CN109143959A - A kind of highly reliable anti-interference discrete magnitude output control circuit - Google Patents
A kind of highly reliable anti-interference discrete magnitude output control circuit Download PDFInfo
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- CN109143959A CN109143959A CN201811053928.0A CN201811053928A CN109143959A CN 109143959 A CN109143959 A CN 109143959A CN 201811053928 A CN201811053928 A CN 201811053928A CN 109143959 A CN109143959 A CN 109143959A
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- discrete magnitude
- magnitude signal
- electromagnetic relay
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- 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
- G05B19/00—Programme-control systems
- G05B19/02—Programme-control systems electric
- G05B19/04—Programme control other than numerical control, i.e. in sequence controllers or logic controllers
- G05B19/05—Programmable logic controllers, e.g. simulating logic interconnections of signals according to ladder diagrams or function charts
- G05B19/054—Input/output
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- 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
- G05B2219/00—Program-control systems
- G05B2219/10—Plc systems
- G05B2219/11—Plc I-O input output
- G05B2219/1103—Special, intelligent I-O processor, also plc can only access via processor
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- General Physics & Mathematics (AREA)
- Engineering & Computer Science (AREA)
- Automation & Control Theory (AREA)
- Programmable Controllers (AREA)
Abstract
Disclose a kind of highly reliable anti-interference discrete magnitude output control circuit comprising programmable logic device, latch are driven in the reverse direction isolation circuit, electromagnetic relay and output driving circuit.The circuit is directed on machine under harsh environments and Safety of Flight Requirements, for the high reliability of airborne dynamoelectric signal (such as: being responsible for the state instruction and on/off switch movement of Mechatronic Systems/equipment) processing, it is proposed a kind of solution based on discrete magnitude hardware circuit (that is: signal repeatedly filters, error correcting is handled), while guaranteeing discrete magnitude output control circuit high reliability and high anti-interfering performance, the complexity of system is reduced.
Description
Technical field
The present invention relates to a kind of output control circuits, more particularly, to a kind of highly reliable anti-interference discrete magnitude output control
Circuit processed.
Background technique
As aircraft industry development is advanced by leaps and bounds, the instrument and equipment on aircraft just develops towards more electric-type, all electric direction.It is electromechanical
Control " brain " of the computer as electromechanical equipment on aircraft is managed, needs to handle more and more electromechanical equipment status signals.
And the reliability that the urgency of working environment and Safety of Flight Requirements severe on machine handles dynamoelectric signal propose it is very high
It is required that.
For aircraft utilities signal, switch discrete magnitude signal is a kind of common signal.The transmitting of discrete magnitude signal is used
In the control of aircraft state, it is dispersed throughout the systems such as machinery, unit, power and the fuel of aircraft.Discrete magnitude signal is mostly relay
Double status signals of control, are responsible for the state instruction and switch motion of electromechanical equipment on machine, such as undercarriage control, in cabin respectively
Kind switch state is distributed in the various pieces such as engine, fuel oil, flight control, the electromechanics of aircraft, these switch controls pair
Flight safety is most important, with stringent data certainty requirement.It is different according to subsystem voltage, there are 28V, 15V, 10V etc.
Multiple voltage classification.
As avionics system is increasingly complicated, the discrete magnitude signal quantity for including in system is more and more, discrete magnitude signal
Processing expends more discrete component；Simultaneously because the data certainty of discrete magnitude signal requires, processing circuit need to have data peace
The sophisticated functions such as complete and data location of mistake, these cause equipment volume and complexity to increase, functions of the equipments and volume and power consumption
Contradiction become increasingly conspicuous.
Summary of the invention
Goal of the invention:
Purpose of this disclosure is to provide a kind of highly reliable anti-interference discrete magnitude output control circuits.
Technical solution:
Present disclose provides a kind of discrete magnitude output control circuits, which includes programmable logic
Device, latch are driven in the reverse direction isolation circuit, electromagnetic relay and output driving circuit, in which:
1) programmable logic device obtains the control instruction for requiring it to export the first discrete magnitude signal, discrete by described first
Amount signal is output to latch；
2) latch receive the first discrete magnitude signal from programmable logic device, by first discrete magnitude signal into
Row latches and obtains the second discrete magnitude signal, and the second discrete magnitude signal is output to and is driven in the reverse direction isolation circuit；
3) it is driven in the reverse direction isolation circuit and receives the second discrete magnitude signal from latch, by second discrete magnitude signal
It carries out reverse isolation and obtains third discrete magnitude signal, and third discrete magnitude signal is output to electromagnetic relay；
4) electromagnetic relay receives the third discrete magnitude signal from driving isolation circuit, after 2ms-3ms is delayed, electricity
Magnetic relay is actuated, and obtains the 4th discrete magnitude signal after the completion of actuating in electromagnetic relay, and by the 4th discrete magnitude signal
It is output to output driving circuit；And
5) output driving circuit receives the 4th discrete magnitude signal from electromagnetic relay, and the 4th discrete magnitude signal is defeated
Out to the actuating system on aircraft.
In a preferred embodiment of the disclosure, discrete magnitude output control circuit can further include back production circuit, described
Back production circuit acquires the 4th discrete magnitude signal, and the 4th discrete magnitude signal is fed back to programmable logic device.It is programmable
The 4th discrete magnitude signal fed back can be compared by logical device with the first discrete magnitude signal exported.
In another preferred embodiment of the disclosure, it may include making the electromagnetic relay that electromagnetic relay, which is actuated,
It is switched on or switched off.
The utility model has the advantages that
The disclosure provides a kind of reasonable highly reliable anti-interference discrete magnitude output control circuit, realizes with self-test function
The redundant hardware configuration of energy carries out repeatedly filtering correction false command design side to interference signal on machine in combination with software mode
Method ensure that the high reliability and correctness of discrete magnitude signal output, provide reliable discrete magnitude conversion function, have stronger
Application value improves potentiality of traditional simple designs in terms of reliability.By using the hardware of the disclosure, hardware is simplified
Configuration, is omitted the development process of software.The application of the technology reduces costs so that the R&D cycle of product shortens.
Detailed description of the invention
Fig. 1 is discrete magnitude output circuit functional block diagram；
Fig. 2 is the timing diagram of " latch-interference "；
Fig. 3 is anti-interference filtration timing diagram.
Specific embodiment
Fig. 1 shows the principle of discrete magnitude output control circuit, wherein the discrete magnitude output control circuit includes programmable patrols
It collects device 1, latch 2, be driven in the reverse direction isolation circuit 3, electromagnetic relay 4 and output driving circuit 5, in which:
1) programmable logic device 1 obtain require its export the first discrete magnitude signal control instruction, by described first from
It dissipates amount signal and is output to latch 2；
2) latch 2 receives the first discrete magnitude signal from programmable logic device 1, by first discrete magnitude signal
It is latched to obtain the second discrete magnitude signal, and the second discrete magnitude signal is output to and is driven in the reverse direction isolation circuit 3；
3) it is driven in the reverse direction isolation circuit 3 and receives the second discrete magnitude signal from latch 2, second discrete magnitude is believed
Number carrying out reverse isolation obtains third discrete magnitude signal, and third discrete magnitude signal is output to electromagnetic relay 4；
4) electromagnetic relay 4 receives the third discrete magnitude signal from driving isolation circuit 3, after 2ms-3ms is delayed,
Electromagnetic relay 4 is actuated, and the 4th discrete magnitude signal is obtained after the completion of actuating in electromagnetic relay, and the 4th discrete magnitude is believed
Number it is output to output driving circuit 5；And
5) output driving circuit 5 receives the 4th discrete magnitude signal from electromagnetic relay 4, and by the 4th discrete magnitude signal
The actuating system being output on aircraft.
More specifically, the discrete magnitude output control circuit in Fig. 1 uses programmable logic device 1, the control of input is received
Instruction, by corresponding conditioning circuit, is converted into 1 identifiable input signal (that is: Transistor-Transistor Logic level) of programmable logic device.?
That is kernel access external interface (such as dual port RAM) of programmable logic device 1 and obtaining external interface data (control referring to
Enable), while the first discrete magnitude signal is output to corresponding I/O interface by programmable logic device 1.
Latch 2 is written via I/O interface with digital signal form in first discrete magnitude signal by programmable logic device 1,
Latch 2 latches the first discrete magnitude signal, and the connection of control electromagnetic relay 4 after isolation circuit 3 is driven by reverse phase
Or disconnect, after the completion of electromagnetic relay 4 acts, programmable logic device 1 is by 4 output end signal of electromagnetic relay (that is, the 4th
Discrete magnitude signal) back production carried out by back production circuit 6, programmable logic device 1 by output order (the first discrete magnitude signal) and
Back production instructs (the 4th discrete magnitude signal) to carry out comparison of coherence, realizes and detects to control instruction closed loop.
Since 4 control section of electromagnetic relay is electromagnet, inductance is larger, and there is control signal to change moment,
Flow through the constant characteristic of the electric current of inductance.Electricity when output driving circuit 5 exports " ground connection " state, on machine in relay coil
Stream can gradually rise to normal current (for example, 28V/ DC impedance, is less than 100mA) from 0A；When output driving circuit 5 exports
When " open circuit " state, the electric current on machine in relay coil can gradually drop to 0A from normal current, but since control signal is
Open-circuit condition can not give coil with electric current circuit, thus can generate very high induced electromotive force (about 600V) in the line, lead to
" sparking " is crossed on 4 contact of electromagnetic relay to form voltage Releasing loop.In this case, stronger electromagnetism can be radiated to space
Interference.Response due to electromagnetic relay 4 with about 2ms~6ms is sluggish, and through measuring, interference signal appears in normal latch
After signal at about 2.2ms.The sequential relationship of " latch-interference " is shown in Fig. 2.
When controlling the connection of electromagnetic relay 4, connected after the delay of electromagnetic relay 4 about 2ms, the 4th discrete magnitude signal is normal
Output；When controlling the disconnection of electromagnetic relay 4, the 4th discrete magnitude signal is first exported, and is disconnected after the delay of electromagnetic relay 4 about 2ms,
The contact of electromagnetic relay 4 generates radiation interference because of induced electromotive force " sparking " at this time, and latch signal is in superposition interference signal
After again lead to latch 2 latch, if input data has been flipped at this time, will lead to control signal be flipped, about
Electromagnetic relay 4 is caused to be connected after 2ms.
If big appointment is in 2ms (when the actuating of relay when programmable logic device 1, which controls electromagnetic relay 4, to be disconnected
Between) after can generate the interference of inverse electromotive force to influence latch 2, cause latch 2 to lock abnormal data；Pass through modification
Programmable logic device 1 export instruction, even if this interference effect to latch abnormal locking data, but from be locked to after
Electric appliance movement also needs about 2ms to be delayed, and since 1 secondary control signal is written in the every 1ms of programmable logic device 1, is written 10 times altogether, because
This can be repaired again before the malfunction of electromagnetic relay 4, to guarantee the correct output order of output driving circuit 5.Fig. 3
In anti-interference filtration timing diagram is shown.
Claims (4)
1. a kind of discrete magnitude output control circuit, the discrete magnitude output control circuit includes programmable logic device (1), latches
Device (2) is driven in the reverse direction isolation circuit (3), electromagnetic relay (4) and output driving circuit (5), in which:
1) programmable logic device (1) obtains the control instruction for requiring it to export the first discrete magnitude signal, discrete by described first
Amount signal is output to latch (2)；
2) latch (2) receives the first discrete magnitude signal for coming from programmable logic device (1), by first discrete magnitude signal
It is latched to obtain the second discrete magnitude signal, and the second discrete magnitude signal is output to and is driven in the reverse direction isolation circuit (3)；
3) isolation circuit (3) are driven in the reverse direction and receive the second discrete magnitude signal for coming from latch (2), second discrete magnitude is believed
Number carrying out reverse isolation obtains third discrete magnitude signal, and third discrete magnitude signal is output to electromagnetic relay (4)；
4) electromagnetic relay (4) receives the third discrete magnitude signal from driving isolation circuit (3), after 2ms-3ms is delayed,
Electromagnetic relay (4) is actuated, and obtains the 4th discrete magnitude signal after the completion of actuating in electromagnetic relay, and by the 4th discrete magnitude
Signal is output to output driving circuit (5)；And
5) output driving circuit (5) receives the 4th discrete magnitude signal for coming from electromagnetic relay (4), and by the 4th discrete magnitude signal
The actuating system being output on aircraft.
2. discrete magnitude output control circuit according to claim 1, when programmable logic device (1) controls electromagnetic relay
(4) it disconnects, when generating inverse electromotive force interference so as to cause latch (2) lock function exception, passes through programmable logic device
(1) the first discrete magnitude signal is modified, so that restoring the lock function of latch (2) before electromagnetic relay (4) malfunction
Normally.
3. discrete magnitude output control circuit according to claim 1 further includes back production circuit (6), the back production circuit (6)
The 4th discrete magnitude signal is acquired, and by the 4th discrete magnitude signal feedback to programmable logic device (1), described may be programmed is patrolled
Device (1) is collected to be compared the 4th discrete magnitude signal fed back with the first discrete magnitude signal exported.
4. discrete magnitude output control circuit described in any one of -3 according to claim 1, electromagnetic relay (4) is actuated packet
Including is switched on or switched off the electromagnetic relay (4).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811053928.0A CN109143959A (en) | 2018-09-11 | 2018-09-11 | A kind of highly reliable anti-interference discrete magnitude output control circuit |
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| CN201811053928.0A CN109143959A (en) | 2018-09-11 | 2018-09-11 | A kind of highly reliable anti-interference discrete magnitude output control circuit |
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| CN109143959A true CN109143959A (en) | 2019-01-04 |
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| CN201811053928.0A Pending CN109143959A (en) | 2018-09-11 | 2018-09-11 | A kind of highly reliable anti-interference discrete magnitude output control circuit |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112859658A (en) * | 2019-11-27 | 2021-05-28 | 株洲中车时代电气股份有限公司 | Dry node output control device |
| CN113467318A (en) * | 2021-07-20 | 2021-10-01 | 四川腾盾科技有限公司 | Discrete signal output system and method for unmanned aerial vehicle airplane management computer |
Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101926130A (en) * | 2008-01-24 | 2010-12-22 | 西门子公司 | Method and system for controlling communication network |
| CN201903876U (en) * | 2010-12-27 | 2011-07-20 | 中国航空工业集团公司第六三一研究所 | Circuit board supporting automatic external test equipment |
| CN103034196A (en) * | 2012-12-07 | 2013-04-10 | 陕西千山航空电子有限责任公司 | Open type and universalized design method of plane electromechanical system control |
| CN103092797A (en) * | 2012-12-13 | 2013-05-08 | 中国航空无线电电子研究所 | Device for synchronously controlling discrete magnitude interfaces, and method for acquiring discrete magnitude and controlling output |
| RU2549231C1 (en) * | 2014-01-09 | 2015-04-20 | Открытое акционерное общество "Акционерная Компания "Туламашзавод" | Method of linearised signal shaping on missile rotating by bank angle signal lineariser switchable signal lineariser integration method for linearised signal shaping and digital integrator for its implementation |
| CN204347826U (en) * | 2014-11-28 | 2015-05-20 | 上海航空电器有限公司 | A kind of ground proximity warning computer with modularization self-checking function |
| CN105699798A (en) * | 2014-11-28 | 2016-06-22 | 上海航空电器有限公司 | BIT self-detection method of onboard complex alarm equipment |
| CN108233347A (en) * | 2016-12-14 | 2018-06-29 | 中国航空工业集团公司西安航空计算技术研究所 | A kind of brushless motor controller Over Current Protection System and over-current protection method |
| CN108241359A (en) * | 2017-12-15 | 2018-07-03 | 中国航空工业集团公司西安飞行自动控制研究所 | A kind of failure safe output method based on SAFEBus buses |
-
2018
- 2018-09-11 CN CN201811053928.0A patent/CN109143959A/en active Pending
Patent Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101926130A (en) * | 2008-01-24 | 2010-12-22 | 西门子公司 | Method and system for controlling communication network |
| CN201903876U (en) * | 2010-12-27 | 2011-07-20 | 中国航空工业集团公司第六三一研究所 | Circuit board supporting automatic external test equipment |
| CN103034196A (en) * | 2012-12-07 | 2013-04-10 | 陕西千山航空电子有限责任公司 | Open type and universalized design method of plane electromechanical system control |
| CN103092797A (en) * | 2012-12-13 | 2013-05-08 | 中国航空无线电电子研究所 | Device for synchronously controlling discrete magnitude interfaces, and method for acquiring discrete magnitude and controlling output |
| RU2549231C1 (en) * | 2014-01-09 | 2015-04-20 | Открытое акционерное общество "Акционерная Компания "Туламашзавод" | Method of linearised signal shaping on missile rotating by bank angle signal lineariser switchable signal lineariser integration method for linearised signal shaping and digital integrator for its implementation |
| CN204347826U (en) * | 2014-11-28 | 2015-05-20 | 上海航空电器有限公司 | A kind of ground proximity warning computer with modularization self-checking function |
| CN105699798A (en) * | 2014-11-28 | 2016-06-22 | 上海航空电器有限公司 | BIT self-detection method of onboard complex alarm equipment |
| CN108233347A (en) * | 2016-12-14 | 2018-06-29 | 中国航空工业集团公司西安航空计算技术研究所 | A kind of brushless motor controller Over Current Protection System and over-current protection method |
| CN108241359A (en) * | 2017-12-15 | 2018-07-03 | 中国航空工业集团公司西安飞行自动控制研究所 | A kind of failure safe output method based on SAFEBus buses |
Non-Patent Citations (1)
| Title |
|---|
| 蔡叶芳，邵刚，李昶，谢运祥: "航空离散量输出处理机理及设计实现", 《电子技术应用》 * |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112859658A (en) * | 2019-11-27 | 2021-05-28 | 株洲中车时代电气股份有限公司 | Dry node output control device |
| CN113467318A (en) * | 2021-07-20 | 2021-10-01 | 四川腾盾科技有限公司 | Discrete signal output system and method for unmanned aerial vehicle airplane management computer |
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Application publication date: 20190104 |
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