Aircraft landing gear fault early warning method, system, equipment and medium

Abstract

The invention discloses an aircraft landing gear fault early warning method, system and device and a medium, and aims to accurately monitor the folding / unfolding process of a landing gear, identify the total abnormal duration, early warn potential faults, analyze the data of multiple flights and identify the trend change of the folding / unfolding time of the landing gear. Possible faults can be warned in advance by analyzing the change trend; meanwhile, the synchronism of each door opening operation is monitored, and whether the situation of asynchronous door opening of the undercarriage exists or not is recognized; and the positions of the undercarriage fault switches can be timely positioned according to the change duration of each switch. According to the invention, the potential risk caused by the fault of the aircraft landing gear can be effectively avoided, and the detection efficiency and accuracy of the fault of the aircraft landing gear are improved, so that the flight operation efficiency and reliability are improved.

Description

TECHNICAL FIELD

[0001] The present application relates to the technical field of aircraft failure early warning, and in particular to an aircraft landing gear failure early warning method, system, device and medium. BACKGROUND

[0002] The landing gear retraction system of an aircraft is crucial to the aircraft, and if a failure occurs, it can have serious consequences and affect flight safety. However, the traditional aircraft landing gear failure troubleshooting method requires aircraft testing, which is time-consuming and labor-intensive, and it is difficult to reproduce the failure, so it is not possible to promptly detect the failure and the degree of failure aging. In addition, the confirmation of the failure relies on maintenance logs and recorded data as well as the experience of engineers, which limits the accuracy.

[0003] In recent years, with the development of aviation data acquisition and analysis technology, based on flight data recorded by aircraft data recording equipment (such as quick access recorder QAR), various parameters of the aircraft during flight can be recorded, including related data of the aircraft landing gear, so it is possible to consider early warning of aircraft landing gear failure based on recorded flight data, thereby improving the efficiency and accuracy of failure detection. SUMMARY

[0004] The technical problem to be solved by the present application is to provide an aircraft landing gear failure early warning method, system, device and medium, which can early warn of aircraft landing gear failure based on flight data, improve the efficiency and accuracy of aircraft landing gear failure detection, and improve the efficiency and reliability of flight operations.

[0005] To solve the above technical problems, the present application provides an aircraft landing gear failure early warning method, comprising:

[0006] Collecting flight data of an aircraft to obtain aircraft landing gear parameters;

[0007] Determining whether there is an aircraft landing gear program recovery condition according to the aircraft landing gear parameters;

[0008] If the aircraft has a landing gear program recovery condition, then the preparation time of each door switch, the change duration of each door switch, and the total duration of the aircraft landing gear retraction / retraction process from the start of the program recovery to the complete closing of all landing gear doors are calculated;

[0009] Determining whether the total duration of the aircraft landing gear retraction / retraction process exceeds a preset threshold;

[0010] If the total duration of the aircraft landing gear retraction / retraction process does not exceed the preset threshold, then the total duration is compared with the total duration of the historical aircraft landing gear retraction / retraction process, and when there is an upward trend in the total duration, a first early warning is performed;

[0011] If the overall length of the aircraft landing gear retraction / extension process exceeds a preset threshold, it is determined whether there is a landing gear door opening asynchronous condition according to the respective door opening switch preparation time, and when there is a landing gear door opening asynchronous condition, a second warning is performed.

[0012] When the first warning or the second warning exists, the position of the aircraft landing gear fault switch is located according to the change length of the respective switch.

[0013] Optionally, the aircraft landing gear parameters include a landing gear control lever selection parameter.

[0014] Further, the determination of whether the aircraft has a landing gear program recovery condition according to the aircraft landing gear parameters includes:

[0015] If the landing gear control lever selection parameter has a change of zero, it is determined that there is a landing gear program recovery condition.

[0016] Optionally, if the overall length of the aircraft landing gear retraction / extension process does not exceed a preset threshold, the overall length of the historical aircraft landing gear retraction / extension process is compared, and when there is an upward trend in the overall length, a first warning is performed, including:

[0017] The overall length of the aircraft landing gear retraction / extension process is compared with the overall length of the aircraft landing gear retraction / extension process of a plurality of historical flights to analyze whether there is an upward trend in the overall length of the aircraft landing gear retraction / extension process.

[0018] If there is an upward trend, the overall length of the aircraft landing gear retraction / extension process is recorded and a first warning message is sent.

[0019] Optionally, if the overall length of the aircraft landing gear retraction / extension process exceeds a preset threshold, it is determined whether there is a landing gear door opening asynchronous condition according to the respective door opening switch preparation time, and when there is a landing gear door opening asynchronous condition, a second warning is performed, including:

[0020] It is determined whether the difference between the respective door opening switch preparation times of the cabin door opening time, the landing gear operation time, the cabin door closing start time, and the cabin door complete closing time exceeds three seconds; wherein the respective doors include left front door, right front door, left door, and right door.

[0021] If the difference between the respective door opening switch preparation times of the respective doors exceeds three seconds, it is determined that there is a landing gear door opening asynchronous condition.

[0022] When there is a landing gear door opening asynchronous condition, the landing gear door opening asynchronous condition is recorded and a second warning message is sent.

[0023] Optionally, the positioning of the aircraft landing gear fault switch according to the change duration of each switch comprises:

[0024] When any of the left door opening duration, front left door opening duration, front right door opening duration and right door opening duration exceeds the first preset threshold, the position of the aircraft landing gear fault switch is determined as the switch corresponding to the opening door;

[0025] When any of the left landing gear operation duration, front landing gear operation duration and right landing gear operation duration exceeds the second preset threshold, the position of the aircraft landing gear fault switch is determined as the switch corresponding to the landing gear;

[0026] When any of the left door closing duration, front door closing duration and right door closing duration exceeds the third preset threshold, the position of the aircraft landing gear fault switch is determined as the switch corresponding to the landing door.

[0027] Optionally, the aircraft landing gear fault warning method further comprises:

[0028] Recording whether the aircraft landing gear program recovery exists, whether the aircraft landing gear door opening is asynchronous, the stage of the aircraft landing gear fault warning and the position of the aircraft landing gear fault switch, and outputting the recording results to the maintenance personnel;

[0029] Generating a visual image based on the recording results to show the stage of the aircraft landing gear fault warning and the position of the aircraft landing gear fault switch.

[0030] To solve the above technical problems, the embodiment of the present application further provides an aircraft landing gear fault warning system, comprising:

[0031] A parameter extraction module is configured to collect flight data of an aircraft and obtain aircraft landing gear parameters;

[0032] A landing gear program recovery detection module is configured to determine whether the aircraft landing gear program recovery exists according to the aircraft landing gear parameters;

[0033] A duration calculation module is configured to calculate the switch preparation time of each opening door, the change duration of each switch and the total duration of the aircraft landing gear retraction / extension process if the aircraft landing gear program recovery exists;

[0034] A total duration detection module is configured to determine whether the total duration of the aircraft landing gear retraction / extension process exceeds a preset threshold;

[0035] The first early warning module is configured to compare the total time length of the landing gear retraction / extension process with the total time length of historical landing gear retraction / extension processes, and perform the first early warning when the total time length has an upward trend.

[0036] The second early warning module is configured to determine whether the landing gear doors are out of synchronization according to the door preparation time of each door when the total time length of the landing gear retraction / extension process exceeds the preset threshold, and perform the second early warning when the landing gear doors are out of synchronization.

[0037] The fault positioning module is configured to locate the position of the faulty landing gear door according to the change time of each door when the first early warning or the second early warning occurs.

[0038] To solve the above technical problems, an embodiment of the present application further provides a terminal device, which comprises a processor, a memory, and a computer program stored in the memory and configured to be executed by the processor, and the processor implements the aircraft landing gear fault early warning method according to any one of the above embodiments when executing the computer program.

[0039] To solve the above technical problems, an embodiment of the present application further provides a computer readable storage medium, which comprises a stored computer program, wherein the computer readable storage medium controls the device where the computer readable storage medium is located to execute the aircraft landing gear fault early warning method according to any one of the above embodiments when the computer program runs.

[0040] Compared with the prior art, the aircraft landing gear fault early warning method, system, device and medium provided by the embodiment of the present application can first accurately monitor the retraction / extension process of the landing gear, identify the total time length of the abnormality, early warn potential faults, analyze the data of multiple flights, identify the trend change of the landing gear retraction / extension time, and early warn possible faults by analyzing the trend change. Meanwhile, the synchronization of each door operation is monitored to identify whether there is an asynchronous or timeout abnormality. The position of the faulty landing gear door is located in time according to the time change of each door. The early warning mechanism of the present application can predict the possible wear and tear of the landing gear and perform maintenance in advance, significantly enhances the safety of flight, effectively avoids potential risks caused by landing gear faults, identifies abnormal faults of the landing gear in the first time, and accurately investigates the faulty door, which not only greatly shortens the time required for fault diagnosis and repair, but also improves the overall efficiency of maintenance work, thereby reducing the maintenance cost. BRIEF DESCRIPTION OF DRAWINGS

[0041] In order to more clearly illustrate the technical solutions of the present application, the drawings used in the embodiments will be briefly introduced as follows. Obviously, the drawings described below are only some embodiments of the present application, and all other drawings obtained by those of ordinary skill in the art without creative effort based on these drawings are within the scope of the present application.

[0042] Figure 1 is a flowchart of the aircraft landing gear stowing process provided by the embodiment of the present application;

[0043] Figure 2 is a flowchart of the aircraft landing gear extension process provided by the embodiment of the present application;

[0044] Figure 3 is a flowchart of the aircraft landing gear failure early warning method provided by the embodiment of the present application;

[0045] Figure 4 is another flowchart of the aircraft landing gear failure early warning method provided by the embodiment of the present application;

[0046] Figure 5 is a structural block diagram of the aircraft landing gear failure early warning system provided by the embodiment of the present application;

[0047] Figure 6 is a structural block diagram of the terminal device provided by the embodiment of the present application. DETAILED DESCRIPTION

[0048] The technical solutions in the embodiments of the present application will be described clearly and completely below with reference to the drawings in the embodiments of the present application. Obviously, the described embodiments are only some of the embodiments of the present application, but not all the embodiments. Based on the embodiments in the present application, all other embodiments obtained by those of ordinary skill in the art without creative effort are within the scope of the present application.

[0049] It should be noted that, referring to Figures 1-2 , Figure 1 is a flowchart of the aircraft landing gear stowing process provided by the embodiment of the present application, Figure 2 is a flowchart of the aircraft landing gear extension process provided by the embodiment of the present application. As shown in Figure 1 , the process of the aircraft landing gear stowing is divided into three stages in total:

[0050] The first stage (PH1) is from the confirmation of landing gear collection procedure (i.e. the gear selection up parameter GEAR SELECTION UP (LEVER POSITION) 1 or 2 signal changes from 0 to 1) through the pull rod (handle UP), the cabin door starts to open, and the Tr00 moment program starts; After the program starts, the door lock state of the front left door 1, the front right door 2, the left door 3, and the right door 4 is detected, and each door has two door locks. When the state of both door locks changes to 1, the landing gear collection work starts. Taking the left door as an example, the two door locks 33 and 35GA of the left door change to 1 at the same time at Tr01 moment, and the landing gear collection work starts. The left door time tr01 = Tr01-Tr00.

[0051] The second stage (PH2) is the landing gear collection, at this time the landing gear collection solenoid supply parameter LG_SOL_R_P_L1 or LG_SOL_R_P_L2 changes from 0 to 1. Taking the left landing gear as an example, Tr10 starts to execute the left landing gear collection work, and the two door locks 09 and 11GA of the left landing gear change to 0 at the same time at Tr11 moment, indicating that the left landing gear collection work is completed. The time for collecting the left landing gear is tr11 = Tr11-Tr10.

[0052] The third stage (PH3) is when all the landing gear collection work is completed, at this time the landing gear door closing solenoid supply parameter LG_DOOR_C_P_L1 or LG_DOOR_C_P_L2 changes from 0 to 1, and the door corresponding to the landing gear locking state changes to 0 at the same time. At this time, the landing gear door starts to enter the closing program, and after all the landing gears are collected and placed, the door is in a completely closed state. Taking the left door as an example, the doors 27 and 29GA corresponding to the left landing gear locking state change to 0 at the same time, and at this time the left landing gear door starts to enter the closing program. The left door time tr21 = Tr21-Tr20.

[0053] Similarly, as shown in Figure 2 The process of placing the landing gear of the aircraft is divided into three stages:

[0054] The first stage (PH1) is that the cabin door starts to open when the landing gear is confirmed to be released by the pull rod (handle DOWN), that is, the gear selection is down parameter GEAR SELECTION DOWN (LEVER POSITION) 1 or 2 signal changes from 0 to 1, and the program starts at the time Te00; after the program starts, the states of the electric door locks of the front left door 1, the front right door 2, the left door 3 and the right door 4 are detected, and when the states of the two electric door locks of each door change to 1, the landing gear release work starts. Taking the left door as an example, the two electric door locks 33 and 35GA of the left door change to 1 at the same time at the time Te01, and the landing gear release work starts, and the left door time te01=Te01-Te00.

[0055] The second stage (PH2) is that the landing gear starts to release, and the landing gear release solenoid supply parameter LG_SOL_E_P_L1 or LG_SOL_E_P_L2 changes from 0 to 1. Taking the left landing gear as an example, the left landing gear release work starts at the time Te10, and the two electric door locks 09 and 11GA of the left landing gear change to 0 at the same time at the time Te11, which indicates that the left landing gear release work is completed, and the left landing gear release time te11=Te11-Te10.

[0056] The third stage (PH3) is that when all the landing gear release work is completed, the landing gear cabin door closing solenoid supply parameter LG_DOOR_C_P_L1 or LG_DOOR_C_P_L2 changes from 0 to 1, and the electric door for controlling the corresponding landing gear locking state changes to 0 at the same time, at which time the landing gear cabin door starts to enter the closing program, and the cabin door is in a completely closed state after all the landing gears are released. Taking the left door closing as an example, the electric doors 27 and 29GA for controlling the left landing gear locking state change to 0 at the same time, at which time the left landing gear cabin door starts to enter the closing program, and the left door closing time te21=Te21-Te20.

[0057] Referring to Figure 3 , Figure 3 is a flowchart of a method for early warning of aircraft landing gear failure provided by an embodiment of the application, and the method for early warning of aircraft landing gear failure comprises steps S1 to S7:

[0058] S1, collect flight data of an aircraft to obtain aircraft landing gear parameters;

[0059] Specifically, the aircraft landing gear parameters comprise a landing gear control lever selection parameter.

[0060] For example, the flight data of the aircraft can be collected by a QAR system on the aircraft, so as to obtain parameters related to the landing gear, including the landing gear control lever selection parameter.

[0061] S2, judging whether the aircraft landing gear program recovery situation exists according to the aircraft landing gear parameters;

[0062] Specifically, the judging whether the aircraft landing gear program recovery situation exists according to the aircraft landing gear parameters comprises:

[0063] If the landing gear control lever selection parameter exists a change of zero, it is judged that the landing gear program recovery situation exists.

[0064] It should be noted that for the landing gear program recovery situation, the subsequent state and the landing gear collection / launching time length after recovery can be concerned through the QAR data to judge whether the door opening exists a fault or an aging risk, so as to exclude the fault false alarm situation caused by the aircraft crew operating air.

[0065] Exemplarily, the time when the state of the landing gear control lever switch changes to 1 indicates that the landing gear collection / launching enters the recovery program, the time and the number of times of entering the recovery program of this flight are recorded by newly calculating the time of each state switch, and the abnormal message is sent to the maintenance personnel. If there is no time when the state of the landing gear downlock switch changes to 1, it is judged that the landing gear recovery situation does not exist in this flight.

[0066] S3, if the aircraft landing gear program recovery situation exists, the preparation time of each door switch, the change time length of each switch and the overall time length of the aircraft landing gear collection / launching process from the program recovery to the complete closing of all landing gear doors are calculated;

[0067] It should be noted that if the landing gear collection / launching process of the aircraft exists a switch fault, a component aging situation and the like, the position of the landing gear fault can be quickly located by detecting the collection / launching time of each switch, so as to help the maintenance personnel to lock the fault switch and save the fault checking time.

[0068] S4, judging whether the overall time length of the aircraft landing gear collection / launching process exceeds a preset threshold;

[0069] It should be noted that by analyzing the fault maintenance data of 50 A320 aircrafts in the past year and the flight data of normal flights, the inventors find that if the overall time length of the aircraft landing gear collection exceeds 16 seconds or the overall time length of the aircraft landing gear launching exceeds 20 seconds, there is a high probability that the landing gear is in a fault state and needs to be checked by the maintenance personnel in time. Therefore, the overall time length threshold of the aircraft landing gear collection can be set to 16 seconds, and the overall time length threshold of the aircraft landing gear launching can be set to 20 seconds.

[0070] S5, if the total length of the aircraft landing gear retraction / extension process does not exceed the preset threshold, comparing with the total length of the historical aircraft landing gear retraction / extension process, and when the total length has an upward trend, a first warning is given;

[0071] Specifically, the first warning when the total length of the aircraft landing gear retraction / extension process does not exceed the preset threshold and the total length has an upward trend includes:

[0072] Comparing the total length of the aircraft landing gear retraction / extension process with the total length of the aircraft landing gear retraction / extension process of several historical flights to analyze whether the total length of the aircraft landing gear retraction / extension process has an upward trend;

[0073] If there is an upward trend, the total length of the aircraft landing gear retraction / extension process is recorded and a first warning message is sent.

[0074] It is worth noting that if the total length of the aircraft landing gear retraction / extension does not exceed the set 16 seconds and 20 seconds, the landing gear retraction / extension data of the aircraft before the flight is monitored. Under the premise of excluding route and weather interference, the overall trend of the aircraft landing gear retraction / extension length will gradually increase when the landing gear is about to fail. By paying special attention to the potential impact of shock strut compression switches on the landing gear, it is found that the trend change of the total length of the landing gear retraction / extension can be used to observe the aging and wear of the landing gear components of the aircraft in real time. Therefore, by establishing a landing gear data QAR database, each flight, each side landing gear, and each landing gear retraction / extension time can be continuously monitored, so that the abnormal change trend of the data can be found in advance through the time change curve, and timely warning and troubleshooting can be performed.

[0075] S6, if the total length of the aircraft landing gear retraction / extension process exceeds the preset threshold, determining whether there is an out-of-sync situation of the landing gear door opening according to the switch preparation time of each door opening, and when there is an out-of-sync situation of the landing gear door opening, a second warning is given;

[0076] Specifically, the second warning when the total length of the aircraft landing gear retraction / extension process exceeds the preset threshold and there is an out-of-sync situation of the landing gear door opening includes:

[0077] Confirming whether the difference between the switch preparation time of each door opening at the door opening time, the landing gear operation time, the door closing start time, and the door completely closing time exceeds three seconds; wherein the each door opening includes the left front door opening, the right front door opening, the left door opening, and the right door opening;

[0078] If the difference in the preparation time of the electric switches of each door exceeds three seconds, it is determined that there is a situation of asynchronous opening of the landing gear doors.

[0079] When there is a situation where the landing gear doors are not opened in sync, the situation is recorded and a second warning message is sent.

[0080] It should be noted that since the landing gear retraction / extension procedure is initiated simultaneously, the difference in preparation time can be captured by monitoring the status of different switches at the same stage. By capturing the preparation times of the four door opening positions (left front, right front, left, and right) during the landing gear retraction / extension phase, it is possible to help determine the impact of aging phenomena on the specific door opening side on the overall landing gear retraction / extension duration. If the preparation times of the four doors are not synchronized, it indicates a possible landing gear door opening asynchrony fault. Subsequently, the location of delayed door opening (i.e., door opening time exceeding 3 seconds) can be used to help maintenance personnel locate the landing gear aging switch. Furthermore, when the aircraft lands, QAR data can be promptly used to inform relevant maintenance personnel to investigate the landing gear faults of the aircraft, ensuring the landing gear safety status of the entire flight.

[0081] S7. When the first warning or the second warning exists, locate the position of the aircraft landing gear fault switch according to the duration of the change of each switch.

[0082] Specifically, locating the position of the aircraft landing gear malfunction switch based on the duration of change of each switch includes:

[0083] When any of the following durations exceeds the first preset threshold: the duration of the left door opening, the duration of the front left door opening, the duration of the front right door opening, and the duration of the right door opening, the position of the aircraft landing gear malfunction switch is determined to be the switch corresponding to the door opening.

[0084] When any one of the following durations exceeds the second preset threshold, the position of the aircraft landing gear fault switch is determined to be the switch of the corresponding landing gear.

[0085] When any of the closing times used for the left door, the front door, or the right door exceeds a third preset threshold, the position of the aircraft landing gear malfunction switch is determined to be the switch of the corresponding landing door.

[0086] In one optional embodiment, the landing gear failure early warning method further includes:

[0087] Record whether the aircraft has lander program reset status, whether the landing gear doors are not synchronized, the stage of the aircraft landing gear failure warning, and the location of the aircraft landing gear failure switch, and output the recorded results to maintenance personnel.

[0088] Based on the recorded results, a visual image is generated to show the stages of the aircraft landing gear failure warning and the location of the aircraft landing gear failure switch.

[0089] It is worth noting that in the above steps, after screening out flights that may have landing gear abnormalities by detecting the overall landing gear retraction / extension time, in order to reduce the workload of maintenance personnel in checking specific switches, the time of each switch status change can be monitored to help maintenance personnel locate the faulty switch. The retraction / extension state of each switch consists of two states, 0 and 1. When both sets of sensors of each switch are 0 at the same time, the switch is locked and the program starts to execute the specific retraction / extension work. In this process, the 1-0 transition process takes a certain amount of time. For example, when the 33 and 35GA switches of the left door change to 1 at the same time during the landing gear extension process, the left door starts to execute the landing gear extension procedure. The time from the start of the program to the start of the extension is recorded as t01 time. When t01 time exceeds 3 seconds, it is judged that there is a risk of wear and aging in the left switch for extending the landing gear. Analysis of QAR data reveals 20 switch transition times related to landing gear retraction / extension. Therefore, by monitoring the time changes of these 20 switches in real time, the location of the faulty switch in the landing gear can be pinpointed promptly, thus helping maintenance personnel to locate the specific faulty switch and saving troubleshooting time.

[0090] In summary, the aircraft landing gear malfunction early warning method provided by this invention first identifies the total duration of abnormalities by accurately monitoring the landing gear retraction / extension process, thus providing early warning of potential malfunctions. It analyzes data from multiple flights to identify trends in landing gear retraction / extension time, and by analyzing these trends, it can provide early warnings of potential malfunctions. Simultaneously, it monitors the synchronicity of each door opening operation to identify any asynchronous or timeout anomalies. Furthermore, it locates the faulty switch position based on the time changes of each switch. Finally, it generates early warning messages and 3D images based on the fault results, visually displaying the stage and location of the malfunction. Compared to traditional technologies, this invention, by monitoring the changing status data of the aircraft landing gear switches in real time, can quickly capture abnormalities during the landing gear retraction / extension process. Once a potential problem is detected, an early warning signal is immediately issued, reminding the crew to take timely countermeasures. This real-time monitoring and early warning mechanism significantly enhances flight safety and effectively avoids potential risks caused by landing gear malfunctions. Furthermore, this invention goes beyond simply responding to malfunctions; it emphasizes preventative maintenance. By real-time monitoring of multiple switch performance parameters and analysis of switch degradation trends, it can predict potential landing gear wear and other problems, allowing for proactive maintenance. This forward-looking maintenance strategy not only extends the landing gear's lifespan but also significantly reduces flight delays or cancellations caused by sudden malfunctions, thereby improving overall flight safety and operational efficiency. Finally, compared to the traditional, complex, and time-consuming manual troubleshooting process, this invention provides a rapid and accurate fault detection and troubleshooting mechanism. It can identify landing gear anomalies immediately and precisely diagnose faulty switches. This efficient mechanism not only significantly reduces the time required for fault diagnosis and repair but also improves the overall efficiency of maintenance work, thereby reducing maintenance costs.

[0091] See Figure 4 , Figure 4 This is another flowchart of an aircraft landing gear failure early warning method provided by an embodiment of the present invention. Figure 4 As shown, the steps for detecting whether an aircraft has a landing gear malfunction during a flight using the aircraft landing gear malfunction early warning method provided in this embodiment of the invention are as follows:

[0092] Step 1: Collect aircraft flight data using the aircraft's QAR system, generate an HDF5 file, and then use the Python h5py package to read the RecordedParameters field to obtain landing gear-related parameters. For example, the obtained parameters are shown in Table 1:

[0093] Table 1 Aircraft landing gear parameters

[0094]

[0095]

[0096]

[0097] It is worth noting that, based on QAR flight data, rich data can be obtained through decoding, providing a foundation for real-time monitoring of the status of various systems and components. Detailed fault data can be output to form early warning messages, and in the future, visualized 3D full-frame images can be developed to intuitively display the stage and location of the fault. Furthermore, a QAR database can be established to continuously monitor the landing gear retraction / extension data trends, thereby enabling early detection of potential anomalies and early warning troubleshooting, greatly improving efficiency and accuracy.

[0098] Step 2: Detect the landing gear recovery procedure. Check if the two landing gear control stick selection parameters LDG_SELDW and LDG_SELDW2 in the extracted parameters change to 0. If so, it means that the aircraft landing gear recovery procedure has been activated. Record the number of times the procedure is activated (the parameter changes from 1 to 0 and then back to 1, which means the recovery procedure has been activated once). Monitor the situation after the landing gear procedure is activated after the last recovery, and proceed to Step 3.

[0099] Step 3: Calculate the preparation time of each door opening switch, the duration of each switch change, and the total duration of the aircraft landing gear retraction / extension process from the start of program recovery to the complete closure of all landing gear doors.

[0100] It should be noted that the aircraft landing gear restoration procedure mainly includes two procedures: retracting the landing gear and extending the landing gear.

[0101] For example, when the aircraft landing gear recovery procedure is to retract the landing gear, the time of change of each electrical switch status position of the aircraft landing gear is calculated using the cross method. Based on the duration of each switch change, the time taken for the left door to open (Tr01), the time taken for the front left door to open (Tr02), the time taken for the front right door to open (Tr03), and the time taken for the right door to open (Tr04) are calculated during the change from the moment the landing gear door begins to open (Tr00) to the moment the landing gear begins to retract (Tr10). Then, the time taken for the landing gear to retract (Tr10) is calculated. During the process from the moment the hatch begins to close (Tr20), calculate the time taken for the left door to retract (Tr11), the time taken for the front door to retract (Tr12), and the time taken for the right door to retract (Tr13). Then, calculate the closing time taken for the left door (Tr21), the closing time taken for the front door (Tr22), and the closing time taken for the right door (Tr23) from the moment the hatch begins to close (Tr20) to the moment the hatch is fully closed (Tr30). Record the time required for all hatches to be fully closed from the start of the procedure as the total time required to retract the landing gear.

[0102] For example, when the aircraft landing gear restoration procedure is to extend the landing gear, the time for the change of each switch status position is calculated using the cross method. The duration of each small switch change is used to calculate the time taken for the four landing gear doors to open from time Te00 to time Te10 when the landing gear doors begin to extend. The time taken for the left door to open is Te01, the time taken for the front left door to open is Te02, the time taken for the front right door to open is Te03, and the time taken for the right door to open is Te04. Then, the time taken for the left door to extend is Te11, the time taken for the front door to extend is Te12, and the time taken for the right door to extend is Te13 from time Te10 when the landing gear begins to extend to time Te20 when the doors begin to close. Then, the closing time taken for the left door to close is Te21, the closing time taken for the front door to close is Te22, and the closing time taken for the right door to close is Te23 from time Te20 when the doors begin to close to time Te30 when the doors are fully closed is calculated. The total time required for all doors to close completely from the start of the procedure is recorded as the total time required for extending the landing gear.

[0103] Step 4: Determine whether the total duration of the aircraft landing gear retraction / extension process exceeds the set threshold. For example, if the total duration of the aircraft landing gear retraction exceeds the set threshold of 16 seconds, or the total duration of the aircraft landing gear extension exceeds the set threshold of 20 seconds, it is preliminarily determined that the aircraft landing gear assembly has malfunctioned; if it does not exceed the set threshold, it is preliminarily determined that the landing gear assembly has not malfunctioned.

[0104] Step 5: If the total landing gear retraction / extension time does not exceed the threshold in Step 4, the total time of the aircraft's landing gear retraction / extension process is entered into the database. The total time of landing gear retraction / extension for the previous 15 flights of the same aircraft is compared to analyze whether there is an upward trend in the total retraction / extension time. If there is an upward trend, it is recorded and the aircraft maintenance personnel are notified that the aircraft may have a landing gear failure risk.

[0105] Step Six: If the total landing gear retraction / extension time exceeds the threshold in Step Four, then check whether the switch preparation times for the left front door, right front door, left door, and right door during the landing gear retraction / extension process differ by more than 3 seconds. If the difference exceeds 3 seconds, record that the aircraft is suspected of having a landing gear door opening asynchrony and issue a warning to the aircraft maintenance personnel.

[0106] Step 7: If a fault warning occurs during the above steps, further locate the position of the aircraft landing gear fault switch.

[0107] For example, if the landing gear failure occurs during the aircraft's landing gear retraction process, the location of the faulty switch can be located using the ten individual time recording modules (Tr01-Tr04, Tr11-Tr13, Tr21-Tr23) calculated in step three. Specifically, if the left door opening time (Tr01), the front left door opening time (Tr02), the front right door opening time (Tr03), and the right door opening time (Tr04) exceed 4 seconds, it indicates a fault in the corresponding door opening switch; if the time taken to retract the left landing gear (Tr11), the front landing gear (Tr12), and the right landing gear (Tr13) exceeds 13 seconds, it indicates a fault in the corresponding landing gear switch; and if the closing time taken to close the left door (Tr21), the front door (Tr22), and the right door (Tr23) exceeds 3 seconds, it indicates a fault in the corresponding door switch.

[0108] For example, if the landing gear failure occurs during the aircraft's landing gear deployment process, the location of the faulty switch can also be located using the ten individual time recording modules (Te01-Te04, Te11-Te13, Te21-Te23) calculated in step three. Specifically, if any of the following durations—left door opening time Te01, front left door opening time Te02, front right door opening time Te03, and right door opening time Te04—exceeds 4 seconds, it indicates a fault in the corresponding door's opening switch; if the durations Te11, Te12, and Te13 for left and front landing gear deployment exceed 16 seconds, it indicates a fault in the corresponding landing gear's opening switch; and if the closing durations Te21, Te22, and Te23 for left, front, and right doors exceed 3 seconds, it indicates a fault in the corresponding door's opening switch.

[0109] Step 8: Record the landing gear malfunction warning stage (landing gear retraction / extension), the location of the fault switch, whether a recovery procedure has been performed, and whether there is any door opening asynchrony during the above steps for the flight experiencing the malfunction. Output the recorded results to maintenance personnel. Alternatively, the data from each flight's three landing gear units (left, front, and right) per second can be used to generate a warning message, and a visualized 3D full-frame image can be created using specific location information to intuitively show the stage of the landing gear malfunction and the location of the fault switch.

[0110] It is worth noting that the key feature of the aircraft landing gear failure early warning system provided in this embodiment of the invention lies in applying QAR (Quick Access Recorder) data to the real-time failure detection of aircraft landing gear. By deeply mining the useful information in the QAR data, the health status of the landing gear can be comprehensively assessed, and an alarm can be immediately issued to the crew when an abnormality is detected. This not only improves the timeliness of failure detection, but also provides strong support for taking timely preventive measures, thereby ensuring the stable operation of the aircraft and the safety of passengers.

[0111] Furthermore, through meticulous feature engineering, the system can monitor the real-time status changes of each landing gear switch. By monitoring the synchronization of switch states and transition times after the landing gear retraction / extension procedure is initiated, it can pinpoint which switch might be aging or malfunctioning, thus enabling precise location of the faulty switch. Special data processing is applied to recurring flights, recording and analyzing the control duration of each landing gear retraction / extension switch after each occurrence to detect anomalies. This significantly simplifies the troubleshooting process, allowing maintenance personnel to quickly pinpoint the fault location and initiate repairs. This not only significantly reduces the time and manpower required for manual troubleshooting but also helps maintenance teams plan maintenance schedules in a timely manner, effectively reducing the risk of malfunctions and ensuring normal flight operations.

[0112] Based on the above method items, the present invention provides corresponding system items embodiments.

[0113] See Figure 5 , Figure 5 This is a structural block diagram of an aircraft landing gear failure early warning system provided in an embodiment of the present invention. The aircraft landing gear failure early warning system includes:

[0114] The parameter extraction module 21 is used to collect the aircraft's flight data and obtain the aircraft's landing gear parameters.

[0115] The landing gear program restoration detection module 22 is used to determine whether the aircraft has a landing gear program restoration situation based on the aircraft landing gear parameters.

[0116] The duration calculation module 23 is used to calculate the preparation time of each door switch, the change duration of each switch, and the total duration of the aircraft landing gear retraction / extension process from the start of the program restoration to the complete closure of all landing gear doors if the aircraft has a landing gear program restoration.

[0117] The overall duration detection module 24 is used to determine whether the overall duration of the aircraft landing gear retraction / extension process exceeds a preset threshold.

[0118] The first early warning module 25 is used to compare the total duration of the aircraft landing gear retraction / extension process with the historical total duration of the aircraft landing gear retraction / extension process if the total duration does not exceed a preset threshold, and to issue a first early warning when the total duration shows an upward trend.

[0119] The second early warning module 26 is used to determine whether there is a situation of asynchronous landing gear door opening based on the switch preparation time of each door if the total duration of the aircraft landing gear retraction / extension process exceeds a preset threshold. When there is a situation of asynchronous landing gear door opening, a second early warning is issued.

[0120] The fault location module 27 is used to locate the position of the aircraft landing gear fault switch according to the duration of change of each switch when the first warning or the second warning is present.

[0121] As an improvement to the above solution, the aircraft landing gear failure early warning system further includes:

[0122] The fault warning result output module is used to record whether the aircraft has a landing gear program reset, whether the landing gear door opening is out of sync, the stage of the aircraft landing gear fault warning, and the position of the aircraft landing gear fault switch, and outputs the recorded results to maintenance personnel.

[0123] The fault warning visualization module generates a visualization image based on the recorded results, showing the stage of the aircraft landing gear fault warning and the location of the aircraft landing gear fault switch.

[0124] Specifically, the aircraft landing gear parameters include landing gear control stick selection parameters.

[0125] Furthermore, the landing gear program restoration detection module 22 is specifically used for:

[0126] If the landing gear control stick selection parameter changes to zero, it is determined that the landing gear program has been reset.

[0127] In one optional implementation, the first early warning module 25 is specifically used for:

[0128] The total duration of the aircraft landing gear retraction / extension process is compared with the total duration of the aircraft landing gear retraction / extension process for several historical flights to analyze whether there is an upward trend in the total duration of the aircraft landing gear retraction / extension process.

[0129] If an upward trend is observed, the total duration of the aircraft landing gear retraction / extension process is recorded and a first warning message is sent.

[0130] In one optional implementation, the second early warning module 26 is specifically used for:

[0131] Confirm whether the difference in the electrical preparation time of each door opening—the opening time of the hatch, the landing gear operation time, the hatch starting to close time, and the hatch fully closing time—exceeds three seconds; wherein each door opening includes the left front door, the right front door, the left door, and the right door.

[0132] If the difference in the preparation time of the electric switches of each door exceeds three seconds, it is determined that there is a situation of asynchronous opening of the landing gear doors.

[0133] When there is a situation where the landing gear doors are not opened in sync, the situation is recorded and a second warning message is sent.

[0134] In one optional embodiment, the fault location module 27 is specifically used for:

[0135] When any of the following durations exceeds the first preset threshold: the duration of the left door opening, the duration of the front left door opening, the duration of the front right door opening, and the duration of the right door opening, the position of the aircraft landing gear malfunction switch is determined to be the switch corresponding to the door opening.

[0136] When any one of the following durations exceeds the second preset threshold, the position of the aircraft landing gear fault switch is determined to be the switch of the corresponding landing gear.

[0137] When any of the closing times used for the left door, the front door, or the right door exceeds a third preset threshold, the position of the aircraft landing gear malfunction switch is determined to be the switch of the corresponding landing door.

[0138] It should be noted that the aircraft landing gear failure early warning system provided in this embodiment of the invention is used to execute all the process steps of the aircraft landing gear failure early warning method in the above embodiment. The working principles and beneficial effects of the two are one-to-one, so they will not be described again.

[0139] This invention also provides a terminal device, such as... Figure 6 The diagram shows a structural block diagram of a terminal device provided in an embodiment of the present invention. The terminal device includes a processor 31, a memory 32, and a computer program stored in the memory 32 and configured to be executed by the processor 31. When the processor 31 executes the computer program, it implements the aircraft landing gear fault early warning method as described in any of the above embodiments.

[0140] In addition, embodiments of the present invention also provide a computer-readable storage medium, the computer-readable storage medium including a stored computer program, wherein, when the computer program is executed, it controls the device where the computer-readable storage medium is located to execute the aircraft landing gear failure early warning method as described in any of the above embodiments.

[0141] When the processor 31 executes the computer program, it implements the steps in the above-described embodiment of the aircraft landing gear failure early warning method, for example... Figure 3 All steps of the aircraft landing gear failure early warning method shown. Alternatively, when the processor 31 executes the computer program, it implements the functions of each module in the above-described aircraft landing gear failure early warning system embodiment, for example... Figure 5 The diagram shows the functions of each module in the aircraft landing gear fault warning system.

[0142] Preferably, the computer program can be divided into one or more modules / units, which are stored in the memory 32 and executed by the processor 31 to complete the present invention. The one or more modules / units can be a series of computer program instruction segments capable of performing specific functions, which describe the execution process of the computer program in the terminal device.

[0143] The processor 31 can be a central processing unit (CPU), or other general-purpose processors, digital signal processors (DSPs), application-specific integrated circuits (ASICs), field-programmable gate arrays (FPGAs), 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 31 can be any conventional processor. The processor 31 is the control center of the terminal device, connecting various parts of the terminal device through various interfaces and lines.

[0144] The memory 32 mainly includes a program storage area and a data storage area. The program storage area can store the operating system, applications required for at least one function, etc., and the data storage area can store related data, etc. In addition, the memory 32 can be a high-speed random access memory, or a non-volatile memory, such as a plug-in hard disk, a smart media card (SMC), a secure digital card (SD), and a flash card, etc., or the memory 32 can also be other volatile solid-state storage devices.

[0145] It should be noted that the aforementioned terminal devices may include, but are not limited to, processors and memory, as will be understood by those skilled in the art. Figure 6The structural block diagram shown is merely a structural example of the terminal device described above and does not constitute a limitation on the structure of the terminal device. The terminal device may include more or fewer components than shown, or combine certain components, or use different components.

[0146] The above description represents the preferred embodiments of the present invention. It should be noted that those skilled in the art can make various improvements and modifications without departing from the principles of the present invention, and these improvements and modifications are also considered to be within the scope of protection of the present invention.

Claims

1. A method for early warning of aircraft landing gear failure, characterized in that, include: Collect aircraft flight data and obtain aircraft landing gear parameters; Determine whether there is a situation where the aircraft landing gear program needs to be restored based on the aircraft landing gear parameters. If the aircraft is in a landing gear program reset situation, calculate the preparation time of each door opening switch, the change duration of each switch, and the total duration of the aircraft landing gear retraction / extension process from the start of the program reset until all landing gear doors are fully closed. Determine whether the total duration of the aircraft landing gear retraction / extension process exceeds a preset threshold; If the total duration of the aircraft landing gear retraction / extension process does not exceed the preset threshold, it is compared with the total duration of the historical aircraft landing gear retraction / extension process. If the total duration shows an upward trend, a first warning is issued. If the total duration of the aircraft landing gear retraction / extension process exceeds a preset threshold, the system will determine whether there is a situation of asynchronous landing gear door opening based on the preparation time of the power switches of each door. If there is a situation of asynchronous landing gear door opening, a second warning will be issued. When the first warning or the second warning is present, the location of the aircraft landing gear malfunction switch is determined based on the duration of the change in each switch.

2. The aircraft landing gear failure early warning method as described in claim 1, characterized in that, The aircraft landing gear parameters include landing gear control stick selection parameters.

3. The aircraft landing gear failure early warning method as described in claim 2, characterized in that, The step of determining whether the aircraft has a landing gear program reset based on the aircraft landing gear parameters includes: If the landing gear control stick selection parameter changes to zero, it is determined that the landing gear program has been reset.

4. The aircraft landing gear failure early warning method as described in claim 1, characterized in that, If the total duration of the aircraft landing gear retraction / extension process does not exceed a preset threshold, it is compared with the total duration of historical aircraft landing gear retraction / extension processes. When the total duration shows an upward trend, a first warning is issued, including: The total duration of the aircraft landing gear retraction / extension process is compared with the total duration of the aircraft landing gear retraction / extension process for several historical flights to analyze whether there is an upward trend in the total duration of the aircraft landing gear retraction / extension process. If an upward trend is observed, the total duration of the aircraft landing gear retraction / extension process is recorded and a first warning message is sent.

5. The aircraft landing gear failure early warning method as described in claim 1, characterized in that, If the total duration of the aircraft landing gear retraction / extension process exceeds a preset threshold, the system determines whether there is a situation of asynchronous landing gear door opening based on the switch preparation time of each door. If asynchronous landing gear door opening is detected, a second warning is issued, including: Confirm whether the difference in the electrical preparation time of each door opening—the opening time of the hatch, the landing gear operation time, the hatch starting to close time, and the hatch fully closing time—exceeds three seconds; wherein each door opening includes the left front door, the right front door, the left door, and the right door. If the difference in the preparation time of the electric switches of each door exceeds three seconds, it is determined that there is a situation of asynchronous opening of the landing gear doors. When there is a situation where the landing gear doors are not opened in sync, the situation is recorded and a second warning message is sent.

6. The aircraft landing gear failure early warning method as described in claim 1, characterized in that, The step of locating the position of the aircraft landing gear malfunction switch based on the duration of change of each switch includes: When any of the following durations exceeds the first preset threshold: the duration of the left door opening, the duration of the front left door opening, the duration of the front right door opening, and the duration of the right door opening, the position of the aircraft landing gear malfunction switch is determined to be the switch corresponding to the door opening. When any one of the following durations exceeds the second preset threshold, the position of the aircraft landing gear fault switch is determined to be the switch of the corresponding landing gear. When any of the closing times used for the left door, the front door, or the right door exceeds a third preset threshold, the position of the aircraft landing gear malfunction switch is determined to be the switch of the corresponding landing door.

7. The aircraft landing gear failure early warning method as described in claim 1, characterized in that, The aircraft landing gear failure early warning method also includes: Record whether the aircraft has lander program reset status, whether the landing gear doors are not synchronized, the stage of the aircraft landing gear failure warning, and the location of the aircraft landing gear failure switch, and output the recorded results to maintenance personnel. Based on the recorded results, a visual image is generated to show the stages of the aircraft landing gear failure warning and the location of the aircraft landing gear failure switch.

8. An aircraft landing gear failure early warning system, characterized in that, include: The parameter extraction module is used to collect aircraft flight data and obtain aircraft landing gear parameters. The landing gear program restoration detection module is used to determine whether the aircraft has a landing gear program restoration situation based on the aircraft landing gear parameters. The duration calculation module is used to calculate the preparation time of each door's switch, the duration of each switch's change, and the total duration of the aircraft's landing gear retraction / extension process from the start of the program restoration until all landing gear doors are fully closed, if the aircraft is in a landing gear program restoration situation. The overall duration detection module is used to determine whether the overall duration of the aircraft landing gear retraction / extension process exceeds a preset threshold. The first early warning module is used to compare the total duration of the aircraft landing gear retraction / extension process with the historical total duration of the aircraft landing gear retraction / extension process if the total duration does not exceed a preset threshold. If the total duration shows an upward trend, the first early warning is issued. The second early warning module is used to determine whether there is a situation of asynchronous landing gear door opening based on the switch preparation time of each door if the total duration of the aircraft landing gear retraction / extension process exceeds a preset threshold. When there is a situation of asynchronous landing gear door opening, a second early warning is issued. The fault location module is used to locate the position of the aircraft landing gear fault switch based on the duration of change of each switch when the first warning or the second warning is present.

9. A terminal device, characterized in that, The system includes a processor, a memory, and a computer program stored in the memory and configured to be executed by the processor, wherein the processor, when executing the computer program, implements the aircraft landing gear failure early warning method as described in any one of claims 1 to 7.

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, it controls the device on which the computer-readable storage medium is located to perform the aircraft landing gear failure early warning method as described in any one of claims 1 to 7.

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