CN107037732A - A kind of aircraft electrical control tolerant system and failure decision-making technique - Google Patents
A kind of aircraft electrical control tolerant system and failure decision-making technique Download PDFInfo
- Publication number
- CN107037732A CN107037732A CN201710385957.6A CN201710385957A CN107037732A CN 107037732 A CN107037732 A CN 107037732A CN 201710385957 A CN201710385957 A CN 201710385957A CN 107037732 A CN107037732 A CN 107037732A
- Authority
- CN
- China
- Prior art keywords
- signal
- electrical control
- module
- detection
- failure
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
Classifications
-
- G—PHYSICS
- G05—CONTROLLING; REGULATING
- G05B—CONTROL OR REGULATING SYSTEMS IN GENERAL; FUNCTIONAL ELEMENTS OF SUCH SYSTEMS; MONITORING OR TESTING ARRANGEMENTS FOR SUCH SYSTEMS OR ELEMENTS
- G05B13/00—Adaptive control systems, i.e. systems automatically adjusting themselves to have a performance which is optimum according to some preassigned criterion
- G05B13/02—Adaptive control systems, i.e. systems automatically adjusting themselves to have a performance which is optimum according to some preassigned criterion electric
- G05B13/04—Adaptive control systems, i.e. systems automatically adjusting themselves to have a performance which is optimum according to some preassigned criterion electric involving the use of models or simulators
- G05B13/042—Adaptive control systems, i.e. systems automatically adjusting themselves to have a performance which is optimum according to some preassigned criterion electric involving the use of models or simulators in which a parameter or coefficient is automatically adjusted to optimise the performance
Abstract
The invention provides a kind of aircraft electrical control tolerant system and failure decision-making technique, Integrated Information Processing System in ground control system or machine is combined by the present invention with the self-inspection loop in electrical control gear, collectively form fault detect and failure decision loop, and use Analog control passage and the parallel electric controling mode of digital quantity control passage, and propose a kind of reliability for being applied to the system failure decision-making technique, improving aircraft electric control system.
Description
Technical field
The present invention relates to the tolerant system in a kind of electrical control dependability design system, it is adaptable to aviation aircraft.
Background technology
Aircraft electric control system performs the electrical control order of Integrated Information Processing System on ground or machine, realizes machine
The power supply of equipment is carried, turns the functions such as electricity, power-off and electric power thus supplied is monitored, the information such as collection power supply state, supply voltage,
And abnormality is handled and system protection in time, realize the reliable electrical control of each equipment safety on aircraft
Critical system.
Fault-tolerant design is reliability design approach fast-developing over a kind of nearly 20 years, refers to work as a certain in system
During partial destruction, enable a system to continue normal operation by means such as fault detect, reparation, reconstruct.The technology be applied to pair
The higher system of reliability, stability, security requirement, such as nuclear electric power generation control system, Aero-Space control system.Cause
Fault-tolerant design is applied to aircraft electric control system and is of great significance for improving its reliability tool by this.
The content of the invention
The technology of the present invention solves problem：The deficiencies in the prior art are overcome, using a kind of new tolerant system, for flight
System and unit power supply control in device electrical control improve its reliability.
The technical solution of the present invention：A kind of aircraft electrical control tolerant system, it is characterised in that：Tolerant system by
Integrated Information Processing System and aircraft electrical control gear composition on ground/machine；On ground/machine Integrated Information Processing System with
Aircraft electrical control gear is connected, and is sent to analog quantity and digital quantity control signal, and receive aircraft electrical control
The digital quantity self-test signal of device；Aircraft electrical control gear is connected with airborne equipment, and power supply signal is provided for it；Ground
Integrated Information Processing System is connected with airborne equipment on face/machine, receives the airborne equipment detection signal of its feedback；
Integrated Information Processing System includes fault detect on ground/machine in described aircraft electrical control tolerant system
System and failure decision system；The status signal that the input of fault detection system feeds back with airborne equipment is connected, failure inspection
The output end of examining system is that input is connected with failure decision system, and state or threshold decision are carried out to the signal of detection, right
Judge whether its state is normal in switching signal, judge its value whether in normal threshold for value signal (such as voltage or current signal)
In the range of value；Failure decision system and the digital signal processor and communication module and analog quantity in aircraft electrical control gear
Control signal drive module is connected, and failure decision-making is carried out according to failure detection result and digital quantity self-test signal；
Aircraft electrical control gear in described aircraft electrical control tolerant system includes Analog control signal
Drive module, discrete control signal drive module, power control module, signal detection module, digital signal processor and logical
Interrogate module；The output end and power control module of Analog control signal drive module and discrete control signal drive module
Input is connected, and can individually or simultaneously drive power control module；Power control module includes system power supply control module and list
First power control module, is respectively designed using parallel redundancy, and power control module output system power supply state detects signal, is
Supply voltage detection signal, unit power supply state detection signal, unit supply voltage detection signal unite to signal detection module, it is defeated
Go out power supply signal to each airborne equipment；Signal detection module carries out electrical isolation, level conversion and A/D to detected signal and turned
Sent after changing processing to digital signal processor and communication module；
A kind of failure decision-making technique of aircraft electrical control tolerant system, it is characterised in that：Integrated information on ground/machine
Failure decision system in processing system performs failure decision process according to failure detection result and digital quantity self-test signal；Failure
Just whether decision process first determines whether whether equipment supply voltage is normal, judge electrical control gear self-detection result if normal
Often, system/unit power supply state testing result and system/unit supply voltage testing result are judged successively if abnormal, so
Afterwards according to result above failure judgement pattern and taking appropriate measures.
The principle of the present invention：Using the Method of fault-tolerant design in reliability design, built in aircraft electric control system
Formwork erection analog quantity control passage and the parallel electric controling mode of digital quantity control passage, control executing agency use Redundancy Design,
And digital quantity self-inspection loop is built in electrical control gear, collectively form failure with Integrated Information Processing System on ground/machine
Detection and the big loop of failure decision-making.
The advantage of the present invention compared with prior art is：
(1) discrete control mode uses digital communication method, reduces the signal wire between system, and transmission information is richer
It is rich, moreover it is possible to the reliability of signal transmission is improved using software approach, but the component species that hardware circuit needs is more, integrated level
It is higher；Analog control mode is more succinct and rapid by contrast, but because signal wire excessively reduces the reliability of system；
Therefore the parallel use of both modes can be formed into mutual supplement with each other's advantages.
(2) design of self-inspection loop is built in electrical control gear, electrical control situation can be carried out monitoring in real time and and
When adopt remedial measures.
(3) quick positioning is carried out to failure using succinct, efficient failure decision-making technique and taken measures in time.
Brief description of the drawings
Fig. 1 is theory diagram of the invention,
Fig. 2 is failure decision process of the invention.
Embodiment
Fig. 1 is given on the theory diagram of aircraft electrical control equipment tolerant system, including ground/machine at integrated information
Reason system and aircraft electrical control gear.Wherein, Integrated Information Processing System includes fault detection system and event on ground/machine
Hinder decision system.Aircraft electrical control gear includes digital signal processor and communication module, the driving of Analog control signal
Module, power control module and signal detection module.
By digital signal processor and communication module, discrete control signal drive module, power control module and letter
Number detection module constitutes the self-inspection loop in electrical control gear.Digital signal processor and communication module pass through signal detection mould
Block acquisition system power supply state detection signal, system power supply voltage detection signal, unit power supply state detection signal, unit are powered
Voltage detection signal, testing result is sent in the form of quantity failure decision system, when discovery system/unit supply voltage
It can in time be disconnected when abnormal and power and send up abnormality processing situation.
The electrical control orders such as the power supply of power control module execution system or unit, turn electricity, power-off, have using by two
There are the system or unit power control module of identical function redundancy structure in parallel, Analog control signal and discrete control letter
Number can simultaneously power control module is acted on by corresponding drive module.
Integrated Information Processing System, aircraft electrical control gear and airborne equipment collectively form failure on ground/machine
The big loop of decision-making.The power supply electricity that failure decision system on ground/machine in Integrated Information Processing System is fed back according to airborne equipment
Pressure and electrical control gear self-detection result carry out fault diagnosis and simultaneously taken measures, and failure decision process is as shown in Fig. 2 and follow table
The detection of failure decision-making technique shown in 1, wherein airborne equipment supply voltage, system/unit power supply state detection, system/unit
Supply voltage detection is consistent with the signal name in Fig. 1.
The failure decision-making technique of table 1
Note：" √ " represents normal, and "×" represents failure.
Claims (4)
1. a kind of aircraft electrical control tolerant system, it is characterised in that：Tolerant system integrated information processing system on ground/machine
System and aircraft electrical control gear composition；Integrated Information Processing System is connected with aircraft electrical control gear on ground/machine
Connect, be sent to analog quantity and digital quantity control signal, and receive the digital quantity self-test signal of aircraft electrical control gear；Fly
Row device electrical control gear is connected with airborne equipment, and power supply signal is provided for it；On ground/machine Integrated Information Processing System with
Airborne equipment is connected, and receives the airborne equipment detection signal of its feedback.
2. aircraft electrical control tolerant system according to claim 1, it is characterised in that comprehensive on the ground/machine
Information processing system includes fault detection system and failure decision system；The input of fault detection system feeds back with airborne equipment
Status signal be connected, output end and the failure decision system of fault detection system are that input is connected, to the letter of detection
Number carry out state or threshold decision, judge whether its state normal for switching signal, for value signal judge its value whether
In the range of normality threshold；Digital signal processor and communication module in failure decision system and aircraft electrical control gear and
Analog control signal drive module is connected, and failure decision-making is carried out according to failure detection result and digital quantity self-test signal.
3. aircraft electrical control tolerant system according to claim 1, it is characterised in that aircraft electrical control gear
Comprising Analog control signal drive module, discrete control signal drive module, power control module, signal detection module,
Digital signal processor and communication module；The output of Analog control signal drive module and discrete control signal drive module
End is connected with the input of power control module, can individually or simultaneously drive power control module；Power control module is included
System power control module and unit power control module, are respectively designed, power control module output system using parallel redundancy
Power supply state detection signal, system power supply voltage detection signal, unit power supply state detection signal, unit supply voltage detection letter
Number to signal detection module, output power supply signal to each airborne equipment；Signal detection module carries out electric to detected signal
Sent after isolation, level conversion and A/D conversion process to digital signal processor and communication module.
4. a kind of failure decision-making technique of aircraft electrical control tolerant system, it is characterised in that：On ground/machine at integrated information
Failure decision system in reason system performs failure decision process according to failure detection result and digital quantity self-test signal；Failure is determined
Plan flow first determines whether whether equipment supply voltage is normal, judges whether electrical control gear self-detection result is normal if normal,
Judge system/unit power supply state testing result and system/unit supply voltage testing result, Ran Houyi successively if abnormal
According to result above failure judgement pattern and take appropriate measures.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710385957.6A CN107037732A (en) | 2017-05-26 | 2017-05-26 | A kind of aircraft electrical control tolerant system and failure decision-making technique |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710385957.6A CN107037732A (en) | 2017-05-26 | 2017-05-26 | A kind of aircraft electrical control tolerant system and failure decision-making technique |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN107037732A true CN107037732A (en) | 2017-08-11 |
Family
ID=59539038
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201710385957.6A Pending CN107037732A (en) | 2017-05-26 | 2017-05-26 | A kind of aircraft electrical control tolerant system and failure decision-making technique |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN107037732A (en) |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101713802A (en) * | 2009-11-13 | 2010-05-26 | 航天东方红卫星有限公司 | Fault on-line repairing method for satellite power supply and distribution test system |
| CN105278516A (en) * | 2014-06-24 | 2016-01-27 | 南京理工大学 | Double-redundancy switch value PLC control system reliable fault-tolerant controller realization method |
| CN105445593A (en) * | 2016-01-22 | 2016-03-30 | 成都纵横智控科技有限公司 | A fault detection apparatus and method for electrical equipment |
| CN105549577A (en) * | 2016-02-05 | 2016-05-04 | 赵红军 | Automatic detection system of airplane AC generator controller and detection method |
| CN106526388A (en) * | 2016-12-20 | 2017-03-22 | 中国航天空气动力技术研究院 | Test system and test method for airborne avionics device of unmanned aerial vehicle |
-
2017
- 2017-05-26 CN CN201710385957.6A patent/CN107037732A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101713802A (en) * | 2009-11-13 | 2010-05-26 | 航天东方红卫星有限公司 | Fault on-line repairing method for satellite power supply and distribution test system |
| CN105278516A (en) * | 2014-06-24 | 2016-01-27 | 南京理工大学 | Double-redundancy switch value PLC control system reliable fault-tolerant controller realization method |
| CN105445593A (en) * | 2016-01-22 | 2016-03-30 | 成都纵横智控科技有限公司 | A fault detection apparatus and method for electrical equipment |
| CN105549577A (en) * | 2016-02-05 | 2016-05-04 | 赵红军 | Automatic detection system of airplane AC generator controller and detection method |
| CN106526388A (en) * | 2016-12-20 | 2017-03-22 | 中国航天空气动力技术研究院 | Test system and test method for airborne avionics device of unmanned aerial vehicle |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN105822433B (en) | A kind of aero-engine redundancy ECU controllers and its control method | |
| CN107143429B (en) | Electronic Unit Pump Diesel Engine ECU redundant system and design method | |
| CN103544092B (en) | A kind of based on ARINC653 standard air environment health monitoring system | |
| CN103149907B (en) | Hot-redundancy CAN (Controller Area Network)-bus high-fault-tolerance control terminal and method based on dual DSPs (Digital Signal Processors) | |
| CN103217974B (en) | Spacecraft autonomous health management architecture based on comprehensive electronic platform | |
| CN109976141B (en) | UAV sensor signal redundancy voting system | |
| CN109888864B (en) | Battery management system | |
| CN104503272A (en) | Automatic train driving system based on double-system hot standby redundancy | |
| CN103809471B (en) | A kind of new type auto switching emergency treatment device and implementation method | |
| CN103077103A (en) | Off-line diagnosing method for server faults | |
| CN202394111U (en) | Manned carrier rocket fault detection system | |
| CN110794805B (en) | Robot safety circuit and control method thereof | |
| CN102331786A (en) | Dual-computer cold-standby system of attitude and orbit control computer | |
| CN108493904A (en) | IGBT Safety Shutdown Systems and method for automobile motor shutdown | |
| CN209739079U (en) | Logic control unit for train | |
| CN106864270A (en) | Relay control system with fault diagnosis functions | |
| CN109747480B (en) | Multi-safety-mode battery management system and design method thereof | |
| CN101476987B (en) | Fault diagnosis method for turbine emergency protection device | |
| CN106814604B (en) | Triple-redundancy passive independent current mutual-detection power-off restarting system and method | |
| CN104267642B (en) | System and method for outputting reliable current signals | |
| CN107688335B (en) | A kind of launch vehicle measurement that cruise mode can be switched with emission mode | |
| CN107037732A (en) | A kind of aircraft electrical control tolerant system and failure decision-making technique | |
| CN202583865U (en) | Dual-redundancy control circuit | |
| CN106451404A (en) | Power supply system and power supply configuration method thereof | |
| CN107800186A (en) | The feedback and device of more rotor manned aircraft powers |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| WD01 | Invention patent application deemed withdrawn after publication | ||
| WD01 | Invention patent application deemed withdrawn after publication |
Application publication date: 20170811 |