CN114705440A - Aeroengine fault simulation method based on data playback - Google Patents
Aeroengine fault simulation method based on data playback Download PDFInfo
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- CN114705440A CN114705440A CN202210483223.2A CN202210483223A CN114705440A CN 114705440 A CN114705440 A CN 114705440A CN 202210483223 A CN202210483223 A CN 202210483223A CN 114705440 A CN114705440 A CN 114705440A
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M15/00—Testing of engines
- G01M15/04—Testing internal-combustion engines
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- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F16/00—Information retrieval; Database structures therefor; File system structures therefor
- G06F16/20—Information retrieval; Database structures therefor; File system structures therefor of structured data, e.g. relational data
- G06F16/24—Querying
- G06F16/245—Query processing
- G06F16/2455—Query execution
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- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F16/00—Information retrieval; Database structures therefor; File system structures therefor
- G06F16/20—Information retrieval; Database structures therefor; File system structures therefor of structured data, e.g. relational data
- G06F16/25—Integrating or interfacing systems involving database management systems
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- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F16/00—Information retrieval; Database structures therefor; File system structures therefor
- G06F16/20—Information retrieval; Database structures therefor; File system structures therefor of structured data, e.g. relational data
- G06F16/25—Integrating or interfacing systems involving database management systems
- G06F16/258—Data format conversion from or to a database
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T90/00—Enabling technologies or technologies with a potential or indirect contribution to GHG emissions mitigation
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- Combustion & Propulsion (AREA)
- Testing And Monitoring For Control Systems (AREA)
Abstract
The invention discloses an aeroengine fault simulation method based on data playback, which can realize the reappearance of real test run faults of an engine and the simulation of sudden engine fault, realize the import, the edition and the calling of the real test run data through database software, input the fault data into a signal simulation case, and further access an engine controller; the method can reproduce real test run faults, and simultaneously simulate sudden engine fault by editing the test run data in the database. The fault simulation method fully utilizes the test run data, realizes the high-reliability combination of the test run data and the fault signal, has high simulation precision, and provides effective fault injection for the verification of the aircraft engine controller.
Description
Technical Field
The invention relates to the technical field of aero-engine fault simulation and simulation test verification, in particular to an aero-engine fault simulation test method.
Background
The aircraft engine may have many faults in operation, the safety and the service life of the engine are influenced by the way of processing the faults by the controller, and the fault tolerance of the controller is an important component of the design of the controller.
The fault-tolerant control is to ensure that the system can be closed and stable by a certain method when the system has faults (such as sensor faults and actuating mechanism faults), so that a controlled object can continue to work.
The research of fault-tolerant control needs a large number of faults to verify whether the fault-tolerant capability meets the control requirement, the current fault simulation is mainly electrical fault simulation and the simulation of faults of some simple sensors, test run data cannot be effectively utilized, sudden engine faults cannot be simulated, the fault types are incomplete, and the fault-tolerant capability of a controller cannot be effectively verified.
Disclosure of Invention
In view of the above, the invention provides a data playback-based aeroengine fault simulation method, and aims to provide a fault simulation method for an aeroengine controller fault tolerance test, which can reproduce real faults occurring during test run by effectively utilizing test run data, and realize the simulation of engine sudden-change faults by editing the test run data.
In order to achieve the purpose, the invention provides a data playback-based aeroengine fault simulation method, which consists of database software, data playback software and a signal simulation case, and further comprises a controller to be tested and corresponding test run data.
Preferably, the database software has the functions of trial run data format conversion and data storage;
preferably, the data playback software supports the import, the editing and the calling of the test run data stored in the database;
preferably, the signal simulation case converts fault signals generated by the test run data into real signals of an engine sensor and an actuating mechanism, so that the fault simulation accuracy is higher.
And after receiving the data of the test run test, the database software arranges the test run data in a self-defined way, divides the test run data into strips according to the data generation time, the data types and the data lengths, and then stores the strips to form a database taking time as a sequence.
The data playback software can recall and playback the data stored in the database, can query the data according to time and parameters, can set playback rate and step length by self, and can edit the retrieved data, thereby configuring sudden change faults of the engine.
The fault simulation case receives fault signals from data playback software, converts the fault signals into corresponding physical signals such as temperature, pressure, rotating speed and the like through a sensor and an execution mechanism mathematical model in the real-time calculation unit, and converts the physical signals into voltage, current, switching value and other electrical signals through a designed sensor model circuit board, so that real sensor signals are simulated, and the fault simulation accuracy is higher.
An aircraft engine fault simulation method based on data playback comprises the following steps:
step one, establishing communication among units and initializing software configuration:
starting the software, ensuring the normal connection between the software to start, initializing configuration, and preparing to import test run data.
Step two, importing test data
The engine test run data is stored in a TXT file form, the database software calls the file, the data in the file is sorted, and the data are stored in the database software in a time sequence form.
Step three, data playback, editing and retrieval
The HTTP communication between the data playback and management software and the database adopts a Microsoft HTTP component, and the HTTP communication module comprises a time query interface, a file name query interface and a parameter query interface, can call engine test data in the database from multiple directions, and has a health monitoring function of the HTTP query interface.
The data display module adopts a Teechart control to display engine test data obtained by inquiring in a database in a dynamic curve mode, and the engine test data comprises various section parameters of the engine, such as pressure, temperature, rotating speed and the like.
The UDP communication module adopts a Microsoft socket interface to check engine test data in a database, and sends the engine test data to the real-time computing unit through UDP data streams, and the period of the UDP communication module is set to be 20ms for guaranteeing the real-time performance of the data.
The test run data extracted from the database can be changed according to the fault simulation requirement.
Step four, outputting fault analog signals
The signal simulation case receives a fault simulation signal sent by the data playback software, converts the signal, simulates a real sensor signal through the signal conditioning circuit and sends the signal to the measured controller.
Compared with the prior art, the aero-engine fault simulation method based on data playback has the beneficial effects that: the fault testing method provides more real faults for the fault tolerance test of the controller, realizes the reproduction of the trial run faults, ensures that the fault tolerance verification of the controller is more reliable, realizes the simulation of the sudden change faults of the engine and enriches the fault types.
Drawings
FIG. 1 is a schematic diagram of a data playback-based aircraft engine fault simulation method and system according to an embodiment of the invention.
Fig. 2 is a data playback flow diagram according to an embodiment of the present invention.
Detailed Description
The present invention will be described in detail with reference to the specific embodiments shown in the drawings, which are not intended to limit the present invention, and structural, methodological, or functional changes made by those skilled in the art according to the specific embodiments are included in the scope of the present invention.
As shown in fig. 1, according to an embodiment of the present invention, the present invention provides a method for simulating an aircraft engine fault based on data playback, where the method includes database software, data playback software, and a signal simulation chassis, and further includes a controller to be tested and corresponding test run data.
And after receiving the data of the test run test, the database software arranges the test run data in a self-defined way, divides the test run data into strips according to the data generation time, the data types and the data lengths, and then stores the strips to form a database taking time as a sequence.
The data playback software can recall and playback the data stored in the database, can query the data according to time and parameters, can set playback rate and step length by self, and can edit the retrieved data, thereby configuring sudden change faults of the engine.
Fig. 2 is a flowchart of data playback software, which recalls and plays back data stored in the database. The software can inquire data according to time and parameters, can set playback rate and step length by itself, and additionally provides a health monitoring function for the database. When the software runs, the system carries out initialization setting, reads given input parameters, inquires corresponding data from the database through HTTP communication, caches the data, and starts the data display module and the UDP communication module to display and send the engine test data in real time.
The fault simulation case receives fault signals from data playback software, converts the fault signals into corresponding physical signals such as temperature, pressure, rotating speed and the like through a sensor and an execution mechanism mathematical model in the real-time calculation unit, and converts the physical signals into voltage, current, switching value and other electrical signals through a designed sensor model circuit board, so that real sensor signals are simulated, and the fault simulation accuracy is higher.
Claims (4)
1. The method is characterized by comprising database software, data playback software and a signal simulation case, and further comprising a controller to be tested and corresponding test run data.
The database software has the functions of trial run data format conversion and data storage;
the data playback software supports the import, the editing and the calling of test run data stored in a database;
the signal simulation case converts fault signals generated by test run data into real signals of an engine sensor and an actuating mechanism, so that the fault simulation accuracy is higher.
2. The method for simulating the faults of the aero-engine based on the data playback as claimed in claim 1, wherein the database software receives data of the test run, arranges the test run data in a self-defined mode, divides the test run data into strips according to data generation time, data types and data lengths, and then stores the strips to form a database with time as a sequence.
3. The method for simulating the faults of the aero-engine based on the data playback as claimed in claim 1, wherein the data playback software can recall and playback the data stored in the database, can query the data according to time and parameters, can set the playback speed and step length by itself, and can edit the retrieved data so as to configure the sudden engine fault.
4. The method for simulating the faults of the aero-engine based on the data playback as claimed in claim 1, wherein the fault simulation chassis receives fault signals from data playback software, the fault signals are converted into corresponding physical signals such as temperature, pressure, rotating speed and the like through a sensor and actuator mathematical model in the real-time computing unit, and the physical signals are converted into electric signals such as voltage, current, switching value and the like through a designed sensor model circuit board, so that real sensor signals are simulated, and the fault simulation accuracy is higher.
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| CN202210483223.2A CN114705440A (en) | 2022-05-05 | 2022-05-05 | Aeroengine fault simulation method based on data playback |
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| CN202210483223.2A CN114705440A (en) | 2022-05-05 | 2022-05-05 | Aeroengine fault simulation method based on data playback |
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Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102855349A (en) * | 2012-08-06 | 2013-01-02 | 南京航空航天大学 | Quick prototype design method and platform for gas path fault diagnosis for aeroengine |
| CN102980771A (en) * | 2012-12-04 | 2013-03-20 | 南京航空航天大学 | Portable failure detection system and method for aero-engine gas path component |
| CN111610027A (en) * | 2019-02-22 | 2020-09-01 | 中国航发商用航空发动机有限责任公司 | Aircraft engine fault simulation system and simulation method |
| CN113358366A (en) * | 2021-06-07 | 2021-09-07 | 南京航空航天大学 | Aircraft engine fault simulation system and control method |
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2022
- 2022-05-05 CN CN202210483223.2A patent/CN114705440A/en active Pending
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102855349A (en) * | 2012-08-06 | 2013-01-02 | 南京航空航天大学 | Quick prototype design method and platform for gas path fault diagnosis for aeroengine |
| CN102980771A (en) * | 2012-12-04 | 2013-03-20 | 南京航空航天大学 | Portable failure detection system and method for aero-engine gas path component |
| CN111610027A (en) * | 2019-02-22 | 2020-09-01 | 中国航发商用航空发动机有限责任公司 | Aircraft engine fault simulation system and simulation method |
| CN113358366A (en) * | 2021-06-07 | 2021-09-07 | 南京航空航天大学 | Aircraft engine fault simulation system and control method |
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