CN106483472A - A kind of power system failure diagnostic method based on airborne power supply management and control device - Google Patents
A kind of power system failure diagnostic method based on airborne power supply management and control device Download PDFInfo
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- CN106483472A CN106483472A CN201510514592.3A CN201510514592A CN106483472A CN 106483472 A CN106483472 A CN 106483472A CN 201510514592 A CN201510514592 A CN 201510514592A CN 106483472 A CN106483472 A CN 106483472A
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Abstract
The contents such as detection to airborne each power supply unit running status, separation, identification and decision-making are mainly included based on the power system failure diagnostic design of device for managing and controlling electrical source.Fault diagnosis is carried out to power-supply systems such as aircraft battery group, left/right power supply hinge, current transformer, left/right generators, Predictive Maintenance is changed in traditional periodic maintenance, the failure condition of power-supply device/component can be known in advance, avoid the generation of malignant event, greatly improve security, reliability and the utilization rate of system operation, a large amount of maintenance times and expense is saved, and then produces huge economic benefit.
Description
Technical field
Type of the present invention belongs to avionics field, is related to a kind of power system failure based on airborne power supply management and control device
Diagnostic method.
Background technology
The performance of aircraft power system and the key factor that quality is guarantee aircraft overall performance, while with present generation aircraft power supply system
The continuous improvement of system complexity, the fault diagnosis of airborne power supply system are increasingly taken seriously and develop.
Fault diagnosis has important meaning as an importance of airborne power supply system maintenance to guarantee aircraft safety, stable operation
Justice.Airborne power supply system is made up of multiple subsystems, and subsystems working mechanism is had nothing in common with each other, and is cross-linked with each other between them,
Complex structure, due to the increase of integral link and influence factor, the Potential feasibility for making aircraft break down and failing is increasing,
Respective power source unit failure can cause chain reaction, cause the operation of whole power-supply system bad so that staff is existing according to fault
As being difficult to quickly find the source of trouble so that airborne power supply system maintenance is poor, reliability is low, constrains significantly carrying for aeroplane performance
High.
Content of the invention
The object of the invention：
The purpose of type of the present invention is to provide a kind of power system failure diagnostic design method based on airborne power supply management and control device,
By the device for managing and controlling electrical source subsystem state monitor in real time numerous and jumbled to aircraft power system and judgement, integrated management, while
Real-time Collection power-supply system dependent failure information and status information, set up power-supply system health account (i.e. power-supply system expertise
Storehouse), according to power-supply system expert knowledge library, real-time diagnosis power system failure mechanism, to detect that aircraft and airborne power unit deposit
Fault or hidden danger, be aircraft maintenance provided auxiliary means；The effective reliability for improving airborne power supply system fault diagnosis,
Accuracy, reduces maintenance manpower and support cost, so that aircraft is run more preferable, safe, reliable, efficiently.
Technical solution of the present invention：
A kind of power system failure diagnostic method based on airborne power supply management and control device, it is characterised in that the diagnostic method
Feature is as follows：
The corresponding relation of step one, failure definition code, working condition and failure cause
Power system failure information definition is code form, and defines equipment working state and failure cause and failure code
Corresponding relation as shown in the table：
Step 2, power-supply system condition monitoring record data
The status information of Real-time Collection power-supply system, status information include that generator voltage signal, generator contactor connect letter
Number, generator overtemperature signal, generator powered signal, generator adjust point voltage signal, dynamo current signal, and will
The status information for collecting is recorded by HDLC bus in the massive store chip of device for managing and controlling electrical source, root
Failure modes are carried out to the data for collecting according to fault and code corresponding relation, described corresponding relation is as follows：
| Signal name | The effective fault-free of signal | Fault | Failure modes |
| Generator overtemperature signal | Ground is effectively | Have effect in vain | Code 1 |
| Generator contactor connects signal | 28V is effective | Have effect in vain | Code 2 |
| Generator powered signal | 28V is effective | Have effect in vain | Code 3 |
| Generator voltage signal | 0～40V | More than 40V | Code 4 |
| Point voltage signal adjusted by generator | 0～40V | More than 40V | Code 4 |
| Dynamo current signal | 0～100mV | More than 100mV | Code 5 |
Failure code is drawn by above-mentioned fault and code corresponding relation；
Step 3, power system failure diagnosis
According to the failure code for obtaining, by airborne power supply working state of system and the corresponding relation of failure code, event is drawn
Barrier reason, while the status information of recording power system, the status information of power-supply system is stored in by HDLC bus
To in the massive store chip of device for managing and controlling electrical source；While the status information of power-supply system is sent to airborne electromechanics
Management system is recorded.
The airborne power supply management and control device has independent data acquisition, discrete magnitude control, fault diagnosis, Large Copacity
Data storage, is connected with batteries, current transformer equipment by data wire, power line.
The feature of the present invention：
1) minimum system is realized：Hardware platform based on device for managing and controlling electrical source, builds ground maintenance with assistant analysis
System, and accumulate fault data；
2) power-supply system expert knowledge library is set up：According to the fault data of accumulation, constantly expand ground maintenance and assistant analysis subsystem
The functional module of system and diagnostic model storehouse, set up the mechanism of simplifying of diagnostic model, through fully checking airborne transplanting backward；
3) fault diagnosis is intelligent：Using the fault data information of power-supply system expert knowledge library, using advanced accident analysis skill
Art, forms more ripe ground maintenance and assistant analysis subsystem, possesses deep layer Intelligent fault diagnostic function, becomes
Gesture prediction and health management function.
Beneficial effect：
It is that subsystem numerous and jumbled for power-supply system is believed based on the power system failure diagnostic design method of airborne power supply management and control device
Number integrated management, carries out unified fault diagnosis, improves diagnosis efficiency and accuracy, so when ensureing aircraft flight safe,
Reliable；By the condition monitoring signal of comprehensive power system, the feature of each power subsystem is studied, set up power-supply system health
Archives are (i.e.：Power-supply system expert knowledge library), reliability, the accuracy of airborne power supply system fault diagnosis is effectively raised,
Reduce maintenance manpower and support cost, so that aircraft is run more preferable, safe, reliable, efficiently；Using based on airborne power supply
The power system failure diagnostic design method of management and control device, it is possible to achieve power-supply system condition monitoring, fault diagnosis and trend
The functions such as prediction, have positive effect to reducing Aircraft Production and maintenance cost, saving maintenance time.
Specific embodiment
The present invention is a kind of power system failure diagnostic method based on airborne power supply management and control device, it is characterised in that described examine
Disconnected method characteristic is as follows：
The corresponding relation of step one, failure definition code, working condition and failure cause
Power system failure information definition is code form, and defines equipment working state and failure cause and failure code
Corresponding relation as shown in the table：
Step 2, power-supply system condition monitoring record data
The status information of Real-time Collection power-supply system, status information include that generator voltage signal, generator contactor connect letter
Number, generator overtemperature signal, generator powered signal, generator adjust point voltage signal, dynamo current signal, and will
The status information for collecting is recorded by HDLC bus in the massive store chip of device for managing and controlling electrical source, root
Failure modes are carried out to the data for collecting according to fault and code corresponding relation, described corresponding relation is as follows：
| Signal name | The effective fault-free of signal | Fault | Failure modes |
| Generator overtemperature signal | Ground is effectively | Have effect in vain | Code 1 |
| Generator contactor connects signal | 28V is effective | Have effect in vain | Code 2 |
| Generator powered signal | 28V is effective | Have effect in vain | Code 3 |
| Generator voltage signal | 0～40V | More than 40V | Code 4 |
| Point voltage signal adjusted by generator | 0～40V | More than 40V | Code 4 |
| Dynamo current signal | 0～100mV | More than 100mV | Code 5 |
Failure code is drawn by above-mentioned fault and code corresponding relation；
Step 3, power system failure diagnosis
According to the failure code for obtaining, by airborne power supply working state of system and the corresponding relation of failure code, must be out of order original
Cause, while the status information of recording power system, the status information of power-supply system is deposited into power management by HDLC bus
In the massive store chip of control device；While the status information of power-supply system is sent to airborne Electric-machinery Management System being remembered
Record.
Fault diagnosis is carried out to dc generator for example with the present invention, first DC power system event is set up according to expert knowledge library
Barrier information table, as shown in table 1, then models for fault tree diagnosis theory.It is top event to define dc generator fault, and table
In 2, each fault mode is elementary event.
1 dc generator fault message table of table
| Sequence number | Fault (state) title | Fault state is analyzed | Remarks |
| 1 | Dc generator is overheated | The load too big, number of starts is many, it is short to start interval time | |
| 2 | Dc generator reflux | In the case of battery parallel connection, stop, at this moment can reflux； | |
| 3 | Dc generator excessively stream | Load is too big, but does not include excessively stream in engine start | |
| 4 | Dc generator overvoltage | Line fault, voltage regulator imbalance, controller component failure on aircraft | |
| 5 | Dc generator short circuit | Unexpected excessively stream, differential current transformer are sensitive |
2 dc generator fault elementary event table of table
| Sequence number | Code name | Elementary event |
| 1 | X1 | Dc generator is overheated |
| 2 | X2 | Dc generator reflux |
| 3 | X3 | Dc generator excessively stream |
| 4 | X4 | Dc generator overvoltage |
| 5 | X5 | Dc generator is grounded |
As long as when any one in 5 faults of dc generator occurs, then judge that dc generator has fault.According to basic
Event table can obtain dc generator fault tree.
For the fault diagnosis result of dc generator, fault diagnosis result is total by RS-422A by device for managing and controlling electrical source
Line is real-time transmitted to airborne Electric-machinery Management System, then is sent to passenger cabin integrated display by Electric-machinery Management System.Can also be by electricity
Source control control device is exported in the form of discrete magnitude lights passenger cabin correlation indicator lamp.
Claims (1)
1. a kind of power system failure diagnostic method based on airborne power supply management and control device, it is characterised in that including airborne electricity
Source control control device, the diagnostic method feature are as follows：
The corresponding relation of step one, failure definition code, working condition and failure cause
Power system failure information definition is code form, and defines equipment working state and failure cause and failure code
Corresponding relation as shown in the table：
Step 2, power-supply system condition monitoring record data
Using the status information of airborne power supply management and control device Real-time Collection power-supply system, status information includes the electromechanics that generates electricity
Pressure signal, generator contactor are connected signal, generator overtemperature signal, generator powered signal, generator and adjust point voltage letter
Number, dynamo current signal, and the status information for collecting recorded device for managing and controlling electrical source by HDLC bus
Massive store chip in, and fault is determined whether according to the status information of collection, according to fault and code corresponding relation
Table carries out failure code classification to the data for collecting, and described mapping table is as follows：
Failure code is drawn by above-mentioned fault and code mapping table；
Step 3, power system failure diagnosis
According to the failure code for obtaining, close by airborne power supply working state of system and failure cause are corresponding with failure code
It is table, failure cause is drawn, while the status information of recording power system, the status information of power-supply system is passed through HDLC
Bus is deposited in the massive store chip of device for managing and controlling electrical source；While the status information of power-supply system is sent to
Airborne Electric-machinery Management System is recorded.
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN107832073A (en) * | 2017-11-24 | 2018-03-23 | 中国航空工业集团公司西安航空计算技术研究所 | A kind of airborne Smart Power Module upgrade maintaining method based on agency |
| CN108803564A (en) * | 2018-05-28 | 2018-11-13 | 湖北三江航天万峰科技发展有限公司 | A kind of communication control equipment automatization test system and method |
| CN110632912A (en) * | 2019-10-17 | 2019-12-31 | 浙江正泰中自控制工程有限公司 | DCS power system fault diagnosis method |
| CN113467278A (en) * | 2021-05-24 | 2021-10-01 | 中国航空工业集团公司沈阳飞机设计研究所 | Man-machine interaction terminal for ground maintenance of airborne power system |
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| CN113467278A (en) * | 2021-05-24 | 2021-10-01 | 中国航空工业集团公司沈阳飞机设计研究所 | Man-machine interaction terminal for ground maintenance of airborne power system |
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Application publication date: 20170308 |