CN115326400B - Fault diagnosis method of aircraft engine surge detection system and electronic equipment - Google Patents
Fault diagnosis method of aircraft engine surge detection system and electronic equipment Download PDFInfo
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- 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
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01R—MEASURING ELECTRIC VARIABLES; MEASURING MAGNETIC VARIABLES
- G01R31/00—Arrangements for testing electric properties; Arrangements for locating electric faults; Arrangements for electrical testing characterised by what is being tested not provided for elsewhere
- G01R31/40—Testing power supplies
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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
- Y02T10/00—Road transport of goods or passengers
- Y02T10/10—Internal combustion engine [ICE] based vehicles
- Y02T10/40—Engine management systems
Abstract
The invention provides a fault diagnosis method and electronic equipment of an aircraft engine surge detection system, which comprises the following steps: step 1, determining fault states of a power supply system and a surge detection system; step 2, collecting the internal fault states of the power supply system and the surge detection system in real time, and storing the corresponding fault states in a fault code form in real time when the power supply system and the surge detection system have the fault states; step 3, connecting the ground fault diagnosis system with a data communication interface to realize the communication function of the ground fault diagnosis system and the airborne surge detection system; step 4, reading the fault code stored in the in-machine fault diagnosis system, positioning the fault states of the power supply system and the surge detection system and displaying the fault states; step 5, positioning and displaying the fault state of the sensor; and 6, judging the health condition of the airborne surge detection system through a fault evaluation module in the ground fault diagnosis system.
Description
Technical Field
The specification relates to the technical field of aero-engines, in particular to a fault diagnosis method of an aero-engine surge detection system and electronic equipment.
Background
The aerodynamic stability of an aircraft engine is lost due to strong interference of external factors during operation, once the engine is unstable in flow and cannot exit in time, the engine is suddenly flamed to cause rapid deterioration of the performance of the engine, and the blade of a gas compressor is broken to cause damage to the whole engine and cause serious accidents. An airborne surge detection system is a device equipped with an engine for detecting the surge state of the engine, which can effectively identify the surge state and issue an alarm signal. Sensors and electronic components related in the device are numerous, the sensors and the electronic components work for a long time under the complex environment of the aircraft engine, faults are inevitably generated, and technicians can be connected with an airborne surge detection system through a communication interface through a ground detection system, so that the faults of the airborne surge detection system can be diagnosed and analyzed.
Disclosure of Invention
In view of this, embodiments of the present disclosure provide a fault diagnosis method for an aircraft engine surge detection system and an electronic device, so as to implement health management for the aircraft engine on-board surge detection system.
The specific scheme of the invention is as follows: a fault diagnosis method of an aircraft engine surge detection system comprises the following steps:
step 1, determining fault states of a power supply system and a surge detection system;
step 2, acquiring the internal fault states of the power supply system and the surge detection system in real time through a microprocessor module in the internal fault diagnosis system, and storing the corresponding fault states in real time in a fault code form through a data storage module in the internal fault diagnosis system when the power supply system and the surge detection system have the fault states;
step 4, reading fault codes stored in the in-machine fault diagnosis system through the ground fault diagnosis system, positioning fault states of the power supply system and the surge detection system, and displaying the fault states;
and 6, judging the health condition of the airborne surge detection system through a fault evaluation module in the ground fault diagnosis system.
Further, step 1 comprises:
step 1.1, comparing consistency of output voltage values of a plurality of channel power supply conversion modules in a power supply system with a design voltage value, if the output voltage values in the plurality of channel power supply conversion modules are consistent with the design value, the plurality of channel power supply conversion modules are normal, and setting output signals representing fault states as low-level signals;
if the output voltage value in any power supply conversion module is not consistent with the design value, the power supply conversion module has a fault, and the output signal representing the fault state is set as a high-level signal.
Further, step 1 further comprises:
and 1.2, performing logic and operation on output signals of the plurality of channel power supply conversion modules representing fault states by a fault signal processing module, and setting fault characteristic signals output by the fault signal processing module in the power supply system as high-level signals when any one of the channel power supply conversion modules fails.
Further, step 1 further comprises:
step 1.3, when a plurality of channel identification modules in the surge detection system detect that signals collected by a plurality of corresponding channel sensors have the characteristic that an engine generates surge, the plurality of channel identification modules are normal, and at the moment, the plurality of channel identification modules all output a pulse signal lasting for a set time;
when any channel identification module in the surge detection system does not detect that the signal collected by the corresponding sensor has the characteristic that the engine has surge, the channel identification module has a fault, and at the moment, the channel identification module outputs a signal keeping a low level.
Further, step 1 further comprises:
step 1.4, when more than two channels in a plurality of channel identification modules in the surge detection system are normal, a pulse signal which lasts the same set time as the identification modules is generated by a judgment module, and then the pulse signal is converted into a switching value signal of set voltage by a switching value output module, if the switching value is consistent with the set voltage value, the switching value output module is normal;
if the output of the switching value output module is continuously low level after the pulse signal which is generated by the judgment module and has the same duration with the identification module and has the set time passes through the switching value output module, the switching value output module fails. Further, step 2 comprises:
and 2.1, acquiring the state of the output signal of the fault signal processing module in the power module in real time by a microprocessor module in the internal fault diagnosis system, and recording a corresponding fault code in the internal fault diagnosis system if the power module has a fault.
Further, step 2 further comprises:
and 2.2, acquiring the states of output signals of a plurality of channel identification modules in the surge detection system in real time by a microprocessor module in the internal fault diagnosis system, and recording a corresponding fault code in the internal fault diagnosis system if any channel identification module in the surge detection system has a fault.
Further, step 2 further comprises:
and 2.3, when the set voltage value generated by the switching value output module in the surge detection system is larger than the voltage range which can be acquired by the microprocessor in the built-in fault diagnosis system, converting the specific voltage value generated by the switching value module into a voltage value suitable for being acquired by the microprocessor through the level conversion module.
Further, step 2 further comprises:
and 2.4, acquiring the switching value signal state converted in the step 2.3 in the surge detection system in real time by a microprocessor module in the internal fault diagnosis system, and recording a corresponding fault code in the internal fault diagnosis system if the switching value output module in the surge detection system has a fault.
Further, step 5 comprises:
step 5.1, detecting the fault state of the sensor before the engine is equipped or in the ground maintenance state, detecting the numerical values acquired by the plurality of channel sensors through a data online monitoring module in the ground fault diagnosis system, comparing the numerical values with the numerical values in the standard state, and judging that the plurality of channel sensors are normal if the numerical values acquired by the plurality of channel sensors are consistent with the numerical values in the standard state;
and when the value acquired by any channel sensor is inconsistent with the value in the standard state, judging that the channel sensor is in fault.
Further, step 5 comprises:
step 5.2, detecting the fault state of the sensor when the engine is in the running state, traversing the numerical values acquired by the sensor in the running process of the engine through a data playback module in the ground fault diagnosis system, comparing the numerical values with the numerical values in the standard state, and judging that the plurality of channel sensors are normal if the numerical values acquired by the plurality of channel sensors are consistent with the numerical values in the corresponding states;
and when the value acquired by any channel sensor is inconsistent with the value in the corresponding state, judging that the channel sensor is in fault.
The present invention also provides an electronic device, comprising:
at least one processor; and the number of the first and second groups,
a memory communicatively coupled to the at least one processor; wherein the content of the first and second substances,
the memory stores instructions executable by the at least one processor to enable the at least one processor to perform the method for fault diagnosis of an aircraft engine surge detection system described above.
Compared with the prior art, the beneficial effects that can be achieved by the at least one technical scheme adopted by the embodiment of the specification at least comprise: according to the invention, through fault diagnosis of different levels in the airborne surge detection system, effective identification of the health condition of the airborne surge detection system under the high-temperature and complex electromagnetic interference environment of the aircraft engine can be met, and the real-time performance and convenience of fault diagnosis of the airborne surge detection system are improved.
Drawings
In order to more clearly illustrate the technical solutions of the embodiments of the present application, the drawings needed to be used in the embodiments will be briefly described below, and it is obvious that the drawings in the following description are only some embodiments of the present application, and it is obvious for those skilled in the art to obtain other drawings based on these drawings without creative efforts.
FIG. 1 is a schematic flow diagram of an embodiment of the present invention;
fig. 2 is a schematic structural diagram of an embodiment of the present invention.
Detailed Description
The embodiments of the present application will be described in detail below with reference to the accompanying drawings.
The following description of the embodiments of the present application is provided by way of specific examples, and other advantages and effects of the present application will be readily apparent to those skilled in the art from the disclosure herein. It is to be understood that the embodiments described are only a few embodiments of the present application and not all embodiments. The present application is capable of other and different embodiments and its several details are capable of modifications and/or changes in various respects, all without departing from the spirit of the present application. It should be noted that the features in the following embodiments and examples may be combined with each other without conflict. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present application.
As shown in fig. 1, an embodiment of the present invention provides a fault diagnosis method for an aircraft engine surge detection system, including the following steps:
step 1, determining fault states of a power supply system and a surge detection system;
step 2, acquiring the internal fault states of the power supply system and the surge detection system in real time through a microprocessor module in the internal fault diagnosis system, and storing the corresponding fault states in real time in a fault code form through a data storage module in the internal fault diagnosis system when the power supply system and the surge detection system have the fault states;
step 4, reading fault codes stored in the in-machine fault diagnosis system through the ground fault diagnosis system, positioning fault states of the power supply system and the surge detection system, and displaying the fault states;
and 6, judging the health condition of the airborne surge detection system through a fault evaluation module in the ground fault diagnosis system.
According to the embodiment of the invention, through fault diagnosis of different levels in the airborne surge detection system, effective identification of the health condition of the airborne surge detection system under the complex environment of the aircraft engine can be met, and the real-time performance and convenience of fault diagnosis of the airborne surge detection system are improved.
Specifically, step 1 comprises:
step 1.1, comparing consistency of output voltage values of N channel power supply conversion modules in a power supply system with a design voltage value, if the output voltage values in the N channel power supply conversion modules are consistent with the design value, enabling the N channel power supply conversion modules to be normal, and setting output signals representing fault states as low-level signals;
if the output voltage value in any power conversion module is not consistent with the design value, the power conversion module has a fault, and the output signal representing the fault state is set as a high-level signal.
And 1.2, performing logic and operation on output signals of the N channel power supply conversion modules representing fault states by a fault signal processing module, and setting fault characteristic signals output by the fault signal processing module in the power supply system as high-level signals when any one of the channel power supply conversion modules fails.
Step 1.3, when N channel identification modules in the surge detection system detect that signals collected by corresponding N channel sensors have the characteristic that an engine generates surge, the N channel identification modules are normal, and at the moment, the N channel identification modules all output a pulse signal lasting for a set time;
when any channel identification module in the surge detection system does not detect that the signal collected by the corresponding sensor has the characteristic that the engine has surge, the channel identification module has a fault, and at the moment, the channel identification module outputs a signal keeping a low level.
Step 1.4, when more than two channels in N channel identification modules in the surge detection system are normal, a judgment module generates a pulse signal which lasts the same set time as the identification module, a switching value output module converts the pulse signal into a switching value signal of set voltage, and if the switching value is consistent with the set voltage value, the switching value output module is normal;
if the output of the switching value output module is continuously low level after the pulse signal which is generated by the judgment module and has the same duration with the identification module and has the set time passes through the switching value output module, the switching value output module fails.
Preferably, step two includes:
and 2.1, acquiring the state of the output signal of the fault signal processing module in the power module in real time by a microprocessor module in the internal fault diagnosis system, and recording a corresponding fault code in the internal fault diagnosis system if the power module has a fault. Otherwise, not recording;
and 2.2, acquiring the states of output signals of the N channel identification modules in the surge detection system in real time by a microprocessor module in the internal fault diagnosis system, and recording a corresponding fault code in the internal fault diagnosis system if any channel identification module in the surge detection system has a fault. Otherwise, not recording;
step 2.3, when the set voltage value generated by a switching value output module in the surge detection system is larger than the voltage range which can be acquired by a microprocessor in the built-in fault diagnosis system, a level conversion module is required to be introduced, and the specific voltage value generated by the switching value module is converted into a voltage value which is suitable for being acquired by the microprocessor;
and 2.4, acquiring the switching value signal state converted in the step 2.3 in the surge detection system in real time by a microprocessor module in the internal fault diagnosis system, and recording a corresponding fault code in the internal fault diagnosis system if the switching value output module in the surge detection system has a fault. Otherwise, not recording;
and 5.1, detecting the fault state of the sensor before the engine is equipped or in the ground maintenance state, detecting the numerical values acquired by the N channel sensors through a data online monitoring module in the ground fault diagnosis system, comparing the numerical values with the numerical values in the standard state, and if the numerical values acquired by the N channel sensors are consistent with the numerical values in the standard state, enabling the N sensors to be normal. And otherwise, if the value acquired by any channel sensor is inconsistent with the value in the standard state, the channel sensor fails.
And 5.2, detecting the fault state of the sensor when the engine is in the running state, traversing the numerical values acquired by the sensor in the running process of the engine through a data playback module in the ground fault diagnosis system, comparing the numerical values with the numerical values in the standard state, and if the numerical values acquired by the N channel sensors are consistent with the numerical values in the standard state, enabling the N sensors to be normal. On the contrary, if the value acquired by any channel sensor is inconsistent with the value in the standard state, the channel sensor fails.
Wherein the onboard surge detection system cannot continue to be equipped for use with the engine if one of the following conditions is met:
1. a power system failure;
2. the number of faults of the N channel identification modules is not less than 2;
3. a switching value module failure;
4. the number of faults of the N channel sensors is not less than 2;
as shown in fig. 2, an embodiment of the present invention further provides an electronic device, where the electronic device includes: at least one processor; and a memory communicatively coupled to the at least one processor; wherein the memory stores instructions executable by the at least one processor to enable the at least one processor to perform the method of fault diagnosis of an aircraft engine surge detection system described above.
The electronic equipment further comprises an N-channel sensor, a power supply system, a surge detection system and an in-machine fault diagnosis system.
Wherein N is not less than 3.
The power supply system comprises an input power supply interface, an N (N & ltn & gt 1) channel power supply conversion module, a fault signal processing module, a fault diagnosis interface and an output power supply interface, wherein the N channel power supply conversion module is connected with the input power supply interface and the output power supply interface, and the fault signal processing module is connected with the N channel power supply conversion module and the fault diagnosis interface.
The surge detection system comprises an input power supply interface, an N (N & gt 3) channel sensor input interface, an N (N & gt 3) channel identification module, a judgment module, a switching value output module, an N (N & gt 3) channel data communication module, an N channel sensor output interface, a data communication interface, an alarm signal interface and a fault diagnosis interface, wherein the N channel identification module is respectively connected with the N channel sensor input interface, the input power supply interface, the judgment module, the N channel data communication module, the N channel sensor output interface and the fault diagnosis interface, the judgment module is also respectively connected with the input power supply module and the switching value output module, the switching value output module is also connected with the input power supply module, the alarm signal interface and the fault diagnosis interface, and the N channel data communication module is also connected with the input power supply interface and the data communication interface.
The built-in fault diagnosis system is provided with an input power interface, a data communication module, a data storage module, a microprocessor module, a level conversion module, a fault diagnosis interface and a data communication interface, wherein the microprocessor module is connected with the input power interface, the data communication module, the data storage module, the level conversion module and the fault diagnosis interface, the input power interface is also connected with the data communication module, the data storage module and the level conversion module, the data communication module is also connected with the data communication interface, and the level conversion module is also connected with the fault diagnosis interface.
The ground fault diagnosis system comprises a data online monitoring module, a data playback module, a fault evaluation module, a data communication module and a data communication interface, wherein the data communication module of the ground fault diagnosis system is connected with the data communication interface, the data online monitoring module, the data playback module and the fault evaluation module, and the communication with the built-in fault diagnosis system is realized through the data communication interface.
The input power interface of the power supply system is connected with the power supply of the engine, and the output power interface is respectively connected with the input power interface of the surge detection system and the input power interface of the built-in fault diagnosis system.
The input power interface of the power supply system is connected with the power supply of the engine, and the output power interface is respectively connected with the input power interface of the surge detection system and the input power interface of the built-in fault diagnosis system.
And the fault diagnosis interface of the built-in fault diagnosis system is respectively connected with the fault diagnosis interface of the power supply system, the fault diagnosis interface of the surge detection system and the alarm signal interface.
The ground fault diagnosis system is a computer.
In a preferred embodiment of the present invention, N is selected to be 3 for the N-channel sensor. And N is selected to be 2 by an N-channel power supply conversion module in the power supply system. N is selected as 3 by an N-channel sensor input interface, N is selected as 3 by an N-channel identification module, N is selected as 3 by an N-channel data communication module, and N is selected as 3 by an N-channel sensor output interface in the surge detection system. And the ground fault diagnosis system is connected with the airborne surge detection system through an RS422 bus.
The above description is only for the specific embodiments of the present application, but the scope of the present application is not limited thereto, and any changes or substitutions that can be easily conceived by those skilled in the art within the technical scope of the present application should be covered within the scope of the present application. Therefore, the protection scope of the present application shall be subject to the protection scope of the claims.
Claims (8)
1. A fault diagnosis method of an aircraft engine surge detection system is characterized by comprising the following steps:
step 1, determining fault states of a power supply system and a surge detection system;
step 2, acquiring the internal fault states of the power supply system and the surge detection system in real time through a microprocessor module in the internal fault diagnosis system, and storing the corresponding fault states in real time in a fault code form through a data storage module in the internal fault diagnosis system when the power supply system and the surge detection system have the fault states;
step 3, connecting a data communication interface of the ground fault diagnosis system with a data communication interface of a surge detection system and an in-machine fault diagnosis system to realize the communication function of the ground fault diagnosis system and the in-machine surge detection system;
step 4, reading fault codes stored in the in-machine fault diagnosis system through the ground fault diagnosis system, positioning fault states of the power supply system and the surge detection system, and displaying the fault states;
step 5, positioning and displaying the fault state of the sensor through a data online monitoring module and a data playback module in the ground fault diagnosis system;
step 6, judging the health condition of the airborne surge detection system through a fault evaluation module in the ground fault diagnosis system;
wherein the step 1 comprises:
step 1.1, comparing consistency of output voltage values of a plurality of channel power supply conversion modules in a power supply system with a design voltage value, if the output voltage values in the plurality of channel power supply conversion modules are consistent with the design value, the plurality of channel power supply conversion modules are normal, and setting output signals representing fault states as low-level signals;
if the output voltage value in any power supply conversion module is not consistent with the design value, the power supply conversion module has a fault, and an output signal representing the fault state is set as a high-level signal;
step 1.2, carrying out logic and operation on output signals of a plurality of channel power supply conversion modules representing fault states by a fault signal processing module, and setting fault characteristic signals output by the fault signal processing module in a power supply system as high-level signals when any one channel power supply conversion module has a fault;
step 1.3, when a plurality of channel identification modules in the surge detection system detect that signals collected by a plurality of corresponding channel sensors have the characteristic that an engine generates surge, the plurality of channel identification modules are normal, and at the moment, the plurality of channel identification modules all output a pulse signal lasting for a set time;
when any channel identification module in the surge detection system does not detect that the signal collected by the corresponding sensor has the characteristic that the engine surges, the channel identification module has a fault, and at the moment, the channel identification module outputs a signal keeping a low level;
step 1.4, when more than two channels in a plurality of channel identification modules in the surge detection system are normal, a judgment module generates a pulse signal which lasts for the same set time as the identification modules, a switching value output module converts the pulse signal into a switching value signal of set voltage, and if the switching value is consistent with the set voltage value, the switching value output module is normal;
if the output of the switching value output module is continuously low level after the pulse signal which is generated by the judgment module and has the same set time with the identification module continuously passes through the switching value output module, the switching value output module is in failure.
2. The method of diagnosing a fault in an aircraft engine surge detection system according to claim 1, wherein said step 2 comprises:
and 2.1, acquiring the state of the output signal of the fault signal processing module in the power module in real time by a microprocessor module in the internal fault diagnosis system, and recording a corresponding fault code in the internal fault diagnosis system if the power module has a fault.
3. The method of diagnosing a fault in an aircraft engine surge detection system according to claim 2, wherein said step 2 further comprises:
and 2.2, acquiring the states of output signals of a plurality of channel identification modules in the surge detection system in real time by a microprocessor module in the internal fault diagnosis system, and recording a corresponding fault code in the internal fault diagnosis system if any channel identification module in the surge detection system has a fault.
4. The method of diagnosing faults in an aircraft engine surge detection system according to claim 3, wherein said step 2 further comprises:
and 2.3, when the set voltage value generated by the switching value output module in the surge detection system is larger than the voltage range which can be acquired by the microprocessor in the built-in fault diagnosis system, converting the specific voltage value generated by the switching value module into a voltage value suitable for being acquired by the microprocessor through the level conversion module.
5. The method of diagnosing a fault in an aircraft engine surge detection system of claim 4, wherein said step 2 further comprises:
and 2.4, a microprocessor module in the internal fault diagnosis system acquires the switching value signal state converted in the step 2.3 in the surge detection system in real time, and if the switching value output module in the surge detection system has a fault, a corresponding fault code is recorded in the internal fault diagnosis system.
6. The method of diagnosing faults in an aircraft engine surge detection system according to claim 5, wherein said step 5 includes:
step 5.1, detecting the fault state of the sensor before the engine is equipped or in the ground maintenance state, detecting the numerical values acquired by the plurality of channel sensors through a data online monitoring module in the ground fault diagnosis system, comparing the numerical values with the numerical values in the standard state, and judging that the plurality of channel sensors are normal if the numerical values acquired by the plurality of channel sensors are consistent with the numerical values in the standard state;
and when the value acquired by any channel sensor is inconsistent with the value in the standard state, judging that the channel sensor has a fault.
7. The method of diagnosing a fault in an aircraft engine surge detection system of claim 6, wherein said step 5 includes:
step 5.2, detecting the fault state of the sensor when the engine is in the running state, traversing the numerical values acquired by the sensor in the running process of the engine through a data playback module in the ground fault diagnosis system, comparing the numerical values with the numerical values in the standard state, and judging that the plurality of channel sensors are normal if the numerical values acquired by the plurality of channel sensors are consistent with the numerical values in the corresponding state;
and when the value acquired by any channel sensor is inconsistent with the value in the corresponding state, judging that the channel sensor has a fault.
8. An electronic device, characterized in that the electronic device comprises:
at least one processor; and the number of the first and second groups,
a memory communicatively coupled to the at least one processor; wherein the content of the first and second substances,
the memory stores instructions executable by the at least one processor to enable the at least one processor to perform a method of fault diagnosis for an aircraft engine surge detection system according to any of claims 1 to 7.
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