CN105298665A - Redundant type electronic control unit for aviation piston-type engine - Google Patents
Redundant type electronic control unit for aviation piston-type engine Download PDFInfo
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- CN105298665A CN105298665A CN201510684865.9A CN201510684865A CN105298665A CN 105298665 A CN105298665 A CN 105298665A CN 201510684865 A CN201510684865 A CN 201510684865A CN 105298665 A CN105298665 A CN 105298665A
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Abstract
The invention provides a redundant type electronic control unit for an aviation piston-type engine. Redundancy optimization is conducted on a random access memory (RAM) data storage structure in the electronic control unit to achieve the self rescue of the RAM, and the RAM data can be recovered and corrected in time when the original data are damaged. In addition, a program is divided into a plurality of modules and blank operating instructions or breakpoints are set among different modules so that the program can be ensured to be executed smoothly, and rollback recovery and failure recovery can be achieved. The program execution is monitored through a counter, and when the program is disturbed, the program can be recovered in time to ensure the normal operation of the program. Moreover, the electronic control unit takes the average value of multiple sampling of a sensor, and thus the accuracy of the data acquisition through the sensor can be ensured. According to the redundant type electronic control unit for the aviation piston-type engine, the safety and the stability of the engine operation can be improved in the application.
Description
Technical field
The present invention relates to the technical field of aviation piston type engine, is a kind of aviation piston type engine redundance type ECU (Electrical Control Unit) specifically.
Background technique
At present, domestic small-sized aviation piston type engine all adopts diaphragm carburetor oil supply system, because Carburetor is by trunnion degree of vacuum and machinery type metering fuel oil, thus can not meet motor climbing, cruise and under the various flight working condition such as underriding, under various environmental conditions to the demand of inflammable mixture optimal air-fuel ratio.And fuel oil electric-controlled injection technology can improve fuel-oil atmozation quality, the fuel tolerance meeting aviation piston type engine require and in flight course to the change demand of power.
Aviation piston type engine ECU (Electrical Control Unit) ECU (being called for short ECU) is the control nerve center of engine electric spray system, it carries out closed loop control to the fuel oil of motor and ignition system, improve engine power performance and fuel economy, and reduce gas pollutant discharge.Aviation piston type engine ECU (Electrical Control Unit) ECU comprises three parts: hardware circuit, Control System Software and ECU (Electrical Control Unit) auxiliary.Due to aviation piston type engine rigorous service condition, to the requirement of ECU reliability, comparatively other system is higher for it.There is many factors that may cause thrashing, as random disturbances, electrostatic, lightning induction, temperature factor etc. in ECU working procedure.Greatly, this proposes requirements at the higher level to electric equipment service behaviours such as ECU to the change of aviation piston type engine operating ambient temperature, and therefore circuit carries out reliability analysis and designs necessary; Secondly, aviation piston type engine has large driven current density, heavy-duty motor and various control system, the basis of original circuitry adds a lot of guide line, motivational drive line etc., makes the complexity of whole circuit, danger, electromagnetic interference etc. rise to higher level.Therefore, meet aviation piston type engine functional requirement, improve circuit anti-interference, simplify wire harness, ensure that circuitry safe and reliable operation becomes the primary and foremost purpose of ECU (Electrical Control Unit) reliability design.
Summary of the invention
It is a kind of aviation piston type engine redundance type ECU (Electrical Control Unit) specifically that the technical problem to be solved in the present invention is to provide.
The technological scheme that the present invention takes for the technical problem existed in solution known technology is:
Aviation piston type engine redundance type ECU (Electrical Control Unit) of the present invention, redundancy backup is arranged to the data stored in the RAM of ECU (Electrical Control Unit), and redundancy backup is not connected with the storage address of former data, redundancy backup and former data synchronization updating, when interference occurs and intercepts program error processing section, the content of redundancy backup is covered former data position; The program performed in ECU (Electrical Control Unit) is split as multiple module and module I D register is set, each module performs simple function, and each module only arranges an outlet, for No. ID of the unique correspondence of each block configuration, before module corresponding function is finished Returning outlet, send correspondence No. ID into ID register, whether correctly judge in ID register No. ID, as No. ID incorrect by program intercepts to initialization segments or program error processing section; Program counter is provided with in ECU (Electrical Control Unit), when there is timer interrupt in program process, "+1 " action is carried out to program counter, during normal work, ECU (Electrical Control Unit) interval sends clear command to counter, ECU (Electrical Control Unit) is resetted when non-normal working occurs and count value reaches maximum; In ECU (Electrical Control Unit) work, all multiple repairing weld is carried out to each sensor, and sampling is averaged as the data of sensor collection.
The present invention can also adopt following technical measures:
In described RAM, the redundancy backup of data is multiple, and the storage address of each redundancy backup is not connected mutually; When disturb occur and intercept program error processing section time, the existing data of the data of each redundancy backup and former data position are compared, adopt the mode decided by vote to select the data that occupy the majority and cover the position of former data.
Between the difference in functionality module of described program, non-operation instruction and breakpoint are set, and carry out scene reservation.
Counter in described ECU (Electrical Control Unit) is separate counters.
The advantage that the present invention has and good effect are:
In aviation piston type engine redundance type ECU (Electrical Control Unit) of the present invention, by carrying out redundancy optimization to realize saving oneself of RAM to the RAM data storage structure in ECU (Electrical Control Unit), can recover RAM data when former data are destroyed in time and correct.And program is divided into multiple module and non-operation instruction and breakpoint are set between disparate modules, the program that can ensure can perform smoothly, and can realize rollback and fault recovery.By counter, program execution is monitored, can recover in time when program gets muddled, to guarantee the normal operation of program.The multiple repairing weld of ECU (Electrical Control Unit) to sensor is averaged, and can ensure the accuracy of sensor data acquisition.Aviation piston type engine redundance type ECU (Electrical Control Unit) of the present invention can improve the safety and stability of engine operation in the application.
Embodiment
Referring to specific embodiment, the present invention will be described in detail.
Aviation piston type engine redundance type ECU (Electrical Control Unit) of the present invention, redundancy backup is arranged to the data stored in the RAM of ECU (Electrical Control Unit), and redundancy backup is not connected with the storage address of former data, redundancy backup and former data synchronization updating, when interference occurs and intercepts program error processing section, the content of redundancy backup is covered former data position; The program performed in ECU (Electrical Control Unit) is split as multiple module and module I D register is set, each module performs simple function, and each module only arranges an outlet, for No. ID of the unique correspondence of each block configuration, before module corresponding function is finished Returning outlet, send correspondence No. ID into ID register, whether correctly judge in ID register No. ID, as No. ID incorrect by program intercepts to initialization segments or program error processing section; Program counter is provided with in ECU (Electrical Control Unit), when there is timer interrupt in program process, "+1 " action is carried out to program counter, during normal work, ECU (Electrical Control Unit) interval sends clear command to counter, ECU (Electrical Control Unit) is resetted when non-normal working occurs and count value reaches maximum; In ECU (Electrical Control Unit) work, all multiple repairing weld is carried out to each sensor, and sampling is averaged as the data of sensor collection.
In RAM, the redundancy backup of data is multiple, and the storage address of each redundancy backup is not connected mutually; When disturb occur and intercept program error processing section time, the existing data of the data of each redundancy backup and former data position are compared, adopt the mode decided by vote to select the data that occupy the majority and cover the position of former data.Further increased the Security of data by the method for multiple redundancy backup, greatly improve the Security of data in RAM.
Between the difference in functionality module of program, non-operation instruction and breakpoint are set, and carry out scene reservation.Make the running of each module keep synchronous by non-operation instruction, and the setting of breakpoint also establish corresponding program restoring running point.
Counter in ECU (Electrical Control Unit) is separate counters, with avoid breaking in a program enabler flags no longer Flushing status time the counter that causes malfunctioning.
In aviation piston type engine redundance type ECU (Electrical Control Unit) of the present invention, by carrying out redundancy optimization to realize saving oneself of RAM to the RAM data storage structure in ECU (Electrical Control Unit), can recover RAM data when former data are destroyed in time and correct.And program is divided into multiple module and non-operation instruction and breakpoint are set between disparate modules, the program that can ensure can perform smoothly, and can realize rollback and fault recovery.By counter, program execution is monitored, can recover in time when program gets muddled, to guarantee the normal operation of program.The multiple repairing weld of ECU (Electrical Control Unit) to sensor is averaged, and can ensure the accuracy of sensor data acquisition.Aviation piston type engine redundance type ECU (Electrical Control Unit) of the present invention can improve the safety and stability of engine operation in the application.
The above, it is only preferred embodiment of the present invention, not any pro forma restriction is done to the present invention, although the present invention with preferred embodiment openly as above, but, and be not used to limit the present invention, any those skilled in the art, do not departing within the scope of technical solution of the present invention, certainly the technology contents of announcement can be utilized to make a little change or modification, become the Equivalent embodiments of equivalent variations, in every case be the content not departing from technical solution of the present invention, according to any simple modification that technical spirit of the present invention is done above embodiment, equivalent variations and modification, all belong in the scope of technical solution of the present invention.
Claims (4)
1. an aviation piston type engine redundance type ECU (Electrical Control Unit), it is characterized in that: redundancy backup is arranged to the data stored in the RAM of ECU (Electrical Control Unit), and redundancy backup is not connected with the storage address of former data, redundancy backup and former data synchronization updating, when interference occurs and intercepts program error processing section, the content of redundancy backup is covered former data position; The program performed in ECU (Electrical Control Unit) is split as multiple module and module I D register is set, each module performs simple function, and each module only arranges an outlet, for No. ID of the unique correspondence of each block configuration, before module corresponding function is finished Returning outlet, send correspondence No. ID into ID register, whether correctly judge in ID register No. ID, as No. ID incorrect by program intercepts to initialization segments or program error processing section; Program counter is provided with in ECU (Electrical Control Unit), when there is timer interrupt in program process, "+1 " action is carried out to program counter, during normal work, ECU (Electrical Control Unit) interval sends clear command to counter, ECU (Electrical Control Unit) is resetted when non-normal working occurs and count value reaches maximum; In ECU (Electrical Control Unit) work, all multiple repairing weld is carried out to each sensor, and sampling is averaged as the data of sensor collection.
2. aviation piston type engine redundance type ECU (Electrical Control Unit) according to claim 1, is characterized in that: in RAM, the redundancy backup of data is multiple, and the storage address of each redundancy backup is not connected mutually; When disturb occur and intercept program error processing section time, the existing data of the data of each redundancy backup and former data position are compared, adopt the mode decided by vote to select the data that occupy the majority and cover the position of former data.
3. aviation piston type engine redundance type ECU (Electrical Control Unit) according to claim 1 and 2, is characterized in that: arrange non-operation instruction and breakpoint between the difference in functionality module of program, and carries out scene reservation.
4. aviation piston type engine redundance type ECU (Electrical Control Unit) according to claim 3, is characterized in that: the counter in ECU (Electrical Control Unit) is 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 |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510684865.9A CN105298665B (en) | 2015-10-22 | 2015-10-22 | Aviation piston type engine redundance type ECU |
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| CN105298665A true CN105298665A (en) | 2016-02-03 |
| CN105298665B CN105298665B (en) | 2018-02-23 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201510684865.9A Active CN105298665B (en) | 2015-10-22 | 2015-10-22 | Aviation piston type engine redundance type ECU |
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Cited By (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 |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US7257813B1 (en) * | 1997-07-19 | 2007-08-14 | Robert Bosch Gmbh | System and method for a control unit with a scheduler preventing simultaneous activation of modules from interference |
| CN101030073A (en) * | 2007-03-30 | 2007-09-05 | 哈尔滨工程大学 | Switch circuit for engine redundant electrically-controlled system and its controlling method |
| CN101705872A (en) * | 2009-11-10 | 2010-05-12 | 南京航空航天大学 | FPGA-based distributed aeroengine electronic controller in chip and control method |
| US20110239992A1 (en) * | 2008-12-12 | 2011-10-06 | Thielert Aircraft Engines Gmbh | Engine Control System For An Aircraft Diesel Engine |
| CN104238435A (en) * | 2014-05-27 | 2014-12-24 | 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 active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US7257813B1 (en) * | 1997-07-19 | 2007-08-14 | Robert Bosch Gmbh | System and method for a control unit with a scheduler preventing simultaneous activation of modules from interference |
| CN101030073A (en) * | 2007-03-30 | 2007-09-05 | 哈尔滨工程大学 | Switch circuit for engine redundant electrically-controlled system and its controlling method |
| US20110239992A1 (en) * | 2008-12-12 | 2011-10-06 | Thielert Aircraft Engines Gmbh | Engine Control System For An Aircraft Diesel Engine |
| CN101705872A (en) * | 2009-11-10 | 2010-05-12 | 南京航空航天大学 | FPGA-based distributed aeroengine electronic controller in chip and control method |
| CN104238435A (en) * | 2014-05-27 | 2014-12-24 | 北京航天自动控制研究所 | Triple-redundancy control computer and fault-tolerant control system |
Cited By (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 |
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| CN105298665B (en) | 2018-02-23 |
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