CN209369938U - A kind of ignition control device and unmanned plane for aero-engine - Google Patents
A kind of ignition control device and unmanned plane for aero-engine Download PDFInfo
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- CN209369938U CN209369938U CN201822127109.8U CN201822127109U CN209369938U CN 209369938 U CN209369938 U CN 209369938U CN 201822127109 U CN201822127109 U CN 201822127109U CN 209369938 U CN209369938 U CN 209369938U
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Abstract
The utility model discloses a kind of ignition control devices and unmanned plane for aero-engine.Ignition control device includes processor chips, voltage detecting sensor, high-voltage capacitance C1 and ignition controller, voltage detecting sensor is connect with processor chips signal, ignition controller is connect with processor chips signal, voltage detecting sensor is used to detect the voltage of high-voltage capacitance C1, ignition controller includes silicon-controlled Q1, triode Q2 and triode Q3, wherein, the base stage of triode Q3 is electrically connected processor chips, the anode of the collector electrical connection DC power supply of triode Q3；In the grounded collector of triode Q3；The base stage and collector of triode Q2 is electrically connected with the anode of DC power supply, the emitter ground connection of triode Q2, the control terminal electrical connection of the silicon-controlled Q1 of the collector of triode Q2.Ignition control device igniting accuracy is high, to improve fuel oil service efficiency.
Description
Technical field
The utility model relates to technical field of aerospace, and in particular to a kind of ignition control device for aero-engine and
Unmanned plane.
Background technique
Aero-engine is that the component of flying power is provided for aircraft, as " heart " of aircraft, is known as " industry
Flower ", directly affect the performance, reliability and economy of aircraft, be the important body of a national science and technology, industry and military capability of the country
It is existing.
The ignition system of aero-engine is the key technology of aero-engine, and when starting engine, power supply is capacitor
Device charging, when the voltage of capacitor reaches default high voltage, capacitor discharge makes spark plug generate spark, which lights hair
The mixture of air and fuel in motivation.The duration of ignition of ignition system and for capacitor power supply power supply it is particularly important,
The efficiency of direct relation fuel oil, the response speed of engine.It is not allowed however, the duration of ignition of existing ignition system holds, causes
Fuel oil service efficiency is relatively low.
Utility model content
The utility model embodiment be designed to provide it is a kind of for the ignition control device of aero-engine and nobody
Machine, the duration of ignition to solve existing ignition system hold inaccurate, the relatively low problem of fuel oil service efficiency.
To achieve the above object, the utility model embodiment provides a kind of ignition control device for aero-engine,
Including processor chips, voltage detecting sensor, high-voltage capacitance C1 and ignition controller, the voltage detecting sensor and processing
The connection of device chip signal, the ignition controller are connect with processor chips signal, and the voltage detecting sensor is for detecting
The voltage of the high-voltage capacitance C1, the ignition controller include silicon-controlled Q1, triode Q2 and triode Q3, wherein
The base stage of the triode Q3 is electrically connected processor chips, and between the base stage and processor chips of triode Q3
Series resistor；The anode of the collector electrical connection DC power supply of triode Q3, and in the collector and DC power supply of triode Q3
Anode between series resistor R2；In the grounded collector of triode Q3；
The base stage of the triode Q2 is electrically connected with the collector of triode Q3, the collector and DC power supply of triode Q2
Anode electrical connection, and the resistance R3 between the base stage and DC power supply of the triode Q2, the emitter of the triode Q2
Ground connection, the collector of the triode Q2 are electrically connected with the control terminal of silicon-controlled Q1.
Preferably, it is grounded after series resistor R9 between the base stage and collector of triode Q3.
Preferably, the processor chips are STM32F407VG chip, the base stage and the processing of the triode Q3
54th pin PB15 of device chip is electrically connected.
Preferably, the ignition controller further includes two-phase diode D7 and diode D3, the two-phase diode D7's
Both ends are electrically connected the anode and cathode of silicon-controlled Q1, the plus earth of silicon-controlled Q1, and the cathode of silicon-controlled Q1 is electrically connected high
The cathode of voltage capacitance C1, the plus earth of diode D3, diode D3 are electrically connected high-voltage capacitance C1 and ignition coil P1.
Wherein, the ignition control device for aero-engine further includes power supply and transformer, the power supply
Power supply is used to the voltage of the power supply being changed into 12V for providing electric energy, the transformer.
Preferably, series diode D1 and diode D2, Er Qiesuo between the output end of transformer and high-voltage capacitance C1
State diode D1 cathode electrical connection transformer T2 one end, the diode D1 anode electrical connection diode D2 cathode, two
The anode of pole pipe D2 is electrically connected one end of the high-voltage capacitance C1.
Preferably, electric connection resistance R1, third capacitor C3 and diode D4 between two input terminals of transformer T2,
One end of resistance R1 and third capacitor C3 are electrically connected with the first input end of transformer T2, the anode electricity of the other end and diode D4
Connection, the second input terminal of the cathode electrical connection transformer T2 of diode D4.
Wherein, the ignition control device for aero-engine further includes the of the first chip U1, the first chip U1
Two pin VFB are electrically connected the 53rd pin PB14 of the processing chip U3；The third pin IS and transformation of first chip U1
The feedback current of device T2 connects, and the 4th pin RT/CT of the first chip U1 is electrically connected with the 8th pin VREF of the first chip U1,
The second end of the 6th pin OUTPUT electrical connection transformer T2 of first chip U1.
Wherein, field-effect tube is provided between the 6th pin OUTPUT and the second end of transformer T2 of the first chip U1
M1, resistance R5 and diode D6, series resistor between the grid of field-effect tube M1 and the 6th pin OUTPUT of the first chip U1
R5, diode D6 are in parallel with resistance R5；The second end of the grid electrical connection transformer T2 of field-effect tube M1；The leakage of field-effect tube M1
Series resistor R7 between pole and ground is arranged in parallel capacitor C8 at the both ends of resistance R7；Two-phase is set between transformer T2 and ground
Diode D5.
In addition, the utility model embodiment also provides a kind of unmanned plane, including ignition control device, the ignition control dress
It sets using ignition control device provided by the embodiment of the utility model.
The utility model embodiment has the advantages that
Ignition control device provided by the embodiment of the utility model for aero-engine will be located by ignition controller
The firing command of reason device chip output is transmitted to silicon-controlled Q1, that is, passes through triode Q2 and triode Q3 for firing command signal
It is transmitted to silicon-controlled Q1, high-voltage capacitance C1 electric discharge is controlled by silicon-controlled Q1, when the high-voltage capacitance of voltage detecting sensor feedback
The voltage of C1, when the voltage of high-voltage capacitance C1 reaches predeterminated voltage, processor chips export firing command, make silicon-controlled Q1's
Turn-on time is more accurate, to improve the accuracy of the duration of ignition, and then improves fuel oil service efficiency.
Detailed description of the invention
Fig. 1 is the functional block diagram for the ignition control device for aero-engine that the utility model embodiment 1 provides.
Processor chips in the ignition control device for aero-engine that Fig. 2 provides for the utility model embodiment 1
Structural schematic diagram.
Ignition controller in the ignition control device for aero-engine that Fig. 3 provides for the utility model embodiment 1
Circuit diagram.
The circuit of power supply in the ignition control device for aero-engine that Fig. 4 provides for the utility model embodiment 1
Figure.
In figure: 1- processor chips, 2- voltage detecting sensor, 3- ignition controller, 4- high-voltage capacitance.
Specific embodiment
The embodiments of the present invention is illustrated by particular specific embodiment below, those skilled in the art can be by this
Content disclosed by specification understands other advantages and effect of the utility model easily.
It should be clear that this specification structure depicted in this specification institute accompanying drawings, ratio, size etc., only to cooperate specification to be taken off
The content shown is not intended to limit the utility model enforceable restriction item so that those skilled in the art understands and reads
Part, therefore do not have technical essential meaning, the modification of any structure, the change of proportionate relationship or the adjustment of size are not influencing
Under the effect of the utility model can be generated and the purpose that can reach, should all still it fall in the revealed technology of the utility model
In the range of Rong get Neng is covered.Meanwhile cited such as "upper", "lower", " left side ", the right side in this specification ", the use of " centre "
Language is merely convenient to being illustrated for narration, rather than to limit the enforceable range of the utility model, the change of relativeness or
Adjustment, under the content of no substantial changes in technology, when being also considered as the enforceable scope of the utility model.
Embodiment 1
The present embodiment provides a kind of ignition control devices for aero-engine.As shown in Figure 1, being used for aero-engine
Ignition control device include processor chips 1, voltage detecting sensor 2, ignition controller 3 and high-voltage capacitance 4, voltage detecting
Sensor 2 is connect with 1 signal of processor chips, and ignition controller 3 is connect with 1 signal of processor chips, voltage detecting sensor 2
For detecting the voltage of high-voltage capacitance 3, and the voltage signal that will test is transmitted to processor chips 1,1 basis of processor chips
The voltage output ignition signal at 3 both ends of high-voltage capacitance, ignition controller 3 ignition signal is transmitted to it is silicon-controlled, and by silicon-controlled
It controls high-voltage capacitance 4 to discharge, to realize igniting.
In the present embodiment, processor chips 1 are STM32F407VG chip, and the 54th by processor chips 1 is drawn
Foot PB15 exports ignition signal.Fig. 2 shows the structural schematic diagrams of processor chips 1.
As shown in figure 3, ignition controller 4 includes silicon-controlled Q1, triode Q2 and triode Q3, wherein
The 54th pin PB15 of the base stage electrical connection processor chips U3 of triode Q3, and in the base stage of triode Q3
The series resistor R8 between processor chips；The anode of the collector electrical connection DC power supply of triode Q3, and in triode Q3
Collector and DC power supply anode between series resistor R2；In the grounded collector of triode Q3；
The base stage of triode Q2 is electrically connected with the collector of triode Q3, and the collector and DC power supply of triode Q2 is just
Pole electrical connection, and the emitter ground connection of the series resistor R3 between the collector and DC power supply of triode Q2, triode Q2, three
The collector of pole pipe Q2 is electrically connected with the control terminal of silicon-controlled Q1.
Preferably, it is grounded after series resistor R9 between the base stage and collector of triode Q3.
As shown in figure 4, ignition controller further includes two-phase diode D7 and diode D3, the both ends point of two-phase diode D7
It is not electrically connected the anode and cathode of silicon-controlled Q1, the cathode of the plus earth of silicon-controlled Q1, silicon-controlled Q1 is electrically connected high-voltage capacitance
The cathode of C1, the plus earth of diode D3, diode D3 are electrically connected high-voltage capacitance C1 and ignition coil coil P1.
In the present embodiment, further include power supply and transformer T2 for the ignition control device of aero-engine, supply
Power supply, usually can be using the DC power supply of 16V as power supply for providing electric energy.Transformer T2 is for the electricity that will power
The voltage in source is changed into 12V.
As shown in figure 4, the series diode D1 and diode D2 between the output end and high-voltage capacitance C1 of transformer T2,
And one end of the cathode electrical connection transformer T2 of diode D1, the anode electrical connection diode D2 cathode of diode D1, two poles
One end of the anode electrical connection high-voltage capacitance C1 of pipe D2.
Electric connection resistance R1, third capacitor C3 and diode D4 between two input terminals of transformer T2, resistance R1 and
One end of third capacitor C3 is electrically connected with the first input end of transformer T2, and the other end is electrically connected with the anode of diode D4, and two
The second input terminal of the cathode electrical connection transformer T2 of pole pipe D4.
The first chip U1 is additionally provided between the first input end and the second input terminal of transformer T2, the first chip U1's
The 53rd pin PB14 of second pin VFB electrical connection processing chip U3；The third pin IS and transformer of first chip U1
The feedback current of T2 connects, and the 4th pin RT/CT of the first chip U1 is electrically connected with the 8th pin VREF of the first chip U1,
The second end of the 6th pin OUTPUT electrical connection transformer T2 of first chip U1.First chip U1 uses model UC2845
Chip.
Preferably, it is concatenated between the 4th pin RT/CT and the 8th pin VREF of the first chip U1 of the first chip U1
Resistance R6 concatenates the 6th capacitor C6 and the 7th capacitor C7 between the both ends and ground of resistance R6 respectively.
It is grounded in the 5th pin of the first chip U1；In the 6th pin OUTPUT and transformer T2 of the first chip U1
It is provided with field-effect tube M1, resistance R5 and diode D6 between second end, the of the grid of field-effect tube M1 and the first chip U1
Series resistor R5 between six pin OUTPUT, diode D6 are in parallel with resistance R5；The grid of field-effect tube M1 is electrically connected transformer
The second end of T2；Series resistor R7 between the drain electrode and ground of field-effect tube M1 is arranged in parallel capacitor C8 at the both ends of resistance R7；
Two-phase diode D5 is set between transformer T2 and ground.
In addition, being provided with the second capacitor C2, the 16th capacitor C16 and the 17th capacitor between DC power supply VCC and ground
C17。
Ignition control device provided in this embodiment for aero-engine passes through ignition controller for processor chips
The firing command of output is transmitted to silicon-controlled Q1, i.e., is transmitted to firing command signal controllably by triode Q2 and triode Q3
Silicon Q1 controls high-voltage capacitance C1 electric discharge, the processor core when the voltage of high-voltage capacitance C1 reaches predeterminated voltage by silicon-controlled Q1
Piece exports firing command, keeps the turn-on time of silicon-controlled Q1 more accurate, to improve the accuracy of the duration of ignition, and then improves combustion
Oily service efficiency.
Embodiment 2
The present embodiment provides a kind of unmanned plane, including ignition control device, ignition control device is provided using embodiment 1
Ignition control device, the detailed construction of ignition control device such as embodiment 1, is repeating no more.
The unmanned plane is due to the ignition controller provided using embodiment 1, and the duration of ignition is more accurate, and improving fuel oil makes
Use efficiency.
Although above having made detailed description to the utility model with generality explanation and specific embodiment,
On the basis of the utility model, it can be made some modifications or improvements, this is apparent to those skilled in the art
's.Therefore, these modifications or improvements on the basis of without departing from the spirit of the present invention, belong to the utility model and want
Seek the range of protection.
Claims (10)
1. a kind of ignition control device for aero-engine, including processor chips, voltage detecting sensor, high-voltage capacitance
C1 and ignition controller, the voltage detecting sensor are connect with processor chips signal, the ignition controller and processor
Chip signal connection, the voltage detecting sensor are used to detect the voltage of the high-voltage capacitance C1, which is characterized in that the point
Fiery controller includes silicon-controlled Q1, triode Q2 and triode Q3, wherein
The base stage of the triode Q3 is electrically connected processor chips, and concatenates between the base stage of triode Q3 and processor chips
Resistance R8；The anode of the collector electrical connection DC power supply of triode Q3, and in the collector of triode Q3 and DC power supply
Series resistor R2 between anode；In the grounded collector of triode Q3；
The base stage of the triode Q2 is electrically connected with the collector of the triode Q3, the collector and DC power supply of triode Q2
Anode electrical connection, and the series resistor R3 between the collector and DC power supply of the triode Q2, the triode Q2's
Emitter ground connection, the collector of the triode Q2 are electrically connected with the control terminal of silicon-controlled Q1.
2. the ignition control device according to claim 1 for aero-engine, which is characterized in that triode Q3's
It is grounded after series resistor R9 between base stage and collector.
3. the ignition control device according to claim 1 for aero-engine, which is characterized in that the processor core
Piece is STM32F407VG chip, and the base stage of the triode Q3 is electrically connected with the 54th pin PB15 of the processor chips
It connects.
4. the ignition control device according to claim 1 for aero-engine, which is characterized in that the ignition control
Device further includes that the both ends of two-phase diode D7 and diode D3, the two-phase diode D7 are electrically connected the anode of silicon-controlled Q1
And cathode, the plus earth of silicon-controlled Q1, the cathode electrical connection high-voltage capacitance C1 of silicon-controlled Q1, the plus earth of diode D3,
The cathode of diode D3 is electrically connected high-voltage capacitance C1 and ignition coil P1.
5. the ignition control device according to claim 1 for aero-engine, which is characterized in that described to be used for aviation
The ignition control device of engine further includes power supply and transformer, and the power supply is for providing electric energy, the transformation
Device is used to the voltage of the power supply being changed into 12V.
6. the ignition control device according to claim 5 for aero-engine, which is characterized in that in the defeated of transformer
Series diode D1 and diode D2 between outlet and high-voltage capacitance C1, and the cathode of the diode D1 is electrically connected transformer
One end of T2, the anode of the diode D1 are electrically connected the diode D2 cathode, the anode electrical connection institute of the diode D2
State one end of high-voltage capacitance C1.
7. the ignition control device according to claim 6 for aero-engine, which is characterized in that transformer T2's
Electric connection resistance R1, third capacitor C3 and diode D4 between two input terminals, one end and change of resistance R1 and third capacitor C3
The first input end of depressor T2 is electrically connected, and the other end is electrically connected with the anode of diode D4, and the cathode of diode D4, which is electrically connected, to be become
The second input terminal of depressor T2.
8. the ignition control device according to claim 6 for aero-engine, which is characterized in that described to be used for aviation
The ignition control device of engine further includes that the second pin VFB of the first chip U1, the first chip U1 is electrically connected the processor
53rd pin PB14 of chip；The third pin IS of first chip U1 is connect with the feedback current of transformer T2, the first core
The 4th pin RT/CT of piece U1 is electrically connected with the 8th pin VREF of the first chip U1, the 6th pin of the first chip U1
The second end of OUTPUT electrical connection transformer T2.
9. the ignition control device according to claim 8 for aero-engine, which is characterized in that in the first chip U1
The 6th pin OUTPUT and the second end of transformer T2 between be provided with field-effect tube M1, resistance R5 and diode D6, field effect
Should between the grid of pipe M1 and the 6th pin OUTPUT of the first chip U1 series resistor R5, diode D6 it is in parallel with resistance R5；
The second end of the grid electrical connection transformer T2 of field-effect tube M1；Series resistor R7 between the drain electrode and ground of field-effect tube M1,
The both ends of resistance R7 are arranged in parallel capacitor C8；Two-phase diode D5 is set between transformer T2 and ground.
10. a kind of unmanned plane, including ignition control device, which is characterized in that the ignition control device uses claim 1-9
Described in any item ignition control devices.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201822127109.8U CN209369938U (en) | 2018-12-18 | 2018-12-18 | A kind of ignition control device and unmanned plane for aero-engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201822127109.8U CN209369938U (en) | 2018-12-18 | 2018-12-18 | A kind of ignition control device and unmanned plane for aero-engine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN209369938U true CN209369938U (en) | 2019-09-10 |
Family
ID=67833338
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201822127109.8U Active CN209369938U (en) | 2018-12-18 | 2018-12-18 | A kind of ignition control device and unmanned plane for aero-engine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN209369938U (en) |
-
2018
- 2018-12-18 CN CN201822127109.8U patent/CN209369938U/en active Active
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| CP03 | Change of name, title or address |
Address after: No. 76-45, Shenbei Road, Shenbei New District, Shenyang City, Liaoning Province 110000 Patentee after: Liaoning Dazhuang UAV Technology Co.,Ltd. Address before: No.76-43, Shenbei Road, Shenbei New District, Shenyang, Liaoning 110000 (gate a) Patentee before: LIAONING ZHUANGLONG UNMANNED AERIAL VEHICLE TECHNOLOGY Co.,Ltd. |