CN109763909A - A kind of unmanned plane electronic fuel injection two-cycle gasoline engine - Google Patents
A kind of unmanned plane electronic fuel injection two-cycle gasoline engine Download PDFInfo
- Publication number
- CN109763909A CN109763909A CN201910105576.7A CN201910105576A CN109763909A CN 109763909 A CN109763909 A CN 109763909A CN 201910105576 A CN201910105576 A CN 201910105576A CN 109763909 A CN109763909 A CN 109763909A
- Authority
- CN
- China
- Prior art keywords
- throttle
- engine
- air
- control unit
- sensor
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
- 239000000446 fuel Substances 0.000 title claims abstract description 33
- 238000002347 injection Methods 0.000 title claims abstract description 23
- 239000007924 injection Substances 0.000 title claims abstract description 23
- 239000003921 oil Substances 0.000 claims abstract description 37
- 239000000295 fuel oil Substances 0.000 claims abstract description 12
- RZVHIXYEVGDQDX-UHFFFAOYSA-N 9,10-anthraquinone Chemical compound C1=CC=C2C(=O)C3=CC=CC=C3C(=O)C2=C1 RZVHIXYEVGDQDX-UHFFFAOYSA-N 0.000 claims abstract description 5
- 239000000203 mixture Substances 0.000 claims description 2
- 239000007921 spray Substances 0.000 claims description 2
- 230000005611 electricity Effects 0.000 description 3
- 230000007704 transition Effects 0.000 description 3
- 230000008859 change Effects 0.000 description 2
- 238000013461 design Methods 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- 238000005299 abrasion Methods 0.000 description 1
- 230000001133 acceleration Effects 0.000 description 1
- 210000001367 artery Anatomy 0.000 description 1
- 230000008901 benefit Effects 0.000 description 1
- 238000002485 combustion reaction Methods 0.000 description 1
- 230000006835 compression Effects 0.000 description 1
- 238000007906 compression Methods 0.000 description 1
- 238000005260 corrosion Methods 0.000 description 1
- 230000007797 corrosion Effects 0.000 description 1
- 238000011161 development Methods 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 230000006872 improvement Effects 0.000 description 1
- 238000012423 maintenance Methods 0.000 description 1
- 238000005259 measurement Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000008569 process Effects 0.000 description 1
- 230000009467 reduction Effects 0.000 description 1
- 239000000243 solution Substances 0.000 description 1
- 210000003462 vein Anatomy 0.000 description 1
Landscapes
- Electrical Control Of Air Or Fuel Supplied To Internal-Combustion Engine (AREA)
- Control Of Vehicle Engines Or Engines For Specific Uses (AREA)
Abstract
The invention discloses a kind of unmanned plane electronic fuel injection two-cycle gasoline engines, including engine cylinder body, crankcase, air-throttle assemble, atomizer, high-pressure mini oil pump, sensor, ignition, electronic control unit and throttle steering engine, the different data for each sensor that the electronic control unit is used to provide when acquiring engine start, the throttle signal that system for flight control computer provides is received simultaneously, by operation, the opening angle signal of fuel supply signal and air throttle to oil outlet pump, the open angle of air throttle and the switching frequency of atomizer are controlled by throttle steering engine.The present invention replaces diaphragm type carburator with air throttle, is controlled fuel oil according to the real-time working condition of engine using fuel oil intake port injection mode and is accurately ejected into crankcase, improved fuel efficiency, reduces oil consumption and improve the stability and reliability of engine operation.Electronic control unit is furnished with ambient pressure sensor, makes engine also can steady operation under high altitude environment.
Description
Technical field
The present invention be it is a set of aim at the two-cycle gasoline engine that unmanned plane uses and specially design and develop, using micro computer
Electronically controlled fuel oil cylinder injection system.
Background technique
Majority mostly uses two-stroke reciprocating piston engine using fuel engines as the unmanned plane of power at present.But
The supply mode overwhelming majority of the two-stroke reciprocating piston gasoline engine fuel oil generally used is using diaphragm type carburetion
Device.It can be referred to as " heart " of engine to the important function of engine.But often carburetor failure in actual use
Rate is very high.Reason has following two points:
(1) since all working characteristic of unmanned vehicle engine is related to carburetor, such as acceleration, transition, oil consumption.
Therefore diaphragm type carburator is in actual work, often because weather conditions, height above sea level, run duration etc. influence, so that
Engine operating condition is often unstable.
(2) quality problems of related components greatly shorten carburetor service life.Such as the reduction of cleannes, increase
Corrosion and abrasion of carburetor components etc..
Diaphragm type two-cycle gasoline engine carburetor, relatively common several phenomena of the failure have: starting difficulty, idling are not
Surely, transition is bad, be short of power, oil leak, oil consumption height etc..70% is accounted for using the failure rate of the engine of diaphragm type carburator.
For unmanned plane, the failure of engine be it is fatal, slightly failure, caused result are exactly air crash.
Summary of the invention
Start in order to solve the above technical problems, the present invention provides a kind of unmanned plane electronic fuel injection two-cycle gasoline
Machine, including engine cylinder body, crankcase, air-throttle assemble, atomizer, high-pressure mini oil pump, sensor, ignition, electricity
Control unit and throttle steering engine, cylinder body, crankcase, air-throttle assemble, atomizer and fuel oil oil pump are sequentially connected composition oil supply system
Closed circuit, ignition is connected with cylinder body, and the air-throttle assemble includes air throttle, throttle steering engine respectively with air throttle
It is electrically connected with atomizer, sensor is connected with electronic control unit and ignition respectively；
The different data for each sensor that the electronic control unit is used to provide when acquiring engine start, receives simultaneously
The throttle signal that system for flight control computer provides, by operation, the opening angle of fuel supply signal and air throttle to oil outlet pump is believed
Number, the open angle of air throttle and the switching frequency of atomizer are controlled by throttle steering engine；
High-pressure mini oil pump is used to receive the fuel supply signal that electronic control unit provides, and calculates charge oil pressure and fuel delivery,
Give atomizer fuel feeding；
The opening angle signal for the air throttle that throttle steering engine is used to provide according to electronic control unit, controls the opening angle of air throttle
Degree.
Preferably, the sensor includes engine temperature sensing unit, air temperature sensor and intake flow sensor.
It preferably, further include ambient pressure sensor, the ambient pressure sensor for acquiring atmospheric pressure in real time
Variation, height above sea level when calculating engine operation correct fuel injection amount automatically.
The present invention be it is a set of aim at the two-cycle gasoline engine that unmanned plane uses and specially design and develop, using micro computer
Electronically controlled fuel oil cylinder injection system.It is the film for the reciprocating piston petrol engine that commercial unmanned plane uses at present
Disadvantages, the development such as starting difficulty existing for chip carburetor, unstable idle speed, transition is bad, be short of power, oil leak, oil consumption height are opened
Electricity controlled fuel injection system.
Diaphragm type carburator is replaced with air throttle, using fuel oil intake port injection mode, according to the real-time working condition of engine,
Control fuel oil be accurately ejected into crankcase, improve fuel efficiency, reduce oil consumption and improve engine operation stability and
Reliability.
Engine temperature sensing unit, air temperature sensor and intake flow sensor are integrated in electric injection system, it is automatically controlled
Unit (ECU) can correct in real time distributive value according to the current operating temperature of environment temperature and engine, charge flow rate, guarantee each
Stable operation under a operating condition.
Electronic control unit (ECU) is furnished with ambient pressure sensor, can acquire the variation of atmospheric pressure in real time, calculate and start
Height above sea level when machine works corrects fuel injection amount automatically, makes engine also can steady operation under high altitude environment.
Detailed description of the invention
Fig. 1 is a kind of structural schematic diagram of unmanned plane electronic fuel injection two-cycle gasoline engine of the present invention.
Fig. 2 is the cut-away view along line A-A in Fig. 1；
1, engine cylinder body in figure, 2, crankcase, 3, air-throttle assemble, 4, atomizer, 5, high-pressure mini oil pump, 6, Hall
Sensor, 7, ignition, 8, electronic control unit, 9, air throttle, 10, throttle steering engine.
Specific embodiment
As shown in Figure 1, 2, the invention discloses a kind of unmanned plane electronic fuel injection two-cycle gasoline engines, including
It is engine cylinder body 1, crankcase 2, air-throttle assemble 3, atomizer 4, high-pressure mini oil pump 5, sensor, ignition 7, automatically controlled
Unit 8 and throttle steering engine 10.
Unmanned plane electronic fuel injection two-cycle gasoline engine passes through cylinder body 1, crankcase 2, air-throttle assemble 3, spray
Oil nozzle 4 and fuel oil oil pump 5 form the closed circuit of oil supply system.Fuel oil is pumped into atomizer 4 by oil pump 5.When engine start,
The enabling signal of engine is sent to electronic control unit 8 and ignition 7 by Hall sensor 6 and other sensors, simultaneously
Send UAV Flight Control System to.
While the different data for each sensor that electronic control unit 8 is provided when acquiring engine start, nothing is received
The throttle signal that man-machine flight control system provides, by operation, the opening angle of fuel supply signal and air throttle 9 to oil outlet pump 5 is believed
Number, the open angle of air throttle 9 and the switching frequency of atomizer 4 are controlled by throttle steering engine 10.
After oil pump 5 receives the fuel supply signal that electronic control unit 8 provides, charge oil pressure and fuel delivery are calculated, gives atomizer 4
Fuel feeding, the switch frequency signal that atomizer 4 is provided according to electronic control unit 8 is to 2 oil spout of crankcase.Throttle steering engine 10 is simultaneously according to electricity
The opening angle signal for the air throttle 9 that control unit 8 provides, controls the opening angle of air throttle 9.
The opening angle signal of air throttle 9 feeds back oil-feed pump 5 further through electronic control unit 8 simultaneously and adjusts injection pressure and oil spout
Amount.Engine controls the revolving speed of engine by opening angle and oil pump 5 the adjustment injection pressure and distributive value of air throttle 9,
Engine changes propeller pulling force by rotation speed change, controls the flight attitude and speed of unmanned plane.
Electric control fuel oil jet system is taken by the air capacity of sensor measurement sucking engine, then suitable gasoline
The mode supply engine of high-pressure injection.Control air and the computer controlled process of gasoline mixing ratio are known as that combustion is controlled electronically
Oil spurts.This fuel system and traditional carburetor have fundamental difference.
Electronic fuel injection system has the advantage that compared with diaphragm type carburator supplies hybrid mode
(1) electronic control technology is used, reduces exhaust pollution, reduces the fuel consumption of engine, can satisfy tightened up
Emission regulation demands.
(2) electronic control unit (ECU) is rapid to the reacting condition of air throttle, changes the maneuvering performance of engine and accelerating ability
It is kind, and it is able to maintain good power performance index；Allow engine to use higher compression ratio, improves the thermal effect of engine
Rate, it is possible to reduce the pinking of engine is inclined to.
(3) adaptability of EFI (EFI) system is stronger, need to only change electronic control unit for the engine of different models
(ECU) " arteries and veins spectrogram " in chip, and same oil pump, nozzle, electronic control unit (ECU) etc. can be used in many different rule
In the product of lattice number, convenient for forming series of products.
(4) engine performance is easy to adjust.
EFI needs special equipment to read electronic control unit (ECU) coding, and the EFI of setting is accurately adjusted by special equipment
Distributive value is accurately fuel-efficient, is atomized, burns, power forced-ventilated is put well, adaptability is good, and height above sea level raising can reduce distributive value point automatically
The fiery time, there is high reliability, maintenance period is long.
Finally, it should be noted that the foregoing is only a preferred embodiment of the present invention, it is not intended to restrict the invention,
Although the present invention is described in detail referring to the foregoing embodiments, for those skilled in the art, still may be used
To modify the technical solutions described in the foregoing embodiments or equivalent replacement of some of the technical features.
All within the spirits and principles of the present invention, any modification, equivalent replacement, improvement and so on should be included in of the invention
Within protection scope.
Claims (3)
1. a kind of unmanned plane electronic fuel injection two-cycle gasoline engine, which is characterized in that including engine cylinder body, crankshaft
Case, air-throttle assemble, atomizer, high-pressure mini oil pump, sensor, ignition, electronic control unit and throttle steering engine, cylinder body,
Crankcase, air-throttle assemble, atomizer and fuel oil oil pump be sequentially connected composition oil supply system closed circuit, ignition with
Cylinder body is connected, and the air-throttle assemble includes air throttle；Throttle steering engine is electrically connected with air throttle and atomizer respectively, sensor point
It is not connected with electronic control unit and ignition, the electronic control unit connection throttle steering engine and high-pressure mini oil pump；
The different data for each sensor that the electronic control unit is used to provide when acquiring engine start, while receiving nobody
The throttle signal that machine flight control system provides, by operation, the opening angle signal of fuel supply signal and air throttle to oil outlet pump leads to
Cross the open angle of throttle steering engine control air throttle and the switching frequency of atomizer；
High-pressure mini oil pump calculates charge oil pressure and fuel delivery, to spray for receiving the fuel supply signal that electronic control unit provides
Oil nozzle fuel feeding；
The opening angle signal for the air throttle that throttle steering engine is used to provide according to electronic control unit, controls the opening angle of air throttle.
2. a kind of unmanned plane electronic fuel injection two-cycle gasoline engine according to claim 1, which is characterized in that
The sensor includes engine temperature sensing unit, air temperature sensor and intake flow sensor.
3. a kind of unmanned plane electronic fuel injection two-cycle gasoline engine according to claim 1, which is characterized in that
It further include ambient pressure sensor, the ambient pressure sensor calculates and starts for acquiring the variation of atmospheric pressure in real time
Height above sea level when machine works corrects fuel injection amount automatically.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910105576.7A CN109763909A (en) | 2019-02-01 | 2019-02-01 | A kind of unmanned plane electronic fuel injection two-cycle gasoline engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910105576.7A CN109763909A (en) | 2019-02-01 | 2019-02-01 | A kind of unmanned plane electronic fuel injection two-cycle gasoline engine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN109763909A true CN109763909A (en) | 2019-05-17 |
Family
ID=66455977
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201910105576.7A Pending CN109763909A (en) | 2019-02-01 | 2019-02-01 | A kind of unmanned plane electronic fuel injection two-cycle gasoline engine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN109763909A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114294116A (en) * | 2021-12-29 | 2022-04-08 | 广东省大湾区集成电路与系统应用研究院 | Two-stroke engine of unmanned aerial vehicle and electric control system and method thereof |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20150152757A1 (en) * | 2012-06-08 | 2015-06-04 | Orbital Australia Pty Ltd | UAV Engine Lubrication System Incorporating an Electric Oil Pump and Lubrication Oil Heating Capability |
| CN108252809A (en) * | 2017-12-27 | 2018-07-06 | 深圳常锋信息技术有限公司 | Power control system and aircraft |
| CN207905958U (en) * | 2018-01-30 | 2018-09-25 | 北京大白科技有限公司 | A kind of novel unmanned vehicle engine electronic fuel atomization system |
| CN109113858A (en) * | 2017-06-22 | 2019-01-01 | 襄阳联航动力技术有限公司 | A kind of electric-control system unmanned plane petrol engine of band list ECU sub-control air throttle |
| CN209959365U (en) * | 2019-02-01 | 2020-01-17 | 北海天际航空科技有限公司 | Electric control fuel injection two-stroke gasoline engine for unmanned aerial vehicle |
-
2019
- 2019-02-01 CN CN201910105576.7A patent/CN109763909A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20150152757A1 (en) * | 2012-06-08 | 2015-06-04 | Orbital Australia Pty Ltd | UAV Engine Lubrication System Incorporating an Electric Oil Pump and Lubrication Oil Heating Capability |
| CN109113858A (en) * | 2017-06-22 | 2019-01-01 | 襄阳联航动力技术有限公司 | A kind of electric-control system unmanned plane petrol engine of band list ECU sub-control air throttle |
| CN108252809A (en) * | 2017-12-27 | 2018-07-06 | 深圳常锋信息技术有限公司 | Power control system and aircraft |
| CN207905958U (en) * | 2018-01-30 | 2018-09-25 | 北京大白科技有限公司 | A kind of novel unmanned vehicle engine electronic fuel atomization system |
| CN209959365U (en) * | 2019-02-01 | 2020-01-17 | 北海天际航空科技有限公司 | Electric control fuel injection two-stroke gasoline engine for unmanned aerial vehicle |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114294116A (en) * | 2021-12-29 | 2022-04-08 | 广东省大湾区集成电路与系统应用研究院 | Two-stroke engine of unmanned aerial vehicle and electric control system and method thereof |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN109973234A (en) | Unmanned plane electronic fuel injection two-cycle gasoline engine | |
| CN106499531B (en) | A kind of twin-jet nozzle gas/liquid double fuel in-cylinder direct-jet internal combustion engine and control method | |
| US4699109A (en) | Closed end fuel injection system | |
| US5791304A (en) | Cylinder wall fuel injection system for cross-scavenged, two-cycle combustion engine | |
| SE431009B (en) | SETTING TO OPERATE AN INCORPORATIVE ENGINE WITH ALTERNATIVE FUEL AND COMBUSTION ENGINE FOR OPERATION WITH ALTERNATIVE FUEL | |
| CN110486151B (en) | Dimethyl ether compression ignition type rotary engine and control method thereof | |
| CN109736937A (en) | A kind of dual ignition plug fuel combination rotor machine and its control method | |
| CN100363605C (en) | Method and apparatus for realizing dual fuel injection of alcohol fuel and oil fuel for combustion | |
| US20140061391A1 (en) | Two-stroke, fuel injected internal combustion engines for unmanned aircraft and associated systems and methods | |
| CN201486647U (en) | Electric control spraying type triangle rotor engine | |
| CN101825027A (en) | Utilize the method and the device of fuel pressure sensor error control fuel rail pressure | |
| CN104929767A (en) | Electric control direct injection multi-fuel two-stroke engine | |
| CN107035577B (en) | The air supply system of gas engine peculiar to vessel | |
| US20240018923A1 (en) | Device for heating fuel | |
| US5259344A (en) | Intermittent fuel-injection method and device for two-stroke engine | |
| CN109763909A (en) | A kind of unmanned plane electronic fuel injection two-cycle gasoline engine | |
| CN204877672U (en) | Automatically controlled many fuel two -cycle engine that directly spouts | |
| CN109538389A (en) | A kind of dual fuel engine system and its control method based on mechanical oil pump feed | |
| US20030024509A1 (en) | Method and apparatus for increasing the delivery of fuel to an engine | |
| CN209959365U (en) | Electric control fuel injection two-stroke gasoline engine for unmanned aerial vehicle | |
| US8683978B2 (en) | Fuel injection system | |
| CN104265482A (en) | Low-pressure-injecting type electric oil injecting system of small petrol engine | |
| CN210317503U (en) | Fuel injection ECU (electronic control unit) of two-stroke gasoline engine for unmanned aerial vehicle | |
| JPS623168A (en) | Fuel injection device for engine | |
| Sogawa et al. | A development of the high pressure direct injection (HPDI) system for two-stroke outboard motor |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination |