CN120308363A - A method, medium, device and system for predicting starting valve failure - Google Patents
A method, medium, device and system for predicting starting valve failureInfo
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- CN120308363A CN120308363A CN202510611042.7A CN202510611042A CN120308363A CN 120308363 A CN120308363 A CN 120308363A CN 202510611042 A CN202510611042 A CN 202510611042A CN 120308363 A CN120308363 A CN 120308363A
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Abstract
本发明公开了一种起动活门故障诊断方法、介质、设备及系统，涉及起动活门技术领域，当飞机处于地面且起动活门处于平稳打开阶段时，绘制发动机核心机转速处于预设转速范围内时起动活门后的空气压力值曲线，当所述空气压力值曲线出现波动时，输出起动活门地面打不开故障预警信号；当起动活门处于最初打开阶段时，若起动活门后的空气压力值在第一预设持续时长内持续大于预设判定阈值或所述空气压力值在预设时段内大于所述预设判定阈值的次数超过预设上限，则输出起动活门地面打不开故障预警信号，其中，所述预设判定阈值与最初打开阶段的空气压力值平均值呈正相关关系。本发明能够通提前预测起动活门地面打不开故障，保障航班的正常运行。
The present invention discloses a method, medium, equipment and system for diagnosing a starter valve fault, and relates to the technical field of the starter valve. When the aircraft is on the ground and the starter valve is in a stable opening stage, a curve of the air pressure value behind the starter valve when the engine core speed is within a preset speed range is drawn. When the air pressure value curve fluctuates, a starter valve ground failure warning signal is output; when the starter valve is in the initial opening stage, if the air pressure value behind the starter valve is continuously greater than a preset judgment threshold value within a first preset duration or the number of times the air pressure value is greater than the preset judgment threshold value within a preset period exceeds a preset upper limit, a starter valve ground failure warning signal is output, wherein the preset judgment threshold value is positively correlated with the average value of the air pressure value in the initial opening stage. The present invention can ensure the normal operation of the flight by predicting the starter valve ground failure in advance.
Description
Technical Field
The present invention relates to the field of starting valves, and in particular, to a method, medium, apparatus, and system for diagnosing faults of a starting valve.
Background
The starting valve of the LEAP-1A engine of the installed A32X aircraft is a butterfly valve capable of monitoring pneumatic parameters, and the low reliability of the valve of the model is a recognized problem of the world fleet. The failure of the starting valve is mainly represented by two types of non-command opening in the air and non-opening on the ground. Since the LEAP engine is put into operation, a flight delay event caused by the fact that the ground of the starting valve cannot be opened has occurred, but no fault early warning method for the fact that the ground of the starting valve cannot be opened exists in the industry at present.
Disclosure of Invention
The embodiment of the invention aims to provide a starting valve fault diagnosis method, medium, equipment and system, which can predict that the ground of the starting valve cannot be opened in advance to ensure the normal operation of flights.
To achieve the above object, an embodiment of the present invention provides a method for diagnosing a failure of a starting valve, including:
When the aircraft running parameters indicate that the aircraft is on the ground, determining the working stage of the starting valve based on the rotating speed of the engine core engine;
When the working stage is a stable opening stage, drawing an air pressure value curve after the valve is started when the rotating speed of the engine core engine is in a preset rotating speed range, and outputting a fault early warning signal that the ground of the valve is not opened when the air pressure value curve fluctuates;
And when the working stage is the initial opening stage, outputting a ground opening failure early warning signal of the starting valve if the air pressure value after the starting valve is continuously larger than a preset judging threshold value in a first preset duration time or the number of times that the air pressure value is larger than the preset judging threshold value in a preset period of time exceeds a preset upper limit, wherein the preset judging threshold value and an average value of the air pressure values in the initial opening stage are in positive correlation.
As an improvement of the above-described scheme, it is judged whether or not the air pressure value curve fluctuates in the following manner:
And calling a sawtooth-shaped fluctuation algorithm to identify the shape of the air pressure value curve, and judging that the air pressure value curve fluctuates when the shape is sawtooth-shaped.
As an improvement of the above solution, when the aircraft operation parameter indicates that the aircraft is in an air flight phase, the starting valve fault diagnosis method further includes:
calling a threshold sequence of air pressure values;
Judging whether the air pressure value is in any overrun gear or not based on the air pressure value threshold sequence;
When the air pressure value is in any overrun gear, calculating corresponding duration time;
and outputting a starting valve air non-instruction opening fault signal when any duration is not smaller than a duration threshold value of the corresponding overrun gear.
As an improvement of the scheme, the air pressure value threshold sequence comprises three air pressure value thresholds, wherein the three air pressure value thresholds divide three non-overlapping overrun gears, the lower limit value of the first overrun gear is larger than the upper limit value of the second overrun gear, and the lower limit value of the second overrun gear is larger than the upper limit value of the third overrun gear;
The first duration threshold is larger than a third duration threshold, the third duration threshold is larger than a second duration threshold, and the first duration threshold, the second duration threshold and the third duration threshold are duration thresholds of the first overrun gear, the second overrun gear and the third overrun gear respectively.
As an improvement of the scheme, the value ranges of the three air pressure value thresholds are 1-5 PSI, 5-8 PSI and 8-45 PSI respectively.
As an improvement of the scheme, 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.
To achieve the above object, an embodiment of the present invention further provides a computer readable storage medium, where the computer readable storage medium includes a stored computer program, and when the computer program runs, controls a device where the computer readable storage medium is located to execute the method for diagnosing a failure of a startup valve according to any one of the embodiments.
To achieve the above object, an embodiment of the present invention further provides a computer apparatus including a processor, a memory, and a computer program stored in the memory and configured to be executed by the processor, the processor implementing the startup shutter failure diagnosis method according to any one of the embodiments described above when executing the computer program.
To achieve the above object, an embodiment of the present invention further provides a system for diagnosing a failure of a starting valve, including the computer device according to the above embodiment, further including:
the data acquisition module is used for acquiring target parameters from the electronic engine controller, transmitting the target parameters to the computer equipment, and acquiring initial message data and transmitting the initial message data to the message generation module after receiving a valve starting fault warning signal sent by the computer equipment;
The message generation module is used for receiving the initial message data and generating a warning message, and sending the warning message to target equipment after receiving a message sending instruction of the computer equipment;
and the multifunctional control display module is used for adjusting the threshold value parameters.
Compared with the prior art, the fault diagnosis method, medium, equipment and system for the starting valve provided by the embodiment of the invention have the advantages that when the aircraft running parameters indicate that the aircraft is on the ground, the working stage where the starting valve is located is determined based on the rotating speed of the engine core engine, when the working stage is a stable opening stage, an air pressure value curve after the starting valve is drawn when the rotating speed of the engine core engine is within a preset rotating speed range, when the air pressure value curve fluctuates, a fault early warning signal for opening the ground of the starting valve is output, and when the working stage is an initial opening stage, if the air pressure value after the starting valve is continuously larger than a preset judging threshold value in a first preset duration time or the frequency of the air pressure value being larger than the preset judging threshold value in a preset period exceeds a preset upper limit, the fault early warning signal for opening the starting valve on the ground is output, wherein the preset judging threshold value and the air pressure value average value in the initial opening stage are in positive correlation. The embodiment of the invention can predict whether the ground opening failure of the starting valve occurs or not in advance by monitoring the data change rule of the air pressure value after the starting valve is positioned on the ground, thereby ensuring the normal operation of flights.
Drawings
FIG. 1 is a flow chart of a method for diagnosing a malfunction of a starting valve according to an embodiment of the present invention;
FIG. 2 is a schematic illustration of a LEAP-1A engine starting valve according to an embodiment of the present invention;
FIG. 3 is a graph showing a data change rule before and after a ground opening failure of a starting valve according to an embodiment of the present invention;
FIG. 4 is a data rule diagram of a first failure mode according to an embodiment of the present invention;
FIG. 5 is a data rule diagram of a second failure mode according to an embodiment of the present invention;
FIG. 6 is a logic diagram for monitoring a floor-based open failure prediction of a starting valve according to one embodiment of the present invention;
FIG. 7 is a logic diagram for monitoring for non-commanded open fault detection in a starting valve air provided by an embodiment of the present invention;
FIG. 8 is a schematic diagram of a computer device according to an embodiment of the present invention;
FIG. 9 is a diagram of a warning message according to an embodiment of the present invention;
FIG. 10 is a schematic diagram of an interface for setting a message download path according to an embodiment of the present invention;
Fig. 11 is a flowchart of the operation of the system for diagnosing a malfunction of the start shutter according to an embodiment of the present invention.
Detailed Description
The following description of the embodiments of the present invention will be made clearly and completely with reference to the accompanying drawings, in which it is apparent that the embodiments described are only some embodiments of the present invention, but not all embodiments. All other embodiments, which can be made by those skilled in the art based on the embodiments of the invention without making any inventive effort, are intended to be within the scope of the invention.
In the description of the present application, it should be understood that the terms "center," "upper," "lower," "front," "rear," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," "outer," and the like indicate orientations or positional relationships based on the orientation or positional relationships shown in the drawings, merely to facilitate describing the present application and simplify the description, and do not indicate or imply that the devices or elements referred to must have a specific orientation, be configured and operated in a specific orientation, and thus should not be construed as limiting the present application.
The terms "first," "second," and the like, are used for descriptive purposes only and are not to be construed as indicating or implying relative importance or implicitly indicating the number of technical features indicated. Thus, a feature defining "a first" or "a second" may explicitly or implicitly include one or more such feature. In the description of the present application, unless otherwise indicated, the meaning of "a plurality" is two or more.
In the description of the present application, unless explicitly stated or limited otherwise, the terms "mounted," "connected," and "connected" are to be construed broadly, and may be, for example, fixedly connected, detachably connected, or integrally connected, mechanically connected, electrically connected, directly connected, indirectly connected via an intervening medium, or in communication between two elements. The specific meaning of the above terms in the present application will be understood in specific cases by those of ordinary skill in the art.
Referring to fig. 1, a flowchart of a method for diagnosing a fault of a starting valve according to an embodiment of the present invention includes steps S1 to S3:
S1, when an aircraft running parameter indicates that the aircraft is on the ground, determining the current working state of a starting valve based on the rotating speed of an engine core engine;
s2, when the current working state is a stable opening stage, drawing an air pressure value curve after the valve is started when the rotating speed of the engine core machine is in a preset rotating speed range, and outputting a fault early warning signal that the ground of the valve is not opened when the air pressure value curve fluctuates;
And S3, when the current working state is the initial opening stage, outputting a ground opening failure early warning signal of the starting valve if the air pressure value after the starting valve is continuously larger than a preset judging threshold value in a first preset duration time or the number of times that the air pressure value is larger than the preset judging threshold value in a preset period of time exceeds a preset upper limit, wherein the preset judging threshold value and an average value of the air pressure values in the initial opening stage are in positive correlation.
It should be noted that the method for diagnosing the fault of the starting valve according to the embodiment of the invention can be implemented by an aircraft state monitoring system (Aircraft Condition Monitoring System, ACMS), and in some embodiments, the implementation of the method for diagnosing the fault of the starting valve covers the whole aircraft power-on stage, so that the detection of the fault of the starting valve in the air without opening the starting valve and the early warning of the fault of the starting valve on the ground can be simultaneously implemented, further, the fault monitoring can be respectively carried out on 2 engines of one aircraft, so as to meet the requirement of monitoring early warning when two abnormal conditions occur at the same time, and in this case, the monitoring logics of the two engines are the same, the difference is only the input real-time acquisition parameters, and the two independent embodiments of the same method can be considered.
According to the research, in the ground starting stage of the aircraft, when the starting valve is difficult to open and jamming occurs at a certain angle, the air pressure (SAP, start Air Pressure) value after the starting valve shows a specific change trend, so that in the step S2 and the step S3, the situation that the starting valve is about to open the ground is predicted in advance by monitoring the data characteristic of the air pressure value, a ground opening failure early warning signal of the starting valve is output, the ground opening failure early warning signal of the starting valve is convenient for ground maintenance personnel to timely take corresponding operation capacity arrangement and troubleshooting preparation measures, flight delay caused by the faults is reduced, and the normal operation of flights is ensured.
Referring to FIG. 2, a schematic diagram of a LEAP-1A engine starting valve according to an embodiment of the present invention is shown, and as can be seen in FIG. 2, the LEAP-1A engine starting valve is a pneumatic butterfly valve. It should be noted that the method for diagnosing the failure of the starting valve provided by the invention can be used for not only the LEAP-1A starting valve, but also other valves capable of monitoring the pneumatic parameters behind the valve, and the model of the starting valve is not limited.
From the fluid mechanics equation of continuity, the flow rate of the fluid is inversely proportional to the cross-sectional area of the tube, i.e., if the tube narrows, the flow rate of the fluid increases. When the start valve is stuck, the opening in front of (upstream of) the butterfly valve is reduced, resulting in a reduction in the cross-sectional area through which air (the "air flow" in fig. 2) passes, and thus the air flow rate is increased, and similarly, the opening in back of (downstream of) the butterfly valve is increased, resulting in an increase in the cross-sectional area through which air passes, and thus the flow rate is reduced.
See bernoulli's equation shown in equation (1):
where P represents the static pressure of the fluid, ρ represents the density of the fluid, v represents the velocity (flow rate) of the fluid, g represents the gravitational acceleration, h represents the height of the fluid relative to a reference point, and constant represents a constant.
As is known from the bernoulli equation, the total energy (including static, kinetic and potential energy) of a fluid (i.e., the "gas stream" in fig. 2) is conserved during the flow. In the event of a stuck start flap, the dead pressure P will correspondingly decrease upstream of the start flap due to the increase in flow velocity v, while the flow velocity behind the start flap decreases and the dead pressure P will increase, thus resulting in a higher air pressure behind the start flap than when the flap is normally open. In addition, the actuation of the shutter jamming may also cause an increase in turbulence of the fluid, which consumes energy, which also causes an increase in the downstream air pressure value.
Referring to fig. 3, a graph of data change rules before and after a ground opening failure of a starting valve according to an embodiment of the present invention is shown, where it can be seen from fig. 3 that before the ground opening failure of the starting valve occurs, the air pressure value increases, and after the starting valve is replaced, the air pressure value decreases.
Specifically, when the performance degradation of components such as a valve solenoid valve and the like causes that the starting valve cannot be stably kept in an opened position, the starting valve can swing from an opened position to a closed position during operation, and when the starting valve is actuated to a certain specific angle towards the closed position, the air pressure value at the downstream of the valve can suddenly rise, when the rising air pressure value can resist the pressure difference between an upper cavity and a lower cavity of a servo control diaphragm capsule, the starting valve moves towards the opened position again, the abnormal swing of the opening state of the starting valve is completed, and the air pressure value after the starting valve has one fluctuation. Referring to fig. 4, a graph of data of a first failure mode according to an embodiment of the present invention is shown in fig. 4, where a first air pressure value curve (that is, SAP1 in fig. 4) shows a saw tooth wave, that is, the first failure mode.
The first fault mode corresponds to the step S2, namely, when the fluctuation of the air pressure value curve is identified, the first fault mode is indicated, and a fault early warning signal that the ground of the starting valve is not opened is output.
In addition, at the initial stage of engine starting, the starting valve should be opened slowly and stably under the instruction of an engine electronic controller (EEC, electronic Engine Controller), and the air pressure value downstream of the valve (behind the valve) should be increased steadily. BUTTERFLY valves (BUTTERFLY valves) of BUTTERFLY start flaps often experience a stuck during the initial opening phase when performance degradation of the start flap assembly (e.g., wear at the ball stop) is imminent. According to the theoretical analysis of the fluid mechanics Bernoulli equation and the continuity equation, when the valve is stuck at a certain angle, the air pressure value at the downstream of the valve can rise, and the air pressure value can show a change rule of keeping for a few seconds and greatly rising due to the fact that the air pressure value is stuck at the angle for a few seconds. Referring to fig. 5, a graph of data of a second failure mode according to an embodiment of the present invention is shown in fig. 5, where the first air pressure value curve (i.e., SAP1 in fig. 5) has a higher value at the initial time, i.e., the second failure mode occurs.
Further, the second fault mode corresponds to step S3, when the air pressure value after the starting valve is identified to be continuously greater than the preset determination threshold value in the first preset duration time or the number of times that the air pressure value is greater than the preset determination threshold value in the preset period of time exceeds the preset upper limit, the second fault mode is indicated to occur, and at the moment, a fault early warning signal that the ground of the starting valve is not opened is output.
It should be noted that in practical situations, the first failure mode and the second failure mode may occur on one fail-safe valve at the same time, or may occur separately.
From the above, it can be seen that, during the ground starting stage of the aircraft, when the starting valve is difficult to open, a clamping stagnation occurs at a certain angle, and the invention finds that the air pressure value after the starting valve shows a specific variation trend, and summarizes the specific variation trend into a first fault mode and a second fault mode.
Further, in steps S2 and S3, when the data rule indicated by the first failure mode or the second failure mode is identified in the air pressure value after the start of the back door, a failure early warning signal is sent out, where the failure early warning signal may be a message, an audible and visual alarm signal, or other signals, and the failure early warning signal may be one form or a combination of multiple forms, which is not limited herein.
Specifically, in step S1, it may be determined whether the aircraft is on the ground by the flight PHASE parameter FWC (FLIGHT WARNING Computer) PHASE, that is, when 1+.fwc phase+.ltoreq.2, indicating that the aircraft is on the ground. In the case of unconventional starting (ground air source vehicle starting) and conventional APU (Auxiliary Power Unit ) starting, the change rule of the air pressure value is different, and in the invention, only the data representation rule of the air pressure value at the time of conventional APU bleed (conventional APU starting) is studied. For example, when the APU bleed air pressure is ≡ 2 and the APU speed is ≡ 95%, it is determined that the APU is normal, and at this time, steps S2 and S3 are continued. Further, the working phase of the starting valve is determined by the rotational speed N2 of the engine core, when N2 is less than 12%, the starting valve is indicated to be in the initial opening phase, and when N2 is less than or equal to 20% and less than or equal to 50%, the starting valve is indicated to be in the stable opening working phase.
For example, in step S2, the preset rotation speed range may be [23%,35% ], because the data at this stage is usually the most stable, so as to accurately distinguish the fault data from the normal data, further, a saw-tooth wave algorithm may be invoked to identify the shape of the air pressure value curve, and when the shape of the air pressure value curve is saw-tooth, it indicates that the air pressure value curve fluctuates, and a ground opening failure of the starting valve will occur, so that an early warning signal is sent.
For example, in step S3, the preset duration may be 4 seconds, and the preset determination threshold may be "average data+3psi", where average data is an average value of air pressure values when 20% +.n2+.50wt%, that is, when the air pressure value lasts for 4 seconds above the average data 3PSI (Pounds per Square Inch pounds force per square inch), a start valve floor opening failure warning signal is sent.
For example, in step S3, the preset upper limit may be 4 times, in some embodiments, a maximum of 4 air pressure values may be taken, and if all the 4 air pressure values exceed a preset determination threshold (e.g., are all higher than the average data 3 PSI), a start valve floor opening failure early warning signal is sent.
Illustratively, in some embodiments, the early warning signal may be transmitted by a fault code and distinguish between different fault types and fault modes, with an exemplary fault code consisting of 4 digits, where the first digit indicates the fault type (e.g., 4 indicates that the starting valve is open to the ground), the second digit takes a 0, is a space-occupying digit, has no practical significance, the third digit indicates the fault mode (e.g., 1 indicates a fault mode one, 2 indicates a fault mode two), and the fourth digit indicates the engine position of the aircraft (e.g., 1 indicates a left engine, 2 indicates a right engine). For example, when the fault code in the message is 4011, it indicates that the left engine is predicted to have a start flap floor non-opening fault, and the data is represented as a first fault mode, i.e., the air pressure value curve fluctuates in a (zigzag) shape.
Referring to fig. 6, a monitoring logic diagram for ground opening failure prediction of a starting valve provided by an embodiment of the present invention is provided, where "main electric door ON" indicates that an aircraft is in an energized PHASE, 1+.fwc phase+.2 indicates that an aircraft is in the ground, that is, in an energized and slipping PHASE, "APU bleed pressure+.2bar (Barometric Pressure, atmospheric pressure)" and "APU rotation speed+.95%" indicate that a conventional APU starts, when the above conditions are satisfied and the double-start-up valve cannot be simultaneously opened, i.e., the left-start-up valve is opened (sav1=1) and the right-start-up valve is closed (savv2=0), or the left-start-up valve is closed (savv1=0) and the right-start-up valve is opened (savv2=1), expressed by the parameters "savv1=1 and savv2=0" or "savv1=0". If the engine core rotation speed satisfies 23% +.n2+.35% the air pressure value curve is saw tooth (SAP saw tooth), then the fault code (code) is sent out, if the engine is left engine (left engine), then 4011 is sent out, if the engine is right engine (right engine), then 4012 is sent out, if the starting valve is in the initial opening stage, namely N2<12%, then maximum four air pressure values SAPmax-SAPmax are collected, and the average value SAPavg of the air pressure values is calculated when 20% < n2+.50%, if the difference between the four maximum air pressure values and SAPavg is not less than 3, then the fault code is sent out, if the engine is left engine (left engine), then 4021 is sent out, if the engine is right engine (right engine), then 4022 is sent out, and further, the fault code is written into the warning message.
Compared with the prior art, the embodiment of the invention can predict whether the starting valve is about to have a ground opening failure or not and send out an early warning signal when needed by monitoring the data change rule of the air pressure value after the starting valve is positioned on the ground, thereby ensuring the normal operation of flights.
As an alternative embodiment, it is determined whether the air pressure value curve fluctuates by:
And calling a sawtooth-shaped fluctuation algorithm to identify the shape of the air pressure value curve, and judging that the air pressure value curve fluctuates when the shape is sawtooth-shaped.
It is worth to say that, except ground opening failure, the starting valve failure also includes the open failure of the air non-instruction, and the open of the starting valve air non-instruction easily causes the starter structure damage and leads to the starter to leak oil in the air, because starter and engine share the same set of lubricating oil system, this can lead to the engine to leak oil in the air, causes serious threat to the safe operation of aircraft. Aiming at the non-command opening faults in the air of the starting valve, an electronic central monitoring system (ECAM/EICAS, electronic Centralized Aircraft Monitor/ENGINE INDICATING AND CREW ALERTING SYSTEM) of the current aircraft only generates warning information to remind a pilot when the starting valve is opened in the air greatly, but the warning mode is not timely, potential safety hazards exist, and due to the limitations of system monitoring logic and factory setting, the related ECAM warning information is not triggered by the non-command opening faults in the air of a plurality of starting valves at present, namely, a timely and accurate detection means for the non-command opening faults in the air of the starting valve in the current industry is lacking. In response to the foregoing deficiencies of the prior art, in some embodiments of the present invention, a method of detecting a non-commanded opening of a starting valve in the air is also provided.
As an alternative embodiment, when the aircraft operation parameter indicates that the aircraft is in an air flight phase, the starting valve fault diagnosis method further includes:
calling a threshold sequence of air pressure values;
Judging whether the air pressure value is in any overrun gear or not based on the air pressure value threshold sequence;
When the air pressure value is in any overrun gear, calculating corresponding duration time;
and outputting a starting valve air non-instruction opening fault signal when any duration is not smaller than a duration threshold value of the corresponding overrun gear.
It is worth to say that when the aircraft is in the air, the starting valve should be closed, so that the air pressure value after the starting valve should be close to 0, and when the starting valve is not tightly closed in the air due to faults, the air pressure value is raised, the inlet pressure of the precooler of the air conditioning system is greatly fluctuated, and the like. According to the embodiment of the invention, the fault condition of the starting valve is judged by setting the out-of-tolerance early warning logic on the air pressure value, so that the situation that the starting air valve (SAV, starter Air Valve) of an Engine (Engine) with no fault of ENG 1/2SAV POS (OPEN) is opened and the more serious events such as oil leakage and the like caused by the damage of the starter due to the fact that the starting valve is not tightly closed can be prevented.
As an alternative implementation manner, the air pressure value threshold value sequence comprises three air pressure value threshold values, wherein the three air pressure value threshold values divide three non-overlapping overrun gears, and the lower limit value of the first overrun gear is larger than the upper limit value of the second overrun gear;
The first duration threshold is larger than a third duration threshold, the third duration threshold is larger than a second duration threshold, and the first duration threshold, the second duration threshold and the third duration threshold are duration thresholds of the first overrun gear, the second overrun gear and the third overrun gear respectively.
As an optional implementation manner, the value ranges of the three air pressure value thresholds are respectively 1-5 PSI, 5-8 PSI and 8-45 PSI.
It is worth to say that, the value range of "1-5 PSI" includes the value of 1PSI and the value of 5PSI, and similarly, the value range of "5-8 PSI" includes the value of 5PSI and the value of 8PSI, and the value range of "8-45 PSI" includes the value of 8PSI and the value of 45PSI. Further, although the above-mentioned value ranges are coincident at the end points, in practical applications, the three air pressure value thresholds should take different values.
As an optional implementation manner, the first duration threshold is 1 minute, the second duration threshold is 5-10 seconds, and the third duration threshold is 20-90 seconds.
It is noted that, the value range of the second duration threshold is "5-10 seconds" including the value of 5 seconds and the value of 10 seconds, and the value range of the third duration threshold is "20-90 seconds" including the value of 20 seconds and the value of 90 seconds.
For example, when 3+.FWC phase+.ltoreq.9, it indicates that the aircraft is in the air flight PHASE, i.e. the aircraft is in the flight state between the start and landing, and when the air pressure value after the start of the valve exceeds 2PSI, it indicates that the start valve has failed with an air tight shut. Further, when the air pressure exceeds 6PSI, the starting valve may actuate the belt-driven starter in the air, which may damage the starter, and seriously cause the starter to leak oil or even cause the engine to stop in the air. For an over-the-air non-commanded open fault, different overrun gears may be set to distinguish due to different severity of the fault caused by different magnitude air pressure values.
The second duration threshold and the third duration threshold may take 5 seconds and 30 seconds, respectively, and the three air pressure value thresholds may take 2PSI, 6PSI, and 8PSI, respectively, and accordingly, the obtained overrun gear and the corresponding duration threshold may be that the first overrun gear may be SAP not less than 8, the first duration threshold is 1 minute, the second overrun gear may be 8> SAP not less than 6, the second duration threshold is 5 seconds, the third overrun gear may be 6> SAP >2, and the third duration threshold is 30 seconds, wherein the SAP value is the air pressure value.
Illustratively, in some embodiments, fault warning information and distinguishing severity of faults may be transmitted through fault codes, and the fault codes are illustratively composed of 4 digits, wherein the first digit indicates a fault type (for example, 5 indicates a start valve in-air non-command open fault), the second digit indicates a source of early warning trigger (for example, 0 indicates that the system automatically detects a start valve abnormal large open fault; 1 indicates non-system detection, and 1 indicates that the fault diagnosis method provided by the embodiment of the invention is also used for detecting), the third digit indicates a fault severity level (for example, 1-3 indicates a high-to-low fault severity level, wherein 1 indicates the highest level), the fourth digit indicates an engine position of an aircraft (for example, 1 indicates a left engine, 2 indicates a right engine), and further, the priority levels of the fault code trigger sequence are 501, 5H1, 5H2 and 5H3 respectively from high to low.
Referring to fig. 7, a logic diagram for monitoring open fault detection of a start valve in air without instruction is provided in an embodiment of the present invention, where "main valve ON" indicates that an aircraft is in an electrified PHASE, 3+.fwc phase+.9 indicates that the aircraft is in an air flight PHASE, that is, a take-off and slide-in PHASE, then if a start valve open signal (sav=1) is received in the air, a fault code 5011 (left) or 5012 (right) is triggered, if sap+.8 and lasts for one minute, a fault code 5H11 (left) or 5H12 (right) is triggered, if sap+.6 and lasts for 5 seconds, a fault code 5H21 (left) or 5H22 (right) is triggered, and if SAP 6 fact exceeds 2 and lasts for 30 seconds, a fault code 5H31 (left) or 5H32 (right) is triggered.
Compared with the prior art, the fault diagnosis method for the starting valve provided by the embodiment of the invention comprises the steps of determining a working stage in which the starting valve is positioned based on the rotating speed of the engine core machine when the aircraft running parameter indicates that the aircraft is positioned on the ground, drawing an air pressure value curve after the starting valve is positioned in a preset rotating speed range when the working stage is a stable opening stage, outputting a fault early warning signal when the air pressure value curve fluctuates, and outputting a fault early warning signal when the starting valve is opened on the ground, wherein when the working stage is an initial opening stage, if the air pressure value after the starting valve is continuously larger than a preset judging threshold value in a first preset duration time or the frequency of the air pressure value being larger than the preset judging threshold value in a preset time period exceeds a preset upper limit, outputting the fault early warning signal when the starting valve is opened on the ground, wherein the preset judging threshold value and an average value of the air pressure value in the initial opening stage are in positive correlation. According to the embodiment of the invention, whether the ground opening failure occurs to the starting valve can be predicted in advance by monitoring the data change rule of the air pressure value after the starting valve is positioned on the ground, so that the normal operation of the flight is ensured.
It should be noted that, in some application scenarios, only the air non-instruction opening fault detection may be performed, that is, the part of the solution that the ground cannot be opened for fault early warning is not included, and in some embodiments, the method for diagnosing the starting valve fault includes:
When the aircraft operation parameters indicate that the aircraft is in an air flight phase, calling an air pressure value threshold sequence;
Judging whether the air pressure value is in any overrun gear or not based on the air pressure value threshold sequence;
When the air pressure value is in any overrun gear, calculating corresponding duration time;
and outputting a starting valve air non-instruction opening fault signal when any duration is not smaller than a duration threshold value of the corresponding overrun gear.
The air pressure value threshold sequence comprises three air pressure value thresholds, wherein the three air pressure value thresholds divide three non-overlapping overrun gears, and the lower limit value of the first overrun gear is larger than the upper limit value of the second overrun gear;
The first duration threshold is larger than a third duration threshold, the third duration threshold is larger than a second duration threshold, and the first duration threshold, the second duration threshold and the third duration threshold are duration thresholds of the first overrun gear, the second overrun gear and the third overrun gear respectively.
The three air pressure value thresholds are exemplified by the values of 1-5 PSI, 5-8 PSI and 8-45 PSI respectively.
For example, the first duration threshold is 1 minute, the second duration threshold is 5-10 seconds, and the third duration threshold is 20-90 seconds.
To achieve the above object, an embodiment of the present invention further provides a computer readable storage medium, where the computer readable storage medium includes a stored computer program, and when the computer program runs, controls a device where the computer readable storage medium is located to execute the method for diagnosing a failure of a startup valve according to any one of the embodiments.
Referring to fig. 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, where the processor 21 implements steps in the above-described embodiment of the method for diagnosing a failure of a starting valve, such as steps S1 to S3 described in fig. 1, when executing the computer program.
The computer equipment can be a desktop computer, a notebook computer, a palm computer, a cloud server and other computing equipment. The computer device may include, but is not limited to, a processor, a memory. It will be appreciated by those skilled in the art that the schematic diagram is merely an example of a computer device and is not limiting of the computer device, and may include more or fewer components than shown, or may combine some of the components, or different components, e.g., the computer device may also include input and output devices, network access devices, buses, etc.
To achieve the above object, an embodiment of the present invention further provides a system for diagnosing a failure of a starting valve, including the computer device according to any one of the above embodiments, and:
the data acquisition module is used for acquiring target parameters from the electronic engine controller, transmitting the target parameters to the computer equipment, and acquiring initial message data and transmitting the initial message data to the message generation module after receiving a starting valve fault warning signal (a starting valve ground opening failure early warning signal and/or a starting valve air non-instruction opening failure signal) sent by the computer equipment;
The message generation module is used for receiving the initial message data and generating a warning message, and sending the warning message to target equipment after receiving a message sending instruction of the computer equipment;
and the multifunctional control display module is used for adjusting the threshold value parameters.
It is worth to say that, at present, the fault monitoring of the starting valve in the industry is mainly carried out by the electronic central monitoring system of the aircraft, the electronic central monitoring system can send warning information to the pilot, and the pilot informs the ground engineer through satellite phones or aviation telegrams, so that the fault reporting mode has delay, and is not beneficial to timely and accurately transmitting the fault information. Therefore, in some embodiments of the invention, after the failure of the starting valve is identified, the warning message is triggered to be downloaded to the ground mailbox and/or the audible and visual alarm device is triggered to carry out real-time notification, so that maintenance personnel can receive the failure warning message at the first time and carry out failure troubleshooting in time.
It will be appreciated that the computer device for performing the method for diagnosing a startup valve failure according to any one of the above embodiments is a core module of the startup valve failure diagnosis system. It should be noted that, in some embodiments, the computer device may also be an ACMS monitoring logic module, that is, in some embodiments, an algorithm may be written in an ACMS system customizable programming module to implement the method for diagnosing a startup valve fault described in the foregoing embodiments. And the ACMS monitoring logic module (computer equipment) can trigger the data acquisition module to acquire initial message data and send a touch warning message when the starting valve is identified to be in or about to be in failure.
Further, the data acquisition module is a data input interface module of the starting valve fault diagnosis system, wherein when the two engines of the same aircraft are respectively subjected to starting valve fault diagnosis and monitoring, the data acquisition modules of the engines also correspondingly and independently operate. The data acquisition module acquires the parameter values of the electronic engine controller in real time through the ARINC 429 bus, the data sources of the parameter values are consistent with the vibration warning data sources of the electronic central monitoring system of the aircraft received by the pilot, and the data acquisition module transmits the acquired target parameters to the computer equipment (ACMS monitoring logic module).
And after receiving the fault early warning signal sent by the computer equipment (ACMS monitoring logic module), the data acquisition module acquires the data required by the message, namely the initial message data, in a snapshot or time window sampling mode, wherein the time window sampling mode ensures the real-time performance and simultaneously ensures the transmission of the parameters required by fault analysis to the greatest extent, and can be regarded as real-time QAR (Quick Access Recorder ) data recording and transmission of the parameters related to the monitoring of the engine starting valve. Further, referring to table 1, an example of initial message data is provided in an embodiment of the present invention, where the initial message data is data obtained at the instant of message activation, and is mainly used to illustrate the overall situation of a data overrun event, including a flight number, a departure airport, a landing airport, a altitude, an engine, and a high-voltage rotation speed N2 (engine core rotation speed), etc.
TABLE 1 initial message data
The initial message data is formatted into the warning message for transmission by an ACARS (Aircraft Communications ADDRESSING AND Reporting System) for example, so that ground staff can decode the warning message by the same rule, and the message data is structured and stored in a database conveniently. Further, the initial message data may also be sent to a printer in a print format for the pilot or ground engineer to read.
The warning message mainly comprises basic information and working state information, and the basic information comprises flight information, event triggering fault codes (fault codes) and operation state information of an Auxiliary Power Unit (APU), and the working state information comprises working state information of an engine and a starting valve, such as N2 rotating speed, air pressure values, valve opening and closing state information of a related air-conditioning bleed air pipeline valve and the like.
For example, referring to fig. 9, a schematic diagram of a warning message provided by an embodiment of the present invention is shown in fig. 9, where the warning message is related to a start valve (start valve) with no open fault early warning on the ground, and includes basic information (number of machine, base, model, flight number, etc.) and early warning information, where the early warning information is recorded for different fault modes and engines respectively.
Further, the message generating module is also used for warning message buffering and route forwarding mechanism setting.
It will be appreciated that different routing settings may meet different message reading requirements, and that exemplary routing settings include 6 large categories (Loader, ACARS, printer, ethernet, recorder and INTEGRATED DISK) and 3 ways (Automatic, manual and Formatted).
The Loader is a handheld data Loader, through the arrangement, messages can be directly transmitted to the Loader after being generated, ACARS is a message space transmission mode, printer is a Printer, the messages can be directly printed through the arrangement after being generated, ethernet is a network connection mode, the Recorder corresponds to QAR, the messages can be backed up in a QAR file medium and downloaded to a ground server through wireless QAR, INTEGRATED DISK corresponds to PCMCIA (Personal Computer Memory Card International Association, personal computer memory card), and the card is arranged in DMU (DATA MANAGEMENT Unit ) equipment of an airplane.
Further, the Automatic mode is a mode of sending a message immediately after a fault early warning event is triggered, the Manual mode is a mode of manually sending a message, in the embodiment of the invention, an ACMS monitoring logic module (computer equipment) sends an instruction to a message generating module, and the Formatted mode represents that data is transmitted in a band format, and if the data is transmitted in a non-Formatted format, all the data are connected in series without intervals.
For example, in some embodiments, loader, ACARS, and Printer Manual and Formatted approaches may be employed.
Further, the message generating module is also used for setting an ACARS downloading path. Referring to fig. 10, an interface diagram of a message download path is provided in an embodiment of the present invention, where an ACMS message download function (Downlinks) is used to add an additional fixed address to an Address (ADDRESSES) column, and if the address is blank, the address set by ATSU (AIR TRAFFIC SERVICES Unit, air traffic service Unit) is selected by default. For example, according to the ACARS transmission path (Destination) of the message defined by its own requirement, a VHF (Very High Frequency ) single path, a satellite single path or a VHF-first satellite leak repairing manner may be selected, and meanwhile, deletion and line changing may be set to save transmission traffic.
Further, the multifunctional display module may be used to view relevant thresholds (e.g., preset decision thresholds and air pressure value thresholds as described in the above embodiments, etc.), and an airline personnel or an engine engineer may adjust the threshold triggered by the warning message to an engine of an aircraft through the module, so as to implement the required individual control, and the module is integrated into an onboard multifunctional control display module (MCDU, multifunction Control Display Unit), and may implement the above functions by developing corresponding pages and associating threshold parameters.
For ease of understanding, referring to fig. 11, which is a flowchart illustrating a system for diagnosing a failure of a starting valve according to an embodiment of the present invention, it can be seen from fig. 2 that parameters of an electronic engine controller are sent to a central electronic monitoring system for a pilot to view in the air, and at the same time, the parameters are also sent to a wireless quick access recorder (WQAR, wireless Quick Access Recorder) and an aircraft status monitoring system through an aircraft data interface and management component (FDIMU, flight Data Interface and Management Unit), and a crew can set a threshold through a multifunctional control display module. The aircraft state monitoring system monitors the air pressure value, when the starting valve is identified to be faulty or will be faulty, a fault warning signal is generated, the warning message is triggered to be sent to the ground data system, decoding analysis is automatically carried out, the warning message is compared with subscription conditions preset by engineers, the successfully matched subscription is sent to a subscription mailbox in the form of mail, meanwhile, an audible and visual alarm connected with the ground and the system is triggered, and the ground engineers can set the early warning logic.
Compared with the prior art, the starting valve fault diagnosis system provided by the embodiment of the invention comprises computer equipment, a data acquisition module, a message generation module and a multifunctional control display module, wherein the embodiment of the invention can accurately predict the starting valve fault and timely send fault warning information to related staff, the timeliness and accuracy of fault information transmission are improved, and the embodiment of the invention can flexibly adjust related threshold values by arranging the multifunctional control display module, thereby being suitable for fault early warning of different starting valves of different types and having strong practicability.
While the foregoing is directed to the preferred embodiments of the present invention, it will be appreciated by those skilled in the art that changes and modifications may be made without departing from the principles of the invention, such changes and modifications are also intended to be within the scope of the invention.
Claims (9)
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