CN109113858A - A kind of electric-control system unmanned plane petrol engine of band list ECU sub-control air throttle - Google Patents
A kind of electric-control system unmanned plane petrol engine of band list ECU sub-control air throttle Download PDFInfo
- Publication number
- CN109113858A CN109113858A CN201710478011.4A CN201710478011A CN109113858A CN 109113858 A CN109113858 A CN 109113858A CN 201710478011 A CN201710478011 A CN 201710478011A CN 109113858 A CN109113858 A CN 109113858A
- Authority
- CN
- China
- Prior art keywords
- control
- engine
- electric
- throttle
- sub
- 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 claims abstract description 11
- 230000003447 ipsilateral effect Effects 0.000 claims abstract 2
- 239000007858 starting material Substances 0.000 claims description 11
- 238000002347 injection Methods 0.000 claims description 3
- 239000007924 injection Substances 0.000 claims description 3
- 239000003638 chemical reducing agent Substances 0.000 claims 1
- NJPPVKZQTLUDBO-UHFFFAOYSA-N novaluron Chemical compound C1=C(Cl)C(OC(F)(F)C(OC(F)(F)F)F)=CC=C1NC(=O)NC(=O)C1=C(F)C=CC=C1F NJPPVKZQTLUDBO-UHFFFAOYSA-N 0.000 claims 1
- 239000000523 sample Substances 0.000 claims 1
- 125000006850 spacer group Chemical group 0.000 claims 1
- 238000009423 ventilation Methods 0.000 abstract 1
- 239000003921 oil Substances 0.000 description 8
- 238000010586 diagram Methods 0.000 description 2
- 239000000295 fuel oil Substances 0.000 description 2
- 238000012423 maintenance Methods 0.000 description 2
- 239000000203 mixture Substances 0.000 description 2
- 239000007921 spray Substances 0.000 description 2
- 238000005507 spraying Methods 0.000 description 2
- 208000020442 loss of weight Diseases 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 238000005457 optimization Methods 0.000 description 1
- 230000000979 retarding effect Effects 0.000 description 1
- -1 throttle body 9 Substances 0.000 description 1
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02B—INTERNAL-COMBUSTION PISTON ENGINES; COMBUSTION ENGINES IN GENERAL
- F02B61/00—Adaptations of engines for driving vehicles or for driving propellers; Combinations of engines with gearing
- F02B61/04—Adaptations of engines for driving vehicles or for driving propellers; Combinations of engines with gearing for driving propellers
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02B—INTERNAL-COMBUSTION PISTON ENGINES; COMBUSTION ENGINES IN GENERAL
- F02B67/00—Engines characterised by the arrangement of auxiliary apparatus not being otherwise provided for, e.g. the apparatus having different functions; Driving auxiliary apparatus from engines, not otherwise provided for
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02D—CONTROLLING COMBUSTION ENGINES
- F02D41/00—Electrical control of supply of combustible mixture or its constituents
- F02D41/0002—Controlling intake air
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02D—CONTROLLING COMBUSTION ENGINES
- F02D41/00—Electrical control of supply of combustible mixture or its constituents
- F02D41/30—Controlling fuel injection
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02N—STARTING OF COMBUSTION ENGINES; STARTING AIDS FOR SUCH ENGINES, NOT OTHERWISE PROVIDED FOR
- F02N15/00—Other power-operated starting apparatus; Component parts, details, or accessories, not provided for in, or of interest apart from groups F02N5/00 - F02N13/00
- F02N15/02—Gearing between starting-engines and started engines; Engagement or disengagement thereof
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02D—CONTROLLING COMBUSTION ENGINES
- F02D41/00—Electrical control of supply of combustible mixture or its constituents
- F02D41/0002—Controlling intake air
- F02D2041/0022—Controlling intake air for diesel engines by throttle control
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Control Of Vehicle Engines Or Engines For Specific Uses (AREA)
- Control Of Throttle Valves Provided In The Intake System Or In The Exhaust System (AREA)
Abstract
The present invention discloses a kind of automatically controlled unmanned plane petrol engine of list ECU sub-control air throttle, contains foundation machine 1, starting system 2, engine foundation 3, air inlet system and exhaust system 4, fuel injector 5, single ECU sub-control air throttle electric-control system 6, air filter 7, intake valve 8.The machine is two stroke electric-controlled petrol engine of twin-tub, list ECU sub-control air throttle electric-control system contains throttle body, fuel injector, steering engine, connector and angular transducer, and by each throttle inflow aperture of single ECU sub-control and oil spout, ECU unit is according to unmanned plane during flying situation, adjust each throttle conditions, reach accurate distributive value, air inflow and oil spout opportunity, while angular transducer feedback signal improves flight Stability and veracity to ECU；In addition the engine uses ipsilateral exhaust, facilitates multi-rotor unmanned aerial vehicle to arrange, effectively solves the problems, such as reversed exhaust ventilation " sooting " fuselage.Fuel injector, steering engine and angular transducer are integrated on solar term gate seat in structure, keep engine more compact, weight advantage is more apparent.
Description
Technical field
The invention discloses a kind of electric-control system unmanned plane petrol engines of list ECU sub-control air throttle, being capable of conduct
The power resources of the equipment such as rotor wing unmanned aerial vehicle, propeller-parachuting, model plane, belong to field of power machinery.
Background technique
Current medium and heavy multi-rotor unmanned aerial vehicle (100kg or more) is most to use gasoline engine as power, and in gasoline engine
Most of in terms of oil supply system to use old-fashioned carburetor fuel spraying system, there are air inflows to be not easy for carburetor fuel spraying system
Control, distributive value and oil spout opportunity can not accurately combine engine behavior to carry out suitable oil spout and air inlet, and carburetor
Structure is complicated, is unfavorable for unmanned plane loss of weight and maintenance.
Need to provide starting power with starter and deceleration train when gasoline starting, common small-sized starter without
Retarder, output revolving speed is higher, to reach engine start request, needs to install two under engine foundation to three-level ratio wheel
System, leading to starting system, structure is complicated, and weight is larger and inconvenient demolition and maintenance.
Twin-tub gas engine also has application on unmanned plane at present, and majority is using reversed exhaust, in multi-rotor unmanned aerial vehicle
On, this exhaust mode often will lead to the exhaust pipe of side against unmanned plane central side, fuselage occurs by tail pipe exhaust
The problem of " sooting ".
Therefore, in view of the above-mentioned problems, integrating fuel injector using throttle body and controlling the automatically controlled of steering engine and angular transducer
The complete machine arrangement of system optimization unmanned plane, cancels old-fashioned carburetor, simultaneously using new-type electric-control system and starting system structure
It improves unmanned plane during flying stability and maintainability is of great significance.
Summary of the invention
In view of the above-mentioned problems, the invention proposes a kind of compact-sized, small in size, light-weight engine overall design sides
Case.Be the twin-tub unmanned plane petrol engine with retarder described in the invention, foundation machine, starting system, engine foundation, into row
Gas system, oil supply system, the electric-control system of list ECU sub-control air throttle, air filter system, intake valve composition.
The exhaust mode of two cylinders of engine is exhaust in the same direction, and engine in more rotor complete machines when arranging, exhaust
Direction can effectively avoid the fuselage of unmanned plane center by exhaust gas " sooting " both facing to outside.
The electric-control system of the engine band list ECU sub-control air throttle carries sub-control air throttle electric-control system, and by single ECU
Air inlet aperture and the fuel injection opportunity of each air throttle are controlled respectively.
The starter of the engine starting system be retarding starter, inside be integrated with primary speed-down mechanism, export
The more common starter of revolving speed is low, therefore gear drive of the starting system from starter gear to crankshaft only needs level-one i.e. reachable
To the starting speed requirement of engine.
To save complete machine space, the starter and exhaust pipe of the engine are located at the two sides of cylinder centerline.
Detailed description of the invention
Fig. 1 is engine structure schematic diagram one.Foundation machine 1, starting system 2, engine foundation 3, air inlet system and exhaust system in figure
4, oil supply system 5, list ECU sub-control air throttle electric-control system 6, air filter system 7, intake valve 8
Fig. 2 is engine structure schematic diagram two.Fuel injector 5, throttle body 9, steering engine 10, angular transducer 11 in figure.
Specific embodiment
The present invention will be described with reference to the accompanying drawings and examples.
The present invention controls the air inlet aperture of each air throttle respectively by single ECU and fuel oil sprays, including throttle body 9,
Fuel injector 5, steering engine and connector 10, angular transducer 11.The throttle body 9 is directly mounted on engine intake valve 8, oil spout
Device 5 is installed on throttle body 9 by bracket, and steering engine 10 is installed on throttle body by bracket, and angular transducer is directly pacified
Loaded on throttle body, air enters from throttle body inlet end, blended fuel oil medium by the fuel injector on throttle body with
Atomised form sprays into, and enters engine inlets in throttle body internal mix, steering engine control throttle body central axis piece is opened
Angle is opened, can control the size of air inlet amount, angular transducer is connected with throttle plate pin end, can detect that in air throttle
The opening angle of mandrel piece, and ECU is fed back information to, electronic control unit adjusts each air throttle according to unmanned plane during flying situation
Working condition.ECU unit adjusts the working condition of each air throttle according to unmanned plane during flying situation, obtains accurate oil spout
Amount, air inflow and oil spout opportunity.
Claims (6)
1. a kind of electric-control system unmanned plane petrol engine of list ECU sub-control air throttle, including foundation machine, starting system, start
Machine base, air inlet system and exhaust system, oil supply system, the electric-control system of list ECU sub-control air throttle, air filter system, air inlet valve group
At.
2. the exhaust mode of air inlet system and exhaust system according to claim 1 is ipsilateral exhaust, exhaust pipe 4 and starter 2 are distinguished
Positioned at the two sides of cylinder centerline.
3. a kind of electric-control system unmanned plane petrol engine of list ECU sub-control air throttle according to claim 1, band sub-control section
Valve, and the air inflow of each air throttle, fuel injection amount and injection opportunity are controlled by single ECU respectively.
4. speed probe 4 according to claim 1 is mounted on reducer shell, rotated together by reading with crankshaft
Generator spacer block 2 on magnet signal measure speed of crankshaft.
5. the starter 12 of starting system according to claim 1 is planetary decelerating starter, it is internally integrated level-one
Slowing-down structure, starter gear assembly are primary speed-down gear drive.
6. the upper box of crankcase body 17 according to claim 1 is integrated with the function of retarder pedestal, retarder is total
It is directly installed on crankcase upper box at 12.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710478011.4A CN109113858A (en) | 2017-06-22 | 2017-06-22 | A kind of electric-control system unmanned plane petrol engine of band list ECU sub-control air throttle |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710478011.4A CN109113858A (en) | 2017-06-22 | 2017-06-22 | A kind of electric-control system unmanned plane petrol engine of band list ECU sub-control air throttle |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN109113858A true CN109113858A (en) | 2019-01-01 |
Family
ID=64732236
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201710478011.4A Pending CN109113858A (en) | 2017-06-22 | 2017-06-22 | A kind of electric-control system unmanned plane petrol engine of band list ECU sub-control air throttle |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN109113858A (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109763909A (en) * | 2019-02-01 | 2019-05-17 | 北海天际航空科技有限公司 | A kind of unmanned plane electronic fuel injection two-cycle gasoline engine |
| CN109973234A (en) * | 2019-02-01 | 2019-07-05 | 北海天际航空科技有限公司 | Unmanned plane electronic fuel injection two-cycle gasoline engine |
| CN111042933A (en) * | 2019-12-23 | 2020-04-21 | 天津布尔科技有限公司 | Intelligent control system for light unmanned aerial vehicle engine and implementation method thereof |
| CN111075628A (en) * | 2019-12-31 | 2020-04-28 | 航天时代飞鸿技术有限公司 | Automatic control system of piston engine |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN201443435U (en) * | 2009-06-12 | 2010-04-28 | 山东华源莱动内燃机有限公司 | Diesel engine |
| CN201723307U (en) * | 2010-04-26 | 2011-01-26 | 孟庆民 | Gasoline engine |
| CN104234821A (en) * | 2014-09-18 | 2014-12-24 | 北京航空航天大学 | Aviation supercharger control system and adjusting method thereof |
| CN104929767A (en) * | 2015-05-26 | 2015-09-23 | 北京银翼科技发展有限公司 | Electric control direct injection multi-fuel two-stroke engine |
-
2017
- 2017-06-22 CN CN201710478011.4A patent/CN109113858A/en active Pending
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN201443435U (en) * | 2009-06-12 | 2010-04-28 | 山东华源莱动内燃机有限公司 | Diesel engine |
| CN201723307U (en) * | 2010-04-26 | 2011-01-26 | 孟庆民 | Gasoline engine |
| CN104234821A (en) * | 2014-09-18 | 2014-12-24 | 北京航空航天大学 | Aviation supercharger control system and adjusting method thereof |
| CN104929767A (en) * | 2015-05-26 | 2015-09-23 | 北京银翼科技发展有限公司 | Electric control direct injection multi-fuel two-stroke engine |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109763909A (en) * | 2019-02-01 | 2019-05-17 | 北海天际航空科技有限公司 | A kind of unmanned plane electronic fuel injection two-cycle gasoline engine |
| CN109973234A (en) * | 2019-02-01 | 2019-07-05 | 北海天际航空科技有限公司 | Unmanned plane electronic fuel injection two-cycle gasoline engine |
| CN111042933A (en) * | 2019-12-23 | 2020-04-21 | 天津布尔科技有限公司 | Intelligent control system for light unmanned aerial vehicle engine and implementation method thereof |
| CN111075628A (en) * | 2019-12-31 | 2020-04-28 | 航天时代飞鸿技术有限公司 | Automatic control system of piston engine |
| CN111075628B (en) * | 2019-12-31 | 2022-03-18 | 航天时代飞鸿技术有限公司 | Automatic control system of piston engine |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN101506487B (en) | Device and method for supplying fresh air to a turbocharged, reciprocating-piston internal combustion engine | |
| CN109113858A (en) | A kind of electric-control system unmanned plane petrol engine of band list ECU sub-control air throttle | |
| CN203189113U (en) | Turbine pressurizing system | |
| EP2531707B1 (en) | Two-stroke, fuel injected internal combustion engines for unmanned aircraft and associated systems and methods | |
| US20140026538A1 (en) | Turbo charger pre-spooler | |
| US11358461B2 (en) | Electricity generation system and propulsion apparatus including the same | |
| CN101975107A (en) | Single-power driven double-generator set using electric injection system | |
| CN104165089A (en) | Method and system for operating an engine turbocharger waste gate | |
| Van Basshuysen et al. | Modern engine technology: from A to Z | |
| US10190547B2 (en) | Partial forced induction system | |
| CN109098861A (en) | A kind of electric-control system of list ECU sub-control air throttle | |
| US8683978B2 (en) | Fuel injection system | |
| CN203257532U (en) | Intelligent control air supplying device of turbocharged engine | |
| CN201747461U (en) | Single-motor-propelled double generator set adopting electronic fuel injection system | |
| CN105525989B (en) | A kind of automobile-used bifuel system using natural gas | |
| CN104389675B (en) | Composite circular rotational flow scavenging system for multi-fuel aerial heavy engine | |
| CN206522209U (en) | A kind of four-cylinder diesel engine of low emission | |
| CN202468037U (en) | Gas control device for dual-fuel internal combustion engine | |
| CN207178043U (en) | A kind of throttle body assembly being used in small aero electric injection system | |
| CN206539434U (en) | A kind of engine environment-protection oil-saving device | |
| CN205532873U (en) | Use automobile -used couple of fuel system of natural gas | |
| CN201546839U (en) | Closed loop electronically-controlled carburetor | |
| CN105736197B (en) | Internal combustion engine gas handling system and its control device and method | |
| CN109098842A (en) | A kind of unmanned plane petrol engine of different axis output | |
| CN208330538U (en) | Exhaust gas turbocharging device utilizing tail gas for heat dissipation |
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 | ||
| WD01 | Invention patent application deemed withdrawn after publication |
Application publication date: 20190101 |
|
| WD01 | Invention patent application deemed withdrawn after publication |