Evaluation method for evaluating the service life of aircraft on-board equipment

Abstract

The present invention discloses an evaluation method for evaluating the service life of airborne equipment of an aircraft. The method includes: constructing a configuration library of the airborne equipment, where the configuration library stores configuration identification information and configuration documentary information for identifying various types of airborne equipment, and the configuration documentary information includes a service life consumption function of the airborne equipment, which defines the relationship between the consumption of the service life and the monitored relevant physical quantities; monitoring the physical quantities characterizing the operating state of the airborne equipment; estimating the service life consumption value of the airborne equipment in a time integration manner based on the service life consumption function; 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 of the present invention, more accurate quantitative analysis and evaluation of the service life of the airborne equipment can be achieved, which helps to avoid the safety risks caused by exceeding the service life of the equipment and the increase in maintenance costs caused by premature maintenance or replacement of the equipment.

Description

Technical Field

[0001] The present invention relates to the use and maintenance of aircraft on-board equipment, specifically to the life cycle management of aircraft on-board equipment, and particularly to an evaluation method for evaluating the service life of aircraft on-board equipment. Background Art

[0002] In the on-board maintenance system, there are various on-board equipment of the time-limited part type, which need to meet the mandatory replacement requirements in the continuous airworthiness documents. Among them, the life of the time-limited part can be divided into time life, cycle life, or both. In current on-board maintenance, only the working hours of pilots or the experience of maintenance personnel are relied on to estimate the service life or remaining service life of various on-board equipment, which means that the service life of various on-board equipment is usually estimated rather vaguely based on experience. This leads to the ambiguity in judging the life of the time-limited part, and may further cause safety risks due to the actual use of the on-board equipment exceeding its due life cycle or service life. It may also occur that the on-board equipment is maintained or replaced when it can still be used normally for a considerable period of time or number of cycles, resulting in unnecessary increase in maintenance costs.

[0003] Although some efforts have been made in the related fields to solve the above problems, the actual feasibility and achieved effects of the various proposed solutions are still not satisfactory. For example, one type of existing solution basically relies entirely on information related to equipment maintenance to estimate the service life, and its disadvantage is that the basis for this estimation is relatively single and thus rather limited. Another type of solution conceptually proposes to use machine learning algorithms to predict the life of the equipment based on data characteristics directly related to faults, but in actual applications, it is often limited by the fact that the number of similar samples may not be sufficient to support the big data algorithms it relies on, and the prediction effect is not good. Another type of algorithm proposes to determine the fatigue life of the corresponding component based on stress monitoring, but this solution is rather limited in terms of application scope. Moreover, the above several types of existing solutions also have the same or similar shortcomings, such as they often only directly provide a qualitative conclusion on whether maintenance is needed, which is often not sufficient to provide the flight crew or maintenance personnel with a sufficiently adequate basis for judging the service life of the on-board equipment.

[0004] Therefore, there is an urgent need for a method that can more accurately evaluate the life of on-board equipment to at least partially alleviate or solve the above problems and defects existing in the existing solutions. Summary of the Invention

[0005] The technical problem to be solved by the present invention is to overcome the defects that the accuracy, applicability, and effect in actual application of the existing evaluation methods for the service life of on-board equipment are not satisfactory, and to propose a new evaluation method for evaluating the service life of aircraft on-board equipment.

[0006] The present invention solves the above technical problems through the following technical solutions:

[0007] The present invention provides an evaluation method for evaluating the service life of airborne equipment of an aircraft. Characteristically, the evaluation method includes the following steps:

[0008] Construct a configuration library of airborne equipment. The configuration library stores configuration identification information and configuration documentary information of the airborne equipment. Among them, the configuration identification information is used to distinguish various types of airborne equipment. The configuration documentary information includes a service life consumption function of the airborne equipment. The service life consumption function is defined by the following definition formula (1),

[0009] f(t) = X i (t)·ω i (t)·W i (1)

[0010] Wherein, i is a physical quantity related to the service life of the airborne equipment, i = 1, 2,..., N; X i (t) represents the value of the i-th physical quantity at the current moment t; the physical quantity characterizes the operating state of the airborne equipment; W i represents the physical quantity weight coefficient of the i-th physical quantity, ω i (t) represents a hierarchical weight coefficient determined according to the numerical range in which the value of X i (t) is located;

[0011] Monitor all physical quantities characterizing the operating state of the airborne equipment;

[0012] Estimate the service life consumption value of the airborne equipment in a time integral manner according to the following formula (2),

[0013]

[0014] Wherein, N represents the total number of all physical quantities monitored;

[0015] Record and update the service life consumption value, and evaluate the service life of the airborne equipment based on the service life consumption value.

[0016] According to an embodiment of the present invention, the configuration identification information further includes the ID information and remaining service life of each airborne equipment. The evaluation method further includes the following steps:

[0017] Feed back the estimated service life consumption value to the configuration library, and update the remaining service life of the corresponding airborne equipment based on the service life consumption value. The initial value of the remaining service life is set to the full service life of the airborne equipment.

[0018] According to an embodiment of the present invention, the service life consumption function includes a time life consumption function and a cycle life consumption function.

[0019] According to an embodiment of the present invention, in the evaluation method, defining the time life consumption function includes:

[0020] Based on the defined conditions, define the physical quantity weight coefficient; and

[0021] Based on the numerical range in which the value of the physical quantity is located, define the hierarchical weight coefficient, where

[0022] when the value X i (t) of the physical quantity corresponds to the working state of the airborne device under standard load, based on the limiting condition of X i (t)·ω i (t)→1, define the hierarchical weight coefficient,

[0023] when the value X i (t) of the physical quantity corresponds to the working state of the airborne device under overload, based on the limiting condition of X i (t)·ω i (t)→A, define the hierarchical weight coefficient, where A>1,

[0024] when the value X i (t) of the physical quantity corresponds to the working state of the airborne device under low load, based on the limiting condition of X i (t)·ω i (t)→B, define the hierarchical weight coefficient, where B<1, and the i-th physical quantity traverses all physical quantities used to characterize the operating state of the airborne device.

[0025] According to an embodiment of the present invention, when the value X i (t) of the physical quantity corresponds to the non-working state of the airborne device without load, define the corresponding hierarchical weight coefficient as zero.

[0026] According to an embodiment of the present invention, the airborne device includes an engine, and the physical quantities monitored for the engine include the engine exhaust temperature and the engine rotor speed.

[0027] According to an embodiment of the present invention, in the monitoring step, a sensing device is used to monitor the physical quantities of the operating state of the airborne device, and in response to a significant change in the monitoring data monitored by the sensing device, trigger the step of estimating the service life consumption value of the airborne device;

[0028] Among them, an obvious change in the monitoring data is defined as that the change in the monitoring data reaches a preset change amplitude threshold within a preset time duration, and the monitoring data includes current, voltage, temperature or pressure.

[0029] According to an embodiment of the present invention, in the evaluation method, the number of times life consumption function is defined as that the consumed number of times life is equal to the number of times the state change signal associated with the airborne equipment appears, where the state change signal represents that a predetermined state change occurs in the operating state of the airborne equipment.

[0030] According to an embodiment of the present invention, the airborne equipment includes a landing gear device, and the state change signal monitored for the landing gear device includes a landing gear upper lock signal; or,

[0031] The airborne equipment includes a flight brake, and the state change signal monitored for the landing gear device includes a hydraulic trigger signal indicating that the hydraulic pressure supplied by the hydraulic system of the flight brake exceeds a predetermined upper limit value of the hydraulic pressure.

[0032] According to an embodiment of the present invention, in the monitoring step, an equipment operation logic judge is used to monitor the state change signal, and in response to the state change signal, an update calculation of the consumed number of times life is triggered;

[0033] Among them, the state change signal includes a power-on signal, a power-off signal, other types of digital signals, or a signal triggered by a corresponding physical quantity exceeding or falling below a preset threshold.

[0034] According to an embodiment of the present invention, the evaluation method further includes the following steps:

[0035] Collect the fault information of the airborne equipment, the fault interval, and the physical quantities representing the operating state of the airborne equipment monitored during the fault interval, and correct the physical quantity weight coefficient and the hierarchical weight coefficient in the corresponding service life consumption function of the airborne equipment based on this information.

[0036] According to an embodiment of the present invention, the evaluation method further includes the following steps:

[0037] Based on the data in the configuration library, monitor whether the remaining service life of the airborne equipment is too low, and issue a warning message when it is monitored that there is an airborne equipment with a too low remaining service life, where the too low remaining service life is defined as being lower than a predetermined lower limit value of the service life or lower than a predetermined lower limit percentage value of the full service life.

[0038] On the basis of conforming to the common knowledge in the art, the above preferred conditions can be combined arbitrarily to obtain various preferred examples of the present invention.

[0039] The positive and progressive effects of the present invention are as follows:

[0040] According to the evaluation method for evaluating the service life of airborne equipment of an aircraft according to the present invention, by monitoring the physical quantity signals associated with the equipment and analyzing based on this, more accurate quantitative analysis and evaluation of the service life of the airborne equipment can be achieved, which helps to avoid the safety risks brought about by exceeding the service life of the equipment and the increase in maintenance costs caused by premature maintenance or replacement of the equipment. Description of the Drawings

[0041] Figure 1 It is a schematic flowchart of an evaluation method for evaluating the service life of airborne equipment of an aircraft according to a preferred embodiment of the present invention.

[0042] Figure 2 It is a schematic flowchart of an application example for predicting the life of a time-life part by the evaluation method according to a preferred embodiment of the present invention.

[0043] Figure 3 It shows an example of a time-life consumption function of an evaluation method for evaluating the service life of airborne equipment of an aircraft according to a preferred embodiment of the present invention, in which the physical quantity of the exhaust gas temperature of an aircraft engine and the physical quantity of the high-pressure rotor speed in a certain time period are shown in sequence from top to bottom, as well as the time-life consumption value predicted based on these two physical quantities. Detailed Embodiments

[0044] The following further describes in detail the preferred embodiments of the present invention in conjunction with the accompanying drawings of the specification. The following description is exemplary and not a limitation to the present invention. Any other similar situations also fall within the protection scope of the present invention.

[0045] In the following specific description, directional terms, such as "left", "right", "up", "down", "front", "rear", etc., are used with reference to the directions described in the drawings. The components of the embodiments of the present invention can be placed in a variety of different directions, and the directional terms are for illustrative purposes and not restrictive.

[0046] Refer to Figure 1 As shown, the evaluation method for evaluating the service life of airborne equipment of an aircraft according to a preferred embodiment of the present invention may include the following steps:

[0047] Construct a configuration library of airborne equipment, where the configuration library stores the configuration identification information and configuration documentary information of the airborne equipment. Among them, the configuration identification information is used to distinguish various types of airborne equipment, and the configuration documentary information includes the service life consumption function of the airborne equipment. The service life consumption function is defined by the following definition formula (1),

[0048] f(t) = X i (t)·ωi (t)·W i (1)

[0049] where i is a physical quantity related to the service life of the airborne equipment, and i = 1, 2, …, N; X i (t) represents the value of the i-th physical quantity at the current moment t; the physical quantity characterizes the operating state of the airborne equipment; W i represents the physical quantity weight coefficient of the i-th physical quantity, ω i (t) represents the hierarchical weight coefficient determined according to the numerical range in which the value of X i (t) lies;

[0050] Monitor all physical quantities characterizing the operating state of the airborne equipment;

[0051] Estimate the service life consumption value of the airborne equipment in a time-integral manner according to the following formula (2),

[0052]

[0053] where N represents the total number of all monitored physical quantities;

[0054] Record and update the service life consumption value, and evaluate the service life of the airborne equipment based on the service life consumption value.

[0055] It can be understood that the airborne equipment here can refer to time-limited parts, which can be modules, components, parts, etc., and need to meet the mandatory replacement requirements in the continuous airworthiness documents. The life of time-limited parts can be divided into time life, cycle life, or both.

[0056] Moreover, the configuration identification information may include or refer to the part number of the equipment, and the part number associates the time-limited part with the configuration record information for use in tracing, querying, etc. The part number includes one or more of the information such as system code, model code, drawing type, configuration model, technical suffix, etc. The configuration identification information can be used to distinguish different configuration products of the recorded equipment under a basic category or model, and it can refer to modules, components, parts, etc.

[0057] Wherein, the configuration identification information further includes the ID information and the remaining service life of each airborne equipment, and the evaluation method may further include the following steps:

[0058] Feed back the estimated service life consumption value to the configuration library, and update the remaining service life of the corresponding airborne equipment based on the service life consumption value, where the initial value of the remaining service life is set to the full service life of the airborne equipment.

[0059] Among them, according to the type difference of the airborne equipment targeted, the service life consumption function includes a time life consumption function and a cycle life consumption function.

[0060] First, the evaluation method applicable to the equipment whose life is measured by time and the definition of the time life consumption function therein and the evaluation method or process of applying it will be described below.

[0061] According to some preferred embodiments of the present invention, in the evaluation method, defining the time life consumption function includes:

[0062] Based on the defined conditions, define the physical quantity weight coefficient; and

[0063] Based on the numerical range where the value of the physical quantity is located, define the hierarchical weight coefficient, where

[0064] when the value X i (t) of the physical quantity corresponds to the working state of the airborne equipment under standard load, based on the limiting condition that X i (t)·ω i (t)→1, define the hierarchical weight coefficient,

[0065] when the value X i (t) of the physical quantity corresponds to the working state of the airborne equipment under overloading, based on the limiting condition that X i (t)·ω i (t)→A (where A>1), define the hierarchical weight coefficient,

[0066] when the value X i (t) of the physical quantity corresponds to the working state of the airborne equipment under low load, based on the limiting condition that X i (t)·ω i (t)→B (where B<1), define the hierarchical weight coefficient, where the i-th physical quantity traverses all physical quantities used to characterize the operating state of the airborne equipment.

[0067] Among them, when the value X i (t) of the physical quantity corresponds to the non-working state of the airborne equipment without load, define the corresponding hierarchical weight coefficient as zero.

[0068] It can be understood that in the present disclosure, the conditions of tending to 1, tending to A, and tending to B as described above can be defined according to actual needs, for example, so that X i (t)·ω i (t) falls between 0.8-1.2 times or even 0.6-1.5 times of the approaching target value, and it is not strictly required to approach a specific value.

[0069] The definition of the time-life consumption function of the above preferred embodiment of the present invention is based on the following insights.

[0070] When making a judgment on the time-life consumption:

[0071] Monitor one or more physical quantities related to the time-life component, such as temperature, pressure, etc. If the number of relevant physical quantities is N, the monitored physical quantities can be denoted as X i (t), i = 1, 2, …, N;

[0072] For each physical quantity, respectively assign a physical quantity weight W i , i = 1, 2, …, N, and

[0073] According to the degree of influence of the value of the physical quantity on the life, respectively classify the value range of each physical quantity;

[0074] For each level of the i-th physical quantity, respectively assign a level weight;

[0075] ω i,j , i = 1, 2, …, N, j = 1, 2, …, n i , where n i is the number of levels divided for the i-th physical quantity.

[0076] On this basis, the time-life consumed by the airborne equipment (time-life component) corresponding to the current moment or time period can be predicted through the following steps:

[0077] 1. Denote the values of each physical quantity at the current moment as X1(t), X2(t), …, X N (t), and the corresponding physical quantity weights as W1, W2, …, W N ;

[0078] 2. Respectively judge the levels where X1(t), X2(t), …, X N (t) are located, and find the weights ω1(t), ω2(t), …, ω N (t) of the corresponding levels;

[0079] 3. The time-life consumed at the current moment is:

[0080]

[0081] Then, by adding up the time-lives consumed at all moments, the predicted value or estimated value of the time-life consumption can be obtained:

[0082]

[0083] Subsequently, the estimated value of the time-life consumed by the time-life component can be output.

[0084] In the above description, the weight coefficient of physical quantities can be defined to satisfy the constraints And the hierarchical weight coefficient is subject to the following constraints:

[0085] When the monitored time-life component is operating stably, ω1(t), ω2(t), …, ω N (t) should be adjusted so that: X1(t)·ω1(t) → 1, …, X N (t)·ω N (t) → 1;

[0086] When the monitored time-life component is operating overloaded, it should be adjusted so that

[0087] ω1(t), ω2(t), …, ω N (t) should be adjusted so that: X1(t)·ω1(t) > 1, …, X N (t)·ω N (t) > 1

[0088] When the monitored time-life component is operating underloaded, it should be adjusted so that

[0089] ω1(t), ω2(t), …, ω N (t) should be adjusted so that: X1(t)·ω1(t) < 1, …, X N (t)·ω N (t) < 1

[0090] Under the condition of satisfying the above constraints, using the time and physical quantity data between two adjacent failures, through machine learning, the weight coefficient of physical quantities and the hierarchical weight coefficient can be continuously optimized, and finally the consumption life of the airborne equipment evaluated or predicted based on the above method is more accurate.

[0091] According to some further preferred embodiments of the present invention, the airborne equipment includes an engine, and the physical quantities monitored for the engine include the engine exhaust temperature and the engine rotor speed.

[0092] Wherein, in the monitoring step, a sensing device can be used to monitor the physical quantities of the operating state of the airborne equipment, and in response to an obvious change in the monitoring data obtained by the sensing device, the step of estimating the consumption value of the service life of the airborne equipment is triggered;

[0093] Wherein, an obvious change in the monitoring data is defined as that the monitoring data changes to reach a preset change amplitude threshold within a preset time duration, and the monitoring data includes current, voltage, temperature or pressure.

[0094] The following will describe an evaluation method applicable to devices whose lifespan is measured by the number of times, such as the number of uses or the number of switch operations, as well as the definition of the number-of-times lifespan consumption function therein and the evaluation method or process of applying it.

[0095] According to some preferred embodiments of the present invention, in the evaluation method, the number-of-times lifespan consumption function is defined as the consumed number of times of lifespan being equal to the number of occurrences of the state change signal associated with the airborne device, where the state change signal characterizes a predetermined state change in the operating state of the airborne device. It can be understood that the above-defined number-of-times lifespan consumption function can also be understood from another perspective as a simplification of the previous formula (1) under specific conditions.

[0096] For the number of times of lifespan, for example but not limited to the following examples: (1) The up-lock signal of the aircraft landing gear. After the signal is triggered, the consumed number of times of lifespan for the retraction and extension of the landing gear is incremented by 1; (2) For the flight controller brake, if the hydraulic system supply pressure is greater than 2800 pounds per square inch, it is regarded as a trigger signal, and the consumed number of times of lifespan for the up-pressure of the flight controller brake is incremented by 1.

[0097] Among them, for the evaluation method of the number of times of lifespan, the applicable airborne devices may include, for example, a landing gear device. The state change signal monitored for the landing gear device includes the up-lock signal of the landing gear; or,

[0098] It may include a flight controller brake. The state change signal monitored for the landing gear device includes a hydraulic trigger signal indicating that the hydraulic system supply pressure of the flight controller brake exceeds a predetermined upper limit value of the hydraulic pressure.

[0099] Among them, in the monitoring step, an equipment operation logic judge is used to monitor the state change signal, and in response to the state change signal, an update calculation of the consumed number of times of lifespan is triggered;

[0100] Among them, the state change signal includes a power-on signal, a power-off signal, other types of digital signals, or a signal triggered by a corresponding physical quantity exceeding or falling below a preset threshold.

[0101] Based on the above-described embodiments of the lifespan evaluation method for devices whose lifespan is measured by time or by the number of times, further preferably, the evaluation method may further include the following steps:

[0102] Collect the fault information, fault interval of the airborne device, and the physical quantities characterizing the operating state of the airborne device monitored during the fault interval, and correct the physical quantity weight coefficient and hierarchical weight coefficient in the corresponding lifespan consumption function of the airborne device based on this information.

[0103] Preferably, refer toFigure 2 As shown, after evaluating or predicting the remaining service life of the airborne equipment, the evaluation method may also be based on this to perform operations including data update, traceability, query, maintenance, replacement, etc.

[0104] For example, the evaluation method may also include the following steps:

[0105] Based on the data in the configuration library, monitor whether the remaining service life of the airborne equipment is too low, and issue a warning message when it is monitored that there is an airborne equipment with a too low remaining service life, where the too low remaining service life is defined as being lower than a predetermined lower limit value of the service life or lower than a predetermined lower limit ratio value of the full service life.

[0106] According to some application examples, with reference to Figure 2 As shown, after starting to count the life of the time-limited part, the corresponding logic judge can be run, and according to the operating characteristics of the time-limited part, the physical quantity signal will be continuously monitored.

[0107] When the trigger signal is received, the equipment runs the logic judge, which will output the time life or cycle life consumed by the time-limited part to the life timer (counter). At the same time, the life timer (counter) will read the currently remaining life saved in the configuration record in the configuration library, calculate and output the latest remaining life.

[0108] If the life is not exhausted at this time, update the remaining life and store it in the configuration record; if the life is exhausted at this time, repair or replace the time-limited part, update the part number, and query the mandatory replacement requirements of the continuous airworthiness document to update the remaining life after the time-limited part is repaired or replaced. It should be noted that if the time-limited part has both time life and cycle life, as long as one of the lives is exhausted, it is regarded as the life of the time-limited part being exhausted.

[0109] Finally, the maintenance personnel can query and trace the record information of the corresponding time-limited part at any time through the part number to obtain the remaining life of the target time-limited part.

[0110] For the evaluation and prediction of the time life, the following refers to Figure 3 The application examples shown therein will be described. As shown in 3, from top to bottom in sequence are the exhaust gas temperature record of an aircraft engine during a certain period, the high-pressure rotor speed, and the predicted time life consumption.

[0111] Such as Figure 3The monitored physical quantities are the exhaust gas temperature (EGT) of the aircraft engine, i.e., X1(t), and the high-pressure rotor speed ratio (N2), i.e., X2(t). The physical quantity weight coefficients of the two are W1 = 0.5 and W2 = 0.5 respectively. For the exhaust gas temperature X1(t) of the aircraft engine, when the temperature is greater than 800 degrees Celsius, the engine is in an overloaded operation state, which has a greater impact on the life, and at this time, a larger hierarchical weight ω1 = 0.0027 is taken; when the temperature is less than or equal to 800 degrees Celsius, the engine is in a normal or low-load operation state, which has a smaller impact on the life, and at this time, a smaller hierarchical weight ω1 = 0.0014 is taken.

[0112] For the high-pressure rotor speed X2(t) of the aircraft engine, when the speed is greater than 100%, the engine is in an overloaded operation state, which has a greater impact on the life, and at this time, a larger hierarchical weight ω2 = 0.0166 is taken; when the speed is less than or equal to 100%, the engine is in a normal or low-load operation state, which has a smaller impact on the life, and at this time, a smaller hierarchical weight ω2 = 0.0105 is taken.

[0113] The function of the time life consumption used in the estimation is:

[0114]

[0115] where

[0116] By summing up X0(t) over the monitoring time ∫X0(t)dt = 8112, the predicted time life consumption is obtained.

[0117] From Figure 3 it can be seen that when the engine is in an overloaded operation state, the predicted time life consumption per unit time is larger; when the engine is in a normal operation state, the predicted time life consumption per unit time is basically the same as the time life consumption per unit time during normal operation; when the engine is in a low-load operation state, the predicted time life consumption per unit time is smaller.

[0118] Therefore, when selecting the hierarchical weight, the situation of normal operation of the time-life component should be fitted first to make the predicted time life consumption and the normal time life consumption basically consistent; in the case of overloaded operation, a larger hierarchical weight should be selected; in the case of low-load operation, the selected hierarchical weight can be the same as or slightly smaller than the situation during normal operation. That is, the hierarchical weight needs to meet the following constraints:

[0119] The evaluation method for evaluating the service life of airborne equipment according to the above preferred embodiment of the present invention can achieve more accurate quantitative analysis and evaluation of the service life of airborne equipment by monitoring the physical quantity signals associated with the equipment and analyzing based on this, which helps to avoid the safety risks brought about by exceeding the service life of the equipment and the increase in maintenance costs caused by premature maintenance or replacement of the equipment.

[0120] Although the specific embodiments of the present invention have been described above, those skilled in the art should understand that these are only examples, and the protection scope of the present invention is defined by the appended claims. Without departing from the principles and essence of the present invention, those skilled in the art can make various changes or modifications to these embodiments, but these changes and modifications all fall within the protection scope of the present invention.

Claims

1. An evaluation method for evaluating the service life of airborne equipment of an aircraft, characterized in that, The evaluation method includes the following steps: Construct a configuration library for airborne equipment, which stores configuration identification information and configuration documentary information of the airborne equipment. Among them, the configuration identification information is used to distinguish various types of airborne equipment and includes the ID information and remaining service life of each airborne equipment. The configuration documentary information includes the service life consumption function of the airborne equipment, and the service life consumption function is defined by the following definition formula (1). f(t)=X i (t)·ω i (t)·W i (1) Among them, i is a physical quantity related to the service life of the airborne equipment, i = 1, 2, …, N; X i (t) represents the value of the i-th physical quantity at the current moment t; the physical quantity characterizes the operating state of the airborne equipment; W i represents the physical quantity weight coefficient of the i-th physical quantity, ω i (t) represents the hierarchical weight coefficient determined according to the numerical range in which the value of X i (t) lies; Monitor all physical quantities representing the operating state of the airborne equipment; Estimate the service life consumption value of the airborne equipment in a time integral manner according to the following formula (2). Where, N represents the total number of all monitored physical quantities; Record and update the service life consumption value, and evaluate the service life of the airborne equipment based on the service life consumption value. Among them, the estimated service life consumption value is fed back to the configuration library, and the remaining service life of the corresponding airborne equipment is updated based on the service life consumption value. The initial value of the remaining service life is set to the full service life of the airborne equipment. Among them, the service life consumption function includes a time service life consumption function and a cycle service life consumption function. And among them, defining the time service life consumption function includes: Based on define the physical quantity weight coefficient according to the defined conditions; and Define the hierarchical weight coefficient based on the numerical range where the value of the physical quantity is located. Among them, When the value X of the physical quantity i (t) corresponds to the working state of the airborne equipment under standard load, based on X i (t)·ω i (t) → 1, define the hierarchical weight coefficient under the limiting condition, When the value X of the physical quantity i (t) corresponds to the overloaded working state of the airborne device, based on X i (t)·ω i (t) → A's limiting condition defines the hierarchical weight coefficient, where A > 1 When the value X of the physical quantity i (t) corresponds to the working state of the airborne equipment at low load, based on X i (t)·ω i (t) → B's limiting condition defines the hierarchical weight coefficient, where B < 1, and the i-th physical quantity traverses all physical quantities used to characterize the operating state of the airborne equipment.

2. The evaluation method for evaluating the service life of airborne equipment of an aircraft according to claim 1, characterized in that, When the value X i (t) corresponds to the non-operating state of the airborne equipment without load, the corresponding hierarchical weight coefficient is defined as zero.

3. The evaluation method for evaluating the service life of the airborne equipment of an aircraft according to claim 1, characterized in that, The airborne equipment includes an engine. The physical quantities monitored for the engine include the engine exhaust temperature and the engine rotor dressing.

4. The evaluation method for evaluating the service life of airborne equipment of an aircraft according to claim 1, characterized in that, In the monitoring step, a sensing device is used to monitor the physical quantities of the operating state of the airborne equipment, and in response to an obvious change in the monitoring data obtained by the sensing device, the step of estimating the service life consumption value of the airborne equipment is triggered; Among them, an obvious change in the monitoring data is defined as that the monitoring data changes reach a preset change amplitude threshold within a preset time duration. The monitoring data includes current, voltage, temperature or pressure.

5. The evaluation method for evaluating the service life of the airborne equipment of an aircraft according to claim 1, characterized in that, In the evaluation method, the cycle service life consumption function is defined as that the consumed cycle service life is equal to the number of times the state change signal associated with the airborne equipment appears, where the state change signal represents a predetermined state change in the operating state of the airborne equipment.

6. The evaluation method for evaluating the service life of aircraft on-board equipment according to claim 5, characterized in that, The airborne equipment includes a landing gear device. The state change signal monitored for the landing gear device includes the landing gear up-lock signal; or, The airborne equipment includes a flight brake. The state change signal monitored for the landing gear device includes a hydraulic trigger signal indicating that the hydraulic pressure supplied by the hydraulic system of the flight brake exceeds a predetermined upper limit value of the hydraulic pressure.

7. The evaluation method for evaluating the service life of airborne equipment of an aircraft according to claim 5, characterized in that, In the monitoring step, an equipment operation logic judge is used to monitor the state change signal, and in response to the state change signal, the update calculation of the consumed cycle service life is triggered; Among them, the state change signal includes a power-on signal, a power-off signal, other types of digital signals, or a signal triggered by a corresponding physical quantity exceeding or falling below a preset threshold.

8. The evaluation method for evaluating the service life of the airborne equipment of an aircraft according to any one of claims 1-7, characterized in that The evaluation method further includes the following steps: Collect the fault information of the airborne equipment, the fault interval, and the physical quantities that characterize the operating state of the airborne equipment monitored during the fault interval, and correct the physical quantity weight coefficient and the hierarchical weight coefficient in the corresponding service life consumption function of the airborne equipment based on this information.

9. The evaluation method for evaluating the service life of airborne equipment of an aircraft according to any one of claims 1-7, characterized in that The evaluation method further includes the following steps: Based on the data in the configuration library, monitor whether the remaining service life of the airborne equipment is too low, and send a warning message when it is monitored that there is an airborne equipment with a too low remaining service life, where the too low remaining service life is defined as being lower than a predetermined lower limit value of the service life or lower than a predetermined lower limit percentage value of the full service life.

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