CN108614179A - A kind of aviation electric detonator remote control and real-time detection circuit - Google Patents
A kind of aviation electric detonator remote control and real-time detection circuit Download PDFInfo
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- CN108614179A CN108614179A CN201611139699.5A CN201611139699A CN108614179A CN 108614179 A CN108614179 A CN 108614179A CN 201611139699 A CN201611139699 A CN 201611139699A CN 108614179 A CN108614179 A CN 108614179A
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- electric detonator
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- back production
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01R—MEASURING ELECTRIC VARIABLES; MEASURING MAGNETIC VARIABLES
- G01R31/00—Arrangements for testing electric properties; Arrangements for locating electric faults; Arrangements for electrical testing characterised by what is being tested not provided for elsewhere
- G01R31/50—Testing of electric apparatus, lines, cables or components for short-circuits, continuity, leakage current or incorrect line connections
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Abstract
The present invention relates to onboard remote interfacing fields, and in particular to a kind of aviation electric detonator remote control and real-time detection circuit.The present invention adds the long-range duplicate protection control function of low side control realization aviation electric detonator by high-end control.When Single Point of Faliure occurs for high-end control terminal and low side control terminal any one end, quick-fried electric detonator will not be misquoted, it ensure that the high security of aviation electric detonator control, have electric detonation tube short circuit and break monitoring function, the state that electric detonator can be monitored in real time by disconnection fault testing mechanism ensure that the high availability of aviation electric detonator.The present invention has complete BIT testing mechanisms.Complete detection can be carried out to the short circuit of the height control terminal and electric detonator itself of electric detonator and open circuit fault, ensure that the high test coverage of aviation electric detonator control.
Description
Technical field
The present invention relates to the electric detonator interfacings of aviation remote interface, and in particular to a kind of aviation electric detonator is remotely controlled
System and real-time detection circuit.
Background technology
Aviation electric detonator is mainly used in aviation cockpit automatic fire extinguisher, has simple in structure, small, weight
Gently, long lifespan can tolerate the plurality of advantages of a variety of adverse circumstances.By the remote control to aviation electric detonator, can beat automatically
Fire-suppression bottle is opened, spraying fire-extinguishing agent achievees the purpose that cabin is put out a fire, protects aircraft safety.
Overwhelming majority aviation electric detonator is using Detonating mode of direct current mode at present, by injecting ignition energy to electric detonator,
It ignites inner fuel, realizes the automatic-explosion sprinkling of extinguishing chemical.The ignitor firing time of electric detonator is extremely short, and general ignitor firing time is in several ms
To between tens ms.
Cockpit automatic fire extinguisher plays the safety of aircraft vital, and the control of electric detonator should ensure just
It will not be misquoted in the case of often quick-fried, it is also necessary to high availability when ensureing really to be abnormal situation.It is unused for a long time on machine
When to electric detonator, the equiva lent impedance of electric detonator can change at any time, it is therefore desirable to design a kind of high security high availability
Has the electric detonator circuit for remotely controlling for improving state-detection mechanism.
Invention content
Has the electric detonator remote control for improving state-detection mechanism the present invention provides a kind of high security high availability
Circuit.
A kind of aviation electric detonator circuit for remotely controlling, including sampling resistor, PMOS tube, overcurrent monitoring unit, 28V/ open from
Dissipate amount output control unit, 28V/ open discrete magnitude output back production unit, NMOS tube ,/open discrete magnitude output back production unit and ground/
Open discrete magnitude output control unit, wherein sampling resistor, PMOS tube, overcurrent monitoring unit and 28V/ open discrete magnitude output control
The high-end remote control terminal of unit composition, NMOS tube and ground/open discrete magnitude output control unit composition low side remote control terminal.
28V power flow concentrations item obtains power supply from aircraft, by the sampling for being serially connected in overcurrent monitoring unit on output channel
Resistance R reaches the ends S of PMOS tube, and 28V/ opens the ends G of discrete magnitude output control unit connection PMOS tube, and the ends D of PMOS tube are also logical
It crosses External cable and is connected to the high-end of distal end electric detonator, the back production of the low side of electric detonator and ground/open discrete magnitude output back production unit
Point and the ends D of NMOS tube connect, and the ends S of NMOS tube connect with Power Groud, and the ends G of NMOS tube and ground/open discrete magnitude output control
Unit connects, overcurrent monitoring unit, 28V/ open discrete magnitude output control unit, 28V/ opens discrete magnitude output back production unit ,/open
Discrete magnitude export back production unit and/open discrete magnitude output control unit and connect with FPGA.It is controlled in high-end control terminal and low side
When end opens simultaneously, complete current path is formed, and electric detonator, which is realized, to be ignited.
28V/ open discrete magnitude output back production unit and ground/open discrete magnitude output back production unit can be to current reality output shape
State is acquired, and when currently practical output state is inconsistent with coomand mode, can be uploaded current failure and be judged with assist trouble.
A kind of electric detonator existence detection circuit, including pull-up voltage cell, ground/open discrete magnitude output back production unit
Partial circuit is pulled up, 28V/ opens the drop-down partial circuit and electric detonator existence voltage monitoring list of discrete magnitude output control unit
Member.Pull-up voltage cell provides+15V pull-up power supplies.The pull-up partial circuit of ground/open discrete magnitude output back production unit provides
The pull-up power supply changed with airborne power power-supply.The drop-down partial circuit that 28V/ opens discrete magnitude output control unit provides drop-down
Resistance.Electric detonator existence voltage monitoring unit provides pull down resistor and partial pressure collection point.
A kind of aviation electric detonator BIT fault detection methods, detection method includes the following steps by the BIT：First to electric detonator
Existence is monitored, if electric detonator exist, timesharing carry out high-end 28V/ open discrete magnitude output control unit output and
Back production, with then carrying out low side/open the output and back production of discrete magnitude output control unit, if the output state of actual circuit and defeated
It is consistent to go out order, then it is assumed that BIT detections are normal；Otherwise, it is determined that BIT exceptions and reporting BIT fault messages.
Description of the drawings
Fig. 1 is high-end and low side duplicate protection circuit for remotely controlling principle schematic.
Fig. 2 is electric detonator existence detection circuit schematic diagram.
Specific implementation mode
The technical program is described in further details below in conjunction with the accompanying drawings.
A kind of aviation electric detonator circuit for remotely controlling, airborne power flow concentration 28V power supplys, sampling resistor, PMOS tube, electric detonation
Pipe itself, NMOS tube constitute complete current path.Single-ended control circuit is avoided by high-end and low side dual control circuit
Electric detonator is caused to misquote quick-fried generation when breaking down.Its middle and high end and low side driving interface individually have the electric current of 5A or more
Driving capability, and there is overcurrent detectability, the short-circuit protection reaction time is inversely proportional with overcurrent multiple.It is to avoid energy simultaneously
It is quick-fried that amount accumulation causes electric detonator to misquote, and high-end and low side driving interface leakage current is respectively less than 0.25mA.High-end and low side is dual
Remote protection control circuit diagram is shown in Fig. 1.
When carrying out electric detonator guiding detonating controlling, the minimum ignition that electric detonator should be met to the energy of electric detonator injection is wanted
It asks, while ensureing complete machine safety again, the energy on saving machine, therefore time control is ignited by electric detonator, ignition energy is carried out
Control.
It is 30ms that electric detonator, which is ignited time control, after height control terminal sends out electric detonator ignition order, in any case
30ms is necessary to switch off external output.Requirement with reference to national military standard to airborne power flow concentration 17V~32V ranges, in external 5A
When aviation electric detonator, the ignition energy externally exported in 30ms is 2.55J~4.8J.The ignition energy can both ensure external electrical
Booster can be by successful detonation, while in turn ensuring aircraft safety.
A kind of aviation electric detonator circuit for remotely controlling, including sampling resistor, PMOS tube, overcurrent monitoring unit, 28V/ open from
Dissipate amount output control unit, 28V/ open discrete magnitude output back production unit, NMOS tube ,/open discrete magnitude output back production unit and ground/
Open discrete magnitude output control unit, wherein sampling resistor, PMOS tube, overcurrent monitoring unit and 28V/ open discrete magnitude output control
The high-end remote control terminal of unit composition, NMOS tube and ground/open discrete magnitude output control unit composition low side remote control terminal.
28V power flow concentrations item obtains power supply from aircraft, by the sampling for being serially connected in overcurrent monitoring unit on output channel
Resistance R reaches the ends S of PMOS tube, and 28V/ opens the ends G of discrete magnitude output control unit connection PMOS tube, and the ends D of PMOS tube are also logical
It crosses External cable and is connected to the high-end of distal end electric detonator, the back production of the low side of electric detonator and ground/open discrete magnitude output back production unit
Point and the ends D of NMOS tube connect, and the ends S of NMOS tube connect with Power Groud, and the ends G of NMOS tube and ground/open discrete magnitude output control
Unit connects, overcurrent monitoring unit, 28V/ open discrete magnitude output control unit, 28V/ opens discrete magnitude output back production unit ,/open
Discrete magnitude export back production unit and/open discrete magnitude output control unit and connect with FPGA.It is controlled in high-end control terminal and low side
When end opens simultaneously, complete current path is formed, and electric detonator, which is realized, to be ignited.
28V/ open discrete magnitude output back production unit and ground/open discrete magnitude output back production unit can be to current reality output shape
State is acquired, and when currently practical output state is inconsistent with coomand mode, can be uploaded current failure and be judged with assist trouble.
A kind of electric detonator existence detection circuit includes pull-up voltage cell, ground/open discrete magnitude output back production unit
Partial circuit is pulled up, 28V/ opens the drop-down partial circuit and electric detonator existence voltage monitoring list of discrete magnitude output control unit
Member.Pull-up voltage cell provides+15V pull-up power supplies.The pull-up partial circuit of ground/open discrete magnitude output back production unit provides
The pull-up power supply changed with airborne power power-supply.The drop-down partial circuit that 28V/ opens discrete magnitude output control unit provides drop-down
Resistance.Electric detonator existence voltage monitoring unit provides pull down resistor and partial pressure collection point.
The schematic diagram of the electric detonator existence detection circuit can be found in Fig. 2.Wherein, pull-up power supply VWET, resistance R1,
R2, R3, R4, R5 and diode V3, V4, V5 constitute the pull-up partial circuit of ground/open discrete magnitude output back production unit.On+15V
Power supply is drawn, resistance R6, diode V6 constitute pull-up voltage cell.Resistance R7, R8, R9, R10 and diode V7 constitute 28V/
Open the drop-down partial circuit of discrete magnitude output control unit.Resistance R11, R12, R13 and R14 constitute electric detonator existence electricity
Press monitoring unit.
Ground/open in the pull-up partial circuit that discrete magnitude exports back production, pull-up voltage is positive successively on the VWET of 28V passes through three
Then diode V3, V4 and V5 pass through pull-up resistor R1 and pull-up resistor R2, with input current-limiting resistance R5 and drop-down divider resistance
R3 common points are connected.By-pass current branch reaches the negative terminal of pull-up voltage cell V6, another way by-pass current point by R5 all the way
Branch is grounded by divider resistance R4.After+15V pull-up power supplies are by pull-up resistor R6 in pull-up voltage cell, then pass through counnter attack two
The low side of pole pipe V6 and R5, the ends D of NMOS tube, electric detonator are connected.I.e. pull-up voltage cell and ground/open discrete magnitude output back production list
The pull-up partial circuit of member realizes pull-up in parallel.Pull-up power supply is transferred to electric detonator height by aircraft cable from electric detonator low side
End, the high-end ends D with high-end control terminal PMOS tube of electric detonator, 28V/ open the drop-down partial circuit of discrete magnitude output back production unit
The current-limiting resistance R11 of R7 and R9, electric detonator existence voltage monitoring unit are connected.28V/ opens discrete magnitude output back production unit
Drop-down partial circuit and electric detonator existence voltage monitoring unit form pull-down circuit in parallel, and the two connecting place is public drop-down
Point.The drop-down partial circuit that 28V/ opens discrete magnitude output back production unit includes two bypasses, and bypass 1 is by R7 resistance and R8 electricity
It hinders to ground, bypass 2 is by resistance R9, R10 and diode V7 to ground.In electric detonator existence voltage monitoring unit, from public affairs
Drop-down point is by resistance R11, R12, R13 and R14 to ground altogether, and the tie point of R13 and R14 are as dividing point progress voltage acquisition.
Since the probability that fire occurs on machine is minimum, electric detonator is chronically at idle unused state, vibrated on long-term machine,
The mal-conditions such as high/low temperature can cause electric detonator control terminal wiring loosening, fall, it is therefore desirable to a kind of electric detonator presence prison
Survey mechanism.
By being pulled up using isolation in low side output end, high-end output end acquires the mode of dividing point voltage using drop-down
Realize the monitoring of electric detonator existence.It is correct in external electric detonator wiring, when electric detonator is not ignited and state is normal, pull-up electricity
Source, pull-up resistor, electric detonator itself circuit constitute complete path between pull down resistor and internal simulation ground.If collected point
Pressure point voltage then proves that electric detonator exists and state is normal in normal range (NR)；If collecting dividing point electric voltage exception, prove
Electric detonator existence is abnormal.If after exporting electric detonator initiation command, electric detonator existence is switched to " break " by " presence ",
Then prove electric detonator by successful detonation.Electric detonator existence detection circuit is shown in Fig. 2.
Pull-up circuit ,/open discrete magnitude output circuit, 28V/ opens discrete magnitude output circuit and monitoring voltage collection point constitute
Complicated topological structure.In view of high-end and low side metal-oxide-semiconductor leakage current, each resistance precision difference, upper pull-up voltage+15V
Normal fluctuation range and VWET power power-supplies 17V~32V scope range of the fluctuation of voltage, calculated by superposition theorem, if electric
Booster monitors voltage on-line and is more than 10V and is less than 32V, then it is assumed that electric detonator is online.If electric detonator monitor on-line voltage not with
In upper range, then it is assumed that electric detonator is not online.
A kind of aviation electric detonator BIT fault detection methods, detection method includes the following steps by the BIT：First to electric detonator
Existence is monitored, if electric detonator exist, timesharing carry out high-end 28V/ open discrete magnitude output control unit output and
Back production, with then carrying out low side/open the output and back production of discrete magnitude output control unit, if the output state of actual circuit and defeated
It is consistent to go out order, then it is assumed that BIT detections are normal；Otherwise, it is determined that BIT exceptions and reporting BIT fault messages.
In order to ensure the high availability of electric detonator, standby BIT testing mechanisms are set up.
Electric detonator BIT fault detection mechanisms are as follows：
A. by electric detonator existence detection circuit monitoring voltage, read per 15ms a load voltage and to voltage into
Row judges：If load voltage is more than 10V and is less than 32V, then it is assumed that be successfully tested, otherwise it is assumed that test crash.When continuous 12
Secondary testing result is test crash, then judges that this powers on electric detonator and is not present, there are failures；
If b. the monitoring voltage of electric detonator existence is normal and height control terminal readback is open circuit, respectively to height
Control terminal carries out continuity test；Otherwise it is assumed that this BIT test crash, exits test；
C. continuity test is carried out to high-end control terminal, i.e., by electric detonator 28V/ open walks output 28V and readback, if readback
Value is also 28V ± 0.5V, then high-end control terminal is successfully tested；Otherwise it is assumed that this BIT test crash, exits test and to high-end
Control terminal carries out shutdown operation；
If d. high-end control terminal is successfully tested, low side control terminal continuity test is carried out after the about 109ms that is delayed.By electric detonator
Ground/open walk output ground connection and readback, if readback value is 0 ± 0.5V, low side control terminal is successfully tested；Otherwise it is assumed that this
BIT test crash exits and tests and carry out shutdown operation to low side control terminal；
E. when any time there is interface over current fault, down interface output and reporting fault information.
By above BIT testing mechanisms, short circuit and the open circuit detection of height control terminal and electric detonator are covered, is realized
The telesecurity of electric detonator controls, and improves the safety of aircraft.
Claims (3)
1. a kind of aviation electric detonator circuit for remotely controlling, characterized in that including sampling resistor, PMOS tube, overcurrent monitoring unit,
28V/ opens discrete magnitude output control unit, 28V/ opens discrete magnitude output back production unit, NMOS tube ,/open discrete magnitude output back production
Unit and ground/open discrete magnitude output control unit, wherein sampling resistor, PMOS tube, overcurrent monitoring unit and 28V/ open discrete magnitude
Output control unit constitutes high-end remote control terminal, and NMOS tube and ground/open discrete magnitude output control unit constitute low side and remotely controls
End processed；
28V power flow concentrations item obtains power supply from aircraft, by the sampling resistor for being serially connected in overcurrent monitoring unit on output channel
R reaches the ends S of PMOS tube, and 28V/ opens the ends G of discrete magnitude output control unit connection PMOS tube, and the ends D of PMOS tube are also by outer
Portion's cable is connected to the high-end of distal end electric detonator, the back production point of the low side of electric detonator and ground/open discrete magnitude output back production unit and
The ends D of NMOS tube connect, and the ends S of NMOS tube connect with Power Groud, and the ends G of NMOS tube and ground/open discrete magnitude output control unit
Connection, overcurrent monitoring unit, 28V/ open discrete magnitude output control unit, 28V/ opens discrete magnitude output back production unit ,/open it is discrete
Amount output back production unit and/open discrete magnitude output control unit and connect with FPGA；It is same in high-end control terminal and low side control terminal
When opening, complete current path is formed, and electric detonator, which is realized, to be ignited；
28V/ open discrete magnitude output back production unit and ground/open discrete magnitude output back production unit can to current reality output state into
Row acquisition can upload current failure and be judged with assist trouble when currently practical output state is inconsistent with coomand mode.
2. a kind of aviation electric detonator circuit for remotely controlling as described in claim 1, characterized in that the circuit for remotely controlling
Further include a kind of electric detonator existence detection circuit, which includes pull-up voltage cell, and ground/open discrete magnitude is defeated
Go out the pull-up partial circuit of back production unit, 28V/ open discrete magnitude output control unit drop-down partial circuit and electric detonator there are shapes
State voltage monitoring unit；Pull-up voltage cell provides+15V pull-up power supplies；Ground/open the pull-up portion that discrete magnitude exports back production unit
Parallel circuit provides the pull-up power supply changed with airborne power power-supply；28V/ opens the drop-down part electricity of discrete magnitude output control unit
Road provides pull down resistor；Electric detonator existence voltage monitoring unit provides pull down resistor and partial pressure collection point.
3. a kind of aviation electric detonator BIT fault detection methods, characterized in that detection method includes the following steps by the BIT：Base first
Electric detonator existence detection circuit described in claim 2 is monitored electric detonator existence, if electric detonator exists,
Then timesharing carries out the output and back production that high-end 28V/ opens discrete magnitude output control unit, with then carrying out low side/to open discrete magnitude defeated
Go out the output and back production of control unit, if the output state of actual circuit is consistent with output order, then it is assumed that BIT detections are normal；
Otherwise, it is determined that BIT exceptions and reporting BIT fault messages.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201611139699.5A CN108614179B (en) | 2016-12-12 | 2016-12-12 | Remote control and real-time detection circuit for aviation electric detonator |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201611139699.5A CN108614179B (en) | 2016-12-12 | 2016-12-12 | Remote control and real-time detection circuit for aviation electric detonator |
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| Publication Number | Publication Date |
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| CN108614179A true CN108614179A (en) | 2018-10-02 |
| CN108614179B CN108614179B (en) | 2020-09-22 |
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| CN201611139699.5A Active CN108614179B (en) | 2016-12-12 | 2016-12-12 | Remote control and real-time detection circuit for aviation electric detonator |
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Cited By (5)
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| CN109521294A (en) * | 2018-11-12 | 2019-03-26 | 中国兵器装备集团上海电控研究所 | The signal acquiring system and method for fire-suppression bottle simulation electric detonator |
| CN110672944A (en) * | 2019-09-27 | 2020-01-10 | 中国兵器装备集团上海电控研究所 | Simulation test method, system, medium and equipment suitable for fire extinguishing device detection |
| CN114188187A (en) * | 2021-11-08 | 2022-03-15 | 陕西千山航空电子有限责任公司 | Control signal system |
| CN114336505A (en) * | 2021-12-23 | 2022-04-12 | 中国航空工业集团公司西安航空计算技术研究所 | High-safety aviation electric detonator driving system and control method |
| CN114442715A (en) * | 2021-12-29 | 2022-05-06 | 中国航空工业集团公司西安航空计算技术研究所 | 28V or open-circuit discrete magnitude output circuit |
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| CN108614179B (en) | 2020-09-22 |
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