CN110504869A - A kind of aviation high-voltage brushless DC motor controller electrifying control circuit and control method - Google Patents
A kind of aviation high-voltage brushless DC motor controller electrifying control circuit and control method Download PDFInfo
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- CN110504869A CN110504869A CN201910854458.6A CN201910854458A CN110504869A CN 110504869 A CN110504869 A CN 110504869A CN 201910854458 A CN201910854458 A CN 201910854458A CN 110504869 A CN110504869 A CN 110504869A
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- power
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- power supply
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- 238000000034 method Methods 0.000 title claims abstract description 20
- 239000004065 semiconductor Substances 0.000 claims abstract description 27
- 230000005611 electricity Effects 0.000 claims abstract description 22
- 230000008569 process Effects 0.000 claims abstract description 9
- 229920006395 saturated elastomer Polymers 0.000 claims description 5
- 230000000630 rising effect Effects 0.000 claims description 2
- 239000000446 fuel Substances 0.000 description 5
- 230000008901 benefit Effects 0.000 description 3
- 238000005516 engineering process Methods 0.000 description 3
- 230000003111 delayed effect Effects 0.000 description 2
- 238000013461 design Methods 0.000 description 2
- 238000012360 testing method Methods 0.000 description 2
- 230000004075 alteration Effects 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 239000003990 capacitor Substances 0.000 description 1
- 230000008859 change Effects 0.000 description 1
- 238000011161 development Methods 0.000 description 1
- 230000013011 mating Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 230000001960 triggered effect Effects 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D47/00—Equipment not otherwise provided for
-
- H—ELECTRICITY
- H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
- H02P—CONTROL OR REGULATION OF ELECTRIC MOTORS, ELECTRIC GENERATORS OR DYNAMO-ELECTRIC CONVERTERS; CONTROLLING TRANSFORMERS, REACTORS OR CHOKE COILS
- H02P6/00—Arrangements for controlling synchronous motors or other dynamo-electric motors using electronic commutation dependent on the rotor position; Electronic commutators therefor
-
- H—ELECTRICITY
- H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
- H02P—CONTROL OR REGULATION OF ELECTRIC MOTORS, ELECTRIC GENERATORS OR DYNAMO-ELECTRIC CONVERTERS; CONTROLLING TRANSFORMERS, REACTORS OR CHOKE COILS
- H02P2207/00—Indexing scheme relating to controlling arrangements characterised by the type of motor
- H02P2207/05—Synchronous machines, e.g. with permanent magnets or DC excitation
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- Engineering & Computer Science (AREA)
- Power Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Control Of Motors That Do Not Use Commutators (AREA)
Abstract
The present invention proposes the control electricity V1 after power supply is converted that a kind of aviation high-voltage brushless DC motor controller electrifying control circuit and control method, aviation high-voltage brushless DC motor controller power on simultaneously, and power supply system exports on electrifying control circuit receiver；The charging of RC circuit, before capacitance voltage rises to V2, metal-oxide-semiconductor is disconnected, and cutting powers to power driving circuit；By adjusting RC parameter, the time for making capacitance voltage rise to V2 is greater than the control chip power up initialization process time；After capacitance voltage rises to V2, driving metal-oxide-semiconductor closure exports control voltage V1 to power driving circuit.The present invention devises electrifying control circuit in control signal output, ensure to control chip before completing power-up initializing, power circuit is in close state always, it effectively avoids that power circuit shoot through failure occurs in power up, improve controller reliability, controller is reduced to the timing requirements of control power supply and power power supply, simplifies aircraft power system power-supply service.
Description
Technical field
The present invention relates to aviation high-voltage brushless DC motor Drive Control Technique field, specially a kind of aviation high pressure without
Brush DC motor control device electrifying control circuit and control method.
Background technique
As China's science and technology of aviation is towards the development of more power technologies, brushless direct current motor is more and more in pump class, machine
Electric and electro-hydraulic actuating system power source uses, such motor is both needed to controller and is driven, and motor controller generally requires
First upper control electricity, then upper power electricity when power supply, to avoid power supply timing mistake, because first after upper power electricity, then upper control electricity, In
Can be unstable due to port status in controller internal control coremaking piece power up initialization process, cause power circuit in controller to occur
The failures such as shoot through, influence mission reliability.
Summary of the invention
The purpose of the present invention is to provide a kind of aviation high-voltage brushless DC motor controllers to power on control technology, with solution
Certainly existing motor controller easily occurs power circuit shoot through failure etc. because of power supply timing mistake and asks in power up
Topic.
The technical solution of the present invention is as follows:
A kind of aviation high-voltage brushless DC motor controller electrifying control circuit, it is characterised in that: including RC electricity
Road, metal-oxide-semiconductor, accurate adjustable voltage benchmark, transistor control circuit；Wherein metal-oxide-semiconductor controls aviation high-voltage brushless DC motor
In power driving circuit power supply；
Aviation high-voltage brushless DC motor controller powers on simultaneously, power supply system on the electrifying control circuit receiver
The control electricity after power supply is converted of output, controls voltage V1；Wherein RC circuit starts to charge, capacitance voltage rise to V2 it
Before, electrifying control circuit output end metal-oxide-semiconductor disconnects, and cutting powers to power driving circuit, makes aviation high-voltage brushless direct current drive
Power circuit in machine is in close state；And by adjusting the RC parameter of RC circuit, make to power on from controller to capacitance voltage
The time for rising to V2 is greater than the power up initialization process time that chip is controlled in controller；
After capacitance voltage rises to V2, control voltage V1 is sent into triode control by accurate adjustable voltage benchmark job
Circuit, control triode are in saturated, metal-oxide-semiconductor control signal are sent into metal-oxide-semiconductor, driving metal-oxide-semiconductor closure will control
Voltage V1 is exported to power driving circuit.
A kind of aviation high-voltage brushless DC motor controller electrification control method, it is characterised in that: including following
Step:
Step 1: aviation high-voltage brushless DC motor controller powers on simultaneously, and the power electricity that power supply system exports on machine is straight
The control electricity for connecing and being added on the power circuit of aviation high-voltage brushless DC motor, and power supply system on machine is exported turns through power supply
It changes corresponding control power supply V1 and V3 into, is exported respectively to electrifying control circuit and control chip；
Step 2: control chip starts power up initialization after receiving V3 power supply power supply, and defeated after completing power-up initializing
Motor control signal is to power driving circuit out；RC circuit in electrifying control circuit starts to fill after receiving V1 power supply power supply
Electricity, capacitance voltage rise to before V2, and electrifying control circuit output end metal-oxide-semiconductor disconnects, and cutting supplies rear class power driving circuit
Electricity is in close state power circuit；And the time that rises to V2 is powered on from controller to capacitance voltage greater than in controller
Control the power up initialization process time of chip；
Step 3: after capacitance voltage rises to V2, control voltage V1 is sent into three poles by accurate adjustable voltage benchmark job
Pipe control circuit, control triode are in saturated, and metal-oxide-semiconductor control signal is sent into metal-oxide-semiconductor, and driving metal-oxide-semiconductor is closed,
Control voltage V1 is exported to power driving circuit, controls the Motor control signal of chip output after power driving circuit,
Output to rear class power circuit, drive motor works normally.
Beneficial effect
For power circuit caused by existing motor controller electrifying timing sequence mistake shoot through easily occurs for the present invention
The problem of, electrifying control circuit is devised in control signal output, it is ensured that chip is controlled before completing power-up initializing, after
Grade power circuit is in close state always, can effectively be avoided that power circuit shoot through failure occurs in power up, be mentioned
The high reliability of controller, reduces controller to the timing requirements of control power supply and power power supply, simplifies aircraft power supply
System power supply design.
Additional aspect and advantage of the invention will be set forth in part in the description, and will partially become from the following description
Obviously, or practice through the invention is recognized.
Detailed description of the invention
Above-mentioned and/or additional aspect of the invention and advantage will become from the description of the embodiment in conjunction with the following figures
Obviously and it is readily appreciated that, in which:
Fig. 1: electrifying control circuit figure；
Fig. 2: electrification control method flow chart.
Specific embodiment
Existing motor controller generally requires first above to control electricity when power supply, then upper power electricity, has strictly to power supply timing
Requirement, once power supply timing mistake, is likely to result in controller failure, reliability is lower.Using motor control of the invention
Device processed can effectively avoid improving control because power circuit shoot through failure easily occurs for power supply timing problem in power up
The reliability of device processed reduces controller to the timing requirements of control power supply and power power supply.
The present invention powers on simultaneously in aviation high-voltage brushless DC motor controller, the power that power supply system on machine is exported
Electricity is applied directly on power circuit, and the control electricity that power supply system on machine exports is converted into 3.3V power supply and 5V electricity through power supply
Source, respectively output to control chip and electrifying control circuit.
Electrifying control circuit is by components such as metal-oxide-semiconductor, triode, accurate adjustable voltage benchmark, diode, resistance, capacitors
It forms, the connection relationship between each component is as shown in Figure 1.
RC circuit in electrifying control circuit starts to charge after receiving 5V power supply power supply, capacitance voltage rise to 2.5V it
Before, electrifying control circuit output end metal-oxide-semiconductor disconnects, and cutting powers to rear class power driving circuit, is in power circuit and closes
State.
Meanwhile controlling after chip receives 3.3V power supply power supply and starting power up initialization, by test, determines and power on initially
Change process about 220ms, control chip is in normal operating conditions after completing power-up initializing, and output motor controls signal to function
Rate driving circuit.It, may accidentally hair control because of the variation of chip port level state but in control chip power up initialization process
Signal processed, but, because electrifying control circuit output end metal-oxide-semiconductor disconnects, cut off to rear class in power up initialization process at this time
Power driving circuit power supply, power driving circuit unpowered, therefore power circuit work will not be triggered.
The RC parameter of RC circuit in electrifying control circuit is adjusted, delay T time (is controlled in the present embodiment after electricity on the controller
Device processed is delayed about 400ms after powering on), capacitance voltage rises to 2.5V, and wherein T duration is greater than the power-up initializing of control chip
The journey time.After capacitance voltage rises to 2.5V, the accurate adjustable voltage benchmark in electrifying control circuit is started to work, by 5V electricity
Transistor control circuit is sent into source, and control triode is in saturated.
Triode operation is sent into electrifying control circuit output end metal-oxide-semiconductor after saturation state, by metal-oxide-semiconductor control signal, drives
Dynamic metal-oxide-semiconductor closure, 5V power supply is exported to power driving circuit, controls the Motor control signal of chip output through power drive
After circuit, output to rear class power circuit, drive motor is worked normally.
Control method flow chart of the present invention is shown in Fig. 2.Flow chart it is simple and clear illustrate this aviation high-voltage brushless direct current
The connection of specific steps and inherence that motor controller electrification control method is implemented.
The present invention is particularly applicable in the matched pump high-voltage brushless DC motor controller of certain model aircraft fuel system
In, data test has been carried out with high-voltage brushless DC motor is mating with the fuel pump controlled.Under different operating conditions, repeatedly
Power on operation is carried out to controller, while electrifying control circuit is tested, determines that control chip is powered on and initialized the time
For 220ms, and electrifying control circuit is according to the parameter of setting, and the 400ms that is delayed exports 5V power supply to power driving circuit, it is ensured that
The reliability that controller powers on, meets design requirement.
The invention has been applied at present on the matched motor controller of Mr. Yu's model aircraft fuel system, technical performance
The requirement for having reached fuel pump meets fuel system general requirement.It is brushless that the invention can also be applied to similar aviation
In DC motor system, there is important military value and economic benefit.
Although the embodiments of the present invention has been shown and described above, it is to be understood that above-described embodiment is example
Property, it is not considered as limiting the invention, those skilled in the art are not departing from the principle of the present invention and objective
In the case where can make changes, modifications, alterations, and variations to the above described embodiments within the scope of the invention.
Claims (2)
1. a kind of aviation high-voltage brushless DC motor controller electrifying control circuit, it is characterised in that: including RC circuit, MOS
Pipe, accurate adjustable voltage benchmark, transistor control circuit；The wherein function in metal-oxide-semiconductor control aviation high-voltage brushless DC motor
Rate drive circuitry；
Aviation high-voltage brushless DC motor controller powers on simultaneously, and power supply system exports on the electrifying control circuit receiver
After power supply is converted control electricity, control voltage V1；Wherein RC circuit starts to charge, before capacitance voltage rises to V2,
Electrifying control circuit output end metal-oxide-semiconductor disconnects, and cutting powers to power driving circuit, makes in aviation high-voltage brushless DC motor
Power circuit be in close state；And by adjusting the RC parameter of RC circuit, make to be powered on from controller to capacitance voltage rising
It is greater than the power up initialization process time of control chip in controller to the time of V2；
After capacitance voltage rises to V2, control voltage V1 is sent into transistor control circuit by accurate adjustable voltage benchmark job,
Control triode is in saturated, metal-oxide-semiconductor control signal is sent into metal-oxide-semiconductor, driving metal-oxide-semiconductor closure will control voltage
V1 is exported to power driving circuit.
2. a kind of aviation high-voltage brushless DC motor controller electrification control method according to claim 1, it is characterised in that: packet
Include following steps:
Step 1: aviation high-voltage brushless DC motor controller powers on simultaneously, and the power electricity that power supply system exports on machine directly adds
It is converted on the power circuit of aviation high-voltage brushless DC motor, and by the control electricity that power supply system on machine exports through power supply
Corresponding control power supply V1 and V3 are exported respectively to electrifying control circuit and control chip；
Step 2: control chip starts power up initialization after receiving V3 power supply power supply, and electricity is exported after completing power-up initializing
Machine control signal is moved to power driving circuit；RC circuit in electrifying control circuit starts to charge after receiving V1 power supply power supply,
Capacitance voltage rises to before V2, and electrifying control circuit output end metal-oxide-semiconductor disconnects, and cutting powers to rear class power driving circuit,
It is in close state power circuit；And power on from controller to capacitance voltage rise to V2 time be greater than controller in control
The power up initialization process time of chip；
Step 3: after capacitance voltage rises to V2, control voltage V1 is sent into triode control by accurate adjustable voltage benchmark job
Circuit processed, control triode are in saturated, metal-oxide-semiconductor control signal are sent into metal-oxide-semiconductor, driving metal-oxide-semiconductor closure will be controlled
Voltage V1 processed is exported to power driving circuit, controls the Motor control signal of chip output after power driving circuit, output
To rear class power circuit, drive motor is worked normally.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910854458.6A CN110504869A (en) | 2019-09-10 | 2019-09-10 | A kind of aviation high-voltage brushless DC motor controller electrifying control circuit and control method |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910854458.6A CN110504869A (en) | 2019-09-10 | 2019-09-10 | A kind of aviation high-voltage brushless DC motor controller electrifying control circuit and control method |
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| CN110504869A true CN110504869A (en) | 2019-11-26 |
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Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101963792A (en) * | 2010-10-29 | 2011-02-02 | 珠海市鑫和电器有限公司 | Time sequence control circuit and control method thereof |
| CN103532533A (en) * | 2012-07-04 | 2014-01-22 | 北京精密机电控制设备研究所 | Power supplying timing sequence management circuit |
| US20170160750A1 (en) * | 2014-08-11 | 2017-06-08 | Amazon Technologies, Inc. | Virtual safety shrouds for aerial vehicles |
-
2019
- 2019-09-10 CN CN201910854458.6A patent/CN110504869A/en active Pending
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101963792A (en) * | 2010-10-29 | 2011-02-02 | 珠海市鑫和电器有限公司 | Time sequence control circuit and control method thereof |
| CN103532533A (en) * | 2012-07-04 | 2014-01-22 | 北京精密机电控制设备研究所 | Power supplying timing sequence management circuit |
| US20170160750A1 (en) * | 2014-08-11 | 2017-06-08 | Amazon Technologies, Inc. | Virtual safety shrouds for aerial vehicles |
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Application publication date: 20191126 |