CN219672753U - Air circulation system of unmanned aerial vehicle engine - Google Patents
Air circulation system of unmanned aerial vehicle engine Download PDFInfo
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- CN219672753U CN219672753U CN202321023049.XU CN202321023049U CN219672753U CN 219672753 U CN219672753 U CN 219672753U CN 202321023049 U CN202321023049 U CN 202321023049U CN 219672753 U CN219672753 U CN 219672753U
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- 238000001816 cooling Methods 0.000 claims abstract description 31
- 230000000694 effects Effects 0.000 abstract description 10
- 230000017525 heat dissipation Effects 0.000 abstract description 9
- 230000009286 beneficial effect Effects 0.000 abstract description 2
- 238000002485 combustion reaction Methods 0.000 description 6
- 230000008093 supporting effect Effects 0.000 description 6
- 239000000203 mixture Substances 0.000 description 5
- 239000002912 waste gas Substances 0.000 description 5
- 239000000428 dust Substances 0.000 description 4
- 239000000446 fuel Substances 0.000 description 4
- 239000002737 fuel gas Substances 0.000 description 4
- 238000000034 method Methods 0.000 description 4
- 239000007789 gas Substances 0.000 description 3
- 239000004576 sand Substances 0.000 description 3
- 238000005299 abrasion Methods 0.000 description 2
- 238000001556 precipitation Methods 0.000 description 2
- 229910000838 Al alloy Inorganic materials 0.000 description 1
- 229910001369 Brass Inorganic materials 0.000 description 1
- 239000010951 brass Substances 0.000 description 1
- 238000004891 communication Methods 0.000 description 1
- 230000000295 complement effect Effects 0.000 description 1
- 230000008878 coupling Effects 0.000 description 1
- 238000010168 coupling process Methods 0.000 description 1
- 238000005859 coupling reaction Methods 0.000 description 1
- 238000001914 filtration Methods 0.000 description 1
- 239000000295 fuel oil Substances 0.000 description 1
- 238000010438 heat treatment Methods 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 238000002156 mixing Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
Landscapes
- Cooling, Air Intake And Gas Exhaust, And Fuel Tank Arrangements In Propulsion Units (AREA)
Abstract
The utility model discloses an air circulation system of an unmanned aerial vehicle engine, and relates to the field of unmanned aerial vehicles. The air circulation system of the unmanned aerial vehicle engine comprises an engine air inlet and exhaust mechanism and an engine cooling circulation mechanism, wherein the engine air inlet and exhaust mechanism comprises an air inlet channel arranged on a machine body and an exhaust channel arranged on the machine body, and the air inlet channel and the exhaust channel are both communicated with the engine and used for driving the air circulation when the engine operates; the engine cooling circulation mechanism comprises an air inlet channel arranged on the engine body and an air outlet channel arranged on the engine body, wherein the air inlet channel and the air outlet channel are communicated with the engine and are used for cooling the engine. The unmanned aerial vehicle heat dissipation system has the beneficial effect of improving the heat dissipation effect of the unmanned aerial vehicle.
Description
Technical Field
The utility model relates to the field of unmanned aerial vehicles, in particular to an air circulation system of an unmanned aerial vehicle engine.
Background
The drone is a drone that is maneuvered with a radio remote control device and a self-contained programming device. The engine is the most widely used power device of the unmanned aerial vehicle at present, and the engine can be generally divided into a piston engine, a turboprop engine, a jet engine and the like, and a great amount of air is required to be inhaled in the use process of the engine, and fuel is comburedly combusted through the air, so that the power for the unmanned aerial vehicle to fly is provided.
In the running process of the engine, the running of the engine can be realized through air inlet and outlet, and the air inlet and outlet can play a certain role in heat dissipation of the engine, but in practical application, the problem that the engine is overheated is found due to poor heat dissipation effect of the air inlet and outlet of the engine.
Disclosure of Invention
In order to improve the heat dissipation effect of an engine, the utility model provides an air circulation system of an unmanned aerial vehicle engine.
The utility model provides an air circulation system of an unmanned aerial vehicle engine, which adopts the following technical scheme:
the air circulation system of the unmanned aerial vehicle engine comprises an engine air inlet and exhaust mechanism and an engine cooling circulation mechanism, wherein the engine air inlet and exhaust mechanism comprises an air inlet channel arranged on a machine body and an exhaust channel arranged on the machine body, and the air inlet channel and the exhaust channel are both communicated with the engine and used for driving the air circulation when the engine operates; the engine cooling circulation mechanism comprises an air inlet channel arranged on the engine body and an air outlet channel arranged on the engine body, wherein the air inlet channel and the air outlet channel are communicated with the engine and are used for cooling the engine.
Through the technical scheme, air enters the engine through the air inlet channel, the air has a combustion supporting effect, and combusted waste gas is discharged through the exhaust channel. The engine generates heat in the running process, air enters the engine from the air inlet channel and is discharged from the air outlet channel after cooling the engine, so that the air cooling effect is achieved, the heat dissipation effect of the engine is improved, and the phenomenon that the engine is overheated is reduced.
Optionally, the air inlet channel is communicated with a carburetor of the engine, the exhaust channel is communicated with a cylinder of the engine, and the air inlet channel and the air outlet channel are both communicated with the cylinder of the engine.
Through the technical scheme, air enters the carburetor from the air inlet channel and is mixed with fuel oil, the mixed fuel gas reaches the cylinder to burn and drive the engine to rotate, and the burnt waste gas is discharged from the exhaust channel, so that the combustion supporting and the discharge of the air are realized. The cylinder is a main heating part, so that cold air enters from the air inlet channel to provide forced air cooling for the cylinder and then is discharged out of the machine body from the air outlet channel.
Optionally, an air cleaner is disposed between the intake passage and a carburetor of the engine, and the air cleaner is communicated with the intake passage and the carburetor of the engine.
Through the technical scheme, after the air enters the engine, dust and sand in the air are removed through the air filter, so that abrasion of the air to the cylinder during combustion supporting is reduced.
Optionally, air inlet cabins are arranged on two sides of the machine body, the air inlet cabins are hollow to form the air inlet channel, and one end of each air inlet cabin is opened and faces the front end of the machine body.
Through the technical scheme, the air inlet cabin faces towards the front end of the airframe, so that fresh air can enter the airframe through the air inlet channel when the aircraft flies, and meanwhile, the effect of partial rain shielding can be achieved.
Optionally, an air inlet cabin is arranged at the bottom of the machine body, the air inlet cabin is hollow and is provided with the air inlet channel, and one end of the air inlet cabin is opened and faces the front end of the machine body.
Through the technical scheme, the air inlet cabin faces the front end of the airframe, so that when the aircraft flies, air is sucked into the air inlet channel and enters the airframe.
Optionally, the air outlet channel is formed by an exhaust pipe, and the exhaust pipe is a straight exhaust pipe.
Through above-mentioned technical scheme, exhaust pipe discharges the waste gas of engine out the fuselage, and the structure of straight calandria is simple simultaneously, and weight is very light, and is very little to unmanned aerial vehicle's weight influence.
Optionally, a cooling fin is arranged at the outer side of the cylinder of the engine, and air enters the air inlet channel to reach the cooling fin and then leaves the machine body through the air outlet channel.
Through the technical scheme, the heat dissipation effect of the cylinder is further improved due to the arrangement of the heat dissipation fins.
Optionally, a plurality of cylinders are provided, and the exhaust passage is provided in plurality and is correspondingly communicated with the cylinders respectively.
Through the technical scheme, the two cylinders are arranged to improve the working stability of the engine, reduce impact vibration generated during working and improve the output of the engine.
In summary, the utility model has the following beneficial effects:
1. air enters the engine through the air inlet channel, the air has a combustion supporting effect, and the combusted waste gas is discharged through the exhaust channel. The engine generates heat in the running process, air enters the engine from the air inlet channel and is discharged from the air outlet channel after cooling the engine, so that the air cooling effect is achieved, the heat dissipation effect of the engine is improved, and the phenomenon that the engine is overheated is reduced.
2. After the air enters the engine, dust and sand in the air are removed through the air filter, so that abrasion of the air to the cylinder during combustion supporting is reduced.
3. The air inlet cabin and the air inlet cabin face the front end of the machine body, so that fresh air can enter the machine body through the air inlet channel and the air inlet channel when the aircraft flies, and meanwhile, the air inlet cabin and the air inlet cabin can also play a part of rain-shielding role.
Drawings
FIG. 1 is a schematic view of the overall structure of an embodiment of the present utility model;
FIG. 2 is a schematic cross-sectional view of an embodiment of the present utility model;
fig. 3 is a schematic view of an engine according to an embodiment of the present utility model.
Reference numerals illustrate: 1. a body; 11. an air intake passage; 12. an air inlet channel; 13. an air outlet channel; 2. an engine mount; 21. an air cleaner; 22. a carburetor; 23. a cylinder; 24. a spark plug; 25. an exhaust passage; 3. inspiring an integrated motor; 4. a heat sink.
Detailed Description
The utility model is described in further detail below with reference to fig. 1-2.
The embodiment of the utility model discloses an air circulation system of an engine of an unmanned aerial vehicle. Referring to fig. 1, an air circulation system of an unmanned aerial vehicle engine comprises an engine air inlet and outlet mechanism and an engine cooling circulation mechanism, wherein the engine air inlet and outlet mechanism is that outside air is introduced into the engine to play a combustion supporting role to drive the engine to work normally, and the engine cooling circulation mechanism is that the engine is cooled by using an air cooling mode.
Referring to fig. 2 and 3, the engine is provided inside the body 1 of the unmanned aerial vehicle, and the engine is fixed inside the body 1 by a lower mounting plate. The engine comprises an engine block 2, an air cleaner 21, a carburetor 22 and two cylinders 23, wherein the air cleaner 21 is used for filtering the incoming air, the carburetor 22 is used for mixing the air with the fuel to form a combustible mixture, and the cylinders 23 are used for combusting the combustible mixture. Two cylinders 23 are located on either side of the engine block 2, and the cylinders 23, carburetor 22 and air cleaner 21 are in communication with the engine block 2. The two cylinders 23 improve the stability of engine operation, and the intake air amount is large, so that there is a higher output.
An opening is formed in one side, away from the engine base 2, of the cylinder 23, a spark plug 24 is connected to the cylinder 23 through the opening, and the spark plug is used for igniting combustible gas mixture in the cylinder 23, and the combustible gas mixture combusts to drive the engine base 2 to rotate. The output shaft coaxial coupling of engine mount 2 has a heuristic integrative motor 3 to heuristic integrative motor 3 rotates the output electric energy, and heuristic integrative motor 3 is complementary with the power battery in the fuselage 1, when unmanned aerial vehicle flight need higher power, heuristic integrative motor 3 and power battery together output electric energy co-unmanned aerial vehicle flight, when needing lower power, the electric energy that heuristic integrative motor 3 output is mostly used for supplying unmanned aerial vehicle flight, and remaining fraction charges for power battery.
Referring to fig. 1 and 3, an air inlet channel 11 is formed in the bottom of a body 1 of the unmanned aerial vehicle, the air inlet channel 11 is communicated with an air cleaner 21, the air cleaner 21 is communicated with a carburetor 22, the carburetor 22 is communicated with cylinders 23, exhaust channels 25 are respectively communicated with the side walls of the two cylinders 23, and the exhaust channels 25 extend out to the bottom of the body 1. Air enters from the air inlet channel 11 at the bottom of the machine body 1, dust and sand contained in the air are removed by the air filter 21, the filtered air enters the carburetor 22 and is mixed with fuel into fuel gas, the fuel gas reaches into the two cylinders 23, the fuel gas is ignited in the cylinders 23, and waste gas is discharged out of the machine body 1 through the exhaust channel 25, so that air circulation of an engine air inlet and exhaust structure is formed.
The machine body 1 is fixedly connected with an air inlet cabin, one end of the air inlet cabin is communicated with the interior of the machine body 1, an air inlet channel 11 is formed in the air inlet cabin in a hollow mode, and one side of the air inlet cabin, which is close to the front end of the machine body 1, is opened. When unmanned aerial vehicle flies, the opening sets up into the wind, and the air passes through the opening and gets into in the air inlet channel reaches fuselage 1, reduces the sudden precipitation in the air simultaneously, and the precipitation passes through the phenomenon in the air inlet channel 11 entering cabin. The exhaust passage 25 is provided as a straight exhaust pipe, and the direction of the exhaust pipe is in a vertical state, so that the influence on the weight of the equipment is reduced.
Air inlet channel 12 has all been seted up to unmanned aerial vehicle's fuselage 1 both sides, and the cooling air gets into fuselage 1 by air inlet channel 12 in, and the cooling air contacts cylinder 23, and the outside of cylinder 23 is provided with fin 4, and fin 4 is aluminum alloy or brass material, improves the cooling effect through fin 4. The bottom of the unmanned aerial vehicle's fuselage 1 is provided with air-out passageway 13, and the cooling air passes through air-out passageway 13 and discharges unmanned aerial vehicle.
The fuselage 1 both sides set up fixedly connected with air inlet cabin, and one side that the air inlet cabin is close to fuselage 1 communicates in fuselage 1 inside, and the cavity in air inlet cabin sets up and forms the air inlet passageway, and one side that the fuselage 1 was kept away from in the air inlet cabin is provided with the opening, and the opening realizes the windward setting towards fuselage 1 front end, and when unmanned aerial vehicle flies, in the air was inhaled the air inlet passageway, the convenience was to engine cylinder's cooling.
The implementation principle of the air circulation system of the unmanned aerial vehicle engine provided by the embodiment of the utility model is as follows: when the unmanned aerial vehicle is in flight, fresh air enters through the air inlet channel 11, contacts the air filter 21 to remove dust and then reaches the carburetor 22, the air and the fuel are mixed into combustible mixture to flow to the cylinder 23, and exhaust gas combusted in the cylinder 23 is discharged through the exhaust channel 25. When the engine is in operation, the air cylinder 23 generates a large amount of heat, cooling air enters the engine body 1 from the air inlet channel 12, contacts the air cylinder 23 and contacts the cooling fins 4 of the air cylinder 23, and the cooling air cools and dissipates the air of the air cylinder 23 and is discharged from the air outlet channel 13, so that the air cooling of the engine is realized.
The present embodiment is only for explanation of the present utility model and is not to be construed as limiting the present utility model, and modifications to the present embodiment, which may not creatively contribute to the present utility model as required by those skilled in the art after reading the present specification, are all protected by patent laws within the scope of claims of the present utility model.
Claims (8)
1. An air circulation system of unmanned aerial vehicle engine, its characterized in that: the engine cooling and air intake mechanism comprises an engine air intake and exhaust mechanism and an engine cooling and air circulation mechanism, wherein the engine air intake and exhaust mechanism comprises an air intake channel (11) arranged on a machine body (1) and an exhaust channel (25) arranged on the machine body (1), and the air intake channel (11) and the exhaust channel (25) are both communicated with the engine and are used for driving air circulation when the engine is operated; the engine cooling circulation mechanism comprises an air inlet channel (12) arranged on the engine body (1) and an air outlet channel (13) arranged on the engine body (1), wherein the air inlet channel (12) and the air outlet channel (13) are communicated with the engine and are used for cooling the engine.
2. An air circulation system for an unmanned aerial vehicle engine according to claim 1, wherein: the air inlet channel (11) is communicated with a carburetor (22) of the engine, the exhaust channel (25) is communicated with a cylinder (23) of the engine, and the air inlet channel (12) and the air outlet channel (13) are both communicated with the cylinder (23) of the engine.
3. An air circulation system of an unmanned aerial vehicle engine according to claim 2, wherein: an air cleaner (21) is provided between the intake passage (11) and a carburetor (22) of the engine, and the air cleaner (21) is communicated with the intake passage (11) and the carburetor (22) of the engine.
4. An air circulation system for an unmanned aerial vehicle engine according to claim 1, wherein: the air inlet cabin is arranged on two sides of the machine body (1), the air inlet channel (12) is formed by the hollow arrangement of the air inlet cabin, and one end of the air inlet cabin is opened and faces the front end of the machine body (1).
5. An air circulation system of an engine of an unmanned aerial vehicle according to claim 1, wherein an air inlet chamber is arranged at the bottom of the main body (1), the air inlet chamber is hollow and is provided with the air inlet channel (11), and one end of the air inlet chamber is opened and faces the front end of the main body (1).
6. An air circulation system of an unmanned aerial vehicle engine according to claim 2, wherein: the air outlet channel (13) is formed by an exhaust pipe, and the exhaust pipe is a straight exhaust pipe.
7. An air circulation system for an unmanned aerial vehicle engine according to claim 6, wherein: the outside of the cylinder (23) of the engine is provided with cooling fins (4), and air enters the air inlet channel (12) to reach the cooling fins (4) and then leaves the machine body (1) through the air outlet channel (13).
8. An air circulation system of an unmanned aerial vehicle engine according to claim 2, wherein: a plurality of cylinders (23) of the engine are provided, and the exhaust passages (25) are provided in plurality and are respectively communicated with the cylinders (23) in a corresponding manner.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202321023049.XU CN219672753U (en) | 2023-04-28 | 2023-04-28 | Air circulation system of unmanned aerial vehicle engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202321023049.XU CN219672753U (en) | 2023-04-28 | 2023-04-28 | Air circulation system of unmanned aerial vehicle engine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN219672753U true CN219672753U (en) | 2023-09-12 |
Family
ID=87897522
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202321023049.XU Active CN219672753U (en) | 2023-04-28 | 2023-04-28 | Air circulation system of unmanned aerial vehicle engine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN219672753U (en) |
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2023
- 2023-04-28 CN CN202321023049.XU patent/CN219672753U/en active Active
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