctuation values ​​on the left and right sides to check whether the switch is abnormal. If the switch is normal, the fault is located on the side with the larger fluctuation coefficient.

[0036] The early warning and display module is used to transmit the abnormal side and related abnormal fluctuation coefficient of the flight with abnormal bleed air pressure fluctuation to the maintenance personnel in the form of early warning messages, and generate 3D full-frame images to display the fault-related situation.

[0037] Preferably, a device comprises a processor, a memory, and a computer program stored in the memory and configured to be executed by the processor, wherein the processor implements the aircraft bleed air pressure fluctuation monitoring method when executing the computer program.

[0038] Preferably, a computer-readable storage medium includes a stored computer program, wherein when the computer program is running, the device where the computer-readable storage medium is located is controlled to execute the aircraft bleed air pressure fluctuation monitoring method.

[0039] Compared with the prior art, the present invention has the following beneficial effects:

[0040] The application discloses an aircraft bleed air pressure fluctuation monitoring method, system, device and medium, through synchronization of QAR data, through detection of the fluctuation change and trend of the aircraft bleed air on the left and right sides, abnormal conditions of the fault side bleed air pressure component can be investigated, and through investigation of the abnormal conditions of the aircraft bleed air pressure fluctuation caused by failure of the bleed air valve component to be timely opened, preventive maintenance measures can be implemented in advance, so that normal operation and flight safety of the aircraft are ensured. BRIEF DESCRIPTION OF DRAWINGS

[0041] Figure 1 is a kind of aircraft bleed air pressure fluctuation monitoring method flow chart provided by the embodiment of the application;

[0042] Figure 2 is the schematic diagram of normal bleed air pressure provided by the embodiment of the application;

[0043] Figure 3 is the schematic diagram of abnormal bleed air pressure provided by the embodiment of the application;

[0044] Figure 4 is the schematic diagram of left and right side fluctuation comparison provided by the embodiment of the application;

[0045] Figure 5 is a kind of aircraft bleed air pressure fluctuation monitoring system module schematic diagram provided by the embodiment of the application;

[0046] Figure 6 is the abnormal early warning architecture diagram of bleed air pressure fluctuation provided by the embodiment of the application. DETAILED DESCRIPTION

[0047] The technical solutions in the embodiments of the application will be described clearly and completely below with reference to the drawings in the embodiments of the application. Apparently, the described embodiments are only part of the embodiments of the application, not all the embodiments. Based on the embodiments in the application, all other embodiments obtained by those skilled in the art without creative labor fall within the scope of protection of the application.

[0048] As shown in Figure 1 , the application provides an aircraft bleed air pressure fluctuation monitoring method, comprising:

[0049] S1: collecting aircraft QAR data and extracting aircraft bleed air fluctuation value data, bleed air pressure switch related data and left and right side bleed air fluctuation abnormal value change amplitude of each flight segment;

[0050] S2: screening bleed air fluctuation value data under the condition that the bleed air valve total switch is opened in suitable flight segment, obtaining the maximum difference value of each group of bleed air fluctuation, and determining the corresponding side bleed air fluctuation value abnormality;

[0051] S3: Based on the data related to the bleed air pressure switch in the QAR data, analyze whether there is any abnormality in the bleed air pressure control system switch by counting the proportion of abnormal values;

[0052] S4: Compare the change amplitude of the abnormal bleed air fluctuation values ​​on the left and right sides of the QAR data to determine the side with abnormal bleed air pressure;

[0053] S5: When an abnormal bleed air fluctuation is detected on a flight, compare the bleed air fluctuation values ​​on the left and right sides to check whether the switch is abnormal. If the switch is normal, locate the abnormal side based on the larger fluctuation coefficient.

[0054] S6: The abnormal side and related abnormal fluctuation coefficient of the flight with abnormal bleed air pressure fluctuation are transmitted to the maintenance personnel in the form of a warning message, and a 3D full-frame image is generated to display the relevant situation of the fault.

[0055] In the above solution, aircraft bleed air pressure fluctuation monitoring based on QAR data effectively monitors changes in bleed air pressure fluctuations in real time through in-depth analysis of key indicators in recent QAR data, such as bleed air fluctuation trends and valve opening and closing scheduling. It can also detect abnormal conditions of bleed air pressure fluctuation components in real time, thereby implementing preventive maintenance measures. This can not only significantly reduce the safety risks caused by bleed air pressure component failures, but also effectively avoid flight delays caused by such failures, thereby improving flight operating efficiency and reliability.

[0056] Preferably, in step S1, the parameters of the aircraft QAR data further include: left bleed air pressure value, right bleed air pressure value, PRV1 switch, PRV2 switch and flight segment.

[0057] In one embodiment provided in this application, QAR data is collected through aircraft records, and the actual value of the aircraft bleed air pressure in each flight segment and the changes in the bleed air parameters during the flight are extracted from the QAR data. The hdf5 file is obtained and the RecordedParameters parameter field is read using the h5py package of Python to obtain parameters related to the bleed air pressure as shown in the following table:

[0058]

[0059]

[0060] Preferably, in step S2, the maximum difference of each group of bleed air fluctuations is obtained as follows:

[0061] Filter the bleed air fluctuation value data for the appropriate flight segment with the bleed air valve master switch open, divide it into sliding group data every 5 seconds, and calculate the maximum difference in bleed air fluctuation within each 5-second period, specifically:

[0062] D i =S i,tmax -Si,tmin

[0063] Among them, S i,tmax Indicates the maximum value of the bleed air fluctuation within 5 seconds; S i,tmin Indicates the minimum value of bleed air fluctuation within 5 seconds, D i Indicates the maximum difference in bleed air fluctuation within 5 seconds.

[0064] Preferably, the determination of the abnormality of the corresponding side air bleed fluctuation value is specifically as follows:

[0065] Filter out the bleed air difference value groups whose maximum bleed air fluctuation difference exceeds the first threshold, specifically:

[0066] There exists j such that |ij| <M且D j >Threshold, then D j Belongs to the difference group, Threshold is the first threshold, and the sum of all difference groups is obtained. D =∑ difference group D i ;

[0067] Calculate the sum of all differences greater than the first threshold and divide it by the total time length to obtain the fluctuation coefficient, specifically:

[0068]

[0069] When the fluctuation coefficient C exceeds the second threshold, the air induction wave value is judged to be abnormal.

[0070] In one embodiment provided by the present application, when the segment data is not 10 segments, segment 10 generally indicates the final shutdown state of the aircraft. The bleed air fluctuation value data when the main switches of the bleed air valves on both sides are open is divided into sliding group data every 5 seconds. The maximum difference of the bleed air fluctuation within 5 seconds is calculated by subtracting the minimum bleed air value from the maximum bleed air fluctuation within 5 seconds. The maximum difference D of the bleed air fluctuation within each 5 seconds is calculated. i =S i,tmax -S i,tmin Filter out the maximum difference exceeding the first threshold, the first threshold is set to 3, and there is a group of air bleed difference values ​​j such that |ij| <M且D j >Threshold, then D j Belongs to the difference group, Threshold is the first threshold, and the sum of all difference groups is obtained. D =∑ difference group D i , calculate the sum of all differences greater than 3 in all sliding windows, and divide the sum by the total time length. If the coefficient C exceeds the second threshold (1.2), the bleed air fluctuation value on that side is considered abnormal. Using the bleed air pressure fluctuations in the QAR data, the system determines if any abnormalities exist in the bleed air pressure-related components by calculating whether relevant parameters exceed the set thresholds. Maintenance personnel are promptly notified to troubleshoot and repair the aircraft's bleed air system failure.

[0071] Preferably, in step S3, the analyzing whether there is any abnormality in the switch of the bleed air pressure control system by counting the proportion of abnormal values ​​is specifically as follows:

[0072] When the bleed air main valve switch is closed for more than 10% of the total flight time, the bleed air valve component is determined to be faulty and is included in the bleed air pressure fluctuation fault troubleshooting scope.

[0073] In the above solution, relevant data on the aircraft's bleed air pressure switches under actual operating conditions is extracted from the QAR data. The percentage of outliers is calculated to analyze whether there are any abnormalities in the bleed air pressure control system switches. When an aircraft bleed air control system malfunctions, the bleed air main valve switch remains closed for a certain percentage of the total flight time. Comparisons of multiple flights revealed that when the closed state exceeds 10% of the total flight time, the bleed air valve assembly is faulty. When troubleshooting the problem, maintenance personnel will only find a bleed air fluctuation value of 0, but further investigation is required to determine whether the valve switch is the cause. This condition is included in the list of bleed air pressure fluctuations to facilitate troubleshooting.

[0074] Preferably, in step S4, the comparison of the change amplitudes of the abnormal bleed air fluctuation values ​​on the left and right sides of the QAR data to determine the abnormal bleed air pressure side is specifically as follows:

[0075] Filter the maximum bleed air pressure values, calculate the difference between the corresponding maximum values ​​on the left and right sides to form a new list, and analyze its mean and variance characteristics. If the minimum difference between the left and right bleed air pressures within the specified time exceeds the preset value, it is recorded as an anomaly point. The sum of the anomaly points divided by the total duration obtains the anomaly coefficient value. The anomaly coefficient value is used to determine whether the flight bleed air fluctuation value is abnormal.

[0076] Preferably, the determination of whether the flight air bleed fluctuation value is abnormal based on the abnormal coefficient value is specifically as follows:

[0077] Calculate the difference between the maximum and minimum values ​​within the corresponding time on the left and right sides to form two new lists. Calculate the mean and variance of the two lists. If the difference between the minimum values ​​of the left and right bleed air pressures within 8 seconds exceeds 5, it is recorded as an anomaly. The sum of the anomaly points divided by the total time is the anomaly coefficient value. If the anomaly coefficient value exceeds 0.75, the flight bleed air fluctuation value is determined to be abnormal.

[0078] In the above scheme, the bleed air pressure fluctuations extracted from the QAR data are compared with the change amplitude of the abnormal bleed air fluctuation values ​​on the left and right sides. The influence of factors such as weather and flight segment can be checked, and the abnormal bleed air pressure side can be independently determined to help maintenance personnel locate the fault position of the bleed air pressure component.

[0079] In one embodiment provided in this application, Figure 2 As shown in the figure, the bleed air pressure changes on both sides of the aircraft are relatively consistent during normal flight. Since there may be a certain time interval between the bleed air pressures on both sides, the difference at the same time cannot be used as the basis for judging bleed air anomalies. By analyzing the maintenance records of the bleed air fluctuation components of 18 A320 series aircraft in the past six months, the bleed air pressure fluctuations of the 15 flights before the maintenance records were obtained, and the bleed air pressure fluctuation abnormal data were obtained. Finally, it was determined that the bleed air fluctuations were grouped into 8S data, and the maximum and minimum bleed air pressure values ​​were screened out. The maximum and minimum differences in the corresponding time on the left and right sides were calculated to form two new lists; the maximum and minimum differences in the corresponding time on the left and right sides were calculated to form two new lists, and the mean and variance of the two lists were calculated. If the minimum difference in the left and right bleed air pressures within 8 seconds exceeded 5, it was recorded as an abnormal point. The sum of the abnormal points divided by the total time was the abnormal coefficient value. If the abnormal coefficient value exceeded 0.75, the flight bleed air fluctuation value was determined to be abnormal.

[0080] like Figure 3 As shown in the figure, the change trend of the bleed air pressure on the faulty side is significantly increased, and the amplitude of the up and down fluctuation is greater than that on the normal side.

[0081] like Figure 4 As shown in the figure, by analyzing a large amount of abnormal bleed air fluctuation data, it was found that the intensity of the bleed air pressure on the left and right sides was significantly different. In order to avoid abnormal bleed air pressure fluctuations caused by reasons such as flight segments or weather, the comparison of the bleed air pressure on the left and right sides was added to the index. The abnormal bleed air pressure was monitored by real-time detection of the difference in the bleed air pressure on the left and right sides.

[0082] In the above scheme, after discovering a flight with abnormal aircraft bleed air fluctuations through the above four steps, compare the fluctuation values ​​on the left and right sides to first rule out whether there is a switch abnormality. When the switch is abnormal, the fluctuation range of the bleed air will tend to be flat, and the switch-off state on the abnormal side will exceed 10% of the total length, so the abnormal side can be directly located. If the switch state is normal, the side with the larger of the two separate amplitude coefficients C calculated in step 2 can be used to locate the abnormal side of the fault, helping maintenance personnel to locate the abnormal side of the fault.

[0083] The abnormal side of the abnormal flight of the bleed air pressure fluctuation and the corresponding abnormal fluctuation coefficient, for example, the message form is 1, the abnormal side of the bleed air pressure fluctuation, "left side", "2, the fluctuation coefficient C", "3", "3, the fluctuation coefficient difference W between left and right", "1.75", "3, the fluctuation time", "2024-08-19-16-53-52", is transmitted to the maintenance group member in the form of early warning message, and a visual 3D full frame image is generated through specific position information, and the coefficient factor and position of the fault are intuitively displayed.

[0084] Preferably, as shown in the drawings, an aircraft bleed air pressure fluctuation monitoring system comprises: Figure 5

[0085] A data acquisition module is configured to acquire QAR data of an aircraft and extract bleed air fluctuation value data of each flight segment, bleed air pressure switch related data, and amplitude of change of abnormal values of bleed air fluctuation on the left and right sides.

[0086] A fluctuation coefficient calculation module is configured to filter bleed air fluctuation value data of suitable flight segments and bleed air valve total switch opening states, obtain maximum difference values of each group of bleed air fluctuation, and determine abnormal values of bleed air fluctuation on the corresponding side.

[0087] A pressure switch troubleshooting module is configured to extract bleed air pressure switch related data in QAR data, and analyze whether there is an abnormality in the bleed air pressure control system switch by counting the proportion of abnormal values.

[0088] A two-side synchronous analysis module is configured to compare the amplitude of change of abnormal values of bleed air fluctuation on the left and right sides in QAR data to determine the abnormal side of bleed air pressure.

[0089] A fault positioning module is configured to compare bleed air fluctuation values on the left and right sides to determine whether the switch is abnormal after discovering an abnormal flight of bleed air fluctuation, and if the switch is normal, the abnormal side of the fault is located according to the side with a larger fluctuation coefficient.

[0090] An early warning and display module is configured to transmit the abnormal side of the abnormal flight of the bleed air pressure fluctuation and the related abnormal fluctuation coefficient to the maintenance personnel in the form of an early warning message, and generate a 3D full frame image to display the fault related situation.

[0091] In an embodiment provided in the present application, through the above six modules, after the flight aircraft lands, first, QAR data is acquired through aircraft recording, and bleed air fluctuation coefficient data, bleed air pressure switch data, and flight segment data are extracted; then three fault conditions when the aircraft bleed air pressure is abnormal are identified:

[0092] ​Case 1: Calculate the difference between the maximum and minimum values ​​of the air flow fluctuation within a sliding window of 5 seconds. If the difference exceeds 3, record the difference of this group. Calculate the sum of all differences and divide it by the total flight time to obtain the average fluctuation coefficient value. If the average fluctuation coefficient value C exceeds 1.2, record an air flow fluctuation fault.

[0093] Case 2: Check whether there is a switch failure by determining whether the left and right switches are closed for more than 10% of the total time. If the switch on one of the left and right sides is closed for more than 10%, an air bleed switch failure is recorded.

[0094] Case 3: Troubleshoot the problem by checking whether the left and right side fluctuations are out of sync. Calculate the minimum pressure difference on the left and right sides of the sliding window within 8 seconds. When the minimum pressure exceeds 5, record the group as an abnormal group. Calculate the sum of all groups with a pressure difference exceeding 5 within 8 seconds and divide it by the total flight time to obtain the left and right abnormal bleed air fluctuation coefficient W. If the left and right bleed air fluctuation abnormal coefficient W exceeds 0.75, it is determined that the left and right side bleed air fluctuations are out of sync.

[0095] If the average fluctuation coefficient value C or the left and right bleed air fluctuation abnormal coefficient W exceeds the threshold, the abnormal side of the bleed air component is located by the side with the larger average fluctuation coefficient value C. After capturing the fault data of the abnormal flight, the maintenance team members are notified in the form of a message and a visual 3D full-frame image is generated based on the specific location information.

[0096] This invention significantly improves the efficiency and accuracy of troubleshooting abnormal bleed air pressure fluctuations on aircraft, helping maintenance personnel quickly identify and resolve faults while promptly notifying the maintenance department to develop appropriate maintenance plans and ensure flight safety. Maintenance records show that abnormal bleed air pressure fluctuations were not captured promptly. By using QAR data to promptly capture abnormal bleed air pressure, maintenance personnel can be notified to troubleshoot bleed air component failures. This preventative maintenance strategy significantly reduces the risk of operational failures caused by abnormal bleed air pressure. By detecting and troubleshooting bleed air pressure component performance issues in real time, this invention helps reduce collateral damage to other components of the aircraft's air conditioning system caused by the bleed air pressure component, further protecting the integrity of the aircraft system.

[0097] like Figure 6 As shown, the process begins with collecting QAR data, quality assurance data related to the bleed air system. Next, characteristic values ​​such as flight segments, bleed air values, and switching coefficients are extracted from the collected data. These characteristic values ​​are crucial for subsequent analysis and calculations.

[0098] Then the bleed air fluctuation coefficient is calculated to evaluate the stability of the bleed air system; the bleed air switch failure is checked to ensure the normal operation of the bleed air switch and avoid system problems caused by switch failure; the left and right side fluctuation synchronization is calculated to check the synchronization of the two sides of the bleed air system and ensure the coordination of the work of both sides.

[0099] Next, the abnormal part of the bleed air assembly is located. The previous calculations and troubleshooting determine the specific location of the bleed air assembly where the abnormality may exist. A warning message is generated, and when an abnormality is discovered, a warning message is promptly generated to notify relevant personnel. Finally, a visual 3D full-frame image is generated, visually displaying the bleed air system status in 3D, facilitating further analysis and processing. The entire process is a complete system, from data collection to troubleshooting, to abnormality location and warning, helping to ensure the normal operation of the bleed air system.

[0100] Preferably, a device comprises a processor, a memory, and a computer program stored in the memory and configured to be executed by the processor, wherein the processor implements the aircraft bleed air pressure fluctuation monitoring method when executing the computer program.

[0101] Preferably, a computer-readable storage medium includes a stored computer program, wherein when the computer program is running, the device where the computer-readable storage medium is located is controlled to execute the aircraft bleed air pressure fluctuation monitoring method.

[0102] Preferably, the computer program can be divided into one or more modules / units (e.g., computer programs), which are stored in the memory and executed by the processor to implement the present invention. The one or more modules / units can be a series of computer program instruction segments that can perform specific functions, and the instruction segments are used to describe the execution process of the computer program in the terminal device.

[0103] The processor can be a central processing unit (CPU), or other general-purpose processors, digital signal processors (DSP), application-specific integrated circuits (ASIC), field-programmable gate arrays (FPGA) or other programmable logic devices, discrete gate or transistor logic devices, discrete hardware components, etc. The general-purpose processor can be a microprocessor, or the processor can be any conventional processor. The processor is the control center of the terminal device, and uses various interfaces and lines to connect the various parts of the terminal device.

[0104] The memory mainly includes a program storage area and a data storage area, wherein the program storage area can store an operating system, an application program required for at least one function, etc., and the data storage area can store related data, etc. In addition, the memory can be a high-speed random access memory, or a non-volatile memory, such as a plug-in hard disk, a smart memory card (SmartMedia Card, SMC), a secure digital (Secure Digital, SD) card, and a flash card, etc., or the memory can also be other volatile solid-state storage devices.

[0105] It should be noted that the above-mentioned terminal device may include, but is not limited to, a processor and a memory. Those skilled in the art will understand that the above-mentioned terminal device is merely an example and does not constitute a limitation on the terminal device. It may include more or fewer components, or a combination of certain components, or different components.

[0106] The above is a preferred embodiment of the present invention. It should be pointed out that for ordinary technicians in this technical field, several improvements and modifications can be made without departing from the principles of the present invention. These improvements and modifications are also considered to be within the scope of protection of the present invention.

Claims

1. A method for monitoring aircraft bleed air pressure fluctuations, characterized in that: include: S1: Collect aircraft QAR data and extract the aircraft bleed air fluctuation value data of each flight segment, bleed air pressure switch related data and the change amplitude of the bleed air fluctuation abnormal values ​​on the left and right sides; S2: Filter the bleed air fluctuation value data for the appropriate flight segment with the bleed air valve master switch open, obtain the maximum difference in bleed air fluctuation values ​​for each group, and determine if the bleed air fluctuation value on the corresponding side is abnormal; S3: Based on the data related to the bleed air pressure switch in the QAR data, analyze whether there is any abnormality in the bleed air pressure control system switch by counting the proportion of abnormal values; S4: Compare the change amplitude of the abnormal bleed air fluctuation values ​​on the left and right sides of the QAR data to determine the side with abnormal bleed air pressure; S5: When an abnormal bleed air fluctuation is detected on a flight, compare the bleed air fluctuation values ​​on the left and right sides to check whether the switch is abnormal. If the switch is normal, locate the abnormal side based on the larger fluctuation coefficient. S6: The abnormal side and related abnormal fluctuation coefficient of the flight with abnormal bleed air pressure fluctuation are transmitted to the maintenance personnel in the form of a warning message, and a 3D full-frame image is generated to display the relevant situation of the fault.

2. The method for monitoring aircraft bleed air pressure fluctuations according to claim 1, wherein: In step S1 , the parameters of the aircraft QAR data further include: left bleed air pressure value, right bleed air pressure value, PRV1 switch, PRV2 switch and flight segment.

3. The method for monitoring aircraft bleed air pressure fluctuations according to claim 2, wherein: In step S2, the maximum difference of each group of bleed air fluctuations is obtained as follows: Filter the bleed air fluctuation value data for the appropriate flight segment with the bleed air valve master switch open, divide it into sliding group data every 5 seconds, and calculate the maximum difference in bleed air fluctuation within each 5-second period, specifically: D i =S i，tmax -S i，tmin Among them, S i,tmax Indicates the maximum value of the bleed air fluctuation within 5 seconds; S i,tmin Indicates the minimum value of bleed air fluctuation within 5 seconds, D i Indicates the maximum difference in bleed air fluctuation within 5 seconds.

4. The method for monitoring aircraft bleed air pressure fluctuations according to claim 3, wherein: The specific method for determining the abnormality of the corresponding side air flow fluctuation value is as follows: Filter out the bleed air difference value groups whose maximum bleed air fluctuation difference exceeds the first threshold, specifically: There exists a j such that |i - j| < M and D j > Threshold, then D j belongs to the difference group, Threshold is the first threshold, and the sum Sum of all difference groups is obtained D = ∑ difference group D i ; Calculate the sum of all differences greater than the first threshold and divide it by the total time length to obtain the fluctuation coefficient, specifically: When the fluctuation coefficient C exceeds the second threshold, the air induction wave value is judged to be abnormal.

5. The method for monitoring aircraft bleed air pressure fluctuations according to claim 4, wherein: In step S3, the analysis of whether there is any abnormality in the switch of the bleed air pressure control system by counting the proportion of abnormal values ​​is specifically as follows: When the bleed air main valve switch is closed for more than 10% of the total flight time, the bleed air valve component is determined to be faulty and is included in the bleed air pressure fluctuation fault troubleshooting scope.

6. The method for monitoring aircraft bleed air pressure fluctuations according to claim 5, wherein: In step S4, the comparison of the change amplitudes of the abnormal bleed air fluctuation values ​​on the left and right sides of the QAR data to determine the abnormal bleed air pressure side is specifically as follows: Filter the maximum bleed air pressure values, calculate the difference between the corresponding maximum values ​​on the left and right sides to form a new list, and analyze its mean and variance characteristics. If the minimum difference between the left and right bleed air pressures within the specified time exceeds the preset value, it is recorded as an anomaly point. The sum of the anomaly points divided by the total duration obtains the anomaly coefficient value. The anomaly coefficient value is used to determine whether the flight bleed air fluctuation value is abnormal.

7. The method for monitoring aircraft bleed air pressure fluctuations according to claim 6, wherein: The specific method of determining the abnormality of the flight bleed air fluctuation value according to the abnormal coefficient value is as follows: Calculate the difference between the maximum and minimum values ​​within the corresponding time on the left and right sides to form two new lists. Calculate the mean and variance of the two lists. If the difference between the minimum values ​​of the left and right bleed air pressures within 8 seconds exceeds 5, it is recorded as an anomaly. The sum of the anomaly points divided by the total time is the anomaly coefficient value. If the anomaly coefficient value exceeds 0.75, the flight bleed air fluctuation value is determined to be abnormal.

8. An aircraft bleed air pressure fluctuation monitoring system, characterized in that: include: The data acquisition module is used to collect aircraft QAR data and extract the aircraft bleed air fluctuation value data of each flight segment, the bleed air pressure switch related data and the change amplitude of the bleed air fluctuation abnormal values ​​on the left and right sides; The fluctuation coefficient calculation module is used to screen the bleed air fluctuation value data for the appropriate flight segment and when the bleed air valve master switch is open, obtain the maximum difference in each group of bleed air fluctuations, and determine whether the bleed air fluctuation value on the corresponding side is abnormal; The pressure switch troubleshooting module is used to extract data related to the bleed air pressure switch in the QAR data and analyze whether there are any abnormalities in the bleed air pressure control system switch by counting the proportion of abnormal values; The two-side synchronous analysis module is used to compare the change amplitude of the abnormal bleed air fluctuation values ​​on the left and right sides of the QAR data to determine the side with abnormal bleed air pressure; The fault location module is used to detect abnormal bleed air fluctuations on a flight and compare the bleed air fluctuation values ​​on the left and right sides to check whether the switch is abnormal. If the switch is normal, the fault is located on the side with the larger fluctuation coefficient. The early warning and display module is used to transmit the abnormal side and related abnormal fluctuation coefficient of the flight with abnormal bleed air pressure fluctuation to the maintenance personnel in the form of early warning messages, and generate 3D full-frame images to display the fault-related situation.

9. A device, characterized in that The invention comprises a processor, a memory, and a computer program stored in the memory and configured to be executed by the processor, wherein when the processor executes the computer program, the method for monitoring aircraft bleed air pressure fluctuations according to one of claims 1 to 7 is implemented.

10. A computer-readable storage medium, characterized in that The computer-readable storage medium includes a stored computer program, wherein when the computer program is executed, the device where the computer-readable storage medium is located is controlled to execute the aircraft bleed air pressure fluctuation monitoring method according to any one of claims 1 to 7.

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