Aero-engine fault prediction method and prediction system thereof

Abstract

The invention discloses an aero-engine fault prediction method and prediction system, and relates to the technical field of fault analysis and prediction, and the method comprises the steps: carrying out the analysis and processing of the historical data of an aero-engine, and obtaining the loss rate of the aero-engine. The method comprises the following steps: performing time analysis on historical data of the aero-engine to determine the working time length and the idle time length of the aero-engine, performing loss analysis on the working time length and the idle time length of the aero-engine to determine the loss rate of the aero-engine, and determining the loss rate of the aero-engine according to the loss rate of the aero-engine. According to the method, the loss rate of the aero-engine and the loss rate critical value of the aero-engine are calculated, the loss deviation value of the aero-engine is determined, finally, fault prediction analysis is conducted on the loss deviation value of the aero-engine, the fault prediction occurrence time of the aero-engine is determined, and the fault occurrence time of the aero-engine can be predicted in the mode. The aero-engine is prevented from suddenly breaking down during working, and the work completion time is shortened.

Description

Technical Field

[0001] The present invention relates to the technical field of fault analysis and prediction, and in particular to an aero-engine fault prediction method and a prediction system thereof. Background Art

[0002] An aircraft engine is a highly complex and sophisticated thermal machine. As the heart of an aircraft, it is not only the driving force for the aircraft to fly, but also an important driving force for the development of the aviation industry. Every important change in human aviation history is closely related to the technological progress of aircraft engines.

[0003] After more than a hundred years of development, aircraft engines have developed into mature products with extremely high reliability. The aircraft engines in use include various types such as turbojet / turbofan engines, turboshaft / turboprop engines, ramjet engines and piston engines. They are not only used as power for military and civilian aircraft, drones and cruise missiles for various purposes, but also gas turbines derived from aircraft engines are widely used in ground power generation, marine power, mobile power stations, natural gas and oil pipeline pumping stations and other fields.

[0004] Aircraft engines may malfunction after long-term use. When an aircraft engine malfunctions during operation, work may be forced to be interrupted, extending the time to complete the work. Summary of the invention

[0005] In order to solve the above technical problems, a method and a prediction system for aircraft engine faults are provided. This technical solution solves the problem raised in the above background technology that aircraft engines may fail after long-term use. When an aircraft engine fails during operation, the work may be forced to be interrupted, which prolongs the time to complete the work.

[0006] In order to achieve the above purpose, the technical solution adopted by the present invention is: An aircraft engine fault prediction method, comprising: Acquire historical data of the aircraft engine, analyze and process the historical data of the aircraft engine based on the fault prediction terminal, and acquire the loss rate of the aircraft engine, wherein the loss rate of the aircraft engine includes the natural loss rate of the aircraft engine and the working loss rate of the aircraft engine; Based on the fault prediction terminal, the loss rate of the aircraft engine is analyzed and processed to determine the loss deviation value of the aircraft engine; Based on the fault prediction terminal, the loss deviation value of the aircraft engine is analyzed and processed to determine the fault prediction occurrence time of the aircraft engine, wherein the fault prediction occurrence time of the aircraft engine includes the idle fault prediction occurrence time of the aircraft engine, the normal working fault prediction occurrence time of the aircraft engine and the overload working fault prediction occurrence time of the aircraft engine.

[0007] Preferably, the acquiring of historical data of the aircraft engine, analyzing and processing the historical data of the aircraft engine based on the fault prediction terminal, and acquiring the loss rate of the aircraft engine specifically comprises the following steps: Based on the fault prediction terminal, control the image acquisition device to acquire images of the aircraft engine and obtain the aircraft engine model; Based on the fault prediction terminal, information retrieval processing is performed on the root directory of the database system based on the aircraft engine model to obtain the data storage location of the aircraft engine; Based on the fault prediction terminal, the database system is processed for data extraction based on the data storage location of the aircraft engine to obtain the historical data of the aircraft engine; Based on the fault prediction terminal, the historical data of aircraft engines is analyzed and processed to obtain the loss rate of aircraft engines.

[0008] Preferably, the analyzing and processing of historical data of the aircraft engine based on the fault prediction terminal to obtain the loss rate of the aircraft engine specifically comprises the following steps: Based on the fault prediction terminal, the historical data of the aircraft engine is extracted and processed to obtain the working time and idle time of the aircraft engine; Based on the fault prediction terminal, the database system is retrieved and processed to obtain the factory specification parameters of the aircraft engine; Based on the fault prediction terminal, the factory specification parameters of the aircraft engine are analyzed and processed to obtain the working loss parameters and idle loss parameters of the aircraft engine; Based on the fault prediction terminal, the idle time and idle loss parameters of the aircraft engine are calculated and processed to obtain the natural loss rate of the aircraft engine; Based on the fault prediction terminal, the working time of the aircraft engine is analyzed and processed to obtain the working loss rate of the aircraft engine.

[0009] Preferably, the analyzing and processing of the working time of the aircraft engine based on the fault prediction terminal to obtain the working loss rate of the aircraft engine specifically comprises the following steps: Based on the fault prediction terminal, the characteristics of the working time of the aircraft engine are analyzed to determine the overload working time characteristics and the normal working time characteristics; Based on the fault prediction terminal, information extraction and processing is performed on the working loss parameters of the aircraft engine to obtain the overload loss parameters and normal working loss parameters of the aircraft engine; Based on the fault prediction terminal, the overload working time characteristics of the working time and the overload loss parameters of the aircraft engine, the normal working time characteristics of the working time and the normal working loss parameters of the aircraft engine are calculated and processed to obtain the working loss rate of the aircraft engine; The specific calculation formula for obtaining the working loss rate of the aircraft engine is: ; In the formula, is the working loss rate of the aircraft engine; Overload working time characteristics for working hours; is the overload loss parameter of the aircraft engine; Normal working time characteristics for the length of working hours; It is the normal working loss parameter of aircraft engine.

[0010] Preferably, the analyzing and processing of the loss rate of the aircraft engine based on the fault prediction terminal to determine the loss deviation value of the aircraft engine specifically comprises the following steps: Based on the fault prediction terminal, the working loss rate of the aircraft engine and the natural loss rate of the aircraft engine are summed and calculated to obtain the total loss rate of the aircraft engine; Based on the fault prediction terminal, the factory specification parameters of the aircraft engine are analyzed and processed to determine the critical value of the loss rate of the aircraft engine; Based on the fault prediction terminal, the total loss rate of the aircraft engine and the critical value of the loss rate of the aircraft engine are calculated and processed to obtain the loss deviation value of the aircraft engine; The specific calculation formula of the loss deviation value of the aircraft engine is: ; In the formula, is the loss deviation value of the aircraft engine; is the critical value of the loss rate of the aircraft engine; is the working loss rate of the aircraft engine; is the idle time of the aircraft engine; is the idle loss parameter of the aircraft engine.

[0011] Preferably, the analyzing and processing of the loss deviation value of the aircraft engine based on the fault prediction terminal to determine the predicted fault occurrence time of the aircraft engine specifically comprises the following steps: Based on the fault prediction terminal, the loss deviation value of the aircraft engine and the idle loss parameter of the aircraft engine are calculated and processed to determine the idle fault prediction occurrence time of the aircraft engine; Based on the fault prediction terminal, the loss deviation value of the aircraft engine and the normal working loss parameters of the aircraft engine are calculated and processed to determine the predicted occurrence time of the normal working fault of the aircraft engine; Based on the fault prediction terminal, the loss deviation value of the aircraft engine and the overload loss parameter of the aircraft engine are analyzed and processed to determine the predicted occurrence time of the overload working fault of the aircraft engine.

[0012] Preferably, the method of analyzing and processing the loss deviation value of the aircraft engine and the overload loss parameter of the aircraft engine based on the fault prediction terminal to determine the predicted occurrence time of the overload fault of the aircraft engine specifically comprises the following steps: Based on the fault prediction terminal, data analysis and processing are performed on the factory specification parameters of the aircraft engine to determine the time when the aircraft engine overloads and the normal working time before the time when the aircraft engine overloads; Based on the fault prediction terminal, the normal working time of the aircraft engine before the overload working moment and the normal working loss parameter of the aircraft engine are calculated and processed to determine the normal loss value of the aircraft engine; Based on the fault prediction terminal, the loss deviation value of the aircraft engine, the normal loss value of the aircraft engine and the overload loss parameter of the aircraft engine are calculated and processed to determine the predicted occurrence time of the overload working fault of the aircraft engine.

[0013] Preferably, the specific calculation formula for determining the predicted occurrence time of the aircraft engine overload failure is: ; In the formula, Predict the occurrence time of overload failure of aircraft engines; is the loss deviation value of the aircraft engine; The normal working time before the aircraft engine overload occurs; is the overload loss parameter of the aircraft engine; It is the normal working loss parameter of aircraft engine.

[0014] Furthermore, an aircraft engine fault prediction system is proposed, which is used to implement the above-mentioned aircraft engine fault prediction method, including: A fault prediction terminal, which is used to control each module to perform loss rate analysis, loss rate calculation and loss deviation value calculation on the historical data of the aircraft engine, determine the predicted occurrence time of the fault of the aircraft engine, and is used to control data transmission and information interaction between each module; A database system, wherein the database system is used to store historical data of the aircraft engine and factory specification parameters of the aircraft engine; An image acquisition device, wherein the image acquisition device is used to acquire images of the aircraft engine and determine the aircraft engine model; A data analysis module, wherein the data analysis module is used to analyze historical data of the aircraft engine and determine the loss rate of the aircraft engine; A data calculation module, the data calculation module is used to calculate the total loss rate of the aircraft engine and the loss rate critical value of the aircraft engine to determine the loss deviation value of the aircraft engine; A fault prediction module is used to analyze and process the loss deviation value of the aircraft engine to determine the fault prediction occurrence time of the aircraft engine.

[0015] Compared with the prior art, the present invention provides an aircraft engine fault prediction method and prediction system thereof, which have the following beneficial effects: The present invention firstly performs time analysis on historical data of an aircraft engine to determine the working time and idle time of the aircraft engine. Secondly, a loss analysis is performed on the working time and idle time of the aircraft engine to determine the loss rate of the aircraft engine. Then, the loss rate of the aircraft engine and the critical value of the loss rate of the aircraft engine are calculated to determine the loss deviation value of the aircraft engine. Finally, a fault prediction analysis is performed on the loss deviation value of the aircraft engine to determine the predicted occurrence time of the fault of the aircraft engine. The above method can predict the occurrence time of the fault of the aircraft engine, avoid sudden failure of the aircraft engine during operation, and shorten the completion time of the work. BRIEF DESCRIPTION OF THE DRAWINGS

[0016] Figure 1 A schematic flow chart of steps S100-S300 in an aircraft engine fault prediction method proposed by the present invention; Figure 2 This is a flow chart of steps S101-S104 in an aircraft engine fault prediction method proposed by the present invention; Figure 3 This is a flow chart of steps S1041-S1045 in an aircraft engine fault prediction method proposed by the present invention; Figure 4 This is a flow chart of steps S10451-S10453 in an aircraft engine fault prediction method proposed by the present invention; Figure 5 This is a flow chart of steps S201-S203 in an aircraft engine fault prediction method proposed by the present invention; Figure 6This is a flow chart of steps S301-S303 in an aircraft engine fault prediction method proposed by the present invention; Figure 7 This is a flow chart of steps S3031-S3033 in an aircraft engine fault prediction method proposed by the present invention; Figure 8 This is a structural block diagram of an aircraft engine fault prediction system proposed by the present invention. DETAILED DESCRIPTION

[0017] The following description is used to disclose the present invention so that those skilled in the art can implement the present invention. The preferred embodiments described below are only examples, and those skilled in the art may think of other obvious variations.

[0018] Reference Figure 1 As shown, a method for predicting aircraft engine failures includes: S100, acquiring historical data of the aircraft engine, and analyzing and processing the historical data of the aircraft engine based on the fault prediction terminal to acquire a loss rate of the aircraft engine, wherein the loss rate of the aircraft engine includes a natural loss rate of the aircraft engine and a working loss rate of the aircraft engine; S200, analyzing and processing the loss rate of the aircraft engine based on the fault prediction terminal to determine the loss deviation value of the aircraft engine; S300, analyzing and processing the loss deviation value of the aircraft engine based on the fault prediction terminal to determine the predicted fault occurrence time of the aircraft engine, wherein the predicted fault occurrence time of the aircraft engine includes the predicted idle fault occurrence time of the aircraft engine, the predicted normal working fault occurrence time of the aircraft engine, and the predicted overload working fault occurrence time of the aircraft engine; It will be understood by those skilled in the art that after an aircraft engine has been put into use for a period of time, the aircraft engine will experience a certain degree of wear and tear. If the wear and tear of the aircraft engine reaches a certain level, the aircraft engine may malfunction. Therefore, the historical data of the aircraft engine is analyzed to determine the wear rate of the aircraft engine. Then, the wear rate of the aircraft engine is calculated to determine the wear deviation value of the aircraft engine. Finally, the wear and tear deviation value of the aircraft engine is used to predict the wear and tear and determine the predicted time of the wear and tear of the aircraft engine.

[0019] Reference Figure 2 As shown, obtaining historical data of the aircraft engine, analyzing and processing the historical data of the aircraft engine based on the fault prediction terminal, and obtaining the loss rate of the aircraft engine specifically includes the following steps: S101, based on the fault prediction terminal, controlling the image acquisition device to acquire images of the aircraft engine to obtain the aircraft engine model; S102, based on the fault prediction terminal, performing information retrieval processing on the root directory of the database system based on the aircraft engine model as a feature to obtain the data storage location of the aircraft engine; S103, based on the fault prediction terminal, extracting data from the database system based on the data storage location of the aircraft engine as a feature to obtain historical data of the aircraft engine; S104, analyzing and processing historical data of the aircraft engine based on the fault prediction terminal to obtain a loss rate of the aircraft engine; In this embodiment, there is more than one model of aircraft engines. Therefore, in order to accurately extract the historical data of a certain model of aircraft engines, images of the aircraft engines are captured by an image acquisition device, and then the captured images are analyzed for models to determine the aircraft engine model. Then, data is extracted from the database system based on the aircraft engine model, so that a certain model of aircraft engines can be accurately obtained, thereby avoiding data analysis errors.

[0020] Reference Figure 3 As shown, based on the fault prediction terminal, the historical data of the aircraft engine is analyzed and processed to obtain the loss rate of the aircraft engine, which specifically includes the following steps: S1041. Based on the fault prediction terminal, extract and process historical data of the aircraft engine to obtain the working time and idle time of the aircraft engine; S1042, based on the fault prediction terminal, performing data retrieval processing on the database system to obtain factory specification parameters of the aircraft engine; S1043. Based on the fault prediction terminal, perform data analysis and processing on the factory specification parameters of the aircraft engine to obtain the working loss parameters and the idle loss parameters of the aircraft engine; S1044. Based on the fault prediction terminal, calculate and process the idle time of the aircraft engine and the idle loss parameter of the aircraft engine to obtain the natural loss rate of the aircraft engine; S1045. Analyze and process the working time of the aircraft engine based on the fault prediction terminal to obtain the working loss rate of the aircraft engine; In this embodiment, the aircraft engine may also wear out when not in use, but the wear rate may be slower. Therefore, by analyzing the factory specification parameters of the aircraft engine, the natural wear rate and the working wear rate of the aircraft engine are determined, and the wear rate of the aircraft engine is calculated based on the working wear rate and the natural wear rate of the aircraft engine.

[0021] Reference Figure 4As shown, based on the fault prediction terminal, analyzing and processing the working time of the aircraft engine to obtain the working loss rate of the aircraft engine specifically includes the following steps: S10451. Based on the fault prediction terminal, perform characteristic analysis on the working time of the aircraft engine to determine the overload working time characteristics and the normal working time characteristics of the working time; S10452. Based on the fault prediction terminal, extract information from the working loss parameters of the aircraft engine to obtain overload loss parameters and normal working loss parameters of the aircraft engine; S10453. Based on the fault prediction terminal, calculate and process the overload working time characteristics of the working time and the overload loss parameters of the aircraft engine, the normal working time characteristics of the working time and the normal working loss parameters of the aircraft engine to obtain the working loss rate of the aircraft engine; The specific calculation formula for obtaining the working loss rate of the aircraft engine is: ; In the formula, is the working loss rate of the aircraft engine; Overload working time characteristics for working hours; is the overload loss parameter of the aircraft engine; Normal working time characteristics for the length of working hours; It is the normal working loss parameter of the aircraft engine; In this embodiment, the aircraft engine will also experience different degrees of wear and tear when it is working. For example, if the aircraft engine works for a long time, it will suffer greater wear and tear, that is, overload work. No matter what equipment it is, the wear and tear of the equipment will accelerate when it works under overload conditions. Therefore, the normal working wear and tear parameters of the aircraft engine and the overload wear and tear parameters of the aircraft engine are calculated to determine the working wear and tear rate of the aircraft engine.

[0022] Reference Figure 5 As shown, based on the fault prediction terminal, the loss rate of the aircraft engine is analyzed and processed to determine the loss deviation value of the aircraft engine, which specifically includes the following steps: S201, based on the fault prediction terminal, summing up the working loss rate of the aircraft engine and the natural loss rate of the aircraft engine to obtain the total loss rate of the aircraft engine; S202, based on the fault prediction terminal, performing data analysis and processing on the factory specification parameters of the aircraft engine to determine the critical value of the loss rate of the aircraft engine; S203, calculating and processing the total loss rate of the aircraft engine and the critical value of the loss rate of the aircraft engine based on the fault prediction terminal to obtain a loss deviation value of the aircraft engine; The specific calculation formula of the loss deviation value of the aircraft engine is: ; In the formula, is the loss deviation value of the aircraft engine; is the critical value of the loss rate of the aircraft engine; is the working loss rate of the aircraft engine; is the idle time of the aircraft engine; is the idle loss parameter of the aircraft engine; In this embodiment, when the loss rate of the aircraft engine reaches a certain level, the probability of aircraft engine failure will greatly increase. Therefore, the total loss rate of the aircraft engine and the critical value of the loss rate of the aircraft engine are calculated and processed to determine the loss deviation value of the aircraft engine. The loss deviation value of the aircraft engine is then analyzed to determine the predicted occurrence time of the aircraft engine failure.

[0023] Reference Figure 6 As shown, based on the fault prediction terminal, analyzing and processing the loss deviation value of the aircraft engine to determine the fault prediction occurrence time of the aircraft engine specifically includes the following steps: S301, based on the fault prediction terminal, calculating and processing the loss deviation value of the aircraft engine and the idle loss parameter of the aircraft engine to determine the idle fault prediction occurrence time of the aircraft engine; S302, based on the fault prediction terminal, calculating and processing the loss deviation value of the aircraft engine and the normal working loss parameter of the aircraft engine, and determining the predicted occurrence time of the normal working fault of the aircraft engine; S303: Based on the fault prediction terminal, the loss deviation value of the aircraft engine and the overload loss parameter of the aircraft engine are analyzed and processed to determine the predicted occurrence time of the overload working fault of the aircraft engine.

[0024] Reference Figure 7 As shown, based on the fault prediction terminal, the loss deviation value of the aircraft engine and the overload loss parameter of the aircraft engine are analyzed and processed to determine the predicted occurrence time of the overload working fault of the aircraft engine, which specifically includes the following steps: S3031. Based on the fault prediction terminal, perform data analysis and processing on the factory specification parameters of the aircraft engine to determine the time when the aircraft engine overloads and the normal working time of the aircraft engine before the time when the aircraft engine overloads; S3032. Based on the fault prediction terminal, calculate and process the normal working time of the aircraft engine before the overload working moment and the normal working loss parameter of the aircraft engine to determine the normal loss value of the aircraft engine; S3033, based on the fault prediction terminal, calculating and processing the loss deviation value of the aircraft engine, the normal loss value of the aircraft engine, and the overload loss parameter of the aircraft engine, and determining the predicted occurrence time of the overload working fault of the aircraft engine; The specific calculation formula for determining the predicted occurrence time of an aircraft engine's overload failure is: ; In the formula, Predict the occurrence time of overload failure of aircraft engines; is the loss deviation value of the aircraft engine; The normal working time before the aircraft engine overload occurs; is the overload loss parameter of the aircraft engine; It is the normal working loss parameter of the aircraft engine; In this embodiment, different states of the aircraft engine will result in different fault occurrence times. For example, if the aircraft engine is always in an idle state, the time when the fault occurs will be extended. If the aircraft engine is always in an overloaded working state, the time when the fault occurs will be advanced. Therefore, the time when the fault occurs is predicted based on the different states of the aircraft engine.

[0025] Reference Figure 8 As shown, an aircraft engine fault prediction system is used to implement an aircraft engine fault prediction method as described above, comprising: A fault prediction terminal, which is used to control each module to perform loss rate analysis, loss rate calculation and loss deviation value calculation on the historical data of the aircraft engine, determine the predicted occurrence time of the fault of the aircraft engine, and is used to control data transmission and information interaction between each module; A database system, wherein the database system is used to store historical data of the aircraft engine and factory specification parameters of the aircraft engine; An image acquisition device, wherein the image acquisition device is used to acquire images of the aircraft engine and determine the aircraft engine model; A data analysis module, wherein the data analysis module is used to analyze historical data of the aircraft engine and determine the loss rate of the aircraft engine; A data calculation module, the data calculation module is used to calculate the total loss rate of the aircraft engine and the loss rate critical value of the aircraft engine to determine the loss deviation value of the aircraft engine; A fault prediction module is used to analyze and process the loss deviation value of the aircraft engine to determine the fault prediction occurrence time of the aircraft engine.

[0026] The above shows and describes 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 above embodiments and descriptions only describe the principles of the present invention. The present invention may be subject to various changes and improvements without departing from the spirit and scope of the present invention. These changes and improvements fall within the scope of the present invention. The scope of protection claimed by the present invention is defined by the attached claims and their equivalents.

Claims

1. A method for predicting aircraft engine failure, characterized in that: include: Acquire historical data of the aircraft engine, analyze and process the historical data of the aircraft engine based on the fault prediction terminal, and acquire the loss rate of the aircraft engine, wherein the loss rate of the aircraft engine includes the natural loss rate of the aircraft engine and the working loss rate of the aircraft engine; Based on the fault prediction terminal, the loss rate of the aircraft engine is analyzed and processed to determine the loss deviation value of the aircraft engine; Based on the fault prediction terminal, the loss deviation value of the aircraft engine is analyzed and processed to determine the fault prediction occurrence time of the aircraft engine, wherein the fault prediction occurrence time of the aircraft engine includes the idle fault prediction occurrence time of the aircraft engine, the normal working fault prediction occurrence time of the aircraft engine and the overload working fault prediction occurrence time of the aircraft engine.

2. The method for predicting aircraft engine failure according to claim 1, characterized in that: The method of obtaining the historical data of the aircraft engine, analyzing and processing the historical data of the aircraft engine based on the fault prediction terminal, and obtaining the loss rate of the aircraft engine specifically includes the following steps: Based on the fault prediction terminal, control the image acquisition device to acquire images of the aircraft engine and obtain the aircraft engine model; Based on the fault prediction terminal, information retrieval processing is performed on the root directory of the database system based on the aircraft engine model to obtain the data storage location of the aircraft engine; Based on the fault prediction terminal, the database system is processed for data extraction based on the data storage location of the aircraft engine to obtain the historical data of the aircraft engine; Based on the fault prediction terminal, the historical data of aircraft engines is analyzed and processed to obtain the loss rate of aircraft engines.

3. The method for predicting aircraft engine failure according to claim 2, characterized in that: The method of analyzing and processing the historical data of the aircraft engine based on the fault prediction terminal to obtain the loss rate of the aircraft engine specifically includes the following steps: Based on the fault prediction terminal, the historical data of the aircraft engine is extracted and processed to obtain the working time and idle time of the aircraft engine; Based on the fault prediction terminal, the database system is retrieved and processed to obtain the factory specification parameters of the aircraft engine; Based on the fault prediction terminal, the factory specification parameters of the aircraft engine are analyzed and processed to obtain the working loss parameters and idle loss parameters of the aircraft engine; Based on the fault prediction terminal, the idle time and idle loss parameters of the aircraft engine are calculated and processed to obtain the natural loss rate of the aircraft engine; Based on the fault prediction terminal, the working time of the aircraft engine is analyzed and processed to obtain the working loss rate of the aircraft engine.

4. The method for predicting aircraft engine failure according to claim 3, characterized in that: The method of analyzing and processing the working time of the aircraft engine based on the fault prediction terminal to obtain the working loss rate of the aircraft engine specifically includes the following steps: Based on the fault prediction terminal, the characteristics of the working time of the aircraft engine are analyzed to determine the overload working time characteristics and the normal working time characteristics; Based on the fault prediction terminal, information extraction and processing is performed on the working loss parameters of the aircraft engine to obtain the overload loss parameters and normal working loss parameters of the aircraft engine; Based on the fault prediction terminal, the overload working time characteristics of the working time and the overload loss parameters of the aircraft engine, the normal working time characteristics of the working time and the normal working loss parameters of the aircraft engine are calculated and processed to obtain the working loss rate of the aircraft engine; The specific calculation formula for obtaining the working loss rate of the aircraft engine is: ； In the formula, is the working loss rate of the aircraft engine; Overload working time characteristics for working hours; is the overload loss parameter of the aircraft engine; Normal working time characteristics for the length of working hours; It is the normal working loss parameter of aircraft engine.

5. The method for predicting aircraft engine failure according to claim 1, characterized in that: The method of analyzing and processing the loss rate of the aircraft engine based on the fault prediction terminal to determine the loss deviation value of the aircraft engine specifically includes the following steps: Based on the fault prediction terminal, the working loss rate of the aircraft engine and the natural loss rate of the aircraft engine are summed and calculated to obtain the total loss rate of the aircraft engine; Based on the fault prediction terminal, the factory specification parameters of the aircraft engine are analyzed and processed to determine the critical value of the loss rate of the aircraft engine; Based on the fault prediction terminal, the total loss rate of the aircraft engine and the critical value of the loss rate of the aircraft engine are calculated and processed to obtain the loss deviation value of the aircraft engine; The specific calculation formula of the loss deviation value of the aircraft engine is: ; In the formula, is the loss deviation value of the aircraft engine; is the critical value of the loss rate of the aircraft engine; is the working loss rate of the aircraft engine; is the idle time of the aircraft engine; is the idle loss parameter of the aircraft engine.

6. The method for predicting aircraft engine failure according to claim 1, characterized in that: The method of analyzing and processing the loss deviation value of the aircraft engine based on the fault prediction terminal to determine the fault prediction occurrence time of the aircraft engine specifically includes the following steps: Based on the fault prediction terminal, the loss deviation value of the aircraft engine and the idle loss parameter of the aircraft engine are calculated and processed to determine the idle fault prediction occurrence time of the aircraft engine; Based on the fault prediction terminal, the loss deviation value of the aircraft engine and the normal working loss parameters of the aircraft engine are calculated and processed to determine the predicted occurrence time of the normal working fault of the aircraft engine; Based on the fault prediction terminal, the loss deviation value of the aircraft engine and the overload loss parameter of the aircraft engine are analyzed and processed to determine the predicted occurrence time of the overload working fault of the aircraft engine.

7. The method for predicting aircraft engine failure according to claim 6, characterized in that: The method of analyzing and processing the loss deviation value of the aircraft engine and the overload loss parameter of the aircraft engine based on the fault prediction terminal to determine the predicted occurrence time of the overload fault of the aircraft engine specifically includes the following steps: Based on the fault prediction terminal, data analysis and processing are performed on the factory specification parameters of the aircraft engine to determine the time when the aircraft engine overloads and the normal working time before the time when the aircraft engine overloads; Based on the fault prediction terminal, the normal working time of the aircraft engine before the overload working moment and the normal working loss parameter of the aircraft engine are calculated and processed to determine the normal loss value of the aircraft engine; Based on the fault prediction terminal, the loss deviation value of the aircraft engine, the normal loss value of the aircraft engine and the overload loss parameter of the aircraft engine are calculated and processed to determine the predicted occurrence time of the overload working fault of the aircraft engine.

8. The method for predicting aircraft engine failure according to claim 1, characterized in that: The specific calculation formula for determining the predicted occurrence time of the overload failure of the aircraft engine is: ； In the formula, Predict the occurrence time of overload failure of aircraft engines; is the loss deviation value of the aircraft engine; The normal working time before the aircraft engine overload occurs; is the overload loss parameter of the aircraft engine; It is the normal working loss parameter of aircraft engine.

9. An aircraft engine fault prediction system, used to implement an aircraft engine fault prediction method according to any one of claims 1 to 8, characterized in that: include: A fault prediction terminal, which is used to control each module to perform loss rate analysis, loss rate calculation and loss deviation value calculation on the historical data of the aircraft engine, determine the predicted occurrence time of the fault of the aircraft engine, and is used to control data transmission and information interaction between each module; A database system, wherein the database system is used to store historical data of the aircraft engine and factory specification parameters of the aircraft engine; An image acquisition device, wherein the image acquisition device is used to acquire images of the aircraft engine and determine the aircraft engine model; A data analysis module, wherein the data analysis module is used to analyze historical data of the aircraft engine and determine the loss rate of the aircraft engine; A data calculation module, the data calculation module is used to calculate the total loss rate of the aircraft engine and the loss rate critical value of the aircraft engine to determine the loss deviation value of the aircraft engine; A fault prediction module is used to analyze and process the loss deviation value of the aircraft engine to determine the fault prediction occurrence time of the aircraft engine.

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