CN108757181A - A kind of aircraft fuel engines - Google Patents
A kind of aircraft fuel engines Download PDFInfo
- Publication number
- CN108757181A CN108757181A CN201810695224.7A CN201810695224A CN108757181A CN 108757181 A CN108757181 A CN 108757181A CN 201810695224 A CN201810695224 A CN 201810695224A CN 108757181 A CN108757181 A CN 108757181A
- Authority
- CN
- China
- Prior art keywords
- oil
- gas
- gas pipe
- pipe
- fuel engines
- 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.)
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Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/04—Air intakes for gas-turbine plants or jet-propulsion plants
- F02C7/057—Control or regulation
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/22—Fuel supply systems
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C9/00—Controlling gas-turbine plants; Controlling fuel supply in air- breathing jet-propulsion plants
- F02C9/26—Control of fuel supply
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Output Control And Ontrol Of Special Type Engine (AREA)
Abstract
The invention discloses a kind of aircraft fuel engines, including engine body, damper assemblies, oil spout component and gas deflation assembly, the engine body is equipped with oil gas mouth, and Oil/Gas Pipe is connected at oil gas mouth；The damper assemblies are installed on the Oil/Gas Pipe, for directly inputting the adjustable air of flow to oil gas mouth through Oil/Gas Pipe；The oil spout component is installed on the Oil/Gas Pipe between the damper assemblies and oil gas mouth, for directly inputting the adjustable fuel oil of flow to oil gas mouth through Oil/Gas Pipe.The aircraft of the present invention has many advantages, such as simple in structure, fast response time with fuel engines.
Description
Technical field
The invention mainly relates to vehicle technology fields, refer in particular to a kind of aircraft fuel engines.
Background technology
Currently, small aircraft is widely used in every field, various measuring instruments can be carried（Such as camera）, carry out high
Sky detection can be used for high-altitude object and throw, and can also be applied to agricultural, detection, meteorological, hazard forecasting and rescue etc..
But small aircraft mostly does power using battery at present, flying distance is with the flight time by battery capacity system
About, the too big Payload that can substantially reduce aircraft again of battery, therefore the exploitation of fuel oil aircraft is increasingly by aircraft
The attention of company is suitable for the carburetor engine that the put-put majority that aircraft uses is traditional, this hair in the market
Motivation is restricted by fuel system, and fuel oil is entered back into after being mixed in carburetor with air to engine, and response speed is apparent
Lag, may occur aircraft accident under specific condition.
Invention content
The technical problem to be solved in the present invention is that：For technical problem of the existing technology, the present invention provides one
Kind aircraft fuel engines simple in structure, fast response time.
In order to solve the above technical problems, technical solution proposed by the present invention is：
A kind of aircraft fuel engines, including engine body, damper assemblies, oil spout component and gas deflation assembly, the hair
Motivation ontology is equipped with oil gas mouth, and Oil/Gas Pipe is connected at oil gas mouth；
The damper assemblies are installed on the Oil/Gas Pipe, for directly inputting the adjustable sky of flow to oil gas mouth through Oil/Gas Pipe
Gas；
The oil spout component is installed on the Oil/Gas Pipe between the damper assemblies and oil gas mouth, for through Oil/Gas Pipe to oil gas
Mouth directly inputs the adjustable fuel oil of flow.
As a further improvement of the above technical scheme：
The damper assemblies include
Air flap, by shaft rotational installation in the Oil/Gas Pipe, for adjusting air mass flow；And
Drive component is connected with the air flap, for driving the air flap to rotate.
The driving component includes transmission mechanism and actuator；The actuator is through the transmission mechanism and the air flap
It is connected；The transmission mechanism includes cursor, first connecting rod and second connecting rod, and the cursor is installed on the defeated of the actuator
On shaft, one end of the first connecting rod and one end of the cursor are rotatablely connected, the other end of the first connecting rod and institute
One end rotation connection of second connecting rod is stated, the other end of the second connecting rod is fastenedly connected with the shaft.
The actuator is steering engine or servo motor or stepper motor.
It is provided with throttle opening detection piece in the shaft, is measured in real time for the aperture to air flap and is opened with realizing
The closed-loop control of degree.
The oil spout component includes oil pipe, atomizer and fuel pump；The atomizer is right against the inner cavity of the Oil/Gas Pipe
And it is connected with the fuel pump by oil pipe.
Oil/Gas Pipe one end opposite with the oil gas mouth is connected with air cleaner.
One end of the Oil/Gas Pipe is connect by connector with the oil gas mouth.
The both ends of the connector are connect by welding manner or thread connecting mode with Oil/Gas Pipe and oil gas mouth.
The gas deflation assembly includes exhaust pipe, oxygen detection part is provided in the exhaust pipe, for detecting in tail gas
Oxygen content is to adjust the flow of air or/and fuel oil.
Compared with the prior art, the advantages of the present invention are as follows：
The aircraft fuel engines of the present invention, directly sprays sky into engine body by damper assemblies and oil spout component
Gas and fuel oil, and carburetor is required no, enter the time of engine body to save air or fuel oil, to improve hair
Motivation fuel oil control response rate；In addition fuel oil directly sprays, without by atomization, its utilization rate can be further increased,
It avoids being discharged with tail gas and polluting environment；In addition engine structure is simple, suitable for carburetor engine and is easily achieved.This hair
Bright damper assemblies and oil spout modular construction are simple, control is accurate and easy to operate.
Description of the drawings
Fig. 1 is the structural diagram of the present invention.
Fig. 2 is the decomposition texture schematic diagram of the present invention.
Fig. 3 is the control block of the present invention.
Figure label indicates：1, Oil/Gas Pipe；101, connector；102, changeover portion；2, damper assemblies；201, air flap；
202, shaft；203, actuator；204, transmission mechanism；2041, cursor；2042, first connecting rod；2043, second connecting rod；3, it sprays
Oily component；4, throttle opening detection piece.
Specific implementation mode
Below in conjunction with Figure of description and specific embodiment, the invention will be further described.
As depicted in figs. 1 and 2, the aircraft fuel engines of the present embodiment, wherein aircraft are rotorcycle, flight
Vehicle or unmanned plane, fuel engines specifically include petrol engine ontology, damper assemblies 2, oil spout component 3 and gas deflation assembly
（It is not shown in figure）, engine body is equipped with oil gas mouth（The interface of input air and fuel oil, is not shown in figure）, at oil gas mouth
It is connected with Oil/Gas Pipe 1, when the bore between oil gas mouth and Oil/Gas Pipe 1 mismatches, Oil/Gas Pipe 1 then passes through connector 101 and oil
Gas port is connected；Damper assemblies 2 are installed on Oil/Gas Pipe 1, for directly inputting the adjustable sky of flow to oil gas mouth through Oil/Gas Pipe 1
Gas；Oil spout component 3 is installed on the Oil/Gas Pipe 1 between damper assemblies 2 and oil gas mouth, for direct to oil gas mouth through Oil/Gas Pipe 1
The adjustable fuel oil of input flow rate.The aircraft fuel engines of the present invention, directly by damper assemblies 2 and oil spout component 3 to
Injection air and fuel oil in engine body, and carburetor is required no, enter engine body to save air or fuel oil
Time, to improve engine fuel control response rate；In addition fuel oil directly sprays, and is atomized without passing through, can
Its utilization rate is further increased, avoids being discharged with tail gas and polluting environment；In addition engine structure is simple, is suitable for carburetor sends out
It motivation and is easily achieved.
As depicted in figs. 1 and 2, in the present embodiment, damper assemblies 2 include air flap 201, are rotatablely installed by shaft 202
In in Oil/Gas Pipe 1, for adjusting air mass flow；And drive component, it is connected with air flap 201, for driving 201 turns of air flap
It is dynamic.Wherein drive component includes transmission mechanism 204 and actuator 203；Actuator 203 is through transmission mechanism 204 and 201 phase of air flap
Even；Transmission mechanism 204 includes cursor 2041, first connecting rod 2042 and second connecting rod 2043, and cursor 2041 is installed on driving
On the output shaft of part 203, one end of first connecting rod 2042 and one end of cursor 2041 are rotatablely connected, first connecting rod 2042 it is another
One end and one end of second connecting rod 2043 are rotatablely connected, and the other end and the shaft 202 of second connecting rod 2043 are fastenedly connected.Actuator
203 be steering engine or servo motor or stepper motor.Under the rotation of actuator 203, cursor 2041, first connecting rod are driven successively
2042 and second connecting rod 2043 move, to drive the air flap 201 in shaft 202 rotate, adjusting of the realization to throttle opening；
Damper assemblies 2 are not only simple in structure, easy to operate and throttle opening is adjusted precisely.In addition, being provided with air door in shaft 202
Measuring opening part 4 is measured in real time to realize the closed-loop control of aperture for the aperture to air flap 201, further increases
The accuracy that throttle opening is adjusted.
In the present embodiment, oil spout component 3 includes oil pipe, atomizer and fuel pump；Atomizer is right against the inner cavity of Oil/Gas Pipe 1
And it is connected with fuel pump by oil pipe.By the control of fuel pump, it is adjustable that flow is sprayed into Oil/Gas Pipe 1 through oil pipe and atomizer
Fuel oil.3 simple structure, convenient control of oil spout component.
In the present embodiment, the one end opposite with oil gas mouth of Oil/Gas Pipe 1 is connected with air cleaner by changeover portion 102（Figure
In be not shown）, for being filtered to the air for entering engine.The both ends of connector 101 are connected by welding manner or screw thread
Mode is connect to connect with Oil/Gas Pipe 1 and oil gas mouth.
In the present embodiment, gas deflation assembly includes exhaust pipe, oxygen detection part is provided in exhaust pipe, for detecting in tail gas
Oxygen content to adjust the flow of air or/and fuel oil.
Workflow：As shown in figure 3, control unit of engine receives the instruction that operator sends out, instruction is sent to again
Damper assemblies 2, damper assemblies 2 can require rotation 201 certain angle of air flap according to instruction, ensure certain air supply amount,
Ensure that fuel oil burning is complete, reduces air pollution；At the same time, fuel injection component 3 receives the instruction of control unit, injection
Quantitative fuel oil enter air flap 201 front end mixed with air after enter back into the deflagrating jar of engine, push piston acting；Separately
Outside, the throttle opening detection piece 4 being mounted in 2 lower section shaft 202 of damper assemblies（Such as air door switch inductor）Air door is received to open
The signal for spending size, is sent to control unit, and the difference between control unit compare instruction and feedback opening amount signal carries out air door
The fine tuning of piece 201 realizes that the aperture closed loop of air flap 201 is adjusted；The oxygen detection part being wherein mounted at exhaust pipe（Such as oxygen
Inductor）The oxygen content that inblock cylinder goes out gas can be detected, and measurement result is sent to control unit, control unit is located again
Reason, and compared with the instruction received, it is reduced with determining（Increase）Distributive value still increases（Reduce）201 aperture of air flap, with
Reach most abundant, the effect of air pollution minimum of fuel oil burning.
Although the present invention has been disclosed as a preferred embodiment, however, it is not intended to limit the invention.It is any to be familiar with ability
The technical staff in domain, without deviating from the scope of the technical scheme of the present invention, all using the technology contents pair of the disclosure above
Technical solution of the present invention makes many possible changes and modifications, or is revised as the equivalent embodiment of equivalent variations.Therefore, every
Without departing from the content of technical solution of the present invention, according to the present invention technical spirit any simple modification made to the above embodiment,
Equivalent variations and modification, all shall fall within the protection scope of the technical scheme of the invention.
Claims (10)
1. a kind of aircraft fuel engines, including engine body, damper assemblies（2）, oil spout component（3）With exhaust group
Part, which is characterized in that the engine body is equipped with oil gas mouth, and Oil/Gas Pipe is connected at oil gas mouth（1）；
The damper assemblies（2）, it is installed on the Oil/Gas Pipe（1）On, for through Oil/Gas Pipe（1）Flow is directly inputted to oil gas mouth
Adjustable air；
The oil spout component（3）, it is installed on the damper assemblies（2）Oil/Gas Pipe between oil gas mouth（1）On, for through oil gas
Pipe（1）The adjustable fuel oil of flow is directly inputted to oil gas mouth.
2. aircraft fuel engines according to claim 1, which is characterized in that the damper assemblies（2）Including
Air flap（201）, pass through shaft（202）It is rotatablely installed in the Oil/Gas Pipe（1）It is interior, for adjusting air mass flow；And
Drive component, with the air flap（201）It is connected, for driving the air flap（201）Rotation.
3. aircraft fuel engines according to claim 2, which is characterized in that the driving component includes driver
Structure（204）And actuator（203）；The actuator（203）Through the transmission mechanism（204）With the air flap（201）It is connected；
The transmission mechanism（204）Including cursor（2041）, first connecting rod（2042）And second connecting rod（2043）, the cursor
（2041）It is installed on the actuator（203）Output shaft on, the first connecting rod（2042）One end and the cursor
（2041）One end rotation connection, the first connecting rod（2042）The other end and the second connecting rod（2043）One end rotation
Connection, the second connecting rod（2043）The other end and the shaft（202）It is fastenedly connected.
4. aircraft fuel engines according to claim 3, which is characterized in that the actuator（203）For steering engine
Or servo motor or stepper motor.
5. the aircraft fuel engines according to Claims 2 or 3 or 4, which is characterized in that the shaft（202）On
It is provided with throttle opening detection piece（4）, for air flap（201）Aperture be measured in real time to realize the closed loop control of aperture
System.
6. aircraft fuel engines as claimed in any of claims 1 to 5, which is characterized in that the oil spout
Component（3）Including oil pipe, atomizer and fuel pump；The atomizer is right against the Oil/Gas Pipe（1）Inner cavity and pass through oil pipe
It is connected with the fuel pump.
7. aircraft fuel engines as claimed in any of claims 1 to 5, which is characterized in that the oil gas
Pipe（1）One end opposite with the oil gas mouth is connected with air cleaner.
8. aircraft fuel engines as claimed in any of claims 1 to 5, which is characterized in that the oil gas
Pipe（1）One end pass through connector（101）It is connect with the oil gas mouth.
9. aircraft fuel engines according to claim 8, which is characterized in that the connector（101）Both ends
Pass through welding manner or thread connecting mode and Oil/Gas Pipe（1）It is connected with oil gas mouth.
10. aircraft fuel engines as claimed in any of claims 1 to 5, which is characterized in that the exhaust
Component includes exhaust pipe, and oxygen detection part is provided in the exhaust pipe, for detecting the oxygen content in tail gas to adjust sky
The flow of gas or/and fuel oil.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810695224.7A CN108757181A (en) | 2018-06-29 | 2018-06-29 | A kind of aircraft fuel engines |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810695224.7A CN108757181A (en) | 2018-06-29 | 2018-06-29 | A kind of aircraft fuel engines |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN108757181A true CN108757181A (en) | 2018-11-06 |
Family
ID=63974871
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201810695224.7A Pending CN108757181A (en) | 2018-06-29 | 2018-06-29 | A kind of aircraft fuel engines |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN108757181A (en) |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN2523970Y (en) * | 2001-07-20 | 2002-12-04 | 重庆力帆轰达实业(集团)有限公司 | Throttle body of horizontal engine |
| CN201486647U (en) * | 2009-08-20 | 2010-05-26 | 宁波贝斯特航空技术工程有限公司 | Electric control spraying type triangle rotor engine |
| CN105257442A (en) * | 2015-11-13 | 2016-01-20 | 吉林大学 | Engine fuel supply air-fuel mixing device and fuel atomization method |
| CN206830347U (en) * | 2017-06-27 | 2018-01-02 | 金浪科技有限公司 | Motorcycle electric spraying structure |
| CN208578644U (en) * | 2018-06-29 | 2019-03-05 | 长沙市云智航科技有限公司 | A kind of aircraft fuel engines |
-
2018
- 2018-06-29 CN CN201810695224.7A patent/CN108757181A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN2523970Y (en) * | 2001-07-20 | 2002-12-04 | 重庆力帆轰达实业(集团)有限公司 | Throttle body of horizontal engine |
| CN201486647U (en) * | 2009-08-20 | 2010-05-26 | 宁波贝斯特航空技术工程有限公司 | Electric control spraying type triangle rotor engine |
| CN105257442A (en) * | 2015-11-13 | 2016-01-20 | 吉林大学 | Engine fuel supply air-fuel mixing device and fuel atomization method |
| CN206830347U (en) * | 2017-06-27 | 2018-01-02 | 金浪科技有限公司 | Motorcycle electric spraying structure |
| CN208578644U (en) * | 2018-06-29 | 2019-03-05 | 长沙市云智航科技有限公司 | A kind of aircraft fuel engines |
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