An intelligent maintenance diagnostic system for self-monitoring aircraft

Abstract

The application discloses a kind of self-monitoring aircraft intelligent maintenance diagnostic system, the application relates to maintenance diagnostic technical field, including temperature monitoring module, abnormal analysis module, data diagnostic module, influence analysis module and maintenance time analysis module, also including maintenance scheme module and maintenance time analysis module, the advantages of the present application are that: through abnormal analysis module, the temperature characteristic mode corresponding to each type of fault can be accurately identified, the accuracy of fault diagnosis is improved, through data diagnostic module, the specific component that appears problem can be quickly and accurately determined, reduce the time and workload of troubleshooting, using influence analysis module can let maintenance personnel know in advance the consequences that fault may bring, take corresponding measures to reduce risk, predict the effective use time of component and the normal operation time of aircraft, help to reasonably arrange maintenance plan, through maintenance time analysis module, the scientific planning of maintenance time can be realized.

Description

Technical Field

[0001] This invention relates to the field of maintenance and diagnostic technology, specifically to an intelligent maintenance and diagnostic system for self-monitoring aircraft. Background Technology

[0002] Aircraft are flying vehicles that can fly within the atmosphere. Any aircraft must generate lift greater than its own weight in order to take off. Based on the principle of lift generation, aircraft can be divided into two main categories: lighter-than-air aircraft and heavier-than-air aircraft. The former takes off by static buoyancy, while the latter takes off by overcoming its own weight through aerodynamics. With social development, more passengers are willing to choose air travel, and cargo transportation can also be completed more efficiently by air. This will drive the business growth of airlines, and intelligent maintenance and diagnosis of aircraft are particularly important for aviation safety.

[0003] Common intelligent maintenance diagnostic systems struggle to accurately predict the effective service life of components and the normal operating time of aircraft. Consequently, they cannot rationally schedule maintenance plans, anticipate the potential consequences of malfunctions, or take timely measures to mitigate risks. Furthermore, they may cause conflicts between maintenance work and aircraft normal operating time. To address these issues, we propose a self-monitoring intelligent maintenance diagnostic system for aircraft. Summary of the Invention

[0004] The purpose of this invention is to provide an intelligent maintenance and diagnostic system for self-monitoring aircraft.

[0005] To address the problems mentioned in the background art, the present invention provides the following technical solution: an intelligent maintenance and diagnostic system for self-monitoring aircraft, including a data acquisition module, which can collect information inside the aircraft and obtain the changing state of the aircraft during normal use, and generate normal operation information; and also includes a temperature rise monitoring module, an anomaly analysis module, a data diagnostic module, an impact analysis module, and a maintenance time analysis module.

[0006] The temperature monitoring module installs temperature sensors on aircraft components to acquire real-time temperature changes on the components and generate real-time temperature change information.

[0007] The anomaly analysis module analyzes the temperature change information of aircraft components when different failures occur, generates abnormal temperature information, and analyzes the temperature change information of multiple aircraft components when different failures occur simultaneously, generating combined abnormal change information.

[0008] The data diagnostic module extracts real-time temperature change information, matches it with abnormal temperature information and combined abnormal change information, analyzes the abnormality index of real-time temperature change information, and obtains information on faulty components.

[0009] The impact analysis module can analyze the impact of aircraft components on the aircraft when real-time temperature change information is abnormal, predict the effective service life of aircraft components, analyze the time when the aircraft can operate normally, and generate component maintenance time information.

[0010] As a further embodiment of the present invention, it also includes a maintenance scheme module and a maintenance time analysis module;

[0011] The maintenance plan module can extract information about faulty components, analyze the maintenance methods for the faulty components, and generate a maintenance plan for the components.

[0012] The maintenance time analysis module extracts information from inside the aircraft to analyze the time periods during which different components are needed when the aircraft is running, determines the downtime of aircraft components, generates idle time information, obtains component maintenance plans for different aircraft components, analyzes the time required for different component maintenance plans, and then derives the maintenance time information for aircraft components based on the idle time information, and displays the time information and maintenance plan information to internal personnel.

[0013] As a further aspect of the present invention: when generating real-time temperature change information, the temperature monitoring module will draw a temperature change graph based on the real-time temperature change information and establish temperature interval limits. When the temperature on the aircraft component reaches the temperature interval limit, it will be marked on the temperature change graph and the time information when the temperature interval limit is reached will be extracted to generate the current temperature limit time information.

[0014] As a further aspect of the present invention: after generating abnormal temperature information, the anomaly analysis module will draw an abnormal temperature change graph based on the abnormal temperature information, extract the time when the temperature of the aircraft components reaches the temperature interval limit in the abnormal temperature change graph, generate abnormal temperature limit time information, and use the aircraft component as the generated name tag, inserting the name tag of the aircraft component into the corresponding current temperature limit time information and abnormal temperature limit time information. Let the number of components that malfunction within the aircraft be L, and let the temperature information of different components that malfunction within the aircraft be... Let the temperature information when multiple components inside the aircraft fail simultaneously be... ;

[0015]

[0016] The above formula can be used to calculate the temperature information when multiple components inside an aircraft fail simultaneously, thus facilitating the analysis of combined abnormal change information.

[0017] As a further aspect of the present invention: the data diagnosis module can receive and extract current temperature limit time information and abnormal temperature limit time information, and then analyze the similarity index between the current temperature limit time information and different abnormal temperature limit time information, assuming the number of temperature interval limits is S, and the current temperature limit time information is... Let the abnormal temperature limit time information be... Let the similarity index be... ;

[0018]

[0019] The similarity index can be calculated using the formula above.

[0020] As a further aspect of the present invention: after calculating the similarity index, the data diagnosis module establishes an index threshold and uses the index threshold to filter the current temperature limit time information. Let the index threshold be... ;

[0021] when At time 1, the current temperature limit time information is determined to be abnormal.

[0022] when If 1 is true, then the current temperature limit time information is determined to be normal, and then the current temperature limit time information is directly stored.

[0023] As a further aspect of the present invention: when analyzing the maintenance methods of faulty components, the maintenance scheme module establishes a process sorting unit, uses the process sorting unit to analyze the installation process of components in the aircraft, then arranges the faulty components in sequence according to the installation steps of the aircraft and records them in the process sorting unit to generate a process sorting table. After obtaining the maintenance methods of different faulty components, the maintenance scheme module sorts the maintenance methods of the faulty components according to the process sorting table to generate a component maintenance scheme.

[0024] As a further aspect of the present invention: the maintenance time analysis module can receive information processed by the maintenance plan module, extract component maintenance plan information, analyze the maintenance time of the component maintenance plan, then determine the time to implement the maintenance plan based on the idle time information, and then determine whether the idle time information is valid time. Valid time refers to time in the idle time information that is higher than the maintenance time of the maintenance plan, providing sufficient time for the maintenance of aircraft components. Let the maintenance time of the maintenance plan be... Let the maintenance preparation time be... Let the idle time information be... ;

[0025] when If so, the corresponding idle time information is determined to be valid time, and then it is recorded;

[0026] when If the time is invalid, the corresponding idle time information is determined to be invalid and then deleted.

[0027] By following the above method, all valid time information in the idle time information can be obtained. Then, the valid time information is sorted in chronological order to obtain a valid time sorting table.

[0028] Compared with the prior art, the beneficial effects of the present invention by adopting the above technical solution are as follows:

[0029] 1. This invention can accurately identify temperature characteristic patterns corresponding to various faults through the anomaly analysis module, improving the accuracy of fault diagnosis. Through the data diagnosis module, it can quickly and accurately determine the specific component with the problem, reducing the time and workload of troubleshooting. The impact analysis module can enable maintenance personnel to know the possible consequences of the fault in advance and take corresponding measures to reduce risks. On the other hand, the prediction of the effective service life of components and the normal operating time of the aircraft helps to rationally arrange maintenance plans. Through the maintenance time analysis module, scientific planning of maintenance time can be achieved, which can not only ensure the normal operation of the aircraft, but also make full use of the idle time of components to complete maintenance work, thereby improving the overall operation and maintenance efficiency of the aircraft.

[0030] 2. This invention enables maintenance personnel to intuitively see the temperature change trend of aircraft components over time through the temperature monitoring module. The anomaly analysis module facilitates maintenance personnel to compare and analyze the temperature anomaly patterns corresponding to various faults, deepening their understanding of the relationship between faults and temperature. This helps to more accurately analyze and combine anomaly change information. The data diagnosis module can quantitatively measure the similarity between real-time temperature changes and known abnormal temperature conditions, providing an objective and scientific basis for judging whether real-time temperature changes are abnormal. This avoids the limitations of relying solely on subjective experience for judgment, and can accurately distinguish the temperature boundary time information between normal and abnormal conditions, reducing potential risks and losses caused by misjudgment of faults or untimely troubleshooting.

[0031] 3. This invention, through its impact analysis module, helps to plan maintenance work in advance, avoids sudden component failures during operation, and ensures the continuous safe operation of the aircraft. The maintenance scheme module ensures that maintenance work is carried out in an orderly manner according to the aircraft's structure and component installation logic, avoiding problems such as repetitive operations, component damage, or installation difficulties that may result from improper maintenance sequence, thus improving the efficiency and quality of maintenance work. The maintenance time analysis module effectively avoids maintenance work not being completed smoothly due to insufficient idle time, achieving scientific planning and rational utilization of maintenance time, ensuring that aircraft components are maintained at the appropriate time, and improving the overall planning and coordination of aircraft operation and maintenance work. Attached Figure Description

[0032] Figure 1 This is a schematic diagram of the system flow in an embodiment of the present invention. Detailed Implementation

[0033] The specific embodiments of the present invention will be further described below with reference to the accompanying drawings. It should be noted that the description of these embodiments is for the purpose of helping to understand the present invention, but does not constitute a limitation of the present invention.

[0034] Furthermore, the technical features involved in the various embodiments of the present invention described below can be combined with each other as long as they do not conflict with each other.

[0035] Example 1:

[0036] Therefore, in order to effectively solve the above problems, this application proposes an intelligent maintenance and diagnostic system for self-monitoring aircraft, as shown in the accompanying drawings. Figure 1 As shown, it includes a data acquisition module, which can collect information inside the aircraft and obtain the changes in the aircraft's status during normal use, and generate normal operation information. It also includes a temperature rise monitoring module, an anomaly analysis module, a data diagnosis module, an impact analysis module, and a maintenance time analysis module.

[0037] The temperature monitoring module installs temperature sensors on aircraft components to acquire real-time temperature changes on the components and generate real-time temperature change information.

[0038] For critical components that are prone to heat accumulation and sensitive to temperature changes during operation, increasing the density of temperature sensors ensures that the most representative temperature changes on these components can be acquired more accurately in real time, and the generated real-time temperature change information will better reflect the true thermal state of the components.

[0039] The anomaly analysis module analyzes the temperature change information of aircraft components when different failures occur, generates abnormal temperature information, and analyzes the temperature change information of multiple aircraft components when different failures occur simultaneously, generating combined abnormal change information.

[0040] The data diagnostic module extracts real-time temperature change information, matches it with abnormal temperature information and combined abnormal change information, analyzes the abnormality index of real-time temperature change information, and obtains information on faulty components.

[0041] The impact analysis module can analyze the impact of aircraft components on the aircraft when real-time temperature change information is abnormal, predict the effective service life of aircraft components, analyze the time when the aircraft can operate normally, and generate component maintenance time information.

[0042] It also includes a maintenance plan module and a maintenance time analysis module;

[0043] The maintenance plan module can extract information about faulty components, analyze the maintenance methods for the faulty components, and generate a maintenance plan for the components.

[0044] The maintenance time analysis module extracts information from inside the aircraft to analyze the time periods during which different components are needed when the aircraft is running, determines the downtime of aircraft components, generates idle time information, obtains component maintenance plans for different aircraft components, analyzes the time required for different component maintenance plans, and then derives the maintenance time information for aircraft components based on the idle time information, and displays the time information and maintenance plan information to internal personnel.

[0045] Simultaneously, the component maintenance plan can be broken down to obtain sub-plan information, analyze the maintenance effect of the sub-plan information and the time that can be extended after maintenance, then analyze the time required for sub-plan maintenance, generate sub-plan maintenance time, and match the sub-plan maintenance time with idle time information to obtain the time for implementing the sub-plan information, perform preliminary maintenance on the aircraft component, and then display the sub-plan information, the extended aircraft normal operating time of the sub-plan information, the sub-plan maintenance time, and the time for implementing the sub-plan information to the staff;

[0046] The specific workflow is as follows: Collect information from inside the aircraft and obtain its changing status during normal use, generating normal operation information; acquire real-time temperature changes on aircraft components, generating real-time temperature change information; analyze temperature changes of aircraft components under different faults, generating abnormal temperature information; analyze temperature changes of multiple aircraft components under simultaneous different faults, generating combined abnormal change information; match real-time temperature change information with abnormal temperature information and combined abnormal change information; analyze the abnormal index of real-time temperature change information; obtain faulty component information; analyze the impact of abnormal real-time temperature change information on the aircraft and predict the effective usage time of aircraft components; analyze the time the aircraft can operate normally; extract faulty component information; analyze the maintenance methods of faulty components; generate component maintenance plans; extract information from inside the aircraft; analyze the time periods during which different components are needed when the aircraft is running; determine the downtime of aircraft components; generate idle time information; simultaneously acquire component maintenance plans for different aircraft components; analyze the time required for different component maintenance plans; then, based on the idle time information, derive the maintenance time information for aircraft components and display the time information and maintenance plan information to internal personnel.

[0047] Furthermore, the anomaly analysis module can accurately identify temperature characteristic patterns corresponding to various faults, improving the accuracy of fault diagnosis. The data diagnosis module can quickly and accurately identify the specific component causing the problem, reducing the time and workload for troubleshooting. The impact analysis module allows maintenance personnel to be aware of the potential consequences of faults in advance and take corresponding measures to reduce risks. On the other hand, the prediction of the effective service life of components and the normal operating time of the aircraft helps to rationally arrange maintenance plans. The maintenance time analysis module enables the scientific planning of maintenance time, ensuring the normal operation of the aircraft while making full use of the idle time of components to complete maintenance work, thereby improving the overall operation and maintenance efficiency of the aircraft.

[0048] Example 2:

[0049] Based on Embodiment 1, as shown in the accompanying drawings of the specification. Figure 1 As shown, when generating real-time temperature change information, the temperature monitoring module will draw a temperature change graph based on the real-time temperature change information and establish temperature interval limits. When the temperature on the aircraft component reaches the temperature interval limit, it will be marked on the temperature change graph and the time information when the temperature interval limit is reached will be extracted to generate the current temperature limit time information.

[0050] Different colors or line styles can be used to distinguish different types of aircraft components, so that the temperature changes of each component can be clearly and intuitively compared on a single graph. The slope of temperature changes can also be displayed on the graph using specific markers or auxiliary curves, so as to more keenly capture the degree of temperature change. This is very helpful for early detection of potential abnormal heating or cooling.

[0051] After generating abnormal temperature information, the anomaly analysis module plots an abnormal temperature change graph based on this information. It then extracts the time when the temperature of aircraft components reaches the temperature interval limit from the graph, generating abnormal temperature limit time information. Using the aircraft component as the generated name tag, the module inserts this name tag into the corresponding current temperature limit time information and abnormal temperature limit time information. Let L be the number of components malfunctioning within the aircraft, and let the temperature information of the different malfunctioning components within the aircraft be... Let the temperature information when multiple components inside the aircraft fail simultaneously be... ;

[0052]

[0053] The above formula can be used to calculate the temperature information when multiple components inside an aircraft fail simultaneously, which facilitates the analysis of combined abnormal change information.

[0054] The changes in other parameters related to the abnormal temperature are also shown in the graph. By observing the synergistic relationship between these parameters and temperature changes, the specific operating conditions at the time of the fault can be analyzed more comprehensively, providing more clues for accurately determining the cause of the fault.

[0055] The abnormal temperature limit time information is grouped according to different fault types, component locations, or the frequency of fault occurrence, so that relevant data can be more targeted in subsequent analysis and combination of abnormal change information.

[0056] The data diagnostic module can receive and extract current temperature limit time information and abnormal temperature limit time information, and then analyze the similarity index between the current temperature limit time information and different abnormal temperature limit time information. Let the number of temperature interval limits be S, and let the current temperature limit time information be S. Let the abnormal temperature limit time information be... Let the similarity index be... ;

[0057]

[0058] The similarity index can be calculated using the formula above.

[0059] After calculating the similarity index, the data diagnostic module establishes an index threshold and uses this threshold to filter the current temperature limit time information. Let the index threshold be... ;

[0060] when At time 1, the current temperature limit time information is determined to be abnormal.

[0061] when If 1 is true, then the current temperature limit time information is determined to be normal information, and then the current temperature limit time information is directly stored.

[0062] The specific workflow is as follows: A temperature change graph is plotted based on real-time temperature change information, and temperature interval limits are established. The time information when the temperature interval limit is reached is extracted to generate the current temperature limit time information. An abnormal temperature change graph is plotted based on abnormal temperature information, and the time when the temperature of aircraft components reaches the temperature interval limit in the abnormal temperature change graph is extracted to generate abnormal temperature limit time information. Using aircraft components as generation name tags, the name tags of the aircraft components are inserted into the corresponding current temperature limit time information and abnormal temperature limit time information. The temperature information when multiple components in the aircraft fail simultaneously is calculated. The similarity index between the current temperature limit time information and different abnormal temperature limit time information is analyzed, and an index threshold is established. The current temperature limit time information is then filtered using the index threshold.

[0063] Furthermore, the temperature monitoring module allows maintenance personnel to intuitively see the temperature changes of aircraft components over time. The anomaly analysis module facilitates comparison and analysis of temperature anomaly patterns corresponding to various faults, deepening the understanding of the relationship between faults and temperature and helping to more accurately analyze and combine abnormal change information. The data diagnostic module can quantitatively measure the similarity between real-time temperature changes and known abnormal temperature conditions, providing an objective and scientific basis for judging whether real-time temperature changes are abnormal. This avoids the limitations of relying solely on subjective experience and can accurately distinguish the time boundary information of normal and abnormal temperatures, reducing potential risks and losses caused by misjudgment of faults or untimely troubleshooting.

[0064] Example 3:

[0065] In addition to analyzing the temperature limits under which components can operate normally, more factors affecting component lifespan can be introduced to build a comprehensive analysis and prediction model. This model considers factors such as mechanical stress, vibration frequency, ambient humidity, and corrosion level that the component experiences. By collecting a large amount of historical data, machine learning algorithms can be used to establish a model of the relationship between these factors and the effective service life of the component.

[0066] When analyzing the maintenance methods of faulty components, the maintenance solution module establishes a process sorting unit. It uses the process sorting unit to analyze the installation process of components in the aircraft, then arranges the faulty components in the order of the aircraft's installation steps and records them in the process sorting unit to generate a process sorting table. After obtaining the maintenance methods of different faulty components, the maintenance solution module sorts the maintenance methods of the faulty components according to the process sorting table to generate a component maintenance solution.

[0067] For components that fail due to overheating, in addition to routine inspections and replacement of damaged components, maintenance methods can include special inspections and optimization measures for the heat dissipation system, such as cleaning heat sinks and checking for blockages in cooling pipes. Through in-depth analysis of different failure modes, more targeted maintenance methods can be generated and then sorted according to the process sorting table, so that the generated component maintenance plan can more effectively solve actual failure problems.

[0068] The maintenance time analysis module receives information processed by the maintenance plan module, extracts component maintenance plan information, analyzes the maintenance time of the component maintenance plan, determines the implementation time of the maintenance plan based on idle time information, and then judges whether the idle time information is valid time. Valid time means that the time in the idle time information is higher than the maintenance time of the maintenance plan, providing sufficient time for the maintenance of aircraft components. Let the maintenance time of the maintenance plan be... Let the maintenance preparation time be... Let the idle time information be... ;

[0069] when If so, the corresponding idle time information is determined to be valid time, and then it is recorded;

[0070] when If the time is invalid, the corresponding idle time information is determined to be invalid and then deleted.

[0071] By following the above method, all valid time information in the idle time information can be obtained. Then, the valid time information is sorted according to the order of time to obtain the valid time sorting table.

[0072] Establish a real-time dynamic adjustment mechanism to continuously update and adjust the maintenance schedule as factors such as aircraft operation, component updates, and changes in flight plans change. When the aircraft's flight plan is temporarily changed, causing changes in the usage of certain components, or when new components are installed and their maintenance requirements differ, the real-time dynamic adjustment mechanism can promptly reassess relevant factors such as idle time information and maintenance time of the maintenance plan, and redetermine the time for implementing the maintenance plan. This ensures that the maintenance schedule can always adapt to changes in the actual situation and improve the overall efficiency of aircraft operation and maintenance.

[0073] Specific workflow: The process sorting unit analyzes the installation process of aircraft components, arranges faulty components in sequence according to the aircraft's installation steps, and records them in the process sorting unit to generate a process sorting table. After obtaining the maintenance methods for different faulty components, the maintenance plan module sorts the maintenance methods of the faulty components according to the process sorting table, generates component maintenance plans, extracts component maintenance plan information, analyzes the maintenance time of the component maintenance plan, determines the time to implement the maintenance plan based on idle time information, and then judges whether the idle time information is a valid time. Valid time refers to the time in the idle time information that is higher than the maintenance time of the maintenance plan. The valid time information is sorted in chronological order to obtain a valid time sorting table.

[0074] Furthermore, the impact analysis module helps to plan maintenance work in advance, avoid sudden component failures during operation, and ensure the continuous safe operation of the aircraft. The maintenance scheme module ensures that maintenance work can be carried out in an orderly manner according to the aircraft's structure and component installation logic, avoiding problems such as repeated operations, component damage, or installation difficulties that may be caused by improper maintenance sequence, thus improving the efficiency and quality of maintenance work. The maintenance time analysis module can effectively avoid maintenance work not being completed smoothly due to insufficient idle time, realizing the scientific planning and rational use of maintenance time, ensuring that aircraft components are maintained at the appropriate time, and improving the overall planning and coordination of aircraft operation and maintenance work.

[0075] The foregoing has shown and described the basic principles, main features, and advantages of the present invention. Those skilled in the art should understand that the present invention is not limited to the above embodiments. The embodiments and descriptions in the specification are merely illustrative of the principles of the invention. Various changes and modifications can be made to the invention without departing from its spirit and scope, and all such changes and modifications fall within the scope of the present invention as claimed. The scope of protection of the present invention is defined by the appended claims and their equivalents.

Claims

1. A self-monitoring intelligent maintenance diagnosis system for an aircraft, comprising a data acquisition module capable of acquiring information inside the aircraft and obtaining the changing state of the aircraft in normal use to generate normal operation information, characterized in that: The temperature monitoring module, the abnormality analysis module, the data diagnosis module, the influence analysis module and the maintenance time analysis module are further included. The temperature monitoring module installs a temperature sensor on the aircraft component to obtain the temperature change of the aircraft component in real time and generate real-time temperature change information. When the temperature monitoring module generates the real-time temperature change information, it draws a temperature change graph according to the real-time temperature change information and establishes a temperature interval limit. When the temperature of the aircraft component reaches the temperature interval limit, it is marked in the temperature change graph and the time information when the temperature interval limit is reached is extracted to generate current temperature limit time information. The abnormality analysis module analyzes the temperature change information of the aircraft component when different faults occur to generate abnormal temperature information, and analyzes the temperature change information of multiple aircraft components when different faults occur simultaneously to generate combined abnormal change information. The abnormality analysis module draws an abnormal temperature change graph according to the abnormal temperature information after generating the abnormal temperature information, extracts the time when the temperature of the aircraft component in the abnormal temperature change graph reaches the temperature interval limit, generates abnormal temperature limit time information, takes the aircraft component as a generated name label, and inserts the name label of the aircraft component into the corresponding current temperature limit time information and abnormal temperature limit time information. Let the number of components that fail in the aircraft be L, let the different component temperature information of the aircraft that fails be , and let the temperature information when multiple components in the aircraft fail simultaneously be . ； （1） According to formula (1), the temperature information of multiple components in the aircraft when faults occur simultaneously can be calculated, thereby facilitating the analysis of combined abnormal change information. The data diagnosis module extracts real-time temperature change information, matches the real-time temperature change information with abnormal temperature information and combined abnormal change information, analyzes the abnormal index of the real-time temperature change information, and obtains fault component information. The data diagnosis module can receive, extract current temperature limit time information and abnormal temperature limit time information, and then analyze the similarity index between the current temperature limit time information and different abnormal temperature limit time information, wherein the number of temperature interval limits is S, the current temperature limit time information is , the abnormal temperature limit time information is , and the similarity index is ; ；（2） According to formula (2), the similarity index can be calculated. The influence analysis module can analyze the influence of the aircraft component on the aircraft when the real-time temperature change information is abnormal, predict the effective use time of the aircraft component, analyze the time when the aircraft can normally operate, and generate component maintenance time information.

2. The self-monitoring intelligent maintenance diagnostic system for aircraft as claimed in claim 1, wherein: The maintenance scheme module and the maintenance time analysis module are further included. The maintenance scheme module can extract fault component information, analyze the maintenance method of the fault component, and generate component maintenance scheme. The maintenance time analysis module extracts information inside the aircraft to analyze the time period when different components are needed during aircraft operation, judges the time when the aircraft component stops running to generate idle time information, obtains component maintenance scheme of different aircraft components, analyzes the time required by different component maintenance schemes, and then obtains the time information of the aircraft component for maintenance according to the idle time information, and displays the time information and maintenance scheme information to internal personnel.

3. The intelligent maintenance diagnostic system for self-monitoring aircraft of claim 1, wherein: The data diagnosis module establishes an index threshold after calculating the similarity index, uses the index threshold to screen the current temperature limit time information, and sets the index threshold as ; When 1, it is determined that the current temperature limit time information is abnormal information; When 1, it is determined that the current temperature limit time information is normal information, and then the current temperature limit time information is directly stored.

4. The intelligent maintenance diagnostic system for self-monitoring aircraft of claim 2, wherein: When the maintenance scheme module analyzes the maintenance method of the fault component, it establishes a process sorting unit to analyze the installation process of the component in the aircraft, then arranges the fault component in sequence according to the installation steps of the aircraft and records it in the process sorting unit to generate a process sorting table. After obtaining the maintenance method of different fault components, the maintenance scheme module sorts the maintenance method of the fault component according to the process sorting table to generate the component maintenance scheme.

5. A self-monitoring intelligent maintenance diagnostic system for aircraft as claimed in claim 4 wherein: The maintenance time analysis module can receive information processed by the maintenance scheme module, extract component maintenance scheme information, analyze the maintenance time of the component maintenance scheme, and then determine the time for implementing the maintenance scheme according to the idle time information. Then it is judged whether the idle time information belongs to the effective time. The effective time refers to the time in the idle time information which is higher than the maintenance time of the maintenance scheme, which provides sufficient time for the maintenance of the aircraft component. Let the maintenance time of the maintenance scheme be , let the maintenance preparation time be , and let the idle time information be ; When the corresponding idle time information is valid time, and then records it. When the corresponding idle time information is invalid time, and then deletes it. According to the above method, all effective time information in the idle time information can be obtained, and then the effective time information is sorted according to the time sequence to obtain an effective time sorting table.

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