CN114036632A - Method for evaluating the service life of an onboard device of an aircraft - Google Patents
Method for evaluating the service life of an onboard device of an aircraft Download PDFInfo
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Abstract
The invention discloses an evaluation method for evaluating the service life of airborne equipment of an aircraft, which comprises the following steps: constructing a configuration library of the airborne equipment, wherein configuration identification information and configuration real information used for distinguishing various airborne equipment are stored in the configuration library, and the configuration real information comprises a service life consumption function of the airborne equipment, which defines the relationship between the service life consumption and the monitored related physical quantity; monitoring a physical quantity representing the operating state of the airborne equipment; estimating the service life consumption value of the airborne equipment in a time integration mode based on the service life consumption function; and recording and updating the service life consumption value, and evaluating the service life of the airborne equipment based on the service life consumption value. According to the method, the service life of the airborne equipment can be quantitatively analyzed and evaluated more accurately, and the increase of the maintenance cost caused by the safety risk caused by exceeding the service life of the equipment and the early maintenance or replacement of the equipment is avoided.
Description
Technical Field
The invention relates to the use and maintenance of equipment on board an aircraft, in particular to the life cycle management of equipment on board an aircraft, and particularly to an evaluation method for evaluating the service life of equipment on board an aircraft.
Background
In onboard maintenance systems, there are various onboard equipment of the temporary life piece type that need to meet the mandatory replacement requirements in the continuous airworthiness documentation. Wherein the lifetime of the time-to-live piece can be divided into a time lifetime, or both. In current on-board maintenance, the service life or the remaining service life of various on-board equipment is estimated only by means of the working hours of a pilot or the experience of maintenance personnel, which means that the service life of various on-board equipment is estimated fuzziness by relying on the experience generally. This results in ambiguity in the lifetime of the life piece when it is determined, which may cause safety risks due to the fact that the onboard equipment is actually used beyond the life cycle or service life that it should be used, and may also result in unnecessary increase in maintenance costs due to corresponding maintenance or equipment replacement of the onboard equipment when it is still normally usable for a considerable time or number of times.
Although some efforts have been made in the related art to solve the above problems, various solutions have been proposed, the practical feasibility and the achieved effect of which have not been satisfactory yet. For example, one class of existing solutions relies substantially entirely on information relating to equipment maintenance to estimate useful life, which has the disadvantage that the basis for such estimation is relatively single and thus limited. Another type of scheme conceptually provides statistical data-based prediction of the service life of equipment by using a machine learning algorithm based on data characteristics directly related to faults, but in practical application, the limit is that the number of samples in the same type may not be enough to support a large data algorithm on which the samples depend, and the prediction effect is poor. Yet another type of algorithm proposes determining the fatigue life of the respective component based on stress monitoring, but such a solution is relatively limited in scope of application. Moreover, the same or similar short boards exist in the above-mentioned several types of existing solutions, such as they often only provide a qualitative conclusion directly as to whether maintenance is required, which is often not enough to provide enough judgment basis for the service life of the onboard equipment for the flight crew or maintenance personnel.
Accordingly, there is a need for a method that can more accurately assess the lifetime of an onboard device to at least partially alleviate or solve the above-mentioned problems and deficiencies with existing solutions.
Disclosure of Invention
The invention aims to overcome the defects that the accuracy of the existing method for evaluating the service life of the airborne equipment and the applicability and effect in practical application are not satisfactory, and provides a novel method for evaluating the service life of the airborne equipment of an airplane.
The invention solves the technical problems through the following technical scheme:
the invention provides an evaluation method for evaluating the service life of airborne equipment of an aircraft, which is characterized by comprising the following steps:
constructing a configuration library of the airborne equipment, wherein configuration identification information and configuration real information of the airborne equipment are stored in the configuration library, the configuration identification information is used for distinguishing various types of airborne equipment, the configuration real information comprises a service life consumption function of the airborne equipment, the service life consumption function is defined by the following definition formula (1),
f(t)＝Xi(t)·ωi(t)·Wi (1)
wherein i is a physical quantity related to the service life of the onboard equipment, and i is 1,2, …, N; xi(t) a value representing the ith physical quantity at the current time t; the physical quantities characterize the operating state of the onboard equipment; wiA weight coefficient of physical quantity, ω, representing the ith physical quantityi(t) represents according to Xi(t) a hierarchy weight factor determined by the range of values in which the value of (t) lies;
monitoring all physical quantities representing the operating state of the airborne equipment;
estimating the service life consumption value of the airborne equipment in a time integration mode according to the following formula (2),
wherein N represents the total number of all physical quantities monitored;
and recording and updating the service life consumption value, and evaluating the service life of the airborne equipment based on the service life consumption value.
According to an embodiment of the present invention, the configuration identification information further includes ID information of each onboard device and remaining service life, and the evaluation method further includes the steps of:
feeding back the estimated service life consumption value to the configuration library, and updating the remaining service life of the corresponding onboard equipment based on the service life consumption value, wherein the initial value of the remaining service life is set as the full service life of the onboard equipment.
According to one embodiment of the invention, the service life consumption function comprises a time life consumption function and a number of times life consumption function.
According to an embodiment of the present invention, in the evaluation method, defining the time-life consumption function includes:
based on
The defining conditions of (2) define a physical quantity weight coefficient; and
the hierarchical weight coefficients are defined based on the range of values in which the values of the physical quantity lie, wherein,
when the value X of the physical quantityi(t) operating condition corresponding to the onboard equipment being under standard load, based on Xi(t)·ωiThe constraint of (t) → 1 defines the hierarchy weight coefficient,
when the value X of the physical quantityi(t) operating condition corresponding to the on-board unit being overloaded, based on Xi(t)·ωiThe constraint of (t) → A defines the hierarchical weight coefficients, where A>1，
When the value X of the physical quantityi(t) operating condition corresponding to low load of the onboard equipment, based on Xi(t)·ωiThe constraint of (t) → B defines the hierarchical weight coefficients, wherein B<1, wherein the ith physical quantity traverses all physical quantities characterizing the operating state of the onboard device.
According to one embodiment of the invention, the value X of the physical quantity is determinediAnd (t) corresponding to the non-working state of the no-load of the airborne equipment, and defining the corresponding hierarchical weight coefficient to be zero.
According to one embodiment of the invention, the onboard equipment comprises an engine, and the physical quantities monitored for said engine comprise engine exhaust temperature, engine rotor pack.
According to one embodiment of the invention, in the monitoring step, a sensing device is used for monitoring the physical quantity of the running state of the airborne equipment, and the step of estimating the service life consumption value of the airborne equipment is triggered in response to the obvious change of the monitoring data monitored by the sensing device;
wherein, the obvious change of the monitoring data is defined as that the change of the monitoring data reaches a preset change amplitude threshold value within a preset time period, and the monitoring data comprises current, voltage, temperature or pressure.
According to one embodiment of the invention, in the evaluation method, the number-of-times-of-life-consumption function is defined as a number of times the number of times the life-of times is consumed equals the number of times associated with the number of times the number.
According to one embodiment of the invention, the onboard equipment comprises a landing gear device, the state change signal monitored for the landing gear device comprises a landing gear uplock signal; alternatively, the first and second electrodes may be,
the onboard equipment comprises a flight controller, and the state change signal monitored for the landing gear device comprises a hydraulic trigger signal which is characterized in that the supply pressure of a hydraulic system of the flight controller exceeds a preset hydraulic pressure upper limit value.
According to one embodiment of the invention, the monitoring step uses a device operational logic judger to monitor the status change signal and, in response to the status change signal, triggers an updated count of the number of times the life is consumed;
wherein the state change signal comprises a power-on signal, a power-off signal, other types of switching value signals, or signals triggered by the corresponding physical quantity exceeding or falling below a preset threshold.
According to an embodiment of the invention, the evaluation method further comprises the steps of:
the method comprises the steps of collecting fault information of the airborne equipment, fault intervals and physical quantities which are monitored during the fault intervals and are used for representing the running state of the airborne equipment, and correcting a physical quantity weight coefficient and a hierarchy weight coefficient in a service life consumption function of the corresponding airborne equipment based on the information.
According to an embodiment of the invention, the evaluation method further comprises the steps of:
and monitoring whether the residual service life of the airborne equipment is too low or not based on the data in the configuration library, and sending out early warning information when the airborne equipment with too low residual service life is monitored, wherein the too low residual service life is defined as being lower than a preset lower limit value of the service life or lower than a preset lower limit proportion value of the full service life.
On the basis of the common knowledge in the field, the above preferred conditions can be combined randomly to obtain the preferred embodiments of the invention.
The positive progress effects of the invention are as follows:
according to the method for evaluating the service life of the onboard equipment of the aircraft, the physical quantity signals related to the equipment are monitored and analyzed based on the physical quantity signals, so that more accurate quantitative analysis and evaluation on the service life of the onboard equipment can be realized, and the increase of maintenance cost caused by safety risks and premature maintenance or replacement of the equipment due to exceeding of the service life of the equipment can be avoided.
Drawings
Fig. 1 is a schematic flow diagram of an evaluation method for evaluating the service life of an onboard device of an aircraft according to a preferred embodiment of the invention.
Fig. 2 is a flowchart illustrating an example of the application of the life prediction of the time-life member according to the evaluation method of the preferred embodiment of the present invention.
Fig. 3 shows an example of a time-life consumption function of an evaluation method for evaluating the service life of an onboard device of an aircraft according to a preferred embodiment of the invention, in which a physical quantity of the exhaust temperature of the aircraft engine, a physical quantity of the high-pressure rotor speed and a time-life consumption value predicted on the basis of the two physical quantities are shown in sequence from top to bottom for a certain period of time.
Detailed Description
The following detailed description of the preferred embodiments of the present invention, taken in conjunction with the accompanying drawings, is intended to be illustrative, and not restrictive, and it is intended that all such modifications and equivalents be included within the scope of the present invention.
In the following detailed description, directional terms, such as "left", "right", "upper", "lower", "front", "rear", and the like, are used with reference to the orientation as illustrated in the drawings. Components of embodiments of the present invention can be positioned in a number of different orientations and the directional terminology is used for purposes of illustration and is in no way limiting.
Referring to fig. 1, an evaluation method for evaluating the service life of an onboard device of an aircraft according to a preferred embodiment of the invention may comprise the following steps:
constructing a configuration library of the airborne equipment, wherein configuration identification information and configuration real information of the airborne equipment are stored in the configuration library, the configuration identification information is used for distinguishing various types of airborne equipment, the configuration real information comprises a service life consumption function of the airborne equipment, the service life consumption function is defined by the following definition formula (1),
f(t)＝Xi(t)·ωi(t)·Wi (1)
wherein i is a physical quantity related to the service life of the onboard equipment, and i is 1,2, …, N; xi(t) a value representing the ith physical quantity at the current time t; the physical quantities characterize the operating state of the onboard equipment; wiA weight coefficient of physical quantity, ω, representing the ith physical quantityi(t) represents according to Xi(t) a hierarchy weight factor determined by the range of values in which the value of (t) lies;
monitoring all physical quantities representing the operating state of the airborne equipment;
estimating the service life consumption value of the airborne equipment in a time integration mode according to the following formula (2),
wherein N represents the total number of all physical quantities monitored;
and recording and updating the service life consumption value, and evaluating the service life of the airborne equipment based on the service life consumption value.
It will be appreciated that the onboard equipment herein may be referred to as a time-of-life item, which may be a module, component, part, etc., that needs to meet the mandated replacement requirements in the continuous airworthiness document. The lifetime of a time-of-life element may be divided into a time lifetime, a number of lifetimes, or both.
And the configuration identification information can comprise or refer to the part number of the equipment, and the part number associates the time-of-life part with the configuration real information for tracing, querying and the like. The part number includes one or more of system code, model code, pattern type, configuration model, technical suffix and other information. The configuration identification information may be used to identify different configuration products of the recording device under one basic category or model, which may refer to modules, components, parts, or the like.
The configuration identification information further comprises ID information and remaining service life of each airborne device, and the evaluation method further comprises the following steps:
feeding back the estimated service life consumption value to the configuration library, and updating the remaining service life of the corresponding onboard equipment based on the service life consumption value, wherein the initial value of the remaining service life is set as the full service life of the onboard equipment.
Wherein the service life consumption function comprises a time service life consumption function and a time service life consumption function according to the type difference of the targeted airborne equipment.
The following first describes an evaluation method suitable for a device whose lifetime is measured in time, and in particular the definition of a time lifetime consumption function therein and an evaluation method or process applying the same.
According to some preferred embodiments of the invention, in the evaluation method, defining the time-life consumption function comprises:
based on
The defining conditions of (2) define a physical quantity weight coefficient; and
the hierarchical weight coefficients are defined based on the range of values in which the values of the physical quantity lie, wherein,
when the value X of the physical quantityi(t) operating condition corresponding to the onboard equipment being under standard load, based on Xi(t)·ωiThe constraint of (t) → 1 defines the hierarchy weight coefficient,
when the value X of the physical quantityi(t) operating condition corresponding to the on-board unit being overloaded, based on Xi(t)·ωiThe constraint of (t) → A defines the hierarchical weight systemA number of, wherein A>1，
When the value X of the physical quantityi(t) operating condition corresponding to low load of the onboard equipment, based on Xi(t)·ωiThe constraint of (t) → B defines the hierarchical weight coefficients, wherein B<1, wherein the ith physical quantity traverses all physical quantities characterizing the operating state of the onboard device.
Wherein, when the value X of the physical quantityiAnd (t) corresponding to the non-working state of the no-load of the airborne equipment, and defining the corresponding hierarchical weight coefficient to be zero.
It is understood that in the present disclosure, the conditions of trend 1, trend A and trend B as described above can be defined as X according to actual needsi(t)·ωi(t) falls between 0.8 and 1.2 times or even 0.6 and 1.5 times the target value, and it is not strictly required that it approaches a specific value.
The definition of the time-life consumption function according to the above preferred embodiment of the present invention is based on the following findings.
When the elapsed time lifetime determination is made:
one or more physical quantities related to the time-of-life piece, such as temperature, pressure, etc., are monitored, and if the number of related physical quantities is N, the monitored physical quantity can be recorded as Xi(t),i＝1,2,…,N；
For each physical quantity, a weight W of the physical quantity is respectively giveniI is 1,2, …, N, and
classifying the value range of each physical quantity according to the influence degree of the value of the physical quantity on the service life;
for each level of the ith physical quantity, respectively giving a level weight;
ωi,j,i＝1,2,…,N,j＝1,2,…,niwherein n isiThe number of levels divided for the ith physical quantity.
On the basis, the time life consumed by the onboard equipment (time life piece) corresponding to the current time or the time period can be predicted through the following steps:
1. recording the value of each physical quantity at the current time as X1(t),X2(t),…,XN(t) corresponding to a physical weight W1,W2,…,WN；
2. Respectively determine X1(t),X2(t),…,XN(t) the level of the hierarchy, finding the weight omega of the corresponding level1(t),ω2(t),…,ωN(t)；
3. The time life consumed at the present moment is:
then, the time life consumed at all times is added to obtain a predicted value or an estimated value of the time life consumption:
an estimate of the time life consumed by the time life piece may then be output.
In the above description, it is possible to define that the physical quantity weight coefficient satisfies the constraint
And the hierarchical weight coefficients are constrained as follows:
when the monitored time-of-life piece is in stationary operation, ω should be adjusted1(t),ω2(t),…,ωN(t) reaction of X1(t)·ω1(t)→1,…,XN(t)·ωN(t)→1；
When the monitored time-service item is in overload operation, it is adjusted so that
ω1(t),ω2(t),…,ωN(t) reaction of X1(t)·ω1(t)>1,…,XN(t)·ωN(t)>1
When the monitored duration is in low-load operation, it is adjusted so that
ω1(t),ω2(t),…,ωN(t) reaction of X1(t)·ω1(t)<1,…,XN(t)·ωN(t)<1
Under the condition of meeting the constraint, time and physical quantity data between two adjacent faults are utilized, and the physical quantity weight coefficient and the level weight coefficient can be continuously optimized through machine learning, so that the service life of the airborne equipment estimated or predicted based on the method is more accurate.
According to some further preferred embodiments of the invention, the on-board device comprises an engine, and the physical quantities monitored for said engine comprise engine exhaust temperature, engine rotor binding.
In the monitoring step, a sensing device can be adopted to monitor the physical quantity of the running state of the airborne equipment, and the step of estimating the service life consumption value of the airborne equipment is triggered in response to the obvious change of monitoring data monitored by the sensing device;
wherein, the obvious change of the monitoring data is defined as that the change of the monitoring data reaches a preset change amplitude threshold value within a preset time period, and the monitoring data comprises current, voltage, temperature or pressure.
The following will describe an evaluation method suitable for a device whose life is measured in the number of times such as the number of times of use or the number of times of switching, and a definition of a number life consumption function therein and an evaluation method or procedure to which it is applied.
According to some preferred embodiments of the invention, the number of lifetime consumption function is defined in the evaluation method as the number of times the lifetime consumed is equal to the number of times a state change signal associated with the onboard equipment occurs, wherein the state change signal is indicative of a predetermined state change of the operating state of the onboard equipment. It will be appreciated that the above defined number lifetime consumption function may also be understood from another point of view as a simplification of the above definition of equation (1) under one particular condition.
For number of times lifetime, for example and without limitation, the following examples: (1) the service life of the number of times of retraction and release of the undercarriage is consumed by +1 after the signal of the uplock of the undercarriage is triggered; (2) for a flight controller, if the hydraulic system supply pressure is greater than 2800 pounds per square inch, which is considered a trigger signal, the number of times the flight controller is pressed up consumes + 1.
For the method of estimating number of times of life, suitable onboard equipment may include, for example, a landing gear device for which the monitored state change signal includes a landing gear uplock signal; alternatively, the first and second electrodes may be,
a flight controller may be included, the monitored state change signal for the landing gear arrangement including a hydraulic trigger signal indicative of a hydraulic system supply pressure of the flight controller exceeding a predetermined upper hydraulic pressure limit.
Wherein in the monitoring step, an equipment operation logic judger is adopted to monitor the state change signal and respond to the state change signal to trigger the update calculation of the consumed time life;
wherein the state change signal comprises a power-on signal, a power-off signal, other types of switching value signals, or signals triggered by the corresponding physical quantity exceeding or falling below a preset threshold.
On the basis of the above-described embodiments of the method for evaluating the lifetime of a device whose lifetime is measured in time or the method for evaluating the lifetime of a device whose lifetime is measured in times, it is further preferable that the evaluation method further includes the steps of:
the method comprises the steps of collecting fault information of the airborne equipment, fault intervals and physical quantities which are monitored during the fault intervals and are used for representing the running state of the airborne equipment, and correcting a physical quantity weight coefficient and a hierarchy weight coefficient in a service life consumption function of the corresponding airborne equipment based on the information.
Preferably, as shown in fig. 2, the evaluation method may further include performing operations including data updating, tracing, querying, repairing, replacing and the like based on the estimated or predicted remaining service life of the onboard equipment.
For example, the evaluation method may further include the steps of:
and monitoring whether the residual service life of the airborne equipment is too low or not based on the data in the configuration library, and sending out early warning information when the airborne equipment with too low residual service life is monitored, wherein the too low residual service life is defined as being lower than a preset lower limit value of the service life or lower than a preset lower limit proportion value of the full service life.
According to some embodiments, referring to fig. 2, after the lifetime of the lifetime piece is counted, a corresponding logic judger may be operated to continuously monitor the physical quantity signal according to the operating characteristics of the lifetime piece.
After the trigger signal, the equipment operates the logic judger, the time life or the number life consumed by the life piece is output, a life timer (counter) is given, meanwhile, the life timer (counter) reads the current remaining life stored in the configuration library, the configuration is real, and the latest remaining life is calculated and output.
If the service life is not exhausted at the moment, updating the residual service life and storing the residual service life in a configuration discipline; and if the service life is exhausted, maintaining or replacing the time-service life piece, updating the number of the piece, inquiring the mandatory replacement requirement of the continuous airworthiness file, and updating the residual service life of the time-service life piece after maintenance or replacement. It should be noted that if an epoch is associated with both a time lifetime and a number of lifetimes, the lifetime of the epoch is considered to be exhausted as long as one of the lifetimes is exhausted.
Finally, maintenance personnel can inquire and trace the real information of the corresponding time-spent life piece through the number of the life piece at any time, and obtain the remaining life of the life piece at the target.
For the evaluation and prediction of the time life, the application example shown therein is explained below with reference to fig. 3. And 3, recording the exhaust temperature of the aircraft engine, the rotating speed of the high-pressure rotor and the predicted time life consumption in sequence from top to bottom in a certain period.
The physical quantity monitored as shown in FIG. 3 is the aircraft engine Exhaust Gas Temperature (EGT), X1(t), the ratio of the high pressure rotor speed to the high pressure rotor speed (N2), i.e., X2(t) of (d). The weight coefficients of the two are respectively W1＝0.5,W20.5. For aircraft enginesExhaust temperature X1(t), when the temperature is higher than 800 ℃, the engine is in an overload running state, the influence on the service life is large, and at the moment, a large hierarchical weight omega is taken10.0027; when the temperature is less than or equal to 800 ℃, the engine is in a normal or low-load operation state, the influence on the service life is small, and the smaller hierarchical weight omega is taken at the moment1＝0.0014。
High pressure rotor speed X for an aircraft engine2(t), when the rotating speed is more than 100%, the engine is in an overload running state, the influence on the service life is large, and at the moment, a large hierarchical weight omega is taken20.0166; when the rotating speed is less than or equal to 100 percent, the engine is in a normal or low-load operation state and has small influence on the service life, and the lower hierarchical weight omega is taken at the moment2＝0.0105。
The function of the time-life consumption used in the estimation is:
wherein
To X0(t) summing ^ X over a monitoring time0(t) dt is 8112, which is the predicted time-life consumption.
As can be seen from FIG. 3, the predicted time life consumed per unit time is greater when the engine is operating in an overload condition; when the engine normally operates, the predicted time life consumed in unit time is basically consistent with the time life consumed in unit time during normal operation; when the engine is operating at low load, the predicted time life consumed per unit time is small.
Therefore, the selection of the hierarchical weight should firstly fit the normal operation condition of the life piece, so that the predicted time life consumption and the normal time life consumption are basically consistent; under the condition of overload operation, a larger level weight should be selected; in the case of low load operation, the selected hierarchical weight may be the same as or slightly less than the case of normal operation. I.e. the hierarchical weights need to satisfy the following constraints:
according to the assessment method for assessing the service life of the onboard equipment of the aircraft in the preferred embodiment of the invention, by monitoring the physical quantity signals related to the equipment and analyzing based on the physical quantity signals, quantitative analysis and assessment of the service life of the onboard equipment can be more accurately realized, and the increase of maintenance cost caused by safety risks caused by exceeding the service life of the equipment and premature maintenance or replacement of the equipment can be avoided.
While specific embodiments of the invention have been described above, it will be appreciated by those skilled in the art that these are by way of example only, and that the scope of the invention is defined by the appended claims. Various changes and modifications to these embodiments may be made by those skilled in the art without departing from the spirit and scope of the invention, and these changes and modifications are within the scope of the invention.
Claims (12)
1. An assessment method for assessing the service life of a device on board an aircraft, characterized in that it comprises the following steps:
constructing a configuration library of the airborne equipment, wherein configuration identification information and configuration real information of the airborne equipment are stored in the configuration library, the configuration identification information is used for distinguishing various types of airborne equipment, the configuration real information comprises a service life consumption function of the airborne equipment, the service life consumption function is defined by the following definition formula (1),
f(t)＝Xi(t)·ωi(t)·Wi (1)
wherein i is a physical quantity related to the service life of the onboard equipment, and i is 1,2, …, N; xi(t) a value representing the ith physical quantity at the current time t; the physical quantities characterize the operating state of the onboard equipment; wiA weight of a physical quantity representing the ith physical quantityCoefficient of gravity, ωi(t) represents according to Xi(t) a hierarchy weight factor determined by the range of values in which the value of (t) lies;
monitoring all physical quantities representing the operating state of the airborne equipment;
estimating the service life consumption value of the airborne equipment in a time integration mode according to the following formula (2),
wherein N represents the total number of all physical quantities monitored;
and recording and updating the service life consumption value, and evaluating the service life of the airborne equipment based on the service life consumption value.
2. An assessment method for assessing the service life of an onboard device of an aircraft according to claim 1, characterized in that said configuration identification information also comprises ID information of the respective onboard device and the remaining service life, said assessment method further comprising the following steps:
feeding back the estimated service life consumption value to the configuration library, and updating the remaining service life of the corresponding onboard equipment based on the service life consumption value, wherein the initial value of the remaining service life is set as the full service life of the onboard equipment.
3. An assessment method for assessing the service life of an apparatus on-board an aircraft according to claim 2, characterized in that said service life consumption function comprises a time service life consumption function and a number of times service life consumption function.
4. An assessment method for assessing the service life of equipment on-board an aircraft according to claim 3, characterized in that in said assessment method, defining said time-life consumption function comprises:
based on
The defining conditions of (2) define a physical quantity weight coefficient; and
the hierarchical weight coefficients are defined based on the range of values in which the values of the physical quantity lie, wherein,
when the value X of the physical quantityi(t) operating condition corresponding to the onboard equipment being under standard load, based on Xi(t)·ωiThe constraint of (t) → 1 defines the hierarchy weight coefficient,
when the value X of the physical quantityi(t) operating condition corresponding to the on-board unit being overloaded, based on Xi(t)·ωiThe constraint of (t) → A defines the hierarchical weight coefficients, where A>1，
When the value X of the physical quantityi(t) operating condition corresponding to low load of the onboard equipment, based on Xi(t)·ωiThe constraint of (t) → B defines the hierarchical weight coefficients, wherein B<1, wherein the ith physical quantity traverses all physical quantities characterizing the operating state of the onboard device.
5. An assessment method for assessing the service life of an apparatus on board an aircraft according to claim 4, characterized in that when the value X of the physical quantity isiAnd (t) corresponding to the non-working state of the no-load of the airborne equipment, and defining the corresponding hierarchical weight coefficient to be zero.
6. An assessment method for assessing the service life of an onboard device of an aircraft according to claim 3, characterized in that the onboard device comprises an engine and the physical quantities monitored for said engine comprise the engine exhaust temperature, the engine rotor loading.
7. An assessment method for assessing the service life of an onboard device of an aircraft according to claim 3, characterized in that said monitoring step uses sensing means to monitor physical quantities of the operating state of the onboard device and triggers the step of estimating the service life consumption value of the onboard device in response to a significant change in the monitored data monitored by said sensing means;
wherein, the obvious change of the monitoring data is defined as that the change of the monitoring data reaches a preset change amplitude threshold value within a preset time period, and the monitoring data comprises current, voltage, temperature or pressure.
8. An assessment method for assessing the service life of an onboard device of an aircraft according to claim 3, characterized in that in said assessment method said number-of-times-of-life-expenditure function is defined as the number of times consumed, being equal to the number of times a state-change signal associated with the onboard device occurs, wherein said state-change signal is characteristic of a predetermined state change occurring in the operating state of the onboard device.
9. An assessment method for assessing the service life of an onboard device of an aircraft according to claim 8, characterised in that the onboard device comprises a landing gear device, the status change signal monitored for said landing gear device comprising a landing gear uplock signal; alternatively, the first and second electrodes may be,
the onboard equipment comprises a flight controller, and the state change signal monitored for the landing gear device comprises a hydraulic trigger signal which is characterized in that the supply pressure of a hydraulic system of the flight controller exceeds a preset hydraulic pressure upper limit value.
10. The method of claim 8, wherein the monitoring step uses a plant operational logic determiner to monitor the status change signal and, in response to the status change signal, triggers an updated count of elapsed time-of-life;
wherein the state change signal comprises a power-on signal, a power-off signal, other types of switching value signals, or signals triggered by the corresponding physical quantity exceeding or falling below a preset threshold.
11. An assessment method for assessing the service life of equipment on board an aircraft according to any one of claims 1 to 10, characterized in that it further comprises the following steps:
the method comprises the steps of collecting fault information of the airborne equipment, fault intervals and physical quantities which are monitored during the fault intervals and are used for representing the running state of the airborne equipment, and correcting a physical quantity weight coefficient and a hierarchy weight coefficient in a service life consumption function of the corresponding airborne equipment based on the information.
12. An assessment method for assessing the service life of equipment on board an aircraft according to any one of claims 2 to 10, characterized in that it further comprises the following steps:
and monitoring whether the residual service life of the airborne equipment is too low or not based on the data in the configuration library, and sending out early warning information when the airborne equipment with too low residual service life is monitored, wherein the too low residual service life is defined as being lower than a preset lower limit value of the service life or lower than a preset lower limit proportion value of the full service life.
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN114973628A (en) * | 2022-04-27 | 2022-08-30 | 深大云网络（深圳）有限公司 | Intelligent monitoring terminal based on artificial intelligence and big data analysis |
| CN114973628B (en) * | 2022-04-27 | 2023-09-22 | 深大云网络（深圳）有限公司 | Intelligent monitoring terminal based on artificial intelligence and big data analysis |
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