CN112329151A - Preventive maintenance method for components - Google Patents
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- CN112329151A CN112329151A CN202011304641.8A CN202011304641A CN112329151A CN 112329151 A CN112329151 A CN 112329151A CN 202011304641 A CN202011304641 A CN 202011304641A CN 112329151 A CN112329151 A CN 112329151A
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- 238000012423 maintenance Methods 0.000 title claims abstract description 58
- 230000003449 preventive effect Effects 0.000 title claims abstract description 52
- 238000000034 method Methods 0.000 title claims abstract description 41
- 238000012512 characterization method Methods 0.000 claims abstract description 19
- 238000004458 analytical method Methods 0.000 claims description 30
- 238000012731 temporal analysis Methods 0.000 claims description 9
- 238000000700 time series analysis Methods 0.000 claims description 9
- 238000012360 testing method Methods 0.000 claims description 3
- 230000036541 health Effects 0.000 abstract description 3
- 230000008859 change Effects 0.000 description 3
- 238000010586 diagram Methods 0.000 description 2
- 208000037265 diseases, disorders, signs and symptoms Diseases 0.000 description 2
- 208000035475 disorder Diseases 0.000 description 2
- 239000000463 material Substances 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 230000008569 process Effects 0.000 description 2
- 238000006467 substitution reaction Methods 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000015556 catabolic process Effects 0.000 description 1
- 238000006243 chemical reaction Methods 0.000 description 1
- 238000006731 degradation reaction Methods 0.000 description 1
- 238000011161 development Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 230000007717 exclusion Effects 0.000 description 1
- 230000000750 progressive effect Effects 0.000 description 1
- 239000002699 waste material Substances 0.000 description 1
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- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F30/00—Computer-aided design [CAD]
- G06F30/10—Geometric CAD
- G06F30/15—Vehicle, aircraft or watercraft design
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- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F30/00—Computer-aided design [CAD]
- G06F30/10—Geometric CAD
- G06F30/17—Mechanical parametric or variational design
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- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F30/00—Computer-aided design [CAD]
- G06F30/20—Design optimisation, verification or simulation
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- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F2119/00—Details relating to the type or aim of the analysis or the optimisation
- G06F2119/02—Reliability analysis or reliability optimisation; Failure analysis, e.g. worst case scenario performance, failure mode and effects analysis [FMEA]
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Abstract
The application belongs to the technical field of comprehensive airplane guarantee and health management, and particularly relates to a preventive maintenance method for a component, which comprises the following steps: establishing a representation model of the component state changing along with time; determining a time point when the component fault can be detected and a time point when the component performance fails based on the characterization model; the frequency of preventive maintenance of the component is set according to the time point when the component failure is detectable and the time point when the component performance fails, so as to avoid over-maintenance of the component to a certain extent.
Description
Technical Field
The application belongs to the technical field of comprehensive airplane guarantee and health management, and particularly relates to a preventive maintenance method for a component.
Background
Preventive maintenance is a maintenance method centered on reliability, and is commonly adopted in the comprehensive guarantee and health management of airplanes.
The airplane is preventively maintained, so that the safety of the airplane can be effectively guaranteed, the occurrence of disaster accidents is reduced, but the current preventive maintenance of the airplane lacks scientific guidance, and the situation of excessive maintenance exists, so that huge waste of manpower and material resources is caused.
The present application has been made in view of the above-mentioned technical drawbacks.
It should be noted that the above background disclosure is only for the purpose of assisting understanding of the inventive concept and technical solutions of the present invention, and does not necessarily belong to the prior art of the present patent application, and the above background disclosure should not be used for evaluating the novelty and inventive step of the present application without explicit evidence to suggest that the above content is already disclosed at the filing date of the present application.
Disclosure of Invention
It is an object of the present application to provide a method of preventive maintenance of a component to overcome or mitigate the technical disadvantages of at least one aspect known to exist.
The technical scheme of the application is as follows:
a method of preventive maintenance of a component, comprising:
establishing a representation model of the component state changing along with time;
determining a time point when the component fault can be detected and a time point when the component performance fails based on the characterization model;
the frequency of preventive maintenance of the component is set based on the point in time at which a component failure is detectable and the point in time at which the component fails in performance.
According to at least one embodiment of the present application, in the method for preventive maintenance of a component, the establishing a characterization model of a component state changing with time includes:
and establishing a characterization model of the component state changing along with time based on one or more of polynomial analysis of a least square method, Gaussian expansion function analysis, time series analysis and multivariate joint entropy analysis.
According to at least one embodiment of the present application, in the method for component preventive maintenance, the model for characterizing the component state changing with time is established based on one or more of polynomial analysis based on a least square method, gaussian expansion function analysis, time series analysis, and multivariate joint entropy analysis, and specifically:
and establishing a characterization model of the component state changing along with time by utilizing corresponding relation data of the component state and the time, which is obtained by component tests or actual operation, based on one or more of polynomial analysis of a least square method, Gaussian expansion function analysis, time series analysis and multivariate joint entropy analysis.
According to at least one embodiment of the present application, in the method for preventive maintenance of a component, the frequency of preventive maintenance of a component is set according to a time point when a component failure is detectable and a time point when a component performance fails, specifically:
the frequency of preventive maintenance of the component is set based on the time interval between the time points at which the component failure is detectable and the time points at which the component fails in performance.
According to at least one embodiment of the present application, in the method for preventive maintenance of a component, the frequency of preventive maintenance of a component is set according to an interval time between a time point when a component failure is detectable and a time point when a component performance fails, specifically:
the longer the interval between the points in time when a component failure is detectable and when the component fails in performance, the lower the frequency of preventive maintenance of the component is set accordingly.
The application has at least the following beneficial technical effects:
provided is a preventive maintenance method for a component, which can be used for preventive maintenance of an aircraft component, and when the preventive maintenance method is applied to preventive maintenance of an aircraft component, the frequency of preventive maintenance of the component is determined according to a time point at which a component failure is detectable and a time point at which a component performance fails, so that excessive maintenance of the component can be avoided to some extent.
Drawings
FIG. 1 is a flow chart of a method for preventive maintenance of a component provided by an embodiment of the present application;
FIG. 2 is a schematic diagram of a characterization model of component state over time provided by an embodiment of the present application;
FIG. 3 is a schematic diagram of a characterization model for establishing a change in component state over time provided by an embodiment of the present application;
wherein:
p-component failure detectable time point; f-point in time when the part failed in performance.
For the purpose of better illustrating the embodiments, certain features of the drawings may be omitted, enlarged or reduced, and do not represent the size of an actual product; further, the drawings are for illustrative purposes, and terms describing positional relationships are limited to illustrative illustrations only and are not to be construed as limiting the patent.
Detailed Description
In order to make the technical solutions and advantages of the present application clearer, the technical solutions of the present application will be further clearly and completely described in the following detailed description with reference to the accompanying drawings, and it should be understood that the specific embodiments described herein are only some of the embodiments of the present application, and are only used for explaining the present application, but not limiting the present application. It should be noted that, for convenience of description, only the parts related to the present application are shown in the drawings, other related parts may refer to general designs, and the embodiments and technical features in the embodiments in the present application may be combined with each other to obtain a new embodiment without conflict.
In addition, unless otherwise defined, technical or scientific terms used in the description of the present application shall have the ordinary meaning as understood by one of ordinary skill in the art to which the present application belongs. The terms "upper", "lower", "left", "right", "center", "vertical", "horizontal", "inner", "outer", and the like used in the description of the present application, which indicate orientations, are used only to indicate relative directions or positional relationships, and do not imply that the devices or elements must have a specific orientation, be constructed and operated in a specific orientation, and when the absolute position of the object to be described is changed, the relative positional relationships may be changed accordingly, and thus, should not be construed as limiting the present application. The use of "first," "second," "third," and the like in the description of the present application is for descriptive purposes only to distinguish between different components and is not to be construed as indicating or implying relative importance. The use of the terms "a," "an," or "the" and similar referents in the context of describing the application is not to be construed as an absolute limitation on the number, but rather as the presence of at least one. The word "comprising" or "comprises", and the like, when used in this description, is intended to specify the presence of stated elements or items, but not the exclusion of other elements or items.
Further, it is noted that, unless expressly stated or limited otherwise, the terms "mounted," "connected," and the like are used in the description of the invention in a generic sense, e.g., connected as either a fixed connection or a removable connection or integrally connected; can be mechanically or electrically connected; they may be directly connected or indirectly connected through an intermediate medium, or they may be connected through the inside of two elements, and those skilled in the art can understand their specific meaning in this application according to the specific situation.
The present application is described in further detail below with reference to figures 1-3.
A method of preventive maintenance of a component, comprising:
establishing a representation model of the component state changing along with time;
determining a time point when the component fault can be detected and a time point when the component performance fails based on the characterization model;
the frequency of preventive maintenance of the component is set based on the point in time at which a component failure is detectable and the point in time at which the component fails in performance.
With respect to the method for preventive maintenance of components disclosed in the above embodiments, it will be understood by those skilled in the art that it can be used for preventive maintenance of aircraft components, and when it is applied to preventive maintenance of aircraft components, the frequency of preventive maintenance of components can be determined according to the time point when component failure is detectable and the time point when component performance fails, so that excessive maintenance of components can be avoided to some extent.
In some optional embodiments, in the method for preventive maintenance of a component, the establishing a characterization model of a component state changing with time includes:
and establishing a characterization model of the component state changing along with time based on one or more of polynomial analysis of a least square method, Gaussian expansion function analysis, time series analysis and multivariate joint entropy analysis.
In some optional embodiments, in the method for component preventive maintenance, the model for characterizing the component state changing with time is established based on one or more of a least square polynomial analysis, a gaussian expansion function analysis, a time series analysis, and a multivariate joint entropy analysis, and specifically:
the method comprises the steps of establishing a characterization model of the state of a component changing along with time by utilizing corresponding relation data of the state of the component and the time, which is obtained by component tests or actual operation, based on one or more of polynomial analysis of a least square method, Gaussian expansion function analysis, time series analysis and multivariate joint entropy analysis, wherein the time point when the fault of the component can be detected is P, and the time point when the performance of the component fails is F, as shown in figure 2.
In order to make the technical content of the above embodiment for establishing a characterization model of the component state changing with time easier for a technician in the field to understand, the present application provides the following more specific embodiments:
the aircraft pump source subsystem is a system comprising a plurality of parameters, the increase of the disorder degree in the aircraft pump source subsystem directly causes the degradation of the overall performance, in the working process, even if related performance parameters are still in an allowable range, the potential disorder development of the aircraft pump source subsystem is still not ignored, a multivariate combined entropy analysis method is adopted, the least square method polynomial analysis is combined, the random degree of the performance parameters is quantized, the multi-parameter data comprehensive analysis is carried out, the performance change rule of the pump source subsystem can be described on the whole, and a characterization model of the state of the aircraft pump source subsystem along with the time change is established, and the specific process is as follows:
selecting flight parameter data of a plurality of frames of a typical airplane, and performing symbol conversion and division on airplane parameters by adopting an equidistant method;
using flight parameter data processed by symbols to obtain the joint entropy of each set of aircraft pump source subsystem;
according to the joint entropy of each set of pump source subsystems of the airplane, the variation trend of the joint entropy is calculated by using a least square method, so that the performance variation trend of the pump source subsystems is analyzed, and a characterization model of the state of the pump source subsystems of the airplane changing along with time is established, and specific steps can be seen in fig. 3.
In some optional embodiments, in the method for component preventive maintenance, the frequency of component preventive maintenance is set according to a time point when a component fault is detectable and a time point when a component performance fails, specifically:
the frequency of preventive maintenance of the component is set based on the time interval between the time points at which the component failure is detectable and the time points at which the component fails in performance.
In some optional embodiments, in the method for preventive maintenance of a component, the frequency of preventive maintenance of a component is set according to a time point when a fault of the component is detectable and an interval time between time points when a performance of the component fails, specifically:
the longer the interval between the points in time when a component failure is detectable and when the component fails in performance, the lower the frequency of preventive maintenance of the component is set accordingly.
With respect to the method for preventive maintenance of components disclosed in the above embodiments, it will be understood by those skilled in the art that, when the time interval between the time points at which the component failure is detectable and the time points at which the component performance fails is longer, the frequency of preventive maintenance of the components is set to be correspondingly lower, that is, the time interval between the time points at which the component failure is detectable and the time points at which the component performance fails is longer, and the frequency of preventive maintenance thereof can be correspondingly reduced, and it can be understood that, when the time point at which the component failure is detectable and the time points at which the component performance fails are longer, that the component does not fail in a short time but fails only after a longer time after the component failure representation can be detected, and that the frequency of preventive maintenance of the component is correspondingly reduced while ensuring safety, and the situation of excessive maintenance can be avoided, saving manpower and material resources.
The embodiments are described in a progressive manner in the specification, each embodiment focuses on differences from other embodiments, and the same and similar parts among the embodiments are referred to each other.
Having thus described the present application in connection with the preferred embodiments illustrated in the accompanying drawings, it will be understood by those skilled in the art that the scope of the present application is not limited to those specific embodiments, and that equivalent modifications or substitutions of related technical features may be made by those skilled in the art without departing from the principle of the present application, and those modifications or substitutions will fall within the scope of the present application.
Claims (5)
1. A method for preventive maintenance of a component, comprising:
establishing a representation model of the component state changing along with time;
determining a time point when the component fault can be detected and a time point when the component performance fails based on the characterization model;
the frequency of preventive maintenance of the component is set based on the point in time at which a component failure is detectable and the point in time at which the component fails in performance.
2. The method for preventive maintenance of a component according to claim 1,
the establishing of the characterization model of the component state changing along with time specifically comprises the following steps:
and establishing a characterization model of the component state changing along with time based on one or more of polynomial analysis of a least square method, Gaussian expansion function analysis, time series analysis and multivariate joint entropy analysis.
3. The method for preventive maintenance of a component according to claim 2,
the method comprises the following steps of establishing a characterization model of the component state changing along with time based on one or more of polynomial analysis based on a least square method, Gaussian expansion function analysis, time series analysis and multivariate joint entropy analysis, and specifically comprises the following steps:
and establishing a characterization model of the component state changing along with time by utilizing corresponding relation data of the component state and the time, which is obtained by component tests or actual operation, based on one or more of polynomial analysis of a least square method, Gaussian expansion function analysis, time series analysis and multivariate joint entropy analysis.
4. The method for preventive maintenance of a component according to claim 1,
the frequency of preventive maintenance of the component is set according to the time point when the component fault can be detected and the time point when the component performance fails, and specifically comprises the following steps:
the frequency of preventive maintenance of the component is set based on the time interval between the time points at which the component failure is detectable and the time points at which the component fails in performance.
5. The method for preventive maintenance of a component according to claim 4,
the frequency of preventive maintenance of the component is set according to the time point when the component fault can be detected and the interval time between the time points when the component performance fails, and specifically comprises the following steps:
the longer the interval between the points in time when a component failure is detectable and when the component fails in performance, the lower the frequency of preventive maintenance of the component is set accordingly.
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| Application Number | Priority Date | Filing Date | Title |
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| CN202011304641.8A CN112329151B (en) | 2020-11-19 | 2020-11-19 | Preventive maintenance method for component |
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| CN202011304641.8A CN112329151B (en) | 2020-11-19 | 2020-11-19 | Preventive maintenance method for component |
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| CN112329151B CN112329151B (en) | 2024-02-23 |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN113158346A (en) * | 2021-05-14 | 2021-07-23 | 杭州积莹科技有限公司 | Preventive maintenance method based on cloud computing |
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