Aero-engine health management platform and health management method

Abstract

The invention discloses an aero-engine health management platform and a health management method. A data management module; a parameter echo module; a health management main function module; when daily health management is carried out, the aircraft parameter data and the engine parameter data are input into the data management module and processed by the data management module, then the management relation with an engine station is established, and the parameter echo module and the health management main function module carry out daily health management according to the management relation of the engine station. Various parameters are displayed through the parameter echoing module, health management is carried out through the various health management function sub-modules, and a health management report is output. The systematic health management method is formed through the architecture design of each function module, the system process, function composition, interface and data flow direction are clear and simplified, the operation is more convenient, and the method is suitable for the use scene of a ground subsystem.

Description

Technical Field

[0001] The present invention belongs to the technical field of intelligent health management of aircraft engines, and specifically relates to an aircraft engine health management platform and a health management method. Background Art

[0002] An aircraft engine health management system (EHMS) utilizes sensor output, data acquisition, data processing, data analysis, and human decision-making to determine the health status of the entire engine, its components, and subsystems, thereby improving the safety, reliability, and maintainability of aircraft engines. The EHMS receives parameters from the engine control system but generally does not send any data or instructions to the control system and does not participate in engine control. An EHMS is generally divided into an onboard subsystem and a ground-based subsystem. The onboard subsystem typically consists of onboard data acquisition and processing equipment, specialized sensors, and related software. The ground-based subsystem typically consists of portable maintenance equipment, ground-based data processing equipment, and related analysis software. The onboard engine subsystem receives information from the engine control system and collaborates with the ground-based subsystem to perform functions such as engine status monitoring, fault diagnosis and isolation, trend analysis and prediction, life management, and alarm generation.

[0003] Currently, existing research and applications on health management are mostly focused on specific technical points, and no relevant architecture has been formed to support the development of health management functions. There is a lack of clarity on the functions, interfaces between functions, and data flows that should be included in the health management platform. At the same time, there is no corresponding systematic health management method, which is not conducive to the practice of aircraft engine health management.

[0004] For example, the patent document with publication number CN115258176A specifically discloses an engine health management system on an aircraft, including: an engine data collector, installed on the engine, connected to an engine-specific sensor installed on the engine, and connected to an engine controller, so as to be able to collect corresponding engine parameters, wherein the engine data collector can only unidirectionally receive data sent by the engine controller; an engine health monitoring unit, installed on the aircraft, connected to the aircraft system, and connected to the engine data collector, so as to be able to receive and store corresponding engine parameters, generate an engine status monitoring report based on the corresponding engine parameters, and store and send the engine status monitoring report to the aircraft system.

[0005] For example, the patent document with publication number CN117131785B specifically discloses an electric aircraft engine health management system and method, including a sensing unit, a data transmission unit, a cloud data storage and processing unit, a state monitoring unit, a state prediction unit, a health examination unit, a decision unit, and a precision control unit. The sensing unit is used to collect information on the working data of the motor components of the UAV electric aircraft engine. The data transmission unit is used to transmit the data collected by the sensing unit to the cloud data storage and processing unit. The cloud data storage and processing unit is used to store and process the data collected by the sensing unit. The state monitoring unit is used to detect and diagnose faults of the UAV electric aircraft engine. The state prediction unit is used to predict faults of the UAV electric aircraft engine and the life of its motor components. The health examination unit performs periodic health examinations on the UAV aircraft engine.

[0006] In summary, the existing technology still lacks a corresponding systematic health management method, and the system process, functional composition and interface, and data flow are complex, which is not conducive to the practice of aircraft engine health management. Therefore, there is a need for an aircraft engine health management platform and health management method that targets the usage scenarios of the ground subsystem, and the system process, functional composition and interface, and data flow are simple and easy to operate. Summary of the Invention

[0007] To solve the above technical problems, this application provides an aircraft engine health management platform, including:

[0008] The data management module is used to receive aircraft parameter data and engine parameter data, process heterogeneous data, and realize data conversion between different parameter units;

[0009] The data management module is used to establish the management relationship between data and engine units, and maintain the data corresponding to the engine with the engine as the management unit;

[0010] The parameter echo module is used to echo the data parameter values, and can realize single-shot parameter echo function and dual-shot parameter echo function;

[0011] The health management main function module is used to host various health management sub-modules, organize and analyze historical engine operating data collected by the aircraft engine health management platform, provide safe operation and condition-based maintenance recommendations, and implement daily aircraft engine health management functions. The health management sub-modules are used to generate and export reports on engine life management, health analysis, fault reasoning, parameter interpretation, maintenance decision-making, and trend prediction results with one click.

[0012] When performing the daily health management, the aircraft parameter data and engine parameter data are input into the data management module. After processing by the data management module, a management relationship with the engine unit is established. The parameter echo module and the health management main function module display various parameters through the parameter echo module according to the management relationship of the engine unit, perform health management through the various health management function sub-modules, and output a health management report.

[0013] Furthermore, the data governance module includes parameter parsing and data mapping functions. When the received data is in binary data format, the parameter parsing function automatically parses it and then maps it according to the data template. When the received data is a data type that does not require parsing, the data mapping function maps it to the data template to realize the conversion of data between different parameter units.

[0014] Furthermore, the data management module includes a fleet management function for managing multiple aircraft and managing the assembly relationship between engines and aircraft.

[0015] Furthermore, the parameter echo module also includes a parameter configuration management function and a user authority management function. The parameter configuration management function is used to uniformly manage the parameter thresholds of the health management platform, and the user authority management function is used to manage user information.

[0016] Furthermore, the health management function submodule includes a life and evaluation module, a parameter rapid judgment module, a maintenance decision module, a health analysis module, a fault analysis isolation module, an air path fault diagnosis module, a vibration fault diagnosis module, a system trend analysis and prediction module and a report export module. The life and evaluation module is used to manage the life of the entire engine and provide prompts for regular maintenance work; the parameter rapid judgment module is used to judge whether the data input to the platform triggers a warning; the maintenance decision module is used to associate the engine maintenance manual according to the results of the parameter rapid judgment module, and automatically display the maintenance decision of the maintenance item; the health analysis module is used to evaluate the health score of the entire machine and system according to the design criteria; the fault analysis isolation module is used to automatically isolate single data according to the engine data and the fault isolation manual; the air path fault diagnosis module is used to perform fault diagnosis on aircraft engine components; the vibration fault diagnosis module is used to perform spectral analysis on the original vibration data; the system trend analysis and prediction module is used to realize trend analysis of multiple parameters; and the report export module is used to export the results in each module.

[0017] Furthermore, the life and evaluation module, parameter rapid judgment module, maintenance decision module, health analysis module, fault analysis and isolation module, air path fault diagnosis module, vibration fault diagnosis module and system trend analysis and prediction module are parallel functional modules, which are used to run separately or simultaneously.

[0018] Furthermore, the objects involved in the system trend analysis and prediction module include the lubricating oil system, fuel system, air system, whole machine vibration, control system and whole machine performance parameters. It adopts an ID card model-based approach to modify the model according to known data to achieve system trend analysis and prediction.

[0019] Furthermore, the parameter quick judgment module has a judgment method as follows: the parameter configuration management module judges the input engine parameter data and aircraft parameter data according to the corresponding threshold value set in the maintenance manual; when the judgment result triggers the alarm item in the maintenance manual, the parameter displayed in the alarm item is displayed in bright color.

[0020] Furthermore, the health score value is evaluated in the following manner: an initial score for the health assessment is defined; after determining the system fault parameter threshold and duration, the score to be deducted is set according to the degree of impact of the fault parameter threshold and duration on the engine; after the evaluation is completed, whether the engine safety is affected is analyzed based on the deduction items, and disposal suggestions are made; if the engine safety is not affected, the score is restored to the initial score.

[0021] Another object of the present invention is to provide an aircraft engine health management method, which is implemented based on the aircraft engine health management platform and includes the following steps:

[0022] Performing aircraft and engine configuration management in the fleet management function, associating aircraft and engine information, inputting the aircraft parameter data and engine parameter data into the data management module, and entering the data management module;

[0023] The data governance module transmits the received data to the health management main function module via the data management module to carry out daily management, including: sequentially entering the health analysis module, parameter rapid judgment module, life and evaluation module, maintenance decision module, and gas path fault diagnosis module for management, and finally generating a daily management report;

[0024] Based on the daily health management report, determine whether the aircraft-engine assembly relationship is correct. If not, repeatedly enter the data management module to carry out the aircraft-engine configuration management. If correct, determine whether there is a fault. If not, determine whether trend analysis is required. If there is a fault, enter the fault analysis and isolation module, the gas path fault diagnosis module, and the vibration fault diagnosis module to perform fault diagnosis and evaluation. Based on the fault diagnosis and evaluation results, determine whether trend analysis is required.

[0025] When it is determined that trend analysis is not necessary, the health management work ends. When it is determined that trend analysis is necessary, the system trend analysis and prediction module is entered for management. After completing the system trend analysis and prediction, the health management work ends.

[0026] The beneficial effects of the present invention are:

[0027] (1) The data governance module is used to realize the conversion of data between different parameter units, and the test flight data is converted into data used by the aviation engine health management platform.

[0028] (2) Through the parallel design of each health management sub-module, the individual and simultaneous operation of each health pipeline sub-module can be realized, and the corresponding health management report can be exported with one click.

[0029] (3) Through the design of the parameter echo module, the normalized image display of the aircraft engine test and flight data curve can be realized, and the parameter deviation value can be automatically calculated.

[0030] (4) Through the design of the air path fault diagnosis module, based on the aircraft parameters and the engine onboard sensor measurement parameters, combined with the engine ID model, the fault diagnosis of aviation engine components is carried out to timely discover the safety hazards of air path components during regular maintenance work.

[0031] (5) Through the design of trend analysis and vibration fault diagnosis, trend prediction of typical objects such as lubricating oil system, fuel system, air system, whole machine vibration, control system, etc., as well as spectrum analysis of raw vibration data, can be realized. Vibration feature extraction and time domain analysis can be carried out on the raw vibration data. On this basis, fault mode diagnosis such as rotor misalignment, imbalance, bearing support, etc. can be realized, and the model can be modified according to the existing data.

[0032] (6) Through the architectural design of each module of the aviation engine health management platform, the system process, functional composition and interface, and data flow are simplified, the operation is more convenient, and it is suitable for the use scenarios of the ground subsystem. BRIEF DESCRIPTION OF THE DRAWINGS

[0033] Figure 1 This is the architecture diagram of the aircraft engine health management platform provided by the present invention;

[0034] Figure 2 This is a data governance flow chart of the aircraft engine health management platform provided by the present invention;

[0035] Figure 3 This is a life and assessment flow chart of the aircraft engine health management platform provided by the present invention;

[0036] Figure 4 This is a flow chart of the aircraft engine health management method provided by the present invention;

[0037] Figure 5 This is a flowchart of the aircraft engine health management method and aircraft engine configuration management provided by the present invention;

[0038] Figure 6 This is a daily health management flow chart of the aircraft engine health management method provided by the present invention;

[0039] Figure 7 This is a flow chart of the fault diagnosis and assessment of the aircraft engine health management method provided by the present invention;

[0040] Figure 8 This is a flow chart of the system trend analysis of the aviation engine health management method provided by the present invention;

[0041] Figure 9 This is a schematic diagram of the interface of the data management module of the aircraft engine health management platform provided by the present invention;

[0042] Figure 10 This is a schematic diagram of the aircraft engine health management platform fleet setting function interface provided by the present invention;

[0043] Figure 11 This is the engine setting interface intention of the aviation engine health management platform provided by the present invention;

[0044] Figure 12 This is the intention of displaying the single-engine parameter of the aviation engine health management platform provided by the present invention;

[0045] Figure 13 This is a schematic diagram of the dual-engine parameter display interface of the aviation engine health management platform provided by the present invention;

[0046] Figure 14 This is a schematic diagram of the life assessment interface of the aircraft engine health management platform provided by the present invention;

[0047] Figure 15 This is a schematic diagram of the parameter interpretation interface of the aircraft engine health management platform provided by the present invention;

[0048] Figure 16 This is a schematic diagram of the maintenance decision suggestion interface of the aircraft engine health management platform provided by the present invention;

[0049] Figure 17 This is a schematic diagram of the health assessment interface of the aircraft engine health management platform provided by the present invention;

[0050] Figure 18 This is a schematic diagram of the fault analysis interface of the aircraft engine health management platform provided by the present invention;

[0051] Figure 19 This is a schematic diagram of the air path fault diagnosis interface of the aircraft engine health management platform provided by the present invention;

[0052] Figure 20 This is a schematic diagram of the vibration fault diagnosis interface of the aircraft engine health management platform provided by the present invention;

[0053] Figure 21 This is a schematic diagram of the trend analysis interface of the aircraft engine health management platform provided by the present invention;

[0054] Figure 22 This is a schematic diagram of the report export interface of the aircraft engine health management platform provided by the present invention;

[0055] Figure 23 It is a schematic diagram of the parameter configuration interface of the aircraft engine health management platform provided by the present invention. DETAILED DESCRIPTION

[0056] The technical solution of the present invention is further described below, but the scope of protection claimed is not limited to the description.

[0057] An embodiment of the present invention provides an aircraft engine health management platform, the architecture of which is shown in FIG. Figure 1 Said, including:

[0058] The data management module P100 is used to receive aircraft parameter data and engine parameter data, process heterogeneous data, and realize data conversion between different parameter units; the data management process is as follows: Figure 2 shown.

[0059] The data governance module P100 includes parameter parsing and data mapping functions. When the received data is in binary data format, the parameter parsing function automatically parses it and then maps it according to the data template. When the received data is a data type that does not require parsing, the data mapping function maps it to the data template. The data mapping function has basic arithmetic operations to realize the conversion of data between different parameter units and convert the test flight data into data used by the aviation engine health management platform.

[0060] The data management module P100 is compatible with and processes historical data stored in both the latest version of digital electronic controllers and those from earlier versions. It can adaptively select communication protocols and parse and convert the controller's ".dat" data into directly readable data. To process data, first select the data path and engine number, then click Save. The program automatically merges the channel's ".dat" data in the background, parsing it to generate a CSV data file with a unified data header, data file format, and naming scheme. The notification includes the master control channel A, master control channel B, and health monitoring channel C.

[0061] The data management module P200 is used to establish a management relationship between data and engine units, and to maintain the data corresponding to the engine with the engine as the management unit. The maintenance includes operations such as adding, deleting, modifying and checking.

[0062] The data management module P200 includes a fleet management function for managing multiple aircraft and managing the assembly relationship between engines and aircraft.

[0063] In the Fleet Status Aircraft interface, click the "+" sign to add an aircraft. During the addition process, you can enter the aircraft name. After entering the aircraft, you can edit or delete the aircraft information. When editing aircraft status, you can set the aircraft number, installation status, engine number, engine status, and engine installation location. The Data Management Module P200 integrates with the fleet management function to manage engine and aircraft unit information, enabling the management of multiple aircraft and the assembly relationship between engines and aircraft. In addition to aircraft fleet configuration, you can also perform detailed configuration and operation of individual engines and engine fleets. In the Fleet Status Engine View interface, click the "+" sign to add an engine unit. During the addition process, you can enter the engine number and engine status. After entering the engine information, you can edit or delete the engine. When editing the status of a single engine, you can edit the engine number, engine status, installation status, aircraft number, installation location, and more. In addition, once the aircraft and engine information are entered, the aircraft and engine assembly relationship can be managed, which can be operated in both the aircraft view and the engine view.

[0064] The parameter echo module P300 is used to echo data parameter values, and can realize single-transmission parameter echo function and dual-transmission parameter echo function.

[0065] The parameter echo module P300 also includes a parameter configuration management function and a user authority management function. The parameter configuration management function is used to uniformly manage the parameter thresholds of the health management platform, and the user authority management function is used to manage user information.

[0066] The parameter values displayed primarily include analog and digital parameters. To achieve curve normalization, select the engine number and data package in the single-engine parameter display interface, then click "Query" to retrieve the parameter curve for the current data package. The curve is normalized by default. To analyze the raw data curve, click "Raw Data" in the upper-right corner to disable normalization. Curves can also be hidden, displayed, or edited. In the curve analysis interface, select the parameter system on the left. After selecting the parameter system, the software displays the raw parameter curves by default. To exclude or increase the display of certain parameters, click the "□" in front of the corresponding parameter name on the right side of the interface. A "·" box appears to indicate that the curve is displayed; if no "·" box appears, the curve is hidden. To add or delete curves, click "Edit" in the single-engine parameter display interface. When the engine parameter table pops up, search for and select the target parameter (the input field provides a fuzzy search function). A "√" will be placed in the "□" box before the parameter name. Click "Confirm" to successfully add the parameter.

[0067] When zooming in or out on a curve, in the parameter echo curve analysis interface, after completing the curve configuration, click the "+" sign in the upper right corner of the curve box (region zoom). Then, hold down the left mouse button to select the zoomed-in area within the curve. Once the selection is complete, release the left mouse button to complete the region zoom. Click the "-" sign (region restore) to restore the curve to its pre-zoom state. When performing curve parameter statistics, first complete the curve configuration and selection. The maximum, minimum, and average values for each parameter of the current data curve will be automatically calculated on the right side of the curve. Place the mouse over the target time point on the curve, and the software will automatically display the curve data corresponding to that time point.

[0068] To facilitate the comparison of dual-engine parameters on a single aircraft, or the comparison of dual or multiple engines on the same engine at different times, the parameter comparison function allows you to select parameter values by dragging the cursor, and automatically calculates the parameter deviation. When performing a dual-engine parameter comparison, after selecting the engine number and data package, click "Query" to retrieve the corresponding curve for the comparison data package. Select a comparison time or status point on the curve. Click and hold the "◎" icon below the curve, drag the mouse to the target point, and release the left mouse button. The software automatically calculates the corresponding curve parameters and displays them in the corresponding position on the right side. The operation is the same for the upper and lower figures. After selecting the comparison parameters, the software automatically calculates the parameter difference between the two curves. After entering the "Dual Engine Trend Comparison" module, select the comparison data type, feature status, comparison parameters, and engine number. Comparison parameters include fuel temperature, main pump inlet metering fuel temperature, fuel temperature difference, auxiliary oil line pressure, and fuel filter pressure difference. Click "Query" to start the comparison of dual trends. The comparison curve can be partially zoomed in. Click the "+" sign in the upper right corner of the curve box, hold down the left mouse button to select the zoomed area, release the left button after the selection is completed, and the area zoom is completed. Click the "-" sign to restore the curve to the state before zooming in. Click "↓" to download the parameter comparison curve in Word format.

[0069] The parameter configuration management function is to uniformly manage the thresholds involved in each functional module, support the management of parameter thresholds based on engine unit information, view and modify the parameter configuration of the trend prediction module, and display different trend prediction parameter configurations by switching the upper tabs. In addition, it can also perform configuration management such as user permission configuration, data type configuration, user interface configuration, maintenance and upgrade management, etc.

[0070] The health management main function module P400 is used to host various health management function sub-modules, organize and analyze the historical engine operating data collected by the aircraft engine health management platform, provide safe use and condition-based maintenance recommendations, and realize the daily health management function of the aircraft engine; the health management function sub-module is used to generate and export one-click reports for engine life management, health analysis, fault reasoning, parameter interpretation, maintenance decision-making, and trend prediction results; complete non-real-time offline monitoring functions such as flight history parameter display, performance trend analysis and degradation assessment, system operating parameter change warning, engine life statistical management, engine fault diagnosis, isolation, etc., and can integrate the above analysis and statistical results to provide engine safe use and condition-based maintenance recommendations.

[0071] The health management function submodule includes a life and evaluation module, a parameter rapid judgment module, a maintenance decision module, a health analysis module, a fault analysis isolation module, an air path fault diagnosis module, a vibration fault diagnosis module, a system trend analysis and prediction module and a report export module. The life and evaluation module is used to manage the life of the entire engine and provide prompts for regular maintenance work; the parameter rapid judgment module is used to judge whether the data input to the platform triggers a warning; the maintenance decision module is used to associate the engine maintenance manual according to the results of the parameter rapid judgment module and automatically display the maintenance decision of the maintenance item; the health analysis module is used to evaluate the health score of the entire machine and system according to the design criteria; the fault analysis isolation module is used to automatically isolate single data according to the engine data and the fault isolation manual; the air path fault diagnosis module is used to perform fault diagnosis on aircraft engine components; the vibration fault diagnosis module is used to perform spectral analysis on the original vibration data; the system trend analysis and prediction module is used to realize trend analysis of multiple parameters; and the report export module is used to export the results in each module.

[0072] The life and evaluation module, parameter rapid judgment module, maintenance decision module, health analysis module, fault analysis and isolation module, gas path fault diagnosis module, vibration fault diagnosis module and system trend analysis and prediction module are parallel functional modules, which are used to run separately or simultaneously.

[0073] The life and evaluation module is combined with regular maintenance work to provide reminders for regular maintenance work. It can collect statistics on the life information used on the day, export information that is consistent with the requirements of the quality control room, and submit it. In the past, manual statistics and calculations were usually required, which reduced the burden of statistics on field personnel. It also includes total life and non-warm-up takeoff life statistics functions. The life and evaluation module can set the engine life threshold. Click "Life Configuration" to configure the life thresholds of various engines according to the number of units. You can choose between "Active" and "Inactive" modes. When "Active" is selected for the life item, a progress bar can be displayed below the graph. In the life and evaluation module, whole machine life management, component life management, and accessory life management can be performed.

[0074] In addition, in the whole machine life management interface of the life and evaluation module, click "Query" to obtain the life information obtained based on this package data. The life information includes engine ground working time, ground equivalent working time, engine air working time, engine total working time, combat working time, afterburner working time, TAC cycle number, ground start number, thrust holding time, afterburner connection number and other whole machine life related items. After selecting the data, click the "Query" button to obtain the corresponding life data. At the same time, the total working time, intermediate and afterburner working time, and TAC cycle number can be displayed using a progress bar. The flow chart of the life and evaluation module is as follows Figure 3 shown.

[0075] The parameter quick interpretation module performs interpretation based on the input engine parameter data and aircraft parameter data and the corresponding thresholds set by the parameter configuration management module according to the maintenance manual. When the interpretation result triggers the alarm item in the maintenance manual, the parameter displayed in the alarm item is displayed in bright color.

[0076] The parameter rapid interpretation module automatically interprets fuel / oil system parameters, control system parameters, starting, air, and vibration parameters. After selecting the corresponding engine and file number, click "Query" to interpret the current data packet. If a parameter exceeds the alarm threshold, the system will automatically issue an alarm. This parameter interpretation function expands the depth of data analysis and resolves inconsistent interpretation issues. If a parameter interpretation anomaly is detected, the required maintenance work can be refined.

[0077] In addition, in the parameter quick judgment module, clicking "Threshold Configuration" can configure each system parameter separately, and clicking "Inspection Suggestion Configuration" can give corresponding inspection work suggestions when each parameter exceeds the threshold.

[0078] The maintenance decision module is used to associate the data judgment results of the parameter quick judgment module with the engine maintenance manual, and mainly includes basic information, maintenance decision suggestions, alarm summary, regular maintenance reminder and other functions. The basic information management function can perform query filtering, data export functions, and list the query information. The maintenance decision suggestion management function can perform query filtering, data export, parameter configuration functions, and list the query information. This function supports threshold configuration and maintenance suggestion configuration. Click the threshold configuration button to query and modify the alarm threshold values of all parameters. The page that exceeds the threshold is displayed in yellow font, and prompts information such as the time of occurrence and maintenance suggestions. Click the maintenance suggestion configuration button to query and modify the maintenance suggestions, tools, spare parts, consumables, and equipment content of all parameter judgments. The alarm summary interface can query and view the alarm data and provide judgment criteria. This module also includes regular maintenance reminders, and performs alarm maintenance queries and editing operations on data from different engines, different files, and different times.

[0079] After selecting the engine number and file number, click query to obtain maintenance decision suggestions based on the data, so as to achieve efficient maintenance according to the situation and realize automatic display of items in the maintenance manual. In addition to realizing rapid maintenance decisions, the displayed results also support the export of reports.

[0080] The health score is evaluated as follows: an initial score is defined for the health assessment, and after determining the system fault parameter threshold and duration, points are deducted based on the degree of impact of the fault parameter threshold and duration on the engine. After the assessment is completed, the deduction items are analyzed to determine whether they affect engine safety, and treatment recommendations are made. If they do not affect engine safety, the initial score is restored. Specific operations are as follows:

[0081] Through the health analysis module, the data is evaluated for health, and the health status of each engine system is displayed with explicit readings to analyze whether there are any abnormalities in each system. In the "Fault Diagnosis" module, click "System Health Assessment", then select the engine number and click "Health Assessment".

[0082] After selecting the engine number, click "Health Assessment" to assess the health of the engine lubrication system, fuel system, air system and control system. The software scores the health of each engine system. When the system is abnormal or reports a fault, the system will deduct points according to the impact of the fault on the engine. The lower the score, the more faults there are and the greater the impact on the engine. When there are items less than "100 points", click "Details and Disposal" on the health assessment interface to see the specific reasons for the deduction. Personnel can analyze whether the deduction causes affect engine safety, etc., and can make disposal suggestions in the "Disposal Suggestions". If it does not affect the engine, click "Restore Health" and the system health will be restored to "100 points".

[0083] The fault analysis and isolation module automatically isolates single data based on engine data and the fault isolation manual, performs automatic diagnosis by automatically interpreting information, and records the user's troubleshooting process in an interactive manner. The fault analysis and isolation module also includes fault information query and fault data analysis functions. Fault information query is based on common engine faults. The system performs hierarchical reasoning on the faults and ultimately gives fault analysis results based on the reasoning. When a similar fault occurs during engine operation, the fault information query module is directly entered to search for the corresponding fault information. The fault location can be quickly located based on system analysis, and staff can analyze and eliminate the fault based on the results. Fault data analysis automatically analyzes and interprets the data of a specified engine unit. The system automatically identifies the fault word and automatically infers and gives the fault location point based on the fault situation, assisting personnel to quickly locate the fault point, analyze the cause of the fault and eliminate the fault.

[0084] The gas path fault diagnosis module is used to diagnose the faults of aviation engine components by combining the aircraft parameters in the data with the parameters measured by the engine onboard sensors, and the engine ID card model, so as to timely detect the safety of gas path components during regular maintenance work. Before performing gas path fault diagnosis, the algorithm is corrected first. In the fault diagnosis module, the gas path fault diagnosis function interface is entered. Click "Algorithm Correction" in the upper right corner of the interface to enter the algorithm correction interface. Select the engine number and data status corresponding to the correction. Click "Untrained Query" to query the engine data file. Select 2 to 3 data packets with full status start-up data. After completing the selection, click "Click to Correct" to start the algorithm correction. After the correction is completed, the correction result will appear on the right. After confirming that the correction is completed, click "OK" below to complete the engine algorithm correction.

[0085] After the algorithm is corrected, you can perform one-click diagnosis on the set of engine data. After confirming that the algorithm correction is completed, return to the gas path fault diagnosis interface, select the engine number, file type and corresponding algorithm for which the algorithm correction has been completed, and then click "File Query" to filter out the set of engine data files. After selecting the target file, click "One-click Diagnosis" to start gas path fault diagnosis of the data package. The diagnosis results are on the right side of the data table. After the diagnosis is completed, you can select the corresponding different diagnostic parameters in the "Performance Parameters" column.

[0086] The vibration fault diagnosis module is used to perform spectrum analysis on the original vibration data. The original vibration data refers to high-frequency stored data. It can perform vibration feature extraction and time domain analysis on the original vibration data. On this basis, it can realize the diagnosis of fault modes such as rotor misalignment, imbalance, and bearing support. The vibration fault diagnosis module mainly includes the following functions:

[0087] a) Waterfall Chart Analysis for Whole-Machine Vibration Analysis and Diagnosis: The waterfall chart analysis function displays raw data, supports input of raw vibration data, displays related data in 3D graphs, and displays speed trends. Clicking on the waterfall chart analysis function allows you to zoom in and out, as well as zoom in and out, by scrolling the mouse wheel.

[0088] b) Feature extraction for whole machine vibration analysis and diagnosis: The feature extraction function displays data of different multiples of the frequency of characteristic parameters and data of different channels, and supports multi-axis linkage.

[0089] c) Time domain analysis for whole machine vibration analysis and diagnosis: Time domain analysis filters data from different channels and displays them as speed curves, front axial and rear vertical, and supports collection.

[0090] d) Vibration spectrum analysis for complete machine vibration analysis and diagnosis: The vibration spectrum analysis function can display raw data, show speed trend graphs, switch between speed and acceleration, and mark the top eight maximum values.

[0091] e) Vibration fault diagnosis of whole machine vibration analysis and diagnosis: Vibration fault diagnosis is a function for diagnosing faults in the original vibration data, and can perform functions such as file selection, fault diagnosis, and fault result export.

[0092] When the system trend analysis and prediction module processes multiple parameters, the states involved include starting, slow running, warm-up, maximum, parking and other processes. Before performing performance parameter trend analysis, due to the inconsistency of model parameters of different engines, the engine performance model training is first performed. Different engine numbers need to train performance models separately. Click "Performance Model Training" to enter the model training module, select the model engine number and data status, select 1-3 data packets in the data table, and click "Click to Train" to start training the model; after the model training is completed, click "Confirm" to complete the performance model training. After completing the performance model training, return to the performance trend prediction interface, select the engine number and parameters for which the performance model training has been completed, select the model version corresponding to the model, and click "Trend Prediction" to start performance trend prediction. After the performance trend prediction is completed, when adding prediction parameters, after completing the selection of added parameters, click "Query" to obtain the added parameter trend prediction curve.

[0093] The objects involved in the system trend analysis and prediction module include the lubricating oil system, fuel system, air system, whole machine vibration, control system and whole machine performance parameters. It adopts an ID card model-based approach to modify the model according to known data to achieve system trend analysis and prediction.

[0094] In addition, the system trend analysis and prediction module also includes trend analysis of the performance parameters of the entire machine, adopts an ID card model-based approach, and supports modification of the model based on known data.

[0095] On the single-engine trend prediction system interface, click "Oil / Fuel / Control / Section / Air System Parameter Trend Prediction" to enter the corresponding parameter trend prediction interface. Select the engine number, engine characteristic status, and predicted parameters on the interface. When adding an engine number or data for the first time, click "Trend Prediction". If trend prediction has been completed, simply click "Query" to obtain the trend prediction curve.

[0096] In the "Dual Engine Trend Comparison" module interface, select the comparison data type, feature status, comparison parameters, and engine number. The comparison parameters include fuel temperature, metered fuel temperature before the main pump, fuel temperature difference, auxiliary oil circuit pressure, and fuel filter pressure difference. Click "Query" to start the dual engine trend comparison. The comparison curve can be partially zoomed in. Click the "+" sign in the upper right corner of the curve box, hold down the left mouse button to select the zoomed area, release the left mouse button after selection, and the area is zoomed in. Click the "-" sign to restore the curve to its pre-zoom state. Click "↓" to download the parameter comparison curve in Word format.

[0097] The report export module is used to export the results of various health management function submodules. After the user enters the data, the user-specified module can be run with one click through this function, and the corresponding information can be exported in the form of a report. This module has a one-click image generation function for key parameters of engine health monitoring, which greatly improves the visualization effect; it has a one-click report generation and export function for health monitoring results such as engine life management, health analysis, fault reasoning, parameter interpretation, trend prediction, etc., which greatly improves the efficiency of report generation; it has the function of setting image configuration, and the default image configuration includes flight speed, Mach number, speed, cross-sectional temperature, pressure, fuel system pressure, fuel system pressure difference, oil system pressure, oil system pressure difference, oil level, oil temperature, air system pressure, vibration and other parameters; it has the function of configuring the template of the whole machine health monitoring report, and a default template is set to improve the digital level of engine health monitoring management.

[0098] The report export module allows you to configure the report image to meet the user's actual needs. Click "Add" to fill in the configured image name. After completion, click "Edit" to assign the image category name. After the image name is added, click "Edit" in the operation bar in the image column to change the image name and other information. Click "Edit" in the configuration edit bar to configure the image parameters, name the image, and configure the image coordinate parameters. The X-axis defaults to the time parameter, and the Y-axis to the engine parameter. Select the Y-axis parameter as needed and click "Confirm" to complete the image configuration.

[0099] The report export module also supports users to configure report templates according to their needs. Click "Add" in the report template configuration interface to assign a template name and report title. After completion, click "Edit" to enter the report template editing interface, and click "Add" to add report chapters. Users can configure basic information, cumulative life, maintenance decision recommendations, resumes, parameter diagnosis, and curve images for each chapter as needed. After the report template is configured, click "Preview" to preview the report template information. When adding a report chapter based on the original template, just click Edit in the original chapter. After selecting the engine number and data package, select the report template, and then click "Generate Report" to generate a health management report with one click.

[0100] When performing the daily health management, the aircraft parameter data and engine parameter data are input into the data management module P100. After processing by the data management module P200, a management relationship with the engine unit is established. The parameter echo module P300 and the health management main function module P400 display various parameters through the parameter echo module P300 according to the management relationship of the engine unit, perform health management through the various health management function sub-modules, and output a health management report.

[0101] In an embodiment of the present invention, an aircraft engine health management method is provided, which is implemented based on the aircraft engine health management platform and mainly includes aircraft engine configuration management, daily health management, fault diagnosis and evaluation, and system trend analysis processes. The aircraft engine health management method process is as follows: Figure 4 As shown, the specific steps include:

[0102] In the fleet management function, the aircraft and engine configuration management is performed, the aircraft and engine information are associated, the aircraft parameter data and engine parameter data are input into the data management module P100, and the data management module P100 is entered; the association of aircraft and engine information is the aircraft and engine information association. The aircraft and engine configuration management process is as follows Figure 5 shown.

[0103] The data management module P100 transmits the received data to the health management main function module P400 via the data management module P200 to carry out daily management, including: entering the health analysis module, parameter rapid judgment module, life and evaluation module, maintenance decision module, gas path fault diagnosis module in sequence for management, and finally generating a daily management report; the daily health management process is as follows: Figure 6 shown.

[0104] According to the daily health management report, determine whether the aircraft assembly relationship is correct. If not, repeatedly enter the data management module P200 to carry out the aircraft configuration management. If it is correct, determine whether there is a fault. If not, determine whether it is necessary to carry out trend analysis. If there is a fault, enter the fault analysis isolation module, gas path fault diagnosis module, and vibration fault diagnosis module to carry out fault diagnosis and evaluation. According to the fault diagnosis and evaluation results, determine whether it is necessary to carry out trend analysis. The fault diagnosis and evaluation process is as follows: Figure 7 As stated.

[0105] If it is determined that trend analysis is not necessary, the health management work ends. If it is determined that trend analysis is necessary, the system trend analysis and prediction module is entered for management. After the system trend analysis and prediction are completed, the health management work ends. Figure 8 shown.

[0106] The association of aircraft and engine information is the basis of engine health management. First, configure the engine information. When the aircraft is installed, configure the aircraft information and configure the aircraft-engine association. When the aircraft is not installed, the aircraft-engine association can be omitted. When the aircraft undergoes engine replacement, the aircraft-engine relationship is changed. The aircraft-engine configuration management process is as follows: Figure 5 As shown. After a successful login, the user enters the fleet status interface by default. This interface displays a preview of the fleet's aircraft and engine fault information. Click the [Update] button to update the fleet status details. Click the plus sign in the aircraft view to add a new aircraft. Click the edit button in the upper left corner of each aircraft in the aircraft view to install an engine for that aircraft. Click the delete button in the upper left corner of each aircraft in the aircraft view to delete the aircraft and unbind the installed engine. Click the plus sign in the engine view to add a new engine. Click edit in the engine view to change the engine's installation status. After the aircraft and engine information are entered, the aircraft and engine matching relationship can be managed. This operation can be performed in both the aircraft view and the engine view. In the aircraft view, click the edit interface. In the pop-up window, you can configure the left and right engines. The engine view also supports the configuration of the aircraft-engine matching relationship, and can configure aircraft sortie information for a single engine.

[0107] The daily health management process is as follows: first, check and configure the aircraft-engine relationship. When the aircraft-engine assembly information does not match the actual status, change the configuration relationship; then carry out data governance based on the downloaded data to ensure that the data entering the system is standardized and unified; subsequently carry out data management, which is to establish a link between the engine and the data; in order to complete the health assessment of the engine in the shortest possible period, carry out parameter interpretation, life assessment, maintenance decision-making and gas path fault diagnosis in sequence, and then carry out report generation, thus completing daily health status management to support the related work of report generation.

[0108] The fault diagnosis and evaluation process is as follows: when a fault occurs, the processing process is carried out, fault evaluation is carried out in sequence, and fault isolation is carried out using the fault analysis and isolation process. After the diagnosis is completed, the corresponding different diagnostic parameters can be selected in the "Performance Parameters" column. If the health level is not "100 points", the fault reasoning function can be used to reason the fault layer by layer and isolate it to the LRU. At the same time, due to the need to analyze the vibration using the original vibration data. Therefore, when it is found that the vibration is too large or there are signs of increasing vibration, vibration fault analysis is performed based on the original vibration data. Vibration fault diagnosis is a function for diagnosing faults in the original vibration data, which can perform file selection, fault diagnosis, fault result export, etc. Figure 7 shown.

[0109] The system trend analysis process is as follows: perform trend analysis on system data within a certain time range, first select the system to be analyzed, the system objects that can be analyzed include fuel system, lubrication system, air system, control system and other typical systems; secondly, determine the state to be analyzed, the state should maintain a high degree of state overlap, typical states include the starting process, slow running process, warm-up process, maximum before takeoff, parking process and other states. After clicking to open the configuration, you can modify the alarm threshold according to the selected feature state, click Export to export the currently displayed prediction results, and click Clear to clear the trend prediction results of the current engine. Click Trend Prediction, and based on the selected engine and model, you can perform trend prediction on the currently selected engine input data and model. Performance trend prediction requires model training first. Such as Figure 8 shown.

[0110] The aircraft engine health management platform data management module P200, fleet setting function, engine setting, single engine parameter echo, dual engine parameter echo, life assessment, parameter interpretation, maintenance decision suggestion, health assessment, fault analysis, gas path fault diagnosis, vibration fault diagnosis, trend analysis and report export interface are shown in the following order. Figure 9-Figure 22 shown.

[0111] The above disclosure is only a specific embodiment of the present invention, but the present invention is not limited thereto. Any changes that can be conceived by those skilled in the art should fall within the scope of protection of the present invention.

Claims

1. An aircraft engine health management platform, characterized by: include: The data management module is used to receive aircraft parameter data and engine parameter data, process heterogeneous data, and realize data conversion between different parameter units; The data management module is used to establish the management relationship between data and engine units, and maintain the data corresponding to the engine with the engine as the management unit; The parameter echo module is used to echo the data parameter values, and can realize single-shot parameter echo function and dual-shot parameter echo function; The health management main function module is used to host various health management sub-modules, organize and analyze historical engine operating data collected by the aircraft engine health management platform, provide safe operation and condition-based maintenance recommendations, and implement daily aircraft engine health management functions. The health management sub-modules are used to generate and export reports on engine life management, health analysis, fault reasoning, parameter interpretation, maintenance decision-making, and trend prediction results with one click. When performing the daily health management, the aircraft parameter data and engine parameter data are input into the data management module. After processing by the data management module, a management relationship with the engine unit is established. The parameter echo module and the health management main function module display various parameters through the parameter echo module according to the management relationship of the engine unit, perform health management through the various health management function sub-modules, and output a health management report.

2. The aircraft engine health management platform according to claim 1, characterized in that: The data governance module includes parameter parsing and data mapping functions. When the received data is in binary data format, the parameter parsing function automatically parses it and then maps it according to the data template. When the received data is a data type that does not require parsing, the data mapping function maps it to the data template to realize the conversion of data between different parameter units.

3. The aircraft engine health management platform according to claim 2, characterized in that: The data management module includes a fleet management function for managing multiple aircraft and managing the assembly relationship between engines and aircraft.

4. The aircraft engine health management platform according to claim 3, characterized in that: The parameter echo module also includes a parameter configuration management function and a user authority management function. The parameter configuration management function is used to uniformly manage the parameter thresholds of the health management platform, and the user authority management function is used to manage user information.

5. The aircraft engine health management platform according to claim 4, characterized in that: The health management function submodule includes a life and evaluation module, a parameter rapid judgment module, a maintenance decision module, a health analysis module, a fault analysis and isolation module, a gas path fault diagnosis module, a vibration fault diagnosis module, a system trend analysis and prediction module, and a report export module. The life and evaluation module is used to manage the life of the entire engine and provide prompts for regular maintenance work; the parameter rapid judgment module is used to judge whether the data input to the platform triggers a warning; the maintenance decision module is used to associate the engine maintenance manual with the results of the parameter rapid judgment module and automatically display the maintenance decision of the maintenance project; the health analysis module is used to evaluate the health score value of the entire engine and system according to the design criteria; The fault analysis and isolation module is used to automatically isolate single data based on engine data and the fault isolation manual; The air path fault diagnosis module is used to diagnose faults of aircraft engine components; the vibration fault diagnosis module is used to perform spectrum analysis on raw vibration data; the system trend analysis and prediction module is used to implement trend analysis of multiple parameters; and the report export module is used to export the results in each module.

6. The aircraft engine health management platform according to claim 5, characterized in that: The life and evaluation module, parameter rapid judgment module, maintenance decision module, health analysis module, fault analysis and isolation module, gas path fault diagnosis module, vibration fault diagnosis module and system trend analysis and prediction module are parallel functional modules, which are used to run separately or simultaneously.

7. The aircraft engine health management platform according to claim 6, characterized in that: The objects involved in the system trend analysis and prediction module include the lubricating oil system, fuel system, air system, whole machine vibration, control system and whole machine performance parameters. It adopts an ID card model-based approach to modify the model according to known data to achieve system trend analysis and prediction.

8. The aircraft engine health management platform according to claim 7, characterized in that: The parameter quick interpretation module performs interpretation based on the input engine parameter data and aircraft parameter data and the corresponding thresholds set by the parameter configuration management module according to the maintenance manual. When the interpretation result triggers the alarm item in the maintenance manual, the parameter displayed in the alarm item is displayed in bright color.

9. The aircraft engine health management platform according to claim 8, characterized in that: The health score is evaluated as follows: an initial score for the health assessment is defined; after determining the system fault parameter threshold and duration, the score to be deducted is set according to the degree of impact of the fault parameter threshold and duration on the engine; after the evaluation is completed, an analysis is made based on the deduction items to determine whether the engine safety is affected, and disposal suggestions are made; if the engine safety is not affected, the score is restored to the initial score.

10. A method for managing the health of an aircraft engine, characterized in that: The implementation of the aircraft engine health management platform according to claims 1 to 9 includes the following steps: Performing aircraft and engine configuration management in the fleet management function, associating aircraft and engine information, inputting the aircraft parameter data and engine parameter data into the data management module, and entering the data management module; The data governance module transmits the received data to the health management main function module via the data management module to carry out daily management, including: sequentially entering the health analysis module, parameter rapid judgment module, life and evaluation module, maintenance decision module, and gas path fault diagnosis module for management, and finally generating a daily management report; Based on the daily health management report, determine whether the aircraft-engine assembly relationship is correct. If not, repeatedly enter the data management module to carry out the aircraft-engine configuration management. If correct, determine whether there is a fault. If not, determine whether trend analysis is required. If there is a fault, enter the fault analysis and isolation module, the gas path fault diagnosis module, and the vibration fault diagnosis module to perform fault diagnosis and evaluation. Based on the fault diagnosis and evaluation results, determine whether trend analysis is required. When it is determined that trend analysis is not necessary, the health management work ends. When it is determined that trend analysis is necessary, the system trend analysis and prediction module is entered for management. After completing the system trend analysis and prediction, the health management work ends.

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