CN105298665B - Aviation piston type engine redundance type ECU - Google Patents
Aviation piston type engine redundance type ECU Download PDFInfo
- Publication number
- CN105298665B CN105298665B CN201510684865.9A CN201510684865A CN105298665B CN 105298665 B CN105298665 B CN 105298665B CN 201510684865 A CN201510684865 A CN 201510684865A CN 105298665 B CN105298665 B CN 105298665B
- Authority
- CN
- China
- Prior art keywords
- ecu
- program
- data
- aviation piston
- redundancy backup
- 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.)
- Expired - Fee Related
Links
- 238000012545 processing Methods 0.000 claims description 8
- 230000009471 action Effects 0.000 claims description 3
- 238000005070 sampling Methods 0.000 claims description 3
- 238000005457 optimization Methods 0.000 abstract description 3
- 238000011084 recovery Methods 0.000 abstract description 3
- 238000005516 engineering process Methods 0.000 description 5
- 239000000295 fuel oil Substances 0.000 description 4
- 230000008859 change Effects 0.000 description 3
- 239000000446 fuel Substances 0.000 description 3
- 230000004048 modification Effects 0.000 description 3
- 238000012986 modification Methods 0.000 description 3
- 238000012937 correction Methods 0.000 description 2
- 238000013461 design Methods 0.000 description 2
- 230000008569 process Effects 0.000 description 2
- 239000000243 solution Substances 0.000 description 2
- 238000002485 combustion reaction Methods 0.000 description 1
- 230000005611 electricity Effects 0.000 description 1
- 230000007613 environmental effect Effects 0.000 description 1
- 238000011010 flushing procedure Methods 0.000 description 1
- 230000006698 induction Effects 0.000 description 1
- 238000002347 injection Methods 0.000 description 1
- 239000007924 injection Substances 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 239000000203 mixture Substances 0.000 description 1
- 239000003921 oil Substances 0.000 description 1
- 230000008092 positive effect Effects 0.000 description 1
- 239000007921 spray Substances 0.000 description 1
- 230000001360 synchronised effect Effects 0.000 description 1
Landscapes
- Combined Controls Of Internal Combustion Engines (AREA)
Abstract
A kind of aviation piston type engine redundance type ECU, by carrying out redundancy optimization to the RAM data memory structure in ECU to realize saving oneself for RAM, RAM data can be recovered and be corrected in time when former data are destroyed.And program is divided into multiple modules and non-operation instruction and breakpoint are set between disparate modules, it can ensure that program can be performed smoothly, and rollback and fault recovery can be realized.Program is performed by counter and is monitored, can be recovered in time when program gets muddled, to ensure the normal operation of program.And ECU is averaged to the multiple repairing weld of sensor, the accuracy of sensor data acquisition can be ensured.The aviation piston type engine redundance type ECU of the present invention can improve the safety and stability of engine work in the application.
Description
Technical field
The present invention relates to the technical field of aviation piston type engine, specifically a kind of aviation piston type engine redundancy
Formula ECU.
Background technology
At present, domestic small-sized aviation piston type engine uses diaphragm type carburator oil supply system, because carburetor leads to
Cross trunnion vacuum and mechanical system metering fuel oil, thus can not meet engine climb, cruise and dive etc. it is various winged
Under row working condition, under various environmental conditions to the demand of combustion mixture optimal air-fuel ratio.And fuel oil electric-controlled injection technology can
To improve fuel-oil atmozation quality, meet aviation piston type engine fuel tolerance requirement and flight course in power
Change demand.
Aviation piston type engine ECU ECU (abbreviation ECU) is the control nerve center of engine electric spray system, it
Fuel oil and ignition system to engine carry out closed-loop control, improve engine power performance and fuel economy, and reduce gas
Body pollution thing discharges.Aviation piston type engine ECU ECU includes three parts：Hardware circuit, Control System Software and electricity
Control unit auxiliary.Due to aviation piston type engine rigorous service condition, its requirement to ECU reliabilities is compared with other systems more
It is high.Many factors that may cause thrashing in the ECU courses of work be present, such as random disturbances, electrostatic, lightning induction, temperature
Factor etc..Aviation piston type engine operating ambient temperature changes greatly, and this proposes higher to the electric equipment service behaviour such as ECU
It is required that therefore circuit carries out fail-safe analysis and design is necessary；Secondly, aviation piston type engine has high current drive
Dynamic, heavy-duty motor and various control systems, add many control lines, power drive on the basis of original circuit system
Line etc. so that entirely the complexity of circuit, danger, electromagnetic interference etc. have risen to higher level.It therefore meets aviation piston
The requirement of the formula duty of engine, improves circuit anti-interference, simplifies wire harness, ensures that circuit system safe and reliable operation turns into automatically controlled list
The primary and foremost purpose of first reliability design.
The content of the invention
The technical problem to be solved in the present invention is to provide specifically a kind of automatically controlled list of aviation piston type engine redundance type
Member.
The present invention is adopted the technical scheme that to solve technical problem present in known technology:
The data stored in the RAM of ECU are set by the aviation piston type engine redundance type ECU of the present invention
Redundancy backup is put, and redundancy backup and the storage address of former data are not attached to, and redundancy backup and former data synchronization updating, work as interference
When occurring and intercepting program error processing section, the content of redundancy backup is covered into former data position；By ECU
The program of middle execution is split as multiple modules and setup module ID registers, and each module performs simple function, and each module
One outlet is all only set, for the unique corresponding ID number of each module configuration, returned out whenever module corresponding function is finished
Mouthful before, by corresponding ID number be sent into ID registers, judge whether the ID number in ID registers correct, as ID number is incorrect will
Program intercepts are to initialization segments or program error processing section；Program counter is provided with ECU, works as program process
"+1 " action is carried out during middle generation timer interrupt to program counter, ECU interval is sent clear to counter during normal work
Zero instruction, ECU is resetted when non-normal working occurs and count value reaches maximum；To each in ECU work
Sensor all carries out multiple repairing weld, and the data as sensor collection of being averaged to sampling.
The present invention can also use following technical measures：
The redundancy backup of data is multiple in described RAM, and the storage address of each redundancy backup is mutually not attached to；Work as interference
When occurring and intercepting program error processing section, the existing data of the data of each redundancy backup and former data position are compared
It is right, the data to occupy the majority are selected by the way of voting and cover the position of former data.
Non-operation instruction and breakpoint are set between the difference in functionality module of described program, and carry out live reservation.
Counter in described ECU is separate counters.
The present invention has the advantages and positive effects of:
In the aviation piston type engine redundance type ECU of the present invention, by being stored up to the RAM data in ECU
Deposit structure and carry out redundancy optimization to realize saving oneself for RAM, in time RAM data can recover when former data are destroyed and
Correction.And program is divided into multiple modules and non-operation instruction and breakpoint are set between disparate modules, it can ensure that program can
Smoothly perform, and rollback and fault recovery can be realized.Program is performed by counter and is monitored, when program gets muddled
When can recover in time, to ensure the normal operation of program.And ECU is averaged to the multiple repairing weld of sensor and then may be used
To ensure the accuracy of sensor data acquisition.The aviation piston type engine redundance type ECU of the present invention in the application can
Enough improve the safety and stability of engine work.
Embodiment
Referring to specific embodiment, the present invention will be described in detail.
The data stored in the RAM of ECU are set by the aviation piston type engine redundance type ECU of the present invention
Redundancy backup is put, and redundancy backup and the storage address of former data are not attached to, and redundancy backup and former data synchronization updating, work as interference
When occurring and intercepting program error processing section, the content of redundancy backup is covered into former data position；By ECU
The program of middle execution is split as multiple modules and setup module ID registers, and each module performs simple function, and each module
One outlet is all only set, for the unique corresponding ID number of each module configuration, returned out whenever module corresponding function is finished
Mouthful before, by corresponding ID number be sent into ID registers, judge whether the ID number in ID registers correct, as ID number is incorrect will
Program intercepts are to initialization segments or program error processing section；Program counter is provided with ECU, works as program process
"+1 " action is carried out during middle generation timer interrupt to program counter, ECU interval is sent clear to counter during normal work
Zero instruction, ECU is resetted when non-normal working occurs and count value reaches maximum；To each in ECU work
Sensor all carries out multiple repairing weld, and the data as sensor collection of being averaged to sampling.
The redundancy backup of data is multiple in RAM, and the storage address of each redundancy backup is mutually not attached to；When interference occurs simultaneously
When intercepting program error processing section, the existing data of the data of each redundancy backup and former data position are compared, adopted
The data to occupy the majority are selected with the mode of voting and cover the position of former data.Enter one by the method for multiple redundancy backups
Step improves the security of data, greatly improves the security of data in RAM.
Non-operation instruction and breakpoint are set between the difference in functionality module of program, and carry out live reservation.Pass through do-nothing operation
Instruction makes the running of each module keep synchronous, and the setting of breakpoint also establishes corresponding program restoring running point.
Counter in ECU is separate counters, with avoid breaking in a program enabler flags no longer Flushing status when
Caused counter failure.
In the aviation piston type engine redundance type ECU of the present invention, by being stored up to the RAM data in ECU
Deposit structure and carry out redundancy optimization to realize saving oneself for RAM, in time RAM data can recover when former data are destroyed and
Correction.And program is divided into multiple modules and non-operation instruction and breakpoint are set between disparate modules, it can ensure that program can
Smoothly perform, and rollback and fault recovery can be realized.Program is performed by counter and is monitored, when program gets muddled
When can recover in time, to ensure the normal operation of program.And ECU is averaged to the multiple repairing weld of sensor and then may be used
To ensure the accuracy of sensor data acquisition.The aviation piston type engine redundance type ECU of the present invention in the application can
Enough improve the safety and stability of engine work.
The above described is only a preferred embodiment of the present invention, any formal limitation not is made to the present invention, though
So the present invention is disclosed as above with preferred embodiment, however, the present invention is not limited to, it is any to be familiar with this professional technology people
Member, without departing from the scope of the present invention, the technology contents disclosed can be utilized to make a little change or modification certainly, into
For the equivalent embodiment of equivalent variations, as long as being the content without departing from technical solution of the present invention, the technical spirit according to the present invention
Any simple modification, equivalent change and modification made to above example, is belonged in the range of technical solution of the present invention.
Claims (4)
- A kind of 1. aviation piston type engine redundance type ECU, it is characterised in that：To the number stored in the RAM of ECU According to setting redundancy backup, and redundancy backup and the storage address of former data are not attached to, redundancy backup and former data synchronization updating, when When interference occurs and intercepts program error processing section, the content of redundancy backup is covered into former data position；Will be automatically controlled The program performed in unit is split as multiple modules and setup module ID registers, and each module performs simple function, and each Module all only sets one outlet, for the unique corresponding ID number of each module configuration, is returned whenever module corresponding function is finished Before returning back out mouth, corresponding ID number is sent into ID registers, judges whether the ID number in ID registers is correct, as ID number is incorrect I.e. by program intercepts to initialization segments or program error processing section；Program counter is provided with ECU, when program performs During "+1 " action is carried out to program counter when timer interrupt occurs, ECU interval is sent out to counter during normal work Clear command is sent, resets ECU when non-normal working occurs and count value reaches maximum；It is right in ECU work Each sensor all carries out multiple repairing weld, and the data as sensor collection of being averaged to sampling.
- 2. aviation piston type engine redundance type ECU according to claim 1, it is characterised in that：Data in RAM Redundancy backup to be multiple, and the storage address of each redundancy backup is mutually not attached to；When interference occurs and intercepts at program error When managing section, the existing data of the data of each redundancy backup and former data position are compared, selected by the way of voting The data that occupy the majority simultaneously cover the position of former data.
- 3. aviation piston type engine redundance type ECU according to claim 1 or 2, it is characterised in that：Program Non-operation instruction and breakpoint are set between disparate modules, and carry out live reservation.
- 4. aviation piston type engine redundance type ECU according to claim 3, it is characterised in that：In ECU Counter be separate counters.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510684865.9A CN105298665B (en) | 2015-10-22 | 2015-10-22 | Aviation piston type engine redundance type ECU |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510684865.9A CN105298665B (en) | 2015-10-22 | 2015-10-22 | Aviation piston type engine redundance type ECU |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN105298665A CN105298665A (en) | 2016-02-03 |
| CN105298665B true CN105298665B (en) | 2018-02-23 |
Family
ID=55196357
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201510684865.9A Expired - Fee Related CN105298665B (en) | 2015-10-22 | 2015-10-22 | Aviation piston type engine redundance type ECU |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN105298665B (en) |
Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113202629A (en) * | 2021-06-07 | 2021-08-03 | 北京理工大学 | Dual-redundancy control system of aircraft engine |
Family Cites Families (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE19731116A1 (en) * | 1997-07-19 | 1999-01-28 | Bosch Gmbh Robert | Control device for automobile engine or drive transmission |
| CN100492223C (en) * | 2007-03-30 | 2009-05-27 | 哈尔滨工程大学 | Switch circuit for engine redundant electrically-controlled system |
| DE102008054589B3 (en) * | 2008-12-12 | 2010-08-19 | Thielert Aircraft Engines Gmbh | Engine control system for a jet diesel engine |
| CN101705872B (en) * | 2009-11-10 | 2011-11-30 | 南京航空航天大学 | FPGA-based distributed aeroengine electronic controller in chip and control method |
| CN104238435B (en) * | 2014-05-27 | 2017-01-18 | 北京航天自动控制研究所 | Triple-redundancy control computer and fault-tolerant control system |
-
2015
- 2015-10-22 CN CN201510684865.9A patent/CN105298665B/en not_active Expired - Fee Related
Also Published As
| Publication number | Publication date |
|---|---|
| CN105298665A (en) | 2016-02-03 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN106593671B (en) | ETPU-based redundant fuel injection method for four-cylinder diesel engine | |
| JP2006283621A (en) | Electronic control device for aero-engine | |
| EP2683078A2 (en) | Generator management system that selectively activates generators based on an operating parameter | |
| CN106762183B (en) | A kind of engine guard method, device, electronic control unit and automobile | |
| CN105298665B (en) | Aviation piston type engine redundance type ECU | |
| CN103941720A (en) | Fault diagnosis circuit and method of internal-drive electrically-controlled ignition system | |
| CN109884879B (en) | Method for cooperative management of master-slave ECU (electronic control unit) on multiple sensors | |
| CN113202629A (en) | Dual-redundancy control system of aircraft engine | |
| CN113062812B (en) | Engine safety monitoring and detecting method, device, medium and electronic equipment | |
| US20200072132A1 (en) | Method of continuously variable valve duration position learning based on conditional application and continuously variable valve duration system therefor | |
| CN203849610U (en) | A fault diagnosis circuit for an inner drive electronic control igniting system | |
| CN110879549B (en) | Redundancy measurement architecture based on cross-comparison method and redundancy management method | |
| CN111075585B (en) | Engine fault diagnosis and correction method and system | |
| CN110286288A (en) | The monitoring method and device of engine electrical system | |
| US8963349B2 (en) | Generator management system that selectively cuts off fuel to a generator to add a load to a bus | |
| CN113982806B (en) | Method and device for determining ignition advance angle of engine and computer storage medium | |
| KR102281650B1 (en) | Battery sensor reset system for vehicle and method for controlling the same | |
| CN201687588U (en) | Signal processing circuit of diesel engine monoblock pump | |
| CN204905982U (en) | Two voltage hybrid power source systems of commercial car | |
| CN105892347B (en) | A kind of double mcu detection device and method based on arbitration technique | |
| CN110109442A (en) | A kind of EMS terminal equipment failure remote diagnosis method based on various dimensions statistics | |
| CN116378875B (en) | Protection method, equipment and storage medium for natural gas engine | |
| CN112780426B (en) | Engine starting method and device, vehicle and storage medium | |
| CN114776453B (en) | Marine dual-fuel engine control method and control system | |
| CN207377670U (en) | A kind of automobile fuel gas controller |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20180223 |