Performance monitoring method and system for aircraft power transmission assembly

Abstract

The invention relates to a performance monitoring method and system for an aircraft power transmission component, and the method comprises the following steps: obtaining aircraft system parameters in real time, transmitting the aircraft system parameters to an airborne WQAR device, and transmitting the aircraft system parameters to a background server through a cellular data link by the WQAR device; and in the background server, WQAR data analysis is carried out on the obtained aircraft system parameters, the performance trend of the aircraft system parameters is monitored, and if it is judged that the aircraft power transmission assembly generates performance degradation, an alarm is given out. Compared with the prior art, the performance trend prediction is carried out by analyzing the system parameters of the aircraft power transmission assembly, when the performance is reduced to a certain degree, a trend abnormity alarm is generated, at the moment, the system is still in a safe range, the flight safety is guaranteed, serious damage caused by PTU work with diseases is avoided, and the economic loss is reduced.

Description

Technical Field

[0001] The present invention relates to the technical field of aircraft power transmission component monitoring, and in particular to a performance monitoring method and system for aircraft power transmission components. Background Art

[0002] PTU (POWER TRANSFER UNIT) is part of the hydraulic system of Airbus 320 series aircraft and is an important supplementary backup system for the main hydraulic system. Failure of this system will reduce the safety margin of the aircraft and is a NO GO project. Once PTU fails, it is very easy to cause flight delays or even AOG. According to investigations, from 2016 to April 2022, China Eastern Airlines had more than 30 flight delays or cancellations due to PTU failures, with an average of 4-5 delays per year. In addition, since the system is usually in a "standby" and non-working state during normal flight operations, even if PTU fails, it is not easy to detect, which is also one of the reasons for the delay.

[0003] PTU stands for power transmission unit. Its function is to use the yellow or green hydraulic system to realize power transmission between different hydraulic systems. For example, if the yellow system fails, the green system will increase the pressure of the yellow system through PTU; or if the green system fails, the yellow system will increase the pressure of the green system through PTU. PTU itself is a purely mechanical component without electrical accessories. The control of PTU is actually achieved through the electromagnetic valve switch on the PTU main pipe of the green and yellow systems. The servo valve in the PTU body senses the pressure difference between the yellow and green systems. When the pressure difference is greater than 500PSI, PTU automatically starts to increase the system pressure to 3000PSI. Figure 1 shown.

[0004] According to Figure 2 As shown in the logic diagram, the current means can only monitor the PTU status when the following conditions are met: (1) the dual engine start switch is on (2) the PTU is in working state. When the above conditions are met, when the green / yellow system difference is greater than 650PSI and lasts for more than 4S, the PTU FAULT warning is triggered. In fact, as the backup hydraulic system of the A320 aircraft, the PTU is usually on standby and does not participate in flight operations under normal conditions. It is activated when the hydraulic green system or yellow system fails in the air. Therefore, the current monitoring means are almost blind to the PTU. Once the system triggers a fault, the PTU function has been seriously degraded. As an emergency system, the PTU is not allowed to fail, which will inevitably cause the aircraft to be unairworthy, causing delays or grounding.

[0005] The current PTU monitoring process is as follows Figure 3As shown, the aircraft system sensor parameters are sent to the onboard computer, which generates a fault alarm based on logical judgment, and the alarm is sent to the background through the data link. The current monitoring status can only know whether there is a fault in the current aircraft system. It is the monitoring of the current status and a single flight. Once an alarm is generated, the system has failed. It is a post-event alarm. In short, it just lets the background know the fact that the fault has occurred. Summary of the invention

[0006] The purpose of the present invention is to provide a performance monitoring method and system for aircraft power transmission components in order to overcome the defects of the prior art that the current aircraft power transmission component monitoring status can only know whether there is a fault in the current aircraft system, and is a monitoring of the current status and a single flight. Once an alarm is generated, the system has failed, which belongs to a post-alarm.

[0007] The purpose of the present invention can be achieved by the following technical solutions:

[0008] A method for monitoring the performance of an aircraft power transmission assembly comprises the following steps:

[0009] Acquire aircraft system parameters in real time and transmit them to the onboard WQAR device, which then transmits them to the backend server via the cellular data link;

[0010] In the background server, the acquired aircraft system parameters are analyzed by WQAR data, and the performance trend of the aircraft system parameters is monitored. If it is determined that the performance of the aircraft power transmission components has degraded, an alarm is issued.

[0011] Furthermore, the process of the background server monitoring the performance trend of the aircraft system parameters includes:

[0012] According to the analyzed aircraft system parameters, data normal values ​​of the aircraft system parameters are collected and stored;

[0013] The aircraft system parameters obtained after real-time analysis are compared with the corresponding data normal values. If the difference reaches a preset performance degradation threshold, it is determined that the aircraft power transmission component has performance degradation; the performance degradation threshold is lower than the failure threshold of the aircraft power transmission component.

[0014] Furthermore, the process of determining whether performance degradation has occurred also includes: if the difference between the aircraft system parameter obtained after analysis and the corresponding data normal value reaches a preset performance degradation threshold and continues for a preset performance degradation time, then it is determined that the aircraft power transmission component has performance degradation, and the performance degradation time is lower than the fault duration threshold of the aircraft power transmission component.

[0015] Furthermore, the aircraft system parameters are aircraft hydraulic parameters.

[0016] Furthermore, the aircraft hydraulic parameters include main switch status, engine N1 and N2 speeds, green system pressure, yellow system pressure, PTU CTL ON status, clutch status and flight information.

[0017] Furthermore, the method also includes formulating an aircraft maintenance plan if it is determined that the aircraft power transmission component has performance degradation.

[0018] The present invention also provides a performance monitoring system for an aircraft power transmission assembly, comprising:

[0019] Airborne WQAR equipment is used to obtain aircraft system parameters in real time and transmit them to the backend server via cellular data link;

[0020] The backend server is used to parse WQAR data based on the acquired aircraft system parameters and monitor the performance trend of the aircraft system parameters. If it is determined that the aircraft power transmission components have performance degradation, an alarm will be issued.

[0021] Furthermore, the background server is provided with decoding software, which is used to perform WQAR data analysis on aircraft system parameters and monitor the performance trend of aircraft system parameters. If the aircraft power transmission component has performance degradation, an alarm is issued; if the aircraft power transmission component has no performance degradation, the data normal value of the aircraft system parameter is collected and stored;

[0022] The system further comprises a database for storing data normal values ​​of aircraft system parameters.

[0023] Furthermore, the process of the decoding software determining that performance degradation has occurred also includes: if the difference between the aircraft system parameter obtained after analysis and the corresponding data normal value reaches a preset performance degradation threshold and continues for a preset performance degradation time, then it is determined that the aircraft power transmission component has performance degradation, and the performance degradation time is lower than the fault duration threshold of the aircraft power transmission component.

[0024] Further, the aircraft system parameters are aircraft hydraulic parameters, which include main switch status, engine N1 and N2 speeds, green system pressure, yellow system pressure, PTU CTL ON status, clutch status and flight information.

[0025] Compared with the prior art, the present invention has the following advantages:

[0026] (1) The existing technical solution belongs to post-event monitoring, which can only synchronously know whether there is a fault in the PTU (power transmission unit), which is a post-event alarm. When the alarm is given, the fault has already occurred, reducing the flight safety margin. This solution can monitor the PTU status performance by setting a higher threshold and normal performance monitoring. When the performance drops to a certain level, an abnormal trend alarm is generated. At this time, the system is still within the safe range, ensuring flight safety.

[0027] (2) The existing technical solution generates an alarm after a failure occurs. Since PTU is an emergency system, it cannot be released, which is very likely to cause flight delays and AOG. This solution can detect performance degradation in advance and discover problems before failure occurs, thus preventing problems before they occur and reducing economic losses caused by flight abnormalities.

[0028] (3) The existing scheme cannot detect PTU performance defects in advance. Severe wear of PTU leads to high cost of subsequent component repairs. This scheme detects performance defects in advance to avoid serious damage caused by PTU working with defects, saving manpower and material resources.

[0029] (4) Existing methods require regular testing of the PTU to confirm the system status. This solution can continuously monitor the data of each flight and clearly understand the PTU status. There is no need to repeatedly test regularly to waste the life of the PTU. Compared with regular testing, the accuracy and precision are greatly improved. BRIEF DESCRIPTION OF THE DRAWINGS

[0030] Figure 1 A schematic diagram of the working principle of an aircraft power transmission unit PTU provided in the background technology of the present invention;

[0031] Figure 2 A warning logic diagram of an aircraft power transmission unit PTU provided in the background technology of the present invention;

[0032] Figure 3 A current monitoring flow chart of an aircraft power transmission unit PTU provided in the background technology of the present invention;

[0033] Figure 4 A schematic flow chart of a method for monitoring the performance of an aircraft power transmission assembly provided in an embodiment of the present invention;

[0034] Figure 5 The present invention is a schematic diagram of a data processing flow of a method for monitoring the performance of an aircraft power transmission component provided in an embodiment of the present invention. DETAILED DESCRIPTION

[0035] In order to make the purpose, technical solutions and advantages of the embodiments of the present invention clearer, the technical solutions in the embodiments of the present invention will be clearly and completely described below in conjunction with the drawings in the embodiments of the present invention. Obviously, the described embodiments are part of the embodiments of the present invention, not all of the embodiments. Generally, the components of the embodiments of the present invention described and shown in the drawings here can be arranged and designed in various different configurations.

[0036] Therefore, the following detailed description of the embodiments of the present invention provided in the accompanying drawings is not intended to limit the scope of the invention claimed for protection, but merely represents selected embodiments of the present invention. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0037] It should be noted that similar reference numerals and letters denote similar items in the following drawings, and therefore, once an item is defined in one drawing, further definition and explanation thereof is not required in subsequent drawings.

[0038] Example 1

[0039] like Figure 4 As shown, this embodiment provides a performance monitoring method for an aircraft power transmission assembly, comprising the following steps:

[0040] S1: Obtain aircraft system parameters in real time and transmit them to the onboard WQAR device, which then transmits them to the backend server via the cellular data link;

[0041] S2: In the background server, the acquired aircraft system parameters are analyzed by WQAR data, and the performance trend of the aircraft system parameters is monitored. If performance degradation occurs, an alarm is issued.

[0042] Aircraft system parameters are aircraft hydraulic parameters, including main switch status, engine N1 and N2 speeds, green system pressure, yellow system pressure, PTU CTL ON status, clutch status and flight information.

[0043] The process of the backend server monitoring the performance trend of aircraft system parameters includes:

[0044] According to the analyzed aircraft system parameters, collect and update the normal value of the aircraft system parameters, and store them;

[0045] The aircraft system parameters obtained after real-time analysis are compared with the corresponding data normal values. If the difference reaches a preset performance degradation threshold, it is determined that performance degradation has occurred; the performance degradation threshold is lower than the failure threshold of the aircraft power transmission component.

[0046] Preferably, in order to accurately determine whether the performance of the aircraft power transmission component is degraded, the judgment condition also needs to include the performance degradation time. Specifically, the process of determining whether performance degradation has occurred also includes: if the difference between the aircraft system parameter obtained after analysis and the corresponding data normal value reaches a preset performance degradation threshold and continues for a preset performance degradation time, it is determined that performance degradation has occurred, and the performance degradation time is lower than the fault duration threshold of the aircraft power transmission component.

[0047] The method also includes formulating an aircraft maintenance plan and promptly repairing the aircraft power transmission components if it is determined that the aircraft power transmission components have performance degradation.

[0048] The above solution is introduced below with a specific example.

[0049] like Figure 4 and 5 As shown, the aircraft hydraulic parameters (MASTER SW, dual engine N1, N2, green system pressure, yellow system pressure, PTU CTL ON, UTC, flight information) are stored in the FDIMU. WQAR obtains the above parameters from the FDIMU and transmits them to the Ground station through the network.

[0050] Decoding software such as AIFASE obtains WQAR data from the ground station for analysis and completes data collection. The backend server processes, monitors and generates alarms through AI algorithms.

[0051] When the aircraft's power transmission unit PTU is working normally, it is controlled by the electromagnetic valve switches on the green and yellow system PTU main pipes. The servo valve in the PTU body senses the pressure difference between the yellow and green systems. When the pressure difference is greater than 500PSI, the PTU automatically starts to increase the system pressure to 3000PSI.

[0052] This solution can detect the working status of each component based on the status information of MASTER SW, twin engine N1, N2, PTU CTL ON and UTC; predict the performance trend of aircraft system parameters based on the signal fluctuations and duration of green system pressure and yellow system pressure, and discover power transmission component PTU failure in advance; understand the PTU status based on flight information, and there is no need to repeatedly test regularly and waste PTU life.

[0053] The above is an introduction to the method embodiment. The following is a further explanation of the solution of the present invention through a system embodiment.

[0054] This embodiment also relates to a performance monitoring system for an aircraft power transmission assembly, comprising:

[0055] Airborne WQAR equipment is used to obtain aircraft system parameters in real time and transmit them to the backend server via cellular data link;

[0056] The backend server is used to parse WQAR data based on the acquired aircraft system parameters and monitor the performance trend of the aircraft system parameters. If performance degradation occurs, an alarm is issued.

[0057] Optionally, the backend server is provided with decoding software, which is used to perform WQAR data analysis on aircraft system parameters and monitor the performance trend of aircraft system parameters. If performance degradation occurs, an alarm is issued; if performance degradation does not occur, the data normal value of the aircraft system parameters is collected and stored;

[0058] The system also includes a database for storing data normal values ​​of aircraft system parameters.

[0059] The aircraft system parameters are aircraft hydraulic parameters, which include main switch status, engine N1 and N2 speeds, green system pressure, yellow system pressure, PTU CTL ON status, clutch status and flight information.

[0060] Optionally, the process of the decoding software determining whether performance degradation has occurred also includes: if the difference between the aircraft system parameters obtained after analysis and the corresponding data normal value reaches a preset performance degradation threshold and continues for a preset performance degradation time, it is determined that performance degradation has occurred, and the performance degradation time is lower than a fault duration threshold of the aircraft power transmission component.

[0061] It should be noted that the specific content and beneficial effects of the device of the present application can be found in the above-mentioned method embodiment, which will not be repeated here.

[0062] The preferred specific embodiments of the present invention are described in detail above. It should be understood that a person skilled in the art can make many modifications and changes based on the concept of the present invention without creative work. Therefore, any technical solution that can be obtained by a person skilled in the art through logical analysis, reasoning or limited experiments based on the concept of the present invention on the basis of the prior art should be within the scope of protection determined by the claims.

Claims

1. A method for monitoring the performance of an aircraft power transmission component, characterized in that: The following steps are involved: Acquire aircraft system parameters in real time and transmit them to the onboard WQAR device, which then transmits them to the backend server via the cellular data link; In the background server, the acquired aircraft system parameters are analyzed by WQAR data, and the performance trend of the aircraft system parameters is monitored. If it is determined that the performance of the aircraft power transmission components has degraded, an alarm is issued.

2. A method for monitoring the performance of an aircraft power transmission component according to claim 1, characterized in that: The process of the background server monitoring the performance trend of the aircraft system parameters includes: According to the analyzed aircraft system parameters, data normal values ​​of the aircraft system parameters are collected and stored; The aircraft system parameters obtained after real-time analysis are compared with the corresponding data normal values. If the difference reaches a preset performance degradation threshold, it is determined that the aircraft power transmission component has performance degradation; the performance degradation threshold is lower than the failure threshold of the aircraft power transmission component.

3. A method for monitoring the performance of an aircraft power transmission component according to claim 2, characterized in that: The process of determining whether performance degradation has occurred also includes: if the difference between the aircraft system parameter obtained after analysis and the corresponding data normal value reaches a preset performance degradation threshold and continues for a preset performance degradation time, then it is determined that the aircraft power transmission component has performance degradation, and the performance degradation time is lower than the fault duration threshold of the aircraft power transmission component.

4. The method for monitoring the performance of an aircraft power transmission component according to claim 1, characterized in that: The aircraft system parameters are aircraft hydraulic parameters.

5. A method for monitoring the performance of an aircraft power transmission assembly according to claim 4, characterized in that: The aircraft hydraulic parameters include main switch status, engine N1 and N2 speeds, green system pressure, yellow system pressure, PTU CTL ON status, clutch status and flight information.

6. The method for monitoring the performance of an aircraft power transmission component according to claim 1, characterized in that: The method further includes formulating an aircraft maintenance plan if it is determined that the aircraft power transmission component has performance degradation.

7. A performance monitoring system for an aircraft power transmission assembly, characterized in that: include: Airborne WQAR equipment is used to obtain aircraft system parameters in real time and transmit them to the backend server via cellular data link; The backend server is used to parse WQAR data based on the acquired aircraft system parameters and monitor the performance trend of the aircraft system parameters. If it is determined that the aircraft power transmission components have performance degradation, an alarm will be issued.

8. A performance monitoring system for an aircraft power transmission assembly according to claim 7, characterized in that: The backend server is provided with decoding software, which is used to perform WQAR data analysis on aircraft system parameters and monitor the performance trend of aircraft system parameters. If the aircraft power transmission component has performance degradation, an alarm is issued; if the aircraft power transmission component has no performance degradation, the data normal value of the aircraft system parameter is collected and stored; The system further comprises a database for storing data normal values ​​of aircraft system parameters.

9. A performance monitoring system for an aircraft power transmission assembly according to claim 8, characterized in that: The process of the decoding software determining whether performance degradation has occurred also includes: if the difference between the aircraft system parameter obtained after analysis and the corresponding data normal value reaches a preset performance degradation threshold and continues for a preset performance degradation time, then it is determined that the aircraft power transmission component has performance degradation, and the performance degradation time is lower than the fault duration threshold of the aircraft power transmission component.

10. The performance monitoring system of an aircraft power transmission assembly according to claim 7, characterized in that: The aircraft system parameters are aircraft hydraulic parameters, which include main switch status, engine N1 and N2 speeds, green system pressure, yellow system pressure, PTU CTL ON status, clutch status and flight information.

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