Aircraft hydraulic system failure monitoring method and device and storage medium

Abstract

The invention relates to an aircraft hydraulic system failure monitoring method and device and a storage medium. The method comprises the steps that firstly, historical flight data are acquired; decoding and analyzing the historical flight data to obtain a hydraulic system pressure distribution diagram; and transversely comparing the hydraulic parameters of each flight according to the time sequence of the flight data, and judging the performance state of the hydraulic system based on the change trend of the parameters of the hydraulic system. Compared with the prior art, the system degradation sign can be observed in advance through trend monitoring, intervention is performed in advance before system failure, flight safety margin decline caused by system completion failure is avoided, flight delay AOG loss caused by system completion failure can be effectively avoided, the component overhaul occurrence rate is reduced, the maintenance cost is reduced, and economic benefits are obvious.

Description

Technical Field

[0001] The present invention relates to the technical field of aircraft condition monitoring, and in particular to a monitoring method for aircraft hydraulic system failure. Background Art

[0002] The aircraft hydraulic system provides hydraulic power for systems such as control surfaces, thrust reversers, landing gears, and brakes, and is one of the most critical systems of the aircraft. In the hydraulic system, pressure sensors, hydraulic oil temperature sensors, and oil quantity sensors are responsible for monitoring the working state of the hydraulic system together. When the system parameters are abnormally exceeded a certain threshold, a warning will be triggered. The warning types mainly include low pressure of the hydraulic pump, over-temperature of the hydraulic oil, low hydraulic oil quantity, etc.

[0003] At present, Airbus mainly monitors the hydraulic system through threshold monitoring. By sensors to sense the oil quantity, temperature, and pressure of the hydraulic system, when the oil quantity, temperature, and pressure of the hydraulic system reach the fault threshold, a fault warning is triggered. At this time, the computer automatically isolates the relevant hydraulic system, and the relevant hydraulic system fails. The hydraulic system is the "blood" of flight operations, and its importance is self-evident. The current technical means cannot meet the operation requirements of large fleets. According to statistics, from 2016 to 2020, in the statistics of abnormal events of a certain airline's A320 fleet caused by hydraulic system failures, it can be seen that there were 145 flight delays, including 45 SDR events such as return flights / alternate landings / taxiing back, and the situation of gravity lowering the landing gear during return flights occurred many times, causing huge economic losses and bad social impacts to the airline.

[0004] The existing technical means adopt threshold monitoring for the hydraulic system. Once the threshold is reached and a fault is triggered, it belongs to single-flight data monitoring. Once the system parameters reach the fault threshold and an alarm is triggered, the hydraulic system has failed, which is extremely likely to cause subsequent flight disruptions. The existing technical means cannot detect the degradation of system performance, and components work with "hidden diseases", resulting in serious "internal injuries" of components and high subsequent maintenance costs. This solution can effectively reduce the incidence of component overhauls and reduce maintenance costs. Summary of the Invention

[0005] The purpose of the present invention is to overcome the defects of the above-mentioned existing technologies and provide a monitoring method, device, and storage medium for aircraft hydraulic system failure.

[0006] The purpose of the present invention can be achieved by the following technical solutions:

[0007] As the first aspect of the present invention, a monitoring method for aircraft hydraulic system failure is provided. The method steps include:

[0008] Obtain historical flight data;

[0009] Decode and analyze the historical flight data to obtain a hydraulic system pressure distribution map;

[0010] Arrange the flight data in chronological order, compare the hydraulic parameters of each flight horizontally, and judge the performance state of the hydraulic system based on the change trend of the hydraulic system parameters.

[0011] As a preferred technical solution, the flight data includes: hydraulic system pressure, temperature, and oil quantity data.

[0012] As a preferred technical solution, the method analyzes the historical flight data after decoding and analysis using the normal distribution statistical method.

[0013] As a preferred technical solution, the abscissa of the hydraulic system pressure distribution diagram represents the maximum pressure value that appears in the hydraulic system during flight operation, and the ordinate represents the number of flights that appear under a certain specific maximum pressure value.

[0014] As a preferred technical solution, the data outside the normal distribution confidence interval is regarded as abnormal flight data.

[0015] As a preferred technical solution, if the maximum hydraulic pressure collected is outside the confidence interval, it is regarded as performance degradation.

[0016] As a preferred technical solution, the confidence interval of the normal distribution is set to 95%.

[0017] As a preferred technical solution, the method performs alarm push according to the judged performance of the hydraulic system.

[0018] As the second aspect of the present invention, there is provided a monitoring device for aircraft hydraulic system failure, including a memory, a processor, and a program stored in the memory. When the processor executes the program, it implements the monitoring method for aircraft hydraulic system failure as described above.

[0019] As the third aspect of the present invention, there is provided a storage medium, on which a program is stored. When the program is executed, it implements the monitoring method for aircraft hydraulic system failure as described above.

[0020] Compared with the prior art, the present invention has the following beneficial effects:

[0021] 1) For the prior art means, the hydraulic system is monitored using thresholds. Once the threshold is reached and a failure is triggered, it belongs to single-flight data monitoring. Once the system parameters reach the failure threshold and an alarm is triggered, the hydraulic system has failed. This solution can observe the signs of system degradation in advance through trend monitoring, intervene in advance before the system fails, and avoid the reduction of flight safety margin caused by the complete failure of the system.

[0022] 2) In the existing technical means, once a hydraulic system failure warning is detected, it is very likely to cause subsequent flight disruptions. (The hydraulic system is an important system of the aircraft and does not allow failure.) This solution can effectively reduce the AOG losses caused by flight delays due to system failures, and the economic benefits are obvious.

[0023] 3) The existing technical means cannot detect the degradation of system performance, and components work with "hidden diseases", resulting in serious "internal injuries" to the components and high subsequent maintenance costs. This solution can effectively reduce the incidence of component overhauls and reduce maintenance costs. BRIEF DESCRIPTION OF THE DRAWINGS

[0024] Figure 1 is a flowchart of the monitoring method for the failure of the aircraft hydraulic system of the present invention;

[0025] Figure 2 is a hydraulic performance degradation trend chart obtained in one of the preferred embodiments of the present invention;

[0026] Figure 3 is a hydraulic system pressure distribution diagram obtained in one of the preferred embodiments of the present invention;

[0027] Figure 4 is a B69XX hydraulic pressure trend chart in one of the embodiments of the present invention. DETAILED DESCRIPTION OF THE INVENTION

[0028] The present invention will be described in detail below with reference to the accompanying drawings and specific embodiments. This embodiment is implemented on the premise of the technical solution of the present invention, and detailed implementation methods and specific operation processes are given, but the protection scope of the present invention is not limited to the following embodiments.

[0029] Embodiment 1

[0030] This solution uses trend monitoring for monitoring, and its specific steps are as Figure 1 described:

[0031] Trend monitoring: Collect data such as the pressure, temperature, and oil volume of the hydraulic system of flights, and compare the hydraulic parameters of each flight horizontally in chronological order of time for each flight. As Figure 2 shown, by observing the change trend of the hydraulic system parameters, the performance state of the hydraulic system is judged.

[0032] Using the normal distribution statistical method, through big data analysis software, for example: by statistically analyzing more than 1 million flight data decodes of the A320 fleet from 2018 to 2020, a hydraulic system pressure distribution diagram is obtained, as Figure 3As shown, the abscissa represents the maximum pressure value of the green system during flight operation, and the ordinate represents the number of flights occurring at a certain specific maximum pressure value. Taking the green system as an example: during more than 700,000 flight operations, the maximum pressure value of the green system is 3008 PSI. It can be clearly seen from the figure that the hydraulic pressure distribution presents a normal distribution, with a higher frequency in the middle (2944 - 3200 PSI) and a smaller probability on both sides (excessive pressure / too low pressure). The 95% confidence interval is commonly used, which can be understood as 95% of the data of the maximum hydraulic pressure collected are considered reasonable and normal data, while the excessive and too low pressure data are regarded as abnormal flight data. The normal distribution range of hydraulic pressure, 2880 - 3200 PSI, is regarded as the normal interval, and values outside this interval are regarded as performance degradation.

[0033] Embodiment 2

[0034] On May 23, 2021, for aircraft B - 69XX, the crew taxied out to the runway, and an over - temperature fault of the grease box was reflected on the ECAM. The right - hand engine EDP was shut down. Due to the loss of hydraulic power, it was finally found that the shaft of the yellow system hydraulic pump was broken. After sending it to the factory for repair, it was determined that the spline shaft of the EDP cracked and broke due to long - term fatigue stress.

[0035] In this fault case, the pressure of the aircraft hydraulic system was always lower than the output pressure of other hydraulic systems throughout the flight, and the hydraulic temperature was on the high side. Through data analysis, it was found that the pressure trend of the hydraulic system of this aircraft was abnormal. As Figure 4 shown, it did not reach the pump low - pressure and hydraulic system fault trigger thresholds, and the existing technical means could not detect the problem. On the other hand, it also shows that this solution can detect system defects in advance.

[0036] Embodiment 3

[0037] As a second aspect of the present invention, the present application also provides an electronic device, including: one or more processors; a memory for storing one or more programs; when the one or more programs are executed by the one or more processors, the one or more processors implement the monitoring method for aircraft hydraulic system failure as described above. In addition to the above - mentioned processors, memory, and interfaces, any device with data - processing capabilities where the device in the embodiment is located usually includes other hardware according to the actual functions of the device with data - processing capabilities, which will not be elaborated here.

[0038] Embodiment 4

[0039] As a third aspect of the present invention, the present application further provides a computer-readable storage medium, on which computer instructions are stored, and when the instructions are executed by a processor, the monitoring method for the failure of the aircraft hydraulic system as described above is implemented. The computer-readable storage medium may be an internal storage unit of any device with data processing capabilities described in any of the foregoing embodiments, such as a hard disk or a memory. The computer-readable storage medium may also be an external storage device, such as a plug-in hard disk, a Smart Media Card (SMC), an SD card, a Flash Card, etc. equipped on the device. Further, the computer-readable storage medium may also include both an internal storage unit of any device with data processing capabilities and an external storage device. The computer-readable storage medium is used to store the computer program and other programs and data required by any device with data processing capabilities, and may also be used to temporarily store the data that has been output or will be output.

[0040] The preferred specific embodiments of the present invention have been described in detail above. It should be understood that those of ordinary skill in the art can make many modifications and variations based on the concept of the present invention without creative work. Therefore, all technical solutions that can be obtained by those skilled in the art in the technical field of the present invention through logical analysis, reasoning, or limited experiments based on the concept of the present invention on the basis of the prior art should fall within the protection scope determined by the claims.

Claims

1. A monitoring method for the failure of an aircraft hydraulic system, characterized in that, The method steps include: Obtain historical flight data; Decode and analyze the historical flight data to obtain a hydraulic system pressure distribution map; Arrange the flight data in chronological order, horizontally compare the hydraulic parameters of each flight, and judge the performance status of the hydraulic system based on the change trend of the hydraulic system parameters.

2. The monitoring method for the failure of an aircraft hydraulic system according to claim 1, characterized in that The flight data described includes: hydraulic system pressure, temperature, and oil quantity data.

3. A monitoring method for the failure of an aircraft hydraulic system according to claim 1, characterized in that, The method analyzes the historical flight data after decoding and analysis using a normal distribution statistical method.

4. A monitoring method for the failure of an aircraft hydraulic system according to claim 3, characterized in that, The abscissa of the hydraulic system pressure distribution map represents the maximum pressure value that appears in the hydraulic system during flight, and the ordinate represents the number of flights that appear under a certain specific maximum pressure value.

5. The monitoring method for the failure of an aircraft hydraulic system according to claim 3, characterized in that, The data outside the normal distribution confidence interval is regarded as abnormal flight data.

6. A monitoring method for the failure of an aircraft hydraulic system according to claim 5, characterized in that, If the maximum hydraulic pressure collected is outside the confidence interval, it is regarded as performance degradation.

7. A monitoring method for the failure of an aircraft hydraulic system according to claim 5, characterized in that, The confidence interval of the normal distribution is set to 95%.

8. A monitoring method for the failure of an aircraft hydraulic system according to claim 1, characterized in that The method performs alarm push according to the judged performance of the hydraulic system.

9. A monitoring device for the failure of an aircraft hydraulic system, comprising a memory, a processor, and a program stored in the memory, characterized in that, When the processor executes the program, it implements the monitoring method for the failure of the aircraft hydraulic system as described in any one of claims 1-8.

10. A storage medium, on which a program is stored, characterized in that, When the program is executed, it implements the monitoring method for the failure of the aircraft hydraulic system as described in any one of claims 1-8.

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