CN109359869A - Aero-engine health control method, apparatus and system - Google Patents
Aero-engine health control method, apparatus and system Download PDFInfo
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Abstract
This application discloses a kind of aero-engine health control methods, including;Obtain engine related data relevant to aero-engine to be managed;Read engine related data;Extract the first valid data compatible with the state to be predicted of engine and second valid data compatible with failure to be predicted;Signature analysis is carried out to the first valid data and the second valid data respectively;Using the first valid data after signature analysis as the theory input of the state to be predicted of engine, the judgement of the state to be predicted of complete coupled engines, and using the second valid data after signature analysis as the theory input of the failure to be predicted of engine, the judgement of the failure to be predicted of complete coupled engines.Disclosed herein as well is aero-engine health controller and systems.Aero-engine health control method, the apparatus and system of the application can analyze engine related data, determine the predetermined state and failure of engine, to realize to engine health control.
Description
Technical field
The application belongs to aero-engine health control technical field, in particular to a kind of aero-engine health control side
Method, apparatus and system.
Background technique
Aero-engine health control carries out health status detection primarily directed to certain type or the aero-engine of certain series
And fault alarm, it is the action that aero-engine working service aspect is integral now.
In addition, aero-engine is that the important component of unmanned vehicle and the important of flight control system are controlled
Object, its stability and reliability are to influence the importance of flight safety, therefore, to the real-time monitoring of its health status and
Periodical evaluation is the effective way that unmanned vehicle safety is promoted.
Summary of the invention
The purpose of the application is above-mentioned to solve there is provided a kind of aero-engine health control method, apparatus and system
The problem of at least one aspect.
In a first aspect, this application discloses a kind of aero-engine health control methods, including;
Data acquisition step: engine related data relevant to aero-engine to be managed is obtained;
Data reading step: the engine related data is read;
Data extraction step: according to the state to be predicted of the engine and the data category demand of failure to be predicted,
Extracted from the engine related data compatible with the state to be predicted of the engine the first valid data and with
Compatible second valid data of the failure to be predicted;
Data analysis step: using threshold threshold as foundation, respectively to first valid data and the second valid data into
Row signature analysis;
Determination step: the theory using the first valid data after signature analysis as the state to be predicted of the engine is defeated
Enter, completes the judgement to the state to be predicted of the engine, and
Using the second valid data after signature analysis as the theory input of the failure to be predicted of the engine, completion pair
The judgement of the failure to be predicted of the engine.
According at least one embodiment of the application, first valid data include the delivery temperature of cylinder
With exhaust total temperature and engine speed, the state to be predicted of the engine is engine operating condition, the engine operating condition packet
Include operating status and flameout state;
Second valid data include the exhaust of engine fuel pressure, the temperature of cylinder, cylinder
Temperature and exhaust total temperature, the failure to be predicted of the engine includes oil pressure faults, cylinder reviewing knowledge already acquired barrier and delivery temperature failure.
According at least one embodiment of the application, the data acquisition step further include: obtain and airborne equipment phase
The equipment-related data of pass;
The data reading step further include: read the equipment-related data;
The data extraction step further include: according to the data category demand of the state to be predicted of the airborne equipment, from
Third valid data compatible with the state to be predicted of the airborne equipment are extracted in the equipment-related data;
The data analysis step further include: using threshold threshold as foundation, feature point is carried out to the third valid data
Analysis;
The determination step further include: using the third valid data after signature analysis as the to be predicted of the airborne equipment
The theoretical input of state, completes the judgement to the predicted state of the airborne equipment.
According at least one embodiment of the application, the third valid data include relay actuation in airborne equipment
Number and FLASH read and write number, and the relevant state to be predicted of the airborne equipment is airborne equipment operating condition, the airborne equipment
Operating condition include it is excellent, good, in, difference and five kinds of states of excess.
According at least one embodiment of the application, the aero-engine health control method further include:
Storing step: by the judgement result of the state to be predicted of the engine and the failure to be predicted of the engine
Determine that result is stored;Or the judgement result of the predicted state of the airborne equipment is stored;
Data sharing step: by the judgement result of the state to be predicted of the engine of storage and the engine to
The judgement result of prediction failure is sent;
Ground test step: the judgement result of the state to be predicted for the engine based on the received and described start
The judgement of the failure to be predicted of machine as a result, to engine carry out ground test and or regular inspection safeguard.
Second aspect, this application discloses a kind of aero-engine health controllers, comprising:
Data acquisition module: for obtaining engine related data relevant to aero-engine to be managed;
Data read module: for reading the engine related data;
Data extraction module: for according to the state to be predicted of the engine and the data category need of failure to be predicted
Ask, extracted from the engine related data compatible with the state to be predicted of the engine the first valid data and
Second valid data compatible with the failure to be predicted;
Data analysis module: it is used for using threshold threshold as foundation, respectively to first valid data and the second significant figure
According to progress signature analysis;
Determination module: the reason for the state to be predicted using the first valid data after signature analysis as the engine
By input, the judgement to the state to be predicted of the engine is completed, and
Using the second valid data after signature analysis as the theory input of the failure to be predicted of the engine, completion pair
The judgement of the failure to be predicted of the engine.
According at least one embodiment of the application, first valid data include the delivery temperature of cylinder
With exhaust total temperature and engine speed, the state to be predicted of the engine is engine operating condition, the engine operating condition packet
Include operating status and flameout state;
Second valid data include the exhaust of engine fuel pressure, the temperature of cylinder, cylinder
Temperature and exhaust total temperature, the failure to be predicted of the engine includes oil pressure faults, cylinder reviewing knowledge already acquired barrier and delivery temperature failure.
According at least one embodiment of the application, the data acquisition module is also used to: being obtained and airborne equipment phase
The equipment-related data of pass;
The data read module is also used to: reading the equipment-related data;
The data extraction module is also used to: according to the data category demand of the state to be predicted of the airborne equipment, from
Third valid data compatible with the state to be predicted of the airborne equipment are extracted in the equipment-related data;
The data analysis module is also used to: using threshold threshold as foundation, carrying out feature point to the third valid data
Analysis;
The determination module is also used to: using the third valid data after signature analysis as the to be predicted of the airborne equipment
The theoretical input of state, completes the judgement to the predicted state of the airborne equipment.
According at least one embodiment of the application, the third valid data include relay actuation in airborne equipment
Number and FLASH read and write number, and the relevant state to be predicted of the airborne equipment is airborne equipment operating condition, the airborne equipment
Operating condition include it is excellent, good, in, difference and five kinds of states of excess.
According at least one embodiment of the application, the aero-engine health controller further include:
Memory module: for by the to be predicted of the judgement result of the state to be predicted of the engine and the engine therefore
The judgement result of barrier is stored;Or the judgement result of the predicted state of the airborne equipment is stored;
Data sharing step: the judgement result of the state to be predicted of the engine for that will store and the engine
The judgement result of failure to be predicted sent;
Ground test module: the judgement result of the state to be predicted for the engine based on the received and described start
The judgement of the failure to be predicted of machine as a result, to engine carry out ground test and or regular inspection safeguard.
The third aspect, this application discloses a kind of aero-engine is health management system arranged, comprising:
Processor, memory and it is stored in the computer journey that can be run on the memory and on the processor
Sequence, the processor execute the computer program for realizing aero-engine health control side described in any of the above embodiments
Method;
Sensor, for obtain relevant to aero-engine to be managed engine related data and or and airborne equipment
Relevant equipment-related data;
Ground checkout equipment, the judgement result of the state to be predicted for the engine based on the received and described starts
The judgement of the failure to be predicted of machine as a result, to engine carry out ground test and or regular inspection safeguard.
According at least one embodiment of the application, the ground checkout equipment is portable intelligent wireless terminal, is led to
Cross sentencing for the judgement result of the state to be predicted of the received engine of wireless mode and the failure to be predicted of the engine
Determine result.
According at least one embodiment of the application, the aero-engine is health management system arranged further include:
Test flight equipment executes the computer program for controlling the processor for realizing any of the above-described institute
The aero-engine health control method stated.
At least there are following advantageous effects in the application:
Aero-engine health control method, the apparatus and system of the application, can be to the engine related data of reading
It is analyzed, determines the predetermined state and failure of engine, to realize to engine health control.
Detailed description of the invention
Fig. 1 is the general flow chart of the application aero-engine health control method;
Fig. 2 is the health management system arranged structure diagram of the application aero-engine;
Fig. 3 is the health management system arranged each section composition schematic diagram of the application aero-engine.
Wherein:
10. test flight end, 20. airborne equipment ends, 30. ground test ends, 40. aero-engines, 50. engines are short
Cabin, 301. wire commutators, 302. wireless devices;
101. winged control machine, 102. reflecting softwares;
201. airborne equipments, 202. airborne equipment end softwares;
301. wire commutators, 302. wireless devices, 303. portable PCs, 304. ground test softwares;
601. exhaust gas temperature sensors, 602. temperature of total exhaust temperature sensors, 603. cylinder head temperature sensors, 604. air inlet temperature
Spend sensor, 605. air temperature sensor, temperature sensor in 606. cabins, 607. accelerator open degree sensors, 608. fuel oil pressures
Force snesor, 609. manifold pressure sensors, 610. speed probes, 611. startings make can control.
Specific embodiment
To keep the purposes, technical schemes and advantages of the application implementation clearer, below in conjunction in the embodiment of the present application
Attached drawing, technical solutions in the embodiments of the present application is further described in more detail.In the accompanying drawings, identical from beginning to end or class
As label indicate same or similar element or element with the same or similar functions.Described embodiment is the application
A part of the embodiment, instead of all the embodiments.The embodiments described below with reference to the accompanying drawings are exemplary, it is intended to use
In explanation the application, and it should not be understood as the limitation to the application.Based on the embodiment in the application, ordinary skill people
Member's every other embodiment obtained without creative efforts, shall fall in the protection scope of this application.Under
Face is described in detail embodiments herein in conjunction with attached drawing.
Aero-engine health control focuses on that aero-engine is health management system arranged to build and theoretical method
Conclude deduction and software realization.The first step of health control is the acquisition of data, wherein being attached most importance to online data, this is just needed
System should include the acquiring and processing device of enough abilities to cope with adopting for aero-engine working environment and itself relevant parameter
Collection and processing work;Second step is to carry out data characterization operation, i.e., extracts actual parameter classification according to the collected data, and divide
The other class of door analyzes data, to obtain out health control relevant one by the fusion of a kind of data or multi-class data
Item or multiple parameters, this deduces with regard to the conclusion of Need Hierarchy Theory method and verifying;Third step is in conjunction with certainly health management system arranged
Hardware system builds software platform, obtains embedded theoretical method, to realize that aero-engine is health management system arranged.
1 to Fig. 3 the application aero-engine health control method, apparatus and system are done further in detail with reference to the accompanying drawing
It describes in detail bright.
In a first aspect, as shown in Figure 1, process is as follows this application provides a kind of aero-engine health control method:
Data acquisition step S101: engine related data relevant to aero-engine to be managed is obtained.
Data reading step S102: engine related data is read by bus.
Data extraction step S103: according to the state to be predicted of engine and the data category demand of failure to be predicted,
Extracted from engine related data compatible with the state to be predicted of engine the first valid data and with it is to be predicted former
Hinder compatible second valid data.
In the preferred embodiment of the application, the state to be predicted of engine can be engine operating condition, at this time
Engine operating condition includes operating status and flameout state, and the first valid data are extracted from engine related data, may include 1
The delivery temperature and exhaust total temperature and engine speed of~6 cylinders.
In the preferred embodiment of the application, the failure to be predicted of engine includes oil pressure faults, cylinder reviewing knowledge already acquired barrier
And delivery temperature failure, the second valid data may include engine fuel pressure, the temperature of cylinder, engine at this time
The delivery temperature and exhaust total temperature of cylinder.
Data analysis step S104: using threshold threshold as foundation, respectively to the first valid data and the second valid data into
Row signature analysis.
Determination step S105: the theory using the first valid data after signature analysis as the state to be predicted of engine is defeated
Enter, the judgement of the state to be predicted of complete coupled engines, and using the second valid data after signature analysis as engine
The theoretical input of failure to be predicted, the judgement of the failure to be predicted of complete coupled engines.Wherein, it is method that exploitation right reviews table
Each data source is merged, and status early warning is carried out to the working condition of aero-engine
In the preferred embodiment of the application, judgement to engine operating condition is differentiated according to engine operating condition
Algorithm judges engine behavior, and records the engine effective time;Have according to airborne equipment end software and hardware is relevant
Parameter is imitated, according to airborne equipment end work condition judging algorithm, judges the working condition at airborne equipment end, and record airborne equipment end
Effectively work total duration, single power on duration and health status.
In the preferred embodiment of the application, the algorithm that the operating condition of engine is differentiated, its input quantity is
The delivery temperature of 1~6 cylinder of engine and exhaust total temperature and engine speed, totally 8 useful variables, using 5ms as the circulating cycle
Phase judges each parameter, and obtains related parameter values, and cyclic process is as described below:
1) delivery temperature of 1 cylinder is read, and with 500 DEG C for distinguishing rule, if more than 500 DEG C, then mark is set to 1, successively
Delivery temperature and exhaust total temperature to 2,3,4,5,6 cylinders are handled;
2) read the revolving speed of engine, and and 100rpm be difference foundation, if more than 100rpm, then mark is set to 1, no
It is then 0;
3) state parameter of above 8 data values is carried out returning reason, and calculates the sum total of each status parameter values, if more than 4,
Then think that engine is in operating status, otherwise, then it is assumed that engine is in flameout state;
If 4) engine is in operating status, engine on time record is opened, including when the operation of this engine
The long and total operation duration of engine, and record data are written in real time in internal FLASH.
In the preferred embodiment of the application, the judgement of the failure to be predicted of engine is by fault alarm mould
Type is realized;Fault alarm mould is the theoretical model handled with the real time fail data for engine, it is with oil pressure
Alarm, the alarm of cylinder temperature and delivery temperature alarm three classes alarm signal are input quantity, in conjunction with engine behavior, are believed this three classes
Number judged, deterministic process is as described below:
1) oil pressure parameter value is set in model as three sections [0, A0], [A0, A1] and [A1, A2], reads the ginseng of oil pressure
Numerical value reads engine behavior, if engine is in running order, oil pressure should be at the section [A0, A1], other sections
The mark that is both needed to will to alarm sets 1, if engine is in flameout state, oil pressure should be at [0, A0] section, other sections be both needed to by
Alarm mark sets 1;
2) cylinder temperature parameter value is set in model as three sections [0, B0], [B0, B1] and [B1, B2], reads the ginseng of cylinder temperature
Numerical value reads engine behavior, if engine is in running order, cylinder temperature should be at the section [B0, B1], other sections
The mark that is both needed to will to alarm sets 1, if engine is in flameout state, oil pressure should be at [0, B0] section, other sections be both needed to by
Alarm mark sets 1;
3) delivery temperature parameter value is set in model as three sections [0, C0], [C0, C1] and [C1, C2], reads exhaust
The parameter value of temperature reads engine behavior, if engine is in running order, delivery temperature should be at [C0, C1]
Section, other sections, which are both needed to alarm to identify, sets 1, if engine is in flameout state, delivery temperature should be at [0, C0] area
Between, other sections, which are both needed to alarm to identify, sets 1.
Further, above-mentioned in aero-engine health control method in the preferred embodiment of the application
Step can also include:
Data acquisition step S101 further include: obtain equipment-related data relevant to airborne equipment;It should be noted that
Data therein may include software data and hardware data.
Data reading step S102 further include: read equipment-related data.
Data extraction step S103 further include: according to the data category demand of the state to be predicted of airborne equipment, and utilize
The mark of each data is classified, and third compatible with the state to be predicted of airborne equipment is extracted from equipment-related data to be had
Imitate data.
In the preferred embodiment of the application, the relevant state to be predicted of equipment is airborne equipment operating condition, airborne
Equipment working condition may include it is excellent, good, in, difference and five kinds of states of excess, mentioned from airborne equipment end software and hardware related data at this time
Third valid data are taken, may include relay operating state data (relay actuation number) 7041 and FLASH working condition
Data 7042 (FLASH reads and writes number).
Data analysis step S104 further include: using threshold threshold as foundation, signature analysis is carried out to third valid data.
Determination step S105 is airborne equipment operating condition determination step: using the third valid data after signature analysis as airborne
The theoretical input of the state to be predicted of equipment, completes the judgement to the predicted state of airborne equipment.
In the preferred embodiment of the application, judgement to airborne equipment end operating condition is according to airborne equipment end
Work condition judging algorithm, its input quantity are relay actuation number and FLASH read-write number, the derating curve according to each component
It is required that the difference standard of formulation judges each parameter using 5ms as cycle period, and obtain related parameter values, is circulated throughout
Journey is as described below:
1) read relay A actuation number, and using derating curve piecewise function A0, A1, A2, A3 and A4 (A4's
Value is determined by derating curve) by the state of relay A be classified as it is excellent, good, in, difference and five kinds of states of excess, respectively with 1,2,
3, it 4 and identifies the state of A and is indicated, as shown in the table;
2) read relay B actuation number, and using derating curve piecewise function B0, B1, B2, B3 and B4 (B4's
Value is determined by derating curve) by the state of relay B be classified as it is excellent, good, in, difference and five kinds of states of excess, respectively with 1,2,
3, it 4 and identifies the state of B and is indicated;
3) the read-write number of FLASH is read, and utilizes piecewise function C0, C1, C2, C3 and C4 (value of B4 of derating curve
Be determined by derating curve) by the state of FLASH be classified as it is excellent, good, in, difference and five kinds of states of excess, respectively with 1,2,3,4 and
The state of C is identified to be indicated, in addition, if read-write exception occurs in FLASH, it will submit the mark D read and write extremely, and merge
In motivation of setting out alarm signal;
Read state value of the maximum value as airborne equipment end of relay A, B and FLASH working condition, and according to 1,2,
3,4 it is corresponding it is excellent, good, in, difference be indicated, if excess mark occurs in any component, airborne equipment end is in excess
State.
Further, in the preferred embodiment of the application, aero-engine health control method can also be wrapped
It includes:
Storing step: by the judgement result of the judgement result of the state to be predicted of engine and the failure to be predicted of engine
It is stored;Or the judgement result of the predicted state of airborne equipment is stored;
Data sharing step: by the failure to be predicted of the judgement result of the state to be predicted of the engine of storage and engine
Judgement result sent;
Ground test step: the judgement result of the state to be predicted for engine based on the received and engine to pre-
Survey failure judgement as a result, to engine carry out ground test and or regular inspection safeguard.
In conclusion data reading is carried out by airborne equipment 201 in the application aero-engine health control method, with
Data classification is realized using sorting algorithm afterwards, and is classified as engine related data, airborne equipment related data and fault alarm,
The algorithm is realized using by constructing a chart in advance, by taking delivery temperature as an example, first reads outlet air temperature, then
It using chart, checks the category classification of this parameter, is stated respectively with 1,2 and 3, correspond to engine related data, machine
Equipment-related data and fault alarm are carried, this is 1 in chart, then delivery temperature should belong to engine related data.
After obtaining engine related data, software systems extract the operation of actual parameter according to related algorithm,
And delivery temperature, temperature of total exhaust temperature and the engine speed for extracting 1~6 cylinder are sentenced as actual parameter using engine operating condition
Other algorithm carries out the work for judging engine operating condition, and the write-in of operating condition assessment parameters is deposited in the operation for finally executing write-in memory
Reservoir.
After obtaining airborne equipment related data, according to relay data and FLASH data, airborne equipment operating condition is executed
Distinguished number, and complete to judge the work of airborne equipment operating condition finally executes the operation of write-in memory for operating condition assessment parameters
Memory is written.
After obtaining fault alarm, alarm parameters value is write to fixed upload frame, and completes to fly examining system record.
Second aspect, corresponding with above-mentioned first aspect embodiment, disclosed herein as well is a kind of aero-engine health
Managing device.
Aero-engine health controller includes:
Data acquisition module: for obtaining engine related data relevant to aero-engine to be managed;
Data read module: for reading engine related data;
Data extraction module: for according to the state to be predicted of engine and the data category demand of failure to be predicted,
Extracted from engine related data compatible with the state to be predicted of engine the first valid data and with it is to be predicted former
Hinder compatible second valid data;
Data analysis module: for using threshold threshold as foundation, respectively to the first valid data and the second valid data into
Row signature analysis;
Determination module: the theory for the state to be predicted using the first valid data after signature analysis as engine is defeated
Enter, the judgement of the state to be predicted of complete coupled engines, and using the second valid data after signature analysis as engine
The theoretical input of failure to be predicted, the judgement of the failure to be predicted of complete coupled engines.
In the preferred embodiment of the application, data acquisition module is also used to obtain set relevant to airborne equipment
Standby related data;Data read module is also used to read the equipment-related data;Data extraction module is also used to airborne equipment
State to be predicted data category demand, extracted from the equipment-related data and the state to be predicted of airborne equipment mutually fitted
The third valid data matched;Data analysis module is also used to using threshold threshold as foundation, carries out signature analysis to institute's valid data;
Determination module is also used to the theoretical input of the state to be predicted using the third valid data after signature analysis as airborne equipment, complete
The judgement of the predicted state of pairs of airborne equipment.
In the preferred embodiment of the application, aero-engine health controller further include:
Memory module: for by the judgement of the judgement result of the state to be predicted of engine and the failure to be predicted of engine
As a result it is stored;Or the judgement result of the predicted state of airborne equipment is stored;
Data sharing step: the judgement result of the state to be predicted of the engine for that will store and engine it is to be predicted
The judgement result of failure is sent;
Ground test module: the judgement result of the state to be predicted for engine based on the received and engine to pre-
Survey failure judgement as a result, to engine carry out ground test and or regular inspection safeguard.
The third aspect can handle device, memory, biography this application discloses a kind of aero-engine is health management system arranged
Sensor and component, ground checkout equipment, test flight equipment etc.;The computer that can be run on a processor is stored on memory
Program, processor execute computer program for realizing above-mentioned aero-engine health control method.
Sensor can according to need be selected as it is a variety of, contain temperature, pressure, flow, aperture and number I/O etc. sensing
Device and control amount can effectively obtain the moulds such as engine nacelle and the relevant temperature of aero-engine, pressure, flow and aperture
Quasi- signal and the quantity of state and alarm amount for being opened and closed type.The relevant mode analog quantity and data amount information of sensor enter airborne equipment
End becomes the digital quantity that software systems can identify, and be demarcated as according to nominal data after hardware pick-up and AD conversion
Effective data value.
In this application in an optional embodiment, according to data in the application aero-engine health control method point
The algorithm requirement of analysis, and combine engine requirement, sensor and component 60 contain exhaust gas temperature sensor 601, total
Exhaust gas temperature sensor 602, cylinder head temperature sensor 603, intake air temperature sensor 604, air temperature sensor 605, in cabin
Temperature sensor 606, accelerator open degree sensor 607, fuel pressure transmitter 608, manifold pressure sensor 609, revolution speed sensing
Device 610, starting make to can control the parts such as 611.Specifically it is divided into several following:
1) six road cylinder exhaust temperature and all the way temperature of total exhaust temperature sensor, are armoured thermocouple, and concrete form is K-type
Thermocouple can meet -40 DEG C~1200 DEG C of surveying range and the measurement accuracy of 0.1%.FS;
2) six road cylinder head temperature sensors, all the way intake air temperature sensor, all the way air temperature sensor, all the way temperature in cabin
Sensor is spent, is two-wire system PT1000 sensor, the measurement of -40 DEG C~300 DEG C of surveying range and 0.1%.FS can be met
Precision;
3) accelerator open degree sensor, accelerator open degree are fed back using resistor type angle sensor all the way, can meet 0 DEG C
~100 DEG C of surveying range and the measurement accuracy of 1%.FS, in addition, signal of the airborne equipment end in addition to acquisition sensor output
Outside, regulated power supply also is provided for sensor;
4) all the way it is fuel pressure transmitter, is all the way manifold pressure sensor, pressure sensor is pressure drag type pressure
Sensor, can meet the surveying range of 0~8Bar and the measurement accuracy of 0.1%.FS, and airborne equipment end receives pressure sensor
0-100mV analog signal, and stable DC10V voltage is provided for sensor;
5) speed probe, speed probe are Mageneto-sensitive type speed probe all the way, can meet the measurement of 0~3000rpm
The measurement accuracy in section and ± 10rpm, airborne equipment end receive the pulse duration frequency signal of speed probe, and provide for sensor
Stable DC12V voltage;
6) two-way starting makes can control, and starts enabled mechanism and is installed on engine body, is closed according to the connection on itself and ground
System is come whether determining that engine start enables.
Further, shown in referring to figs. 2 and 3, health management system arranged the application aero-engine is to be with hardware platform
Basis, equipped with embedded software system and based on the test configurations software systems of the end PC (ground checkout equipment);Mainly include
Airborne equipment end 20, ground checkout equipment end 30, sensor and component 60 and 10 4 part of test flight equipment end.Each section
The acquisition and processing and the on-line analysis of health status of data are mainly completed in definite functions, airborne equipment end;Ground checkout equipment
The main completion instruction operation in end, data are summed up and Configuration Online;Sensor and component mainly complete aero-engine working environment
And the conversion of inherent parameters;Test flight end is mature flight controller, passes through the in house software of carrying (including reflecting software
102) realize that the upload of parsing and the order of data issues work (i.e. the conversion of the frame decoding and control instruction of data), and control
Processor executes computer program for realizing the aero-engine health control method of any of the above-described.
Airborne equipment end is the core component of system, while the formant for being also the acquisition of data, handling and summing up, it
By the airborne equipment end software 202 of carrying may be implemented collection capacity acquisition and resolving, equipment interconnection, data characteristics analysis and
The functions such as health status early warning.
Airborne equipment end using sensor and component 60 monitor nacelle and aero-engine relevant environmental parameter and
Itself important parameter, airborne equipment end 20 are carried out the transmission of data and instruction by RS422 bus and test flight end 10, gone forward side by side
Row processing obtains the relevant data of health control and stores, in ground test or ground maintenance, passes through wire commutator 301
(RS422 bus) or wireless device 302 and ground test end 30 carry out the transmission of data and instruction and share.
Airborne equipment end is an integrated embedded device, contains software and hardware two parts, hardware is with center
Processing unit and functional cards are core, and equipped with filtering unit and electromagnetic shielding box;Software section is with data acquisition process
It is core with health control algorithm, is embedded in the software architecture of front and back, functional requirement required for cooperation hardware components are realized.
Wherein, central processing unit has extended out spi bus, serial bus, storage using High Performance DSP as core on hardware
The modules such as unit and clock unit, the embedded software equipped with front and back table frame on software, may be implemented command analysis and number
It is the core of airborne equipment end data processing according to work such as processing.Functional cards contain power supply media board, low-temperature sensor
The parts such as board and pyrostat board acquire list respectively as power supply power supply unit, the low-temperature sensor at airborne equipment end
Member and pyrostat acquisition unit.Wherein, software section obtains bus data, is converted to health control after summing up processing
On the one hand relevant data are written internal storage, are on the other hand packaged and are uploaded.
In the preferred embodiment of the application, ground checkout equipment is to be predicted for engine based on the received
The judgement of the failure to be predicted of the judgement result and engine of state as a result, to engine carry out ground test and or regular inspection tie up
Shield.
As shown in figure 3, ground test end 30 is the main tool of aero-engine ground test and regular inspection, contain wired
Adapter 301, wireless device 302, portable PC 303 and ground test software 304 totally four part, wire commutator 301 is to turn
It changes based on unit, the main conversion for completing level with USB interface or the network port needed for PC, wireless device 302 is in Wifi
Based on device, using the interconnection of network implementations portable PC 303 and airborne equipment 201, ground test software 304 runs on portable
On formula PC303, it is the software platform developed based on C#, contains ground test function and regular inspection maintenance function.
The data at the airborne equipment end that ground test end is received by wired or wireless form, can pass through software systems
Real-time display is carried out, and according to the preservation and post-processing work for passing time reference progress data down.Also, at ground test end
On, operator selects specific control instruction by the operation interface of software systems and issues according to the requirement of commanding,
Software systems are according to the operation format of operator come framing upload operation data frame;It is the nominal data value of analog channel, airborne
The working condition of the equipment and working condition of engine can be zeroed out by online data configuration feature or particular state
Write-in read.
Further, ground test end can import the alert data that test flight end issues, and hand over major repair record to return according to going through
Manage data, to check actual parameter about health control in the memory at airborne equipment end again, as transducer calibration value,
Engine total working duration, engine single operating time, airborne equipment operating time, airborne equipment single operating time, after
Electrical work number and FLASH read-write number etc..
In the preferred embodiment of the application, ground test end can pass through two based on consolidating with portable heating
Class mode is connected with airborne equipment end, and one kind is wireless connection form (such as portable intelligent wireless terminal), be divided into it is airborne
Equipment end is direct-connected and is used as bridge joint to be connected with airborne equipment end by adapter;Two classes are wired connection forms, pass through RS422
Adapter and the ground at airborne equipment end survey mouth and carry out direct connection.
Further, ground test end can be divided into ground according to function equipped with ground test software, ground test software
Test function and regular inspection maintenance function, ground test function judge power using real-time engines ground firing test data as foundation
Working state of system, and alarm abnormality or abnormal data, using operational order data as foundation, check dynamical system
Response characteristic, to judge the work validity of dynamical system executing agency;Regular inspection is safeguarded using health control data as foundation, is tied
Engines ground repair data is closed, the calculating and next maintenance time for carrying out engine available duration are inferred, with each sensor mark
Fixed number carries out periodic calibrating to each sensor of engine and reconfigures according to being foundation.
Aero-engine health control method, the apparatus and system of the application has the beneficial effect that:
1) it constructs based on the hair based on airborne equipment end, ground test end, sensor and component and test flight end
Motivation is health management system arranged, can complete engine monitoring and health control work, using wirelessly or non-wirelessly form, realizes data
It is shared, using special healthy management algorithm, realize engine health control;
2) airborne equipment end can acquire the relevant six roads cylinder temperature of engine, seven tunnel delivery temperatures, all the way accelerator open degree, all the way
Fuel pressure, all the way manifold pressure and all the way tach signal start in addition, also possessing two-way starting enable signal for controlling
Machine start and stop;
3) airborne equipment end is equipped with airborne equipment end software, using data acquisition process and health control algorithm as core,
It is embedded in the software architecture of front and back, contains engine operating condition distinguished number, airborne equipment end work condition judging algorithm and failure
Alarm model can be respectively completed engine operating condition judgement, airborne equipment end operating condition determines and engine failure alarm;
4) ground test end cooperates wireless relay device or wired 422 adapter real using portable PC as hardware platform
Ground test function and regular inspection maintenance function may be implemented equipped with ground test software in existing data sharing.
The above, the only specific embodiment of the application, but the protection scope of the application is not limited thereto, it is any
Within the technical scope of the present application, any changes or substitutions that can be easily thought of by those familiar with the art, all answers
Cover within the scope of protection of this application.Therefore, the protection scope of the application should be with the scope of protection of the claims
It is quasi-.
Claims (13)
1. a kind of aero-engine health control method, which is characterized in that including;
Data acquisition step: engine related data relevant to aero-engine to be managed is obtained;
Data reading step: the engine related data is read;
Data extraction step: according to the state to be predicted of the engine and the data category demand of failure to be predicted, from institute
State extracted in engine related data compatible with the state to be predicted of the engine the first valid data and with it is described
Compatible second valid data of failure to be predicted;
Data analysis step: using threshold threshold as foundation, first valid data and the second valid data are carried out respectively special
Sign analysis;
Determination step: the theory using the first valid data after signature analysis as the state to be predicted of the engine inputs,
The judgement to the state to be predicted of the engine is completed, and
Using the second valid data after signature analysis as the theory input of the failure to be predicted of the engine, complete to described
The judgement of the failure to be predicted of engine.
2. aero-engine health control method according to claim 1, which is characterized in that first effective data packets
It includes the delivery temperature of cylinder and is vented total temperature and engine speed, the state to be predicted of the engine is to start
Machine operating condition, the engine operating condition include operating status and flameout state;
Second valid data include engine fuel pressure, the temperature of cylinder, the delivery temperature of cylinder
With exhaust total temperature, the failure to be predicted of the engine includes oil pressure faults, cylinder reviewing knowledge already acquired barrier and delivery temperature failure.
3. aero-engine health control method according to claim 1, which is characterized in that the data acquisition step is also
It include: acquisition equipment-related data relevant to airborne equipment;
The data reading step further include: read the equipment-related data;
The data extraction step further include: according to the data category demand of the state to be predicted of the airborne equipment, from described
Third valid data compatible with the state to be predicted of the airborne equipment are extracted in equipment-related data;
The data analysis step further include: using threshold threshold as foundation, signature analysis is carried out to the third valid data;
The determination step further include: using the third valid data after signature analysis as the state to be predicted of the airborne equipment
Theoretical input, complete the judgement to the predicted state of the airborne equipment.
4. aero-engine health control method according to claim 3, which is characterized in that the third effective data packets
Include in airborne equipment relay actuation number and FLASH read-write number, the relevant state to be predicted of the airborne equipment is machine
Carry equipment working condition, the airborne equipment operating condition include it is excellent, good, in, difference and five kinds of states of excess.
5. aero-engine health control method according to claim 1-4, which is characterized in that further include:
Storing step: by the judgement of the judgement result of the state to be predicted of the engine and the failure to be predicted of the engine
As a result it is stored;Or the judgement result of the predicted state of the airborne equipment is stored;
Data sharing step: by the to be predicted of the judgement result of the state to be predicted of the engine of storage and the engine
The judgement result of failure is sent;
Ground test step: the judgement result of the state to be predicted for the engine based on the received and the engine
The judgement of failure to be predicted as a result, to engine carry out ground test and or regular inspection safeguard.
6. a kind of aero-engine health controller characterized by comprising
Data acquisition module: for obtaining engine related data relevant to aero-engine to be managed;
Data read module: for reading the engine related data;
Data extraction module: for according to the state to be predicted of the engine and the data category demand of failure to be predicted,
Extracted from the engine related data compatible with the state to be predicted of the engine the first valid data and with
Compatible second valid data of the failure to be predicted;
Data analysis module: for using threshold threshold as foundation, respectively to first valid data and the second valid data into
Row signature analysis;
Determination module: the theory for the state to be predicted using the first valid data after signature analysis as the engine is defeated
Enter, completes the judgement to the state to be predicted of the engine, and
Using the second valid data after signature analysis as the theory input of the failure to be predicted of the engine, complete to described
The judgement of the failure to be predicted of engine.
7. aero-engine health controller according to claim 6, which is characterized in that first effective data packets
It includes the delivery temperature of cylinder and is vented total temperature and engine speed, the state to be predicted of the engine is to start
Machine operating condition, the engine operating condition include operating status and flameout state;
Second valid data include engine fuel pressure, the temperature of cylinder, the delivery temperature of cylinder
With exhaust total temperature, the failure to be predicted of the engine includes oil pressure faults, cylinder reviewing knowledge already acquired barrier and delivery temperature failure.
8. aero-engine health controller according to claim 6, which is characterized in that the data acquisition module is also
For: obtain equipment-related data relevant to airborne equipment;
The data read module is also used to: reading the equipment-related data;
The data extraction module is also used to: according to the data category demand of the state to be predicted of the airborne equipment, from described
Third valid data compatible with the state to be predicted of the airborne equipment are extracted in equipment-related data;
The data analysis module is also used to: using threshold threshold as foundation, carrying out signature analysis to the third valid data;
The determination module is also used to: using the third valid data after signature analysis as the state to be predicted of the airborne equipment
Theoretical input, complete the judgement to the predicted state of the airborne equipment.
9. aero-engine health controller according to claim 8, which is characterized in that the third effective data packets
Include in airborne equipment relay actuation number and FLASH read-write number, the relevant state to be predicted of the airborne equipment is machine
Carry equipment working condition, the airborne equipment operating condition include it is excellent, good, in, difference and five kinds of states of excess.
10. according to the described in any item aero-engine health controllers of claim 6-9, which is characterized in that further include:
Memory module: for by the failure to be predicted of the judgement result of the state to be predicted of the engine and the engine
Determine that result is stored;Or the judgement result of the predicted state of the airborne equipment is stored;
Data sharing step: the judgement result of the state to be predicted of the engine for that will store and the engine to
The judgement result of prediction failure is sent;
Ground test module: the judgement result of the state to be predicted for the engine based on the received and the engine
The judgement of failure to be predicted as a result, to engine carry out ground test and or regular inspection safeguard.
11. a kind of aero-engine is health management system arranged characterized by comprising
Processor, memory and it is stored in the computer program that can be run on the memory and on the processor, institute
It states processor and executes the computer program for realizing aero-engine health control as described in any one in claim 1-5
Method;
Sensor, for obtain relevant to aero-engine to be managed engine related data and or it is related with airborne equipment
Equipment-related data;
Ground checkout equipment, the judgement result of the state to be predicted for the engine based on the received and the engine
The judgement of failure to be predicted as a result, to engine carry out ground test and or regular inspection safeguard.
12. aero-engine according to claim 11 is health management system arranged, which is characterized in that the ground checkout equipment
For portable intelligent wireless terminal, the wirelessly judgement result of the state to be predicted of the received engine and described
The judgement result of the failure to be predicted of engine.
13. aero-engine according to claim 11 is health management system arranged, which is characterized in that further include:
Test flight equipment executes the computer program for controlling the processor for realizing such as claim 1-5
Aero-engine health control method described in one.
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