Starting valve fault prediction method, medium, equipment and system

Abstract

The invention discloses a starting valve fault diagnosis method, medium, equipment and system, and relates to the technical field of starting valves, when an aircraft is on the ground and a starting valve is in a stable opening stage, an air pressure value curve after the valve is started when the rotating speed of an engine core engine is in a preset rotating speed range is drawn; when the air pressure value curve fluctuates, a fault early warning signal that the ground of the starting valve cannot be opened is output; when the starting valve is in the initial opening stage, if the air pressure value after the valve is started is continuously larger than a preset judgment threshold value within a first preset duration or the number of times that the air pressure value is larger than the preset judgment threshold value within a preset time period exceeds a preset upper limit, an early warning signal for the fault that the ground of the starting valve cannot be opened is output, the preset judgment threshold value is in positive correlation with the average value of the air pressure values in the initial opening stage. The method can predict the ground non-opening fault of the starting valve in advance, and guarantees the normal operation of the flight.

Description

Technical Field

[0001] The present invention relates to the technical field of starting valves, and particularly to a method, medium, device and system for diagnosing starting valve faults. Background Art

[0002] The starting valve installed on the LEAP-1A engine of the A32X aircraft is a butterfly valve that can monitor pneumatic parameters. The low reliability of this type of valve is a well-known problem in the global fleet. The starting valve faults mainly manifest as two types: non-command opening in the air and inability to open on the ground. Since the LEAP engine was put into operation, there have been many flight delay incidents caused by the inability of the starting valve to open on the ground. However, there is currently no fault warning method for the inability of the starting valve to open on the ground in the industry. Summary of the Invention

[0003] The purpose of the embodiments of the present invention is to provide a method, medium, device and system for diagnosing starting valve faults, which can predict in advance the fault that the starting valve cannot open on the ground and ensure the normal operation of flights.

[0004] To achieve the above purpose, the embodiments of the present invention provide a method for diagnosing starting valve faults, including:

[0005] When the aircraft operating parameters indicate that the aircraft is on the ground, determine the working stage of the starting valve based on the core engine speed of the engine;

[0006] When the working stage is the stable opening stage, draw a curve of the air pressure value behind the starting valve when the core engine speed of the engine is within a preset speed range. When the air pressure value curve fluctuates, output a fault warning signal that the starting valve cannot open on the ground;

[0007] When the working stage is the initial opening stage, if the air pressure value behind the starting valve continuously exceeds a preset determination threshold within a first preset duration or the number of times the air pressure value exceeds the preset determination threshold within a preset time period exceeds a preset upper limit, output a fault warning signal that the starting valve cannot open on the ground, where the preset determination threshold has a positive correlation with the average air pressure value in the initial opening stage.

[0008] As an improvement of the above solution, determine whether the air pressure value curve fluctuates through the following method:

[0009] Call the sawtooth fluctuation algorithm to identify the shape of the air pressure value curve. When the shape is sawtooth, determine that the air pressure value curve fluctuates.

[0010] As an improvement of the above solution, when the aircraft operating parameters indicate that the aircraft is in the air flight stage, the starting valve fault diagnosis method further includes:

[0011] Retrieve the air pressure value threshold sequence;

[0012] Based on the air pressure value threshold sequence, determine whether the air pressure value is in any over-limit gear;

[0013] When the air pressure value is in any over-limit gear, calculate the corresponding duration;

[0014] When there is any duration that is not less than the duration threshold of the corresponding over-limit gear, output a starting valve non-command opening fault signal.

[0015] As an improvement to the above solution, the air pressure value threshold sequence includes three air pressure value thresholds, and the three air pressure value thresholds divide three non-overlapping over-limit gears; among them, the lower limit value of the first over-limit gear is greater than the upper limit value of the second over-limit gear; the lower limit value of the second over-limit gear is greater than the upper limit value of the third over-limit gear;

[0016] And, the first duration threshold is greater than the third duration threshold; the third duration threshold is greater than the second duration threshold; among them, the first duration threshold, the second duration threshold, and the third duration threshold are the duration thresholds of the first over-limit gear, the second over-limit gear, and the third over-limit gear respectively.

[0017] As an improvement to the above solution, the value ranges of the three air pressure value thresholds are 1 - 5 PSI, 5 - 8 PSI, and 8 - 45 PSI respectively.

[0018] As an improvement to the above solution, the first duration threshold is 1 minute, the value range of the second duration threshold is 5 - 10 seconds, and the value range of the third duration threshold is 20 - 90 seconds.

[0019] To achieve the above object, an embodiment of the present invention further provides a computer-readable storage medium, and the computer-readable storage medium includes a stored computer program, wherein when the computer program runs, it controls the device where the computer-readable storage medium is located to execute the starting valve fault diagnosis method as described in any one of the above embodiments.

[0020] To achieve the above object, an embodiment of the present invention further provides a computer device, including a processor, a memory, and a computer program stored in the memory and configured to be executed by the processor. When the processor executes the computer program, it implements the starting valve fault diagnosis method as described in any one of the above embodiments.

[0021] To achieve the above object, an embodiment of the present invention further provides a starting valve fault diagnosis system, including the computer device as described in the above embodiment, and further including:

[0022] A data acquisition module, configured to acquire target parameters from an engine electronic controller and transmit the target parameters to the computer device, and after receiving a starting valve fault warning signal sent by the computer device, acquire initial message data and transmit the initial message data to a message generation module;

[0023] A message generation module, configured to receive the initial message data and generate a warning message, and after receiving a message sending instruction from the computer device, send the warning message to a target device;

[0024] A multi-functional control and display module, configured to adjust threshold parameters.

[0025] Compared with the prior art, in the starting valve fault diagnosis method, medium, device and system provided by the embodiment of the present invention, when the aircraft operation parameters indicate that the aircraft is on the ground, the working stage of the starting valve is determined based on the engine core speed; when the working stage is a stable opening stage, a curve of the air pressure value behind the starting valve when the engine core speed is within a preset speed range is drawn, and when the air pressure value curve fluctuates, a ground opening failure warning signal of the starting valve is output; when the working stage is an initial opening stage, if the air pressure value behind the starting valve continuously exceeds a preset determination threshold within a first preset duration or the number of times the air pressure value exceeds the preset determination threshold within a preset time period exceeds a preset upper limit, a ground opening failure warning signal of the starting valve is output, where the preset determination threshold has a positive correlation with the average value of the air pressure value in the initial opening stage. The embodiment of the present invention can predict in advance whether the starting valve will have a ground opening failure by monitoring the data change rule of the air pressure value behind the starting valve when the aircraft is on the ground, ensuring the normal operation of the flight. Description of the Drawings

[0026] Figure 1 is a flowchart of a starting valve fault diagnosis method provided by an embodiment of the present invention;

[0027] Figure 2 is a schematic diagram of a LEAP-1A engine starting valve provided by an embodiment of the present invention;

[0028] Figure 3 is a data change rule diagram before and after the starting valve has a ground opening failure provided by an embodiment of the present invention;

[0029] Figure 4 is a data rule diagram of fault mode 1 provided by an embodiment of the present invention;

[0030] Figure 5 It is the data pattern diagram of failure mode two provided by an embodiment of the present invention;

[0031] Figure 6 It is the monitoring logic diagram of the ground-opening failure prediction of the starting valve provided by an embodiment of the present invention;

[0032] Figure 7 It is the monitoring logic diagram of the non-command opening failure detection of the starting valve in the air provided by an embodiment of the present invention;

[0033] Figure 8 It is the structural schematic diagram of a computer device provided by an embodiment of the present invention;

[0034] Figure 9 It is the schematic diagram of the warning message provided by an embodiment of the present invention;

[0035] Figure 10 It is the schematic diagram of the interface for setting the message download path provided by an embodiment of the present invention;

[0036] Figure 11 It is the working flow chart of the starting valve fault diagnosis system provided by an embodiment of the present invention. Detailed implementation manners

[0037] Next, the technical solutions in the embodiments of the present invention will be clearly and completely described in conjunction with the accompanying drawings in the embodiments of the present invention. Obviously, the described embodiments are only a part of the embodiments of the present invention, rather than all of the embodiments. All other embodiments obtained by those of ordinary skill in the art based on the embodiments of the present invention without creative efforts shall fall within the protection scope of the present invention.

[0038] In the description of the present application, it should be understood that the orientation or positional relationship indicated by the terms "center", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc. is based on the orientation or positional relationship shown in the accompanying drawings, and is only for the convenience of describing the present application and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore should not be construed as a limitation to the present application.

[0039] The terms "first" and "second" are only used for descriptive purposes and cannot be understood as indicating or implying relative importance or implicitly indicating the quantity of the indicated technical features. Thus, the features defined with "first" and "second" may explicitly or implicitly include one or more of such features. In the description of the present application, unless otherwise specified, the meaning of "a plurality" is two or more.

[0040] In the description of the present application, it should be noted that, unless otherwise clearly specified and limited, the terms "installed", "connected", and "coupled" should be understood in a broad sense. For example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be directly connected or indirectly connected through an intermediate medium, and it can be the communication inside two components. For those of ordinary skill in the art, the specific meanings of the above terms in the present application can be understood according to specific circumstances.

[0041] See Figure 1 , which is a flowchart of a starting valve fault diagnosis method provided by an embodiment of the present invention, including steps S1 to S3:

[0042] S1. When the aircraft operation parameters indicate that the aircraft is on the ground, determine the current working state of the starting valve based on the engine core speed.

[0043] S2. When the current working state is the stable opening stage, draw a curve of the air pressure value after the starting valve when the engine core speed is within a preset speed range. When the air pressure value curve fluctuates, output a ground opening failure warning signal for the starting valve.

[0044] S3. When the current working state is the initial opening stage, if the air pressure value after the starting valve continuously exceeds a preset determination threshold within a first preset duration or the number of times the air pressure value exceeds the preset determination threshold within a preset time period exceeds a preset upper limit, output a ground opening failure warning signal for the starting valve, where the preset determination threshold has a positive correlation with the average air pressure value in the initial opening stage.

[0045] It is worth noting that the starting valve fault diagnosis method described in the embodiments of the present invention can be implemented by an Aircraft Condition Monitoring System (ACMS); and, in some embodiments, the execution of the starting valve fault diagnosis method covers the entire aircraft power-on stage, so that the detection of the non-command opening fault of the starting valve in the air and the ground opening failure warning of the starting valve can be achieved simultaneously; further, the fault monitoring of the two engines of an aircraft can be carried out separately, so as to meet the monitoring and warning requirements when abnormal conditions occur in both engines at the same time. And, in this case, the monitoring logics of the two engines are the same, and the only difference lies in the real-time acquisition parameters input, which can be regarded as two independent embodiments of the same method.

[0046] It has been found through research that during the ground start-up phase of an aircraft, when the start valve is difficult to open and gets stuck at a certain angle, the value of the air pressure (SAP, Start Air Pressure) behind the start valve will exhibit a specific changing trend. Therefore, in steps S2 and S3, by monitoring the data characteristics of the air pressure value, it is possible to predict in advance that the start valve is about to have a ground-opening failure, and output a warning signal for the ground-opening failure of the start valve, which facilitates the ground maintenance personnel to take corresponding capacity arrangements and troubleshooting preparation measures in a timely manner, reduce flight delays caused by such failures, and ensure the normal operation of flights.

[0047] See Figure 2 , which is a schematic diagram of the start valve of the LEAP-1A engine provided by an embodiment of the present invention. It can be seen from Figure 2 that the start valve of the LEAP-1A engine is a pneumatic butterfly valve. It should be noted that the start valve fault diagnosis method provided by the present invention can not only be used for the LEAP-1A start valve, but also be applied to other valves that can monitor the pneumatic parameters behind the valve. The type of the start valve is not limited here.

[0048] According to the continuity equation of fluid mechanics, the flow velocity of a fluid is inversely proportional to the cross-sectional area of the pipeline, that is, if the pipeline narrows, the flow velocity of the fluid will increase. When the start valve gets stuck, the opening in front (upstream) of the butterfly valve decreases, resulting in a reduction in the cross-sectional area through which air ( Figure 2 "airflow" in

[0049] See the Bernoulli equation shown in formula (1):

[0050]

[0051] where P represents the static pressure of the fluid; ρ represents the density of the fluid; v represents the velocity (flow velocity) of the fluid; g represents the acceleration due to gravity; h represents the height of the fluid relative to the reference point; constant represents a constant.

[0052] According to the Bernoulli equation, the total energy (including static pressure energy, kinetic energy and potential energy) of a fluid (that is, Figure 2 "airflow" in

[0053] See Figure 3 , which is a graph showing the data change pattern before and after the starting valve fails to open on the ground provided by an embodiment of the present invention. It can be seen from Figure 3 that before the starting valve fails to open on the ground, the air pressure value will rise, while after replacing the starting valve, the air pressure value will drop.

[0054] Specifically, when the performance of components such as the valve solenoid degrades and the starting valve cannot be stably held in the open position, the starting valve will swing from the open to the closed position during operation. Similarly, when the starting valve actuates to a certain specific angle towards the closed position, the air pressure value downstream of the valve will suddenly increase. When the increased air pressure value can resist the pressure difference between the upper and lower chambers of the servo control diaphragm, the starting valve moves back towards the open position again, completing an abnormal swing of the starting valve in the open state. The data shows that there is a fluctuation in the air pressure value behind the starting valve. The present invention refers to this failure mode of the starting valve being unable to open on the ground as "Failure Mode One". See Figure 4 , which is a graph showing the data pattern of Failure Mode One provided by an embodiment of the present invention. It can be seen from Figure 4 that the first air pressure value curve (i.e., SAP1 in Figure 4 ) shows sawtooth fluctuations, indicating the occurrence of Failure Mode One.

[0055] Among them, Failure Mode One corresponds to step S2, that is, when it is recognized that the air pressure value curve fluctuates, it indicates the occurrence of Failure Mode One, and at this time, a warning signal for the starting valve being unable to open on the ground is output.

[0056] In addition, at the initial stage of engine starting, under the command of the engine electronic controller (EEC, Electronic Engine Controller), the starting valve should open slowly and steadily, and the air pressure value downstream of the valve (behind the valve) will rise steadily. When the performance of the starting valve components degrades (such as wear at the spherical stop) and a failure to open is about to occur, the butterfly valve of the butterfly starting valve usually gets stuck during the initial opening stage. According to the theoretical analysis of Bernoulli's equation and the continuity equation in fluid mechanics, when the valve gets stuck at a certain specific angle, the air pressure value downstream of the valve will increase. Since the stuck state will last for a few seconds, the air pressure value will show a pattern of a large sudden increase for a few seconds. The present invention refers to this failure mode of the starting valve being unable to open on the ground as "Failure Mode Two". See Figure 5 , which is a graph showing the data pattern of Failure Mode Two provided by an embodiment of the present invention. It can be seen from Figure 5 that the first air pressure value curve (i.e., SAP1 in Figure 5 ) has a relatively high value at the initial moment, indicating the occurrence of Failure Mode Two.

[0057] Further, fault mode two corresponds to step S3. When it is recognized that the air pressure value after the start valve continuously exceeds the preset determination threshold within the first preset duration or the number of times the air pressure value exceeds the preset determination threshold within the preset time period exceeds the preset upper limit, it indicates that fault mode two has occurred. At this time, a fault warning signal that the start valve cannot be opened on the ground is output.

[0058] It should be noted that in actual situations, fault mode one and fault mode two may occur simultaneously on a faulty start valve or may occur separately.

[0059] As can be seen from the above, during the ground start phase of the aircraft, when the start valve is difficult to open, it will get stuck at a certain angle. Through research, the present invention has found that at this time, the air pressure value after the start valve will show a specific change trend, which is summarized as "fault mode one" and "fault mode two". Moreover, through analysis of a large amount of operation data, it is found that after the occurrence of the above fault mode one or fault mode two, the start valve will develop a fault of being completely unable to open within 2 to 10 days.

[0060] Further, in steps S2 and S3, when it is recognized that the air pressure value after the start valve shows the data pattern shown in fault mode one or fault mode two, a fault warning signal that the start valve cannot be opened on the ground is issued. Among them, the fault warning signal can be a message, an audible and visual alarm signal, or others. The fault warning signal can be in one form or a combination of multiple forms, which is not limited here.

[0061] Specifically, in step S1, it can be determined whether the aircraft is on the ground through the flight phase parameter FWC (Flight Warning Computer) PHASE, that is, when 1 ≤ FWC PHASE ≤ 2, it indicates that the aircraft is on the ground. It should be noted that the change rules of the air pressure value during unconventional start (ground air source vehicle start) and conventional APU (Auxiliary Power Unit) start are different. In the present invention, only the data performance rules of the air pressure value during conventional APU air extraction (conventional APU start) are studied. Exemplarily, when the APU air extraction pressure ≥ 2 and the APU speed ≥ 95%, it is determined that it is a conventional APU start, and then steps S2 and S3 are continued. Further, the working phase of the start valve is determined by the engine core speed N2. When N2 < 12%, it indicates that the start valve is in the initial opening stage, and when 20% ≤ N2 ≤ 50%, it indicates that the start valve is in the stable opening working stage.

[0062] Exemplarily, in step S2, the preset rotational speed range can be [23%, 35%] because the data in this stage is usually the most stable, which is convenient for accurately distinguishing between fault data and normal data. Further, the sawtooth fluctuation algorithm can be called to identify the shape of the air pressure value curve. When the shape of the air pressure value curve is sawtooth-shaped, it indicates that the air pressure value curve fluctuates, and a ground start valve cannot be opened fault will occur. Therefore, a warning signal is issued.

[0063] Exemplarily, in step S3, the preset duration can be 4 seconds, and the preset determination threshold can be "average data + 3 PSI", where the average data refers to the average value of the air pressure value when 20% ≤ N2 ≤ 50%. That is, when the air pressure value is continuously higher than the average data by 3 PSI (Pounds per Square Inch) for 4 seconds, a warning signal for the ground start valve cannot be opened fault is issued.

[0064] Exemplarily, in step S3, the preset upper limit can be 4 times. In some embodiments, the largest 4 air pressure values can be taken. If the above 4 air pressure values all exceed the preset determination threshold (for example, all are higher than the above average data by 3 PSI), a warning signal for the ground start valve cannot be opened fault is issued.

[0065] Exemplarily, in some embodiments, the warning signal can be transmitted through a fault code to distinguish different fault types and fault modes. Exemplarily, the fault code consists of 4 digits. Among them, the first digit indicates the fault type (for example, 4 indicates the ground start valve cannot be opened fault), the second digit is 0, which is a placeholder digit and has no actual meaning, the third digit indicates the fault mode (for example, 1 indicates fault mode one, 2 indicates fault mode two), and the fourth digit indicates the engine position of the aircraft (for example, 1 indicates the left engine, 2 indicates the right engine). For example, when the fault code in the message is 4011, it indicates that it is predicted that the ground start valve of the left engine is about to have a cannot be opened fault, and the data manifestation form is fault mode one, that is, the air pressure value curve fluctuates in a (sawtooth shape).

[0066] See Figure 6, which is the monitoring logic diagram for predicting the failure that the starting valve cannot be opened on the ground provided by an embodiment of the present invention. Among them, "main switch ON" indicates that the aircraft is in the power-on stage, and 1 ≤ FWC PHASE ≤ 2 indicates that the aircraft is on the ground, that is, in the power-on and taxi-out stages. "APU bleed air pressure ≥ 2 Bar (Barometric Pressure, atmospheric pressure)" and "APU speed ≥ 95%" indicate a conventional APU start. When the above conditions are met and the starting valves of both engines cannot be opened simultaneously, that is, the starting valve of the left engine is open (SAV1 = 1) and the starting valve of the right engine is closed (SAV2 = 0), or the starting valve of the left engine is closed (SAV1 = 0) and the starting valve of the right engine is open (SAV2 = 1), it is represented by the parameter "SAV1 = 1 and SAV2 = 0" or "SAV1 = 0 and SAV2 = 1". If the air pressure value curve is serrated (SAP serrated) when the engine core speed satisfies 23% ≤ N2 ≤ 35%, a fault code (code) is issued. If it is the left engine (left engine), 4011 is issued; if it is the right engine (right engine), 4012 is issued. If the starting valve is in the initial opening stage, that is, when N2 < 12%, the four largest air pressure values SAPmax1 to SAPmax4 are collected, and the average value SAPavg of the air pressure values is calculated when 20% < N2 ≤ 50%. If the difference between the above four largest air pressure values and SAPavg is not less than 3, a fault code is issued. If it is the left engine (left engine), 4021 is issued; if it is the right engine (right engine), 4022 is issued. Further, the above fault code is written into the warning message.

[0067] Compared with the prior art, the embodiment of the present invention can predict whether the starting valve will have a failure that it cannot be opened on the ground and issue a warning signal when necessary by monitoring the data change law of the air pressure value after the starting valve when the aircraft is on the ground, ensuring the normal operation of the flight.

[0068] As an optional implementation manner, the following method is used to determine whether the air pressure value curve fluctuates:

[0069] Call the serrated fluctuation algorithm to identify the shape of the air pressure value curve. When the shape is serrated, it is determined that the air pressure value curve fluctuates.

[0070] It should be noted that in addition to the ground-opening failure, the starting valve failure also includes the in-flight non-command opening failure. The in-flight non-command opening of the starting valve is likely to cause damage to the starter structure, resulting in oil leakage of the starter in the air. Since the starter and the engine share the same lubricating oil system, this will lead to oil leakage of the engine in the air, posing a serious threat to the safe operation of the aircraft. For the in-flight non-command opening failure of the starting valve, currently, the aircraft's Electronic Centralized Aircraft Monitor (ECAM) / Engine Indicating and Crew Alerting System (EICAS) will only generate a warning message to alert the pilot when the starting valve opens significantly in the air. However, this warning method is not timely and there are potential safety hazards. Moreover, due to the limitations of the system monitoring logic and factory settings, there have been multiple cases where the in-flight non-command opening failure of the starting valve did not trigger the relevant ECAM warning message. That is, currently, the industry lacks timely and accurate detection means for the in-flight non-command opening failure of the starting valve. In view of the above-mentioned defects of the existing technology, in some embodiments of the present invention, a detection method for the in-flight non-command opening failure of the starting valve is also provided.

[0071] As an optional embodiment, when the aircraft operation parameters indicate that the aircraft is in the in-flight phase, the starting valve fault diagnosis method further includes:

[0072] Retrieving a sequence of air pressure value thresholds;

[0073] Based on the sequence of air pressure value thresholds, determining whether the air pressure value is in any over-limit gear;

[0074] When the air pressure value is in any over-limit gear, calculating the corresponding duration;

[0075] When there is any duration that is not less than the duration threshold of the corresponding over-limit gear, outputting a signal of the in-flight non-command opening failure of the starting valve.

[0076] It should be noted that when the aircraft is in the air, the start valve should be closed, so the air pressure value after the start valve should be close to 0; when the start valve fails to close tightly in the air, it will show states such as an increase in the air pressure value and a large fluctuation in the inlet pressure of the pre-cooler of the air-conditioning system. In the embodiment of the present invention, by setting an out-of-tolerance early warning logic for the air pressure value to judge the failure condition of the start valve, it is possible to prevent the occurrence of non-release failure "ENG 1 / 2SAV POS(OPEN)" (the position of the start air valve (SAV) of the No. 1 or No. 2 engine (ENG) is in the open state) during operation, and prevent more serious events such as damage and oil leakage of the starter due to the loose closure of the start valve.

[0077] As an optional implementation manner, the air pressure value threshold sequence includes three air pressure value thresholds, and the three air pressure value thresholds divide three non-overlapping over-limit levels; wherein, the lower limit value of the first over-limit level is greater than the upper limit value of the second over-limit level; the lower limit value of the second over-limit level is greater than the upper limit value of the third over-limit level;

[0078] Moreover, the first duration threshold is greater than the third duration threshold; the third duration threshold is greater than the second duration threshold; wherein, the first duration threshold, the second duration threshold, and the third duration threshold are the duration thresholds of the first over-limit level, the second over-limit level, and the third over-limit level respectively.

[0079] As an optional implementation manner, the value ranges of the three air pressure value thresholds are 1 - 5 PSI, 5 - 8 PSI, and 8 - 45 PSI respectively.

[0080] It should be noted that the value range "1 - 5 PSI" includes the values of 1 PSI and 5 PSI. Similarly, the value range "5 - 8 PSI" includes the values of 5 PSI and 8 PSI, and the value range "8 - 45 PSI" includes the values of 8 PSI and 45 PSI. Further, although the above value ranges overlap at the endpoints, in practical applications, the three air pressure value thresholds should take different values.

[0081] As an optional implementation manner, the first duration threshold is 1 minute, the value range of the second duration threshold is 5 - 10 seconds, and the value range of the third duration threshold is 20 - 90 seconds.

[0082] It should be noted that the value range "5 - 10 seconds" of the second duration threshold includes the values of 5 seconds and 10 seconds, and the value range "20 - 90 seconds" of the third duration threshold includes the values of 20 seconds and 90 seconds.

[0083] For example, when 3≦FWC PHASE≦9, it indicates that the aircraft is in the air flight stage, that is, the aircraft is in the flight state between takeoff and landing. When the air pressure value behind the starting valve exceeds 2PSI, it indicates that the starting valve has a fault of not closing tightly in the air. Furthermore, when the air pressure value exceeds 6PSI, the starting valve may be activated in the air to drive the starter, which in turn causes damage to the starter. In severe cases, it may cause the starter to leak lubricating oil or even cause the engine to stop in the air. For non-commanded opening failures in the air, since the severity of the failures caused by different air pressure values is different, different over-limit gears can be set to distinguish them.

[0084] Exemplarily, the second duration threshold and the third duration threshold can be 5 seconds and 30 seconds respectively, and the three air pressure value thresholds can be 2PSI, 6PSI and 8PSI respectively. Then, accordingly, the obtained over-limit gear and corresponding duration threshold can be: the first over-limit gear can be SAP≥8, and the first duration threshold is 1 minute; the second over-limit gear can be 8>SAP≥6, and the second duration threshold is 5 seconds; the third over-limit gear can be 6>SAP>2, and the third duration threshold is 30 seconds; wherein, the SAP value is the air pressure value.

[0085] Exemplarily, in some embodiments, fault warning information can be transmitted and the severity of the fault can be distinguished through a fault code. Exemplarily, the fault code consists of 4 digits, wherein the first digit indicates the fault type (for example, 5 indicates a non-commanded opening fault of the starting valve in the air), the second digit indicates the warning trigger source (for example, 0 indicates that the system automatically detects a fault of abnormal and large opening of the starting valve; 1 indicates non-system detection, and 1 also indicates that it is detected by the fault diagnosis method provided by an embodiment of the present invention), the third digit indicates the fault severity level (for example, 1 to 3 are used to indicate the fault severity level from high to low, wherein 1 indicates the highest level), and the fourth digit indicates the engine position of the aircraft (for example, 1 indicates the left engine, and 2 indicates the right engine). Furthermore, the priority levels of the fault code triggering sequence are 501, 5H1, 5H2, and 5H3 from high to low.

[0086] See also Figure 7, which is the monitoring logic diagram for detecting the non-command opening fault of the starting valve in the air provided by an embodiment of the present invention. Among them, "main switch ON" indicates that the aircraft is in the power-on stage, and 3 ≦ FWC PHASE ≦ 9 indicates that the aircraft is in the air flight stage, that is, from takeoff roll to landing roll-in stage. Then: If a starting valve opening signal (SAV = 1) is received in the air, the fault code 5011 (left engine) or 5012 (right engine) is triggered; if SAP ≥ 8 and lasts for one minute, the fault code 5H11 (left engine) or 5H12 (right engine) is triggered; if 8 > SAP ≥ 6 and lasts for 5 seconds, the fault code 5H21 (left engine) or 5H22 (right engine) is triggered; if 6 > SAP > 2 and lasts for 30 seconds, the fault code 5H31 (left engine) or 5H32 (right engine) is triggered.

[0087] Compared with the prior art, the starting valve fault diagnosis method provided by the embodiment of the present invention determines the working stage of the starting valve based on the engine core speed when the aircraft operating parameters indicate that the aircraft is on the ground; when the working stage is the smooth opening stage, a curve of the air pressure value after the starting valve is drawn when the engine core speed is within a preset speed range, and when the air pressure value curve fluctuates, a ground-opening fault warning signal of the starting valve is output; when the working stage is the initial opening stage, if the air pressure value after the starting valve continuously exceeds a preset determination threshold within a first preset duration or the number of times the air pressure value exceeds the preset determination threshold within a preset time period exceeds a preset upper limit, a ground-opening fault warning signal of the starting valve is output, where the preset determination threshold has a positive correlation with the average air pressure value in the initial opening stage. The embodiment of the present invention can predict in advance whether the starting valve will have a ground-opening fault by monitoring the data change rule of the air pressure value after the starting valve when the aircraft is on the ground, ensuring the normal operation of the flight.

[0088] It should be noted that in some application scenarios, only the non-command opening fault detection in the air can be performed, that is, the part regarding the ground-opening fault warning in this solution is not included. Then, in some embodiments, the starting valve fault diagnosis method includes:

[0089] When the aircraft operating parameters indicate that the aircraft is in the air flight stage, retrieve the air pressure value threshold sequence;

[0090] Based on the air pressure value threshold sequence, determine whether the air pressure value is in any over-limit gear;

[0091] When the air pressure value is in any over-limit gear, calculate the corresponding duration;

[0092] When there is any duration that is not less than the duration threshold of the corresponding over-limit gear, output a non-command opening fault signal of the starting valve in the air.

[0093] Exemplarily, the air pressure value threshold sequence includes three air pressure value thresholds, and the three air pressure value thresholds divide three non-overlapping overlimit gears; wherein, the lower limit value of the first overlimit gear is greater than the upper limit value of the second overlimit gear; the lower limit value of the second overlimit gear is greater than the upper limit value of the third overlimit gear;

[0094] Moreover, the first duration threshold is greater than the third duration threshold; the third duration threshold is greater than the second duration threshold; wherein, the first duration threshold, the second duration threshold, and the third duration threshold are respectively the duration thresholds of the first overlimit gear, the second overlimit gear, and the third overlimit gear.

[0095] Exemplarily, the value ranges of the three air pressure value thresholds are 1-5 PSI, 5-8 PSI, and 8-45 PSI respectively.

[0096] Exemplarily, the first duration threshold is 1 minute, the value range of the second duration threshold is 5-10 seconds, and the value range of the third duration threshold is 20-90 seconds.

[0097] To achieve the above object, an embodiment of the present invention further provides a computer-readable storage medium, and the computer-readable storage medium includes a stored computer program, wherein when the computer program runs, it controls the device where the computer-readable storage medium is located to execute the starting valve fault diagnosis method as described in any of the above embodiments.

[0098] See Figure 8 , an embodiment of the present invention further provides a computer device 20, including a processor 21, a memory 22, and a computer program stored in the memory 22 and configured to be executed by the processor 21. When the processor 21 executes the computer program, it implements the steps in the embodiment of the above starting valve fault diagnosis method, for example Figure 1 the steps S1-S3 described in

[0099] The computer device may be a computing device such as a desktop computer, a notebook, a palm computer, and a cloud server. The computer device may include, but is not limited to, a processor and a memory. Those skilled in the art can understand that the schematic diagram is only an example of the computer device, and does not constitute a limitation on the computer device. It may include more or fewer components than shown in the figure, or combine some components, or different components. For example, the computer device may further include input / output devices, network access devices, a bus, etc.

[0100] To achieve the above object, an embodiment of the present invention further provides a starting valve fault diagnosis system, including the computer device described in any of the above embodiments, and:

[0101] A data acquisition module, configured to acquire target parameters from an engine electronic controller, transmit the target parameters to the computer device, and after receiving a starting valve fault warning signal (a starting valve ground opening failure warning signal and / or a starting valve in-air uncommanded opening signal) sent by the computer device, acquire initial message data and transmit the initial message data to a message generation module;

[0102] A message generation module, configured to receive the initial message data, generate a warning message, and after receiving a message sending instruction from the computer device, send the warning message to a target device;

[0103] A multi-functional control and display module, configured to adjust threshold parameters.

[0104] It should be noted that currently, the starting valve fault monitoring in the industry is mainly performed by the aircraft's electronic central monitoring system. The electronic central monitoring system will send warning information to the pilot, and then the pilot will inform the ground engineer through a satellite phone or an aviation telegram. This fault reporting method has a delay and is not conducive to timely and accurate transmission of fault information. Therefore, in some embodiments of the present invention, after identifying a starting valve fault, a warning message is triggered to be sent to a ground mailbox and / or an acoustic-optic alarm device is triggered for real-time notification, so that maintenance personnel can receive the fault warning information in the first time and conduct fault troubleshooting in a timely manner.

[0105] It can be understood that the computer device is used to execute the starting valve fault diagnosis method described in any of the above embodiments and is the core module of the starting valve fault diagnosis system. It should be noted that in some embodiments, the computer device can also be an ACMS monitoring logic module, that is, in some embodiments, an algorithm can be written in the ACMS system customizable programming module to implement the starting valve fault diagnosis method described in the above embodiments. Moreover, the ACMS monitoring logic module (the computer device) can trigger the data acquisition module to acquire initial message data and trigger the sending of a warning message when it identifies that a starting valve fault has occurred or is about to occur.

[0106] Furthermore, the data acquisition module is the data input interface module of the starting valve fault diagnosis system. When the starting valve fault diagnosis and monitoring are respectively performed on two engines of the same aircraft, the data acquisition modules of each engine operate independently accordingly. Exemplarily, the data acquisition module collects each parameter value of the engine electronic controller in real time through the ARINC 429 bus. Its data source is the same as that of the vibration warning data received by the pilot from the aircraft electronic central monitoring system. Moreover, the data acquisition module transmits the collected target parameters to the computer device (ACMS monitoring logic module).

[0107] In addition, after receiving the fault warning signal sent by the computer device (ACMS monitoring logic module), the data acquisition module also collects the data required for the message through snapshot or time window sampling methods, that is, the initial message data. Among them, the time window sampling method ensures real-time performance while maximizing the transmission of parameters required for fault analysis, and can be regarded as the real-time QAR (Quick Access Recorder) data recording and transmission of relevant parameters for engine starting valve monitoring. Further, referring to Table 1, it is an example of the initial message data provided by an embodiment of the present invention. The initial message data is the data obtained at the moment when the message is activated, mainly used to illustrate the overall situation of the data overrun event, including flight number, departure airport, arrival airport, altitude, engine, and high-pressure speed N2 (engine core speed), etc.

[0108] Table 1 Initial Message Data

[0109]

[0110]

[0111] Exemplarily, the initial message data is arranged in the warning message in the ACARS (Aircraft Communications Addressing and Reporting System) format for transmission, so as to facilitate the ground staff to decode the warning message according to the same rules. At the same time, structuring the message data also facilitates storage in the database. Further, the initial message data can also be sent to the printer in print format for the pilot or ground engineer to read.

[0112] Exemplarily, the warning message mainly consists of basic information and working status information, both of which are instantaneously collected data. Among them, the basic information includes flight information, event-triggered fault codes (fault codes), and operating status information of the auxiliary power unit APU. The working status information includes the working status information of the engine and the start valve, such as N2 speed, air pressure value, and relevant air-conditioning bleed air duct valve switch status information, etc.

[0113] Exemplarily, referring to Figure 9 , which is a schematic diagram of the warning message provided by an embodiment of the present invention. It is composed of Figure 9 It can be seen that this warning message is for the ground-opening failure warning of the start valve (starting valve). Among them, it includes basic information (aircraft number, base, aircraft type, flight number, etc.) and warning information. And, in the warning information, different fault modes and engines are respectively recorded.

[0114] Furthermore, the message generation module is also used for setting the caching and routing forwarding mechanism of the warning message.

[0115] It can be understood that setting different routes can meet different message reading requirements. Exemplarily, the route settings include 6 major categories (Loader, ACARS, Printer, Ethernet, Recorder, and Integrated Disk) and 3 modes (Automatic, Manual, and Formatted).

[0116] Among them, Loader is a handheld data loader. Through this setting, the message can be directly transmitted to the loader after being generated; ACARS is the message air-ground transmission mode; Printer represents a printer, and the message can be directly printed through this setting after being generated; Ethernet is the network connection mode; Recorder corresponds to QAR, and the message can be backed up in the QAR file medium and downloaded to the ground server through wireless QAR; Integrated Disk corresponds to PCMCIA (Personal Computer Memory Card International Association, personal computer memory card), and this card is installed in the aircraft's DMU (Data Management Unit, data management unit) device.

[0117] Further, in the Automatic mode, a message is sent immediately after a fault warning event is triggered; Manual is a mode of sending messages manually. In the embodiments of the present invention, that is, an instruction is sent from the ACMS monitoring logic module (computer device) to the message generation module; the Formatted mode means transmitting data with formatting. If the non-Formatted format is used for transmission, all data will be concatenated together without intervals.

[0118] Exemplarily, in some embodiments, the Manual and Formatted modes of Loader, ACARS, and Printer can be adopted.

[0119] Further, the message generation module is also used for setting the ACARS downlink path. Refer to Figure 10 , which is a schematic diagram of the interface for setting the message downlink path provided by an embodiment of the present invention. Among them, through the ACMS message downlink function (Downlinks), additional fixed message sending addresses can be added in the Addresses column. If this place is blank, the message sending address set by the ATSU (Air Traffic Services Unit) will be selected by default. Exemplarily, the ACARS sending path (Destination) of the message can be defined according to one's own needs. The VHF (Very High Frequency) single path, satellite single path, or the method of VHF priority and satellite filling can be selected. At the same time, line breaks can be deleted to save transmission traffic.

[0120] Further, the multifunctional display module can be used to view relevant thresholds (for example, the preset determination threshold and air pressure value threshold described in the above embodiments, etc.). Moreover, flight crew or engine engineers can adjust the threshold for triggering warning messages of a certain engine of a certain aircraft through this module to achieve individualized control as needed. This module is integrated in the airborne multifunctional control display unit (MCDU, Multifunction Control Display Unit). The above functions can be realized by developing corresponding pages and associating threshold parameters.

[0121] For ease of understanding, refer to Figure 11 , which is a working flowchart of the starting valve fault diagnosis system provided by an embodiment of the present invention. It is composed of Figure 2It can be seen that the parameters of the engine electronic controller are sent to the central electronic monitoring system for the pilot to view in the air. At the same time, the above parameters are also sent to the Wireless Quick Access Recorder (WQAR) and the aircraft status monitoring system through the Flight Data Interface and Management Unit (FDIMU). Moreover, the maintenance personnel can set the threshold through the multi-functional control display module. The aircraft status monitoring system monitors the air pressure value and, when it identifies that the start valve has failed or is about to fail, sends a fault warning signal and triggers the sending of a warning message. The warning message transmitted to the ground data system will be automatically decoded and analyzed, and compared with the subscription conditions preset by the engineer. The successfully matched subscriptions will be sent to the subscription email in the form of an email, and at the same time, the audible and visual alarm connected to the ground and the system will be triggered. Also, the ground engineer can set the warning logic.

[0122] Compared with the prior art, the start valve fault diagnosis system provided by the embodiment of the present invention includes a computer device, a data acquisition module, a message generation module, and a multi-functional control display module. The embodiment of the present invention can accurately predict the start valve fault and timely send the fault warning information to the relevant staff, improving the timeliness and accuracy of the transmission of the fault information. Moreover, by setting the multi-functional control display module, the embodiment of the present invention can flexibly adjust the relevant thresholds, so as to be applicable to the fault warning of different start valves of different aircraft models, and has strong practicability.

[0123] The above is the preferred embodiment of the present invention. It should be noted that for those of ordinary skill in the art in this technical field, without departing from the principle of the present invention, several improvements and refinements can be made, and these improvements and refinements are also regarded as the protection scope of the present invention.

Claims

1. A starting valve fault diagnosis method, characterized in that, Including: When the aircraft operation parameters indicate that the aircraft is on the ground, determine the working stage of the starting valve based on the engine core speed; When the working stage is the smooth opening stage, draw the air pressure value curve after the starting valve when the engine core speed is within the preset speed range. When the air pressure value curve fluctuates, output a ground-opening failure warning signal for the starting valve; When the working stage is the initial opening stage, if the air pressure value after the starting valve continuously exceeds the preset determination threshold within the first preset duration or the number of times the air pressure value exceeds the preset determination threshold within the preset time period exceeds the preset upper limit, output a ground-opening failure warning signal for the starting valve, where the preset determination threshold has a positive correlation with the average air pressure value in the initial opening stage.

2. The starting valve fault diagnosis method according to claim 1, characterized in that Judge whether the air pressure value curve fluctuates in the following way: Call the sawtooth fluctuation algorithm to identify the shape of the air pressure value curve. When the shape is sawtooth, it is determined that the air pressure value curve fluctuates.

3. The starting valve fault diagnosis method according to claim 1, characterized in that, When the aircraft operation parameters indicate that the aircraft is in the in-flight stage, the starting valve fault diagnosis method further includes: Retrieve the air pressure value threshold sequence; Based on the air pressure value threshold sequence, judge whether the air pressure value is in any overlimit gear; When the air pressure value is in any overlimit gear, calculate the corresponding duration; When there is any duration that is not less than the duration threshold of the corresponding overlimit gear, output a non-command opening fault signal for the starting valve in the air.

4. The starting valve fault diagnosis method according to claim 3, characterized in that, The air pressure value threshold sequence includes three air pressure value thresholds, and the three air pressure value thresholds divide three non-overlapping overlimit gears; among them, the lower limit value of the first overlimit gear is greater than the upper limit value of the second overlimit gear; the lower limit value of the second overlimit gear is greater than the upper limit value of the third overlimit gear; And, the first duration threshold is greater than the third duration threshold; the third duration threshold is greater than the second duration threshold; where the first duration threshold, the second duration threshold, and the third duration threshold are the duration thresholds of the first overlimit gear, the second overlimit gear, and the third overlimit gear respectively.

5. The starting valve fault diagnosis method according to claim 4, characterized in that The value ranges of the three air pressure value thresholds are 1 - 5 PSI, 5 - 8 PSI, and 8 - 45 PSI respectively.

6. The starting valve fault diagnosis method according to claim 4, characterized in that The first duration threshold is 1 minute, the value range of the second duration threshold is 5 - 10 seconds, and the value range of the third duration threshold is 20 - 90 seconds.

7. A computer-readable storage medium, characterized in that, The computer-readable storage medium includes a stored computer program, where when the computer program runs, it controls the device where the computer-readable storage medium is located to execute the starting valve fault diagnosis method according to any one of claims 1 - 6.

8. A computer device, characterized in that, Including a processor and a memory, the memory stores a computer program, and the computer program is configured to be executed by the processor. When the processor executes the computer program, it implements the starting valve fault diagnosis method according to any one of claims 1 - 6.

9. A starting valve fault diagnosis system, the starting valve fault diagnosis system includes the computer device as described in claim 8; and the starting valve fault diagnosis system further includes: A data acquisition module, configured to acquire target parameters from an engine electronic controller and transmit the target parameters to the computer device, and after receiving a starting valve fault warning signal sent by the computer device, acquire initial message data and transmit the initial message data to a message generation module; A message generation module, configured to receive the initial message data and generate a warning message, and after receiving a message sending instruction from the computer device, send the warning message to a target device; A multi-functional control and display module, configured to adjust threshold parameters.

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