CN211500781U - Hybrid cooling device for engine of unmanned aerial vehicle - Google Patents
Hybrid cooling device for engine of unmanned aerial vehicle Download PDFInfo
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- CN211500781U CN211500781U CN201921900062.2U CN201921900062U CN211500781U CN 211500781 U CN211500781 U CN 211500781U CN 201921900062 U CN201921900062 U CN 201921900062U CN 211500781 U CN211500781 U CN 211500781U
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- 238000001816 cooling Methods 0.000 title claims abstract description 69
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 claims abstract description 137
- 238000005524 ceramic coating Methods 0.000 claims description 3
- 238000012544 monitoring process Methods 0.000 claims description 3
- 230000017525 heat dissipation Effects 0.000 abstract description 11
- 239000011248 coating agent Substances 0.000 description 4
- 238000000576 coating method Methods 0.000 description 4
- 239000002826 coolant Substances 0.000 description 3
- 230000000694 effects Effects 0.000 description 3
- 238000004781 supercooling Methods 0.000 description 3
- 239000000110 cooling liquid Substances 0.000 description 2
- 238000009434 installation Methods 0.000 description 2
- 230000001788 irregular Effects 0.000 description 2
- 239000011148 porous material Substances 0.000 description 2
- VYZAMTAEIAYCRO-UHFFFAOYSA-N Chromium Chemical compound [Cr] VYZAMTAEIAYCRO-UHFFFAOYSA-N 0.000 description 1
- 210000001015 abdomen Anatomy 0.000 description 1
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 description 1
- 229910052782 aluminium Inorganic materials 0.000 description 1
- 239000000919 ceramic Substances 0.000 description 1
- 229910052804 chromium Inorganic materials 0.000 description 1
- 239000011651 chromium Substances 0.000 description 1
- 239000000498 cooling water Substances 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 239000011888 foil Substances 0.000 description 1
- 230000008595 infiltration Effects 0.000 description 1
- 238000001764 infiltration Methods 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 238000013021 overheating Methods 0.000 description 1
- 238000007747 plating Methods 0.000 description 1
- 230000000087 stabilizing effect Effects 0.000 description 1
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Abstract
The utility model discloses an unmanned aerial vehicle engine mixed cooling device, which is assembled with an opposite engine and comprises a radiator, a cooling cylinder body and a water cooling pipeline; the cooling cylinder body is arranged on the left side and the right side of the engine in an opposite mode respectively, the cooling cylinder body comprises a cylinder body, a water inlet, a water outlet and a cylinder body cover arranged on the surface of the cylinder body, and first radiating fins are arranged on the surface of the cylinder body and/or the surface of the cylinder body cover; the water cooling pipeline comprises a water pump, a first circulating water cavity in the radiator, a second circulating water cavity formed between the cylinder body cover and the cooling cylinder body, and a plurality of water pipes. The utility model discloses locate main rotor below with the radiator, utilize paddle and flight air current to realize the forced air cooling and combine the water-cooling circulation that the improvement was optimized fully to improve unmanned aerial vehicle's radiating efficiency. The cooling cylinder body adopts water-cooling circulation and fin heat dissipation to realize double heat exchange, and improves the water flow speed and the heat exchange efficiency in the circulating water cavity.
Description
Technical Field
The utility model relates to an aviation field and unmanned aerial vehicle engine field, specifically speaking relate to an unmanned aerial vehicle engine mixed cooling device.
Background
At present, the aero-engine mainly adopts two heat dissipation modes of water cooling and air cooling, and the aero-engine is mostly applied in an air cooling mode. The air-cooled heat dissipation is mainly applied to the high-speed flight state of the unmanned aerial vehicle, and the heat dissipation effect is poor when the unmanned aerial vehicle is frequently in a hovering or low-speed state; the water-cooling heat dissipation system is usually preset with a single temperature threshold value to control the start and stop of the water-cooling circulation system, so that resources are wasted, and particularly, the single water-cooling and air-cooling cannot play the characteristics of the long-endurance large-load oil-driven unmanned aerial vehicle.
Disclosure of Invention
The purpose of the invention is as follows: the utility model aims at providing an utilize paddle and flight air current to realize forced air cooling and combine water-cooling circulation fully to improve radiating efficiency's unmanned aerial vehicle engine mixed cooling device.
The technical scheme is as follows: the utility model discloses a hybrid cooling device of an unmanned aerial vehicle engine, which is assembled with an opposite engine and comprises a radiator, a cooling cylinder body and a water cooling pipeline; the cooling cylinder body is arranged on the left side and the right side of the engine in an opposite mode respectively, the cooling cylinder body comprises a cylinder body, a water inlet, a water outlet and a cylinder body cover arranged on the surface of the cylinder body, and first radiating fins are arranged on the surface of the cylinder body and/or the surface of the cylinder body cover; the water cooling pipeline comprises a water pump, a first circulating water cavity in the radiator, a second circulating water cavity formed between the cylinder body cover and the cooling cylinder body, and a plurality of water pipes.
The radiator comprises a hollow second radiating fin, wherein a hollow inner cavity is a first circulating water cavity. The shape of the protrusions of the second heat dissipation fin includes, but is not limited to, any one or combination of more of grid type, vertical stripe type, diagonal stripe type, spiral line type, and other irregular shape protrusions, and those skilled in the art can modify the shape of the protrusions to increase the heat exchange surface area based on the inventive principle described above, and the present invention is within the protection scope of the present invention.
In order to improve the water storage capacity and the heat exchange capacity of the first circulating water cavity, the radiator comprises a first water tank and a second water tank, wherein the first water tank is respectively communicated with the water inlets of the cooling cylinder bodies on two sides through two water pipes, and the second water tank is communicated with the water pump through the other water pipe; and a second heat radiating fin is arranged between the first water tank and the second water tank to jointly form a first circulating water cavity.
Preferably, the water inlet direction of the first circulating water cavity is connected to the water outlet of the water pump through a first pipeline; the water outlet direction of the first circulating water cavity is provided with two water outlets which are respectively connected to the upper water inlets of the two cooling cylinder bodies through two second pipelines, and the water outlets from the second circulating water cavity to the lower end are respectively converged to the water inlet of the water pump through two third pipelines, so that complete cooling circulation is realized.
Further, a water filling port is arranged on the first water tank or the second water tank. Preferably, the water filling port is provided at one of the first and second water tanks located at a higher level.
Furthermore, the cylinder body is provided with an exhaust port, and a pressure reducing valve for adjusting the internal pressure of the second circulating water cavity is arranged at the exhaust port. The pressure relief valve begins to operate when the pressure within the engine cylinder caused by high temperatures exceeds a pressure relief valve threshold. The cylinder body cover is also provided with a temperature sensor for monitoring the temperature in the cylinder body.
The radiator of the existing aviation aircraft is generally arranged at the belly part or the rear part of a tail pipe, and incoming flow and down-wash air flow in flight cannot effectively radiate the radiator. Radiator locate unmanned aerial vehicle owner rotor below, the incoming flow when making the rotatory downwash air current that forms of unmanned aerial vehicle paddle and unmanned aerial vehicle flight fully cools off the radiator, increases substantially the supercooling effect.
Further, the water inlet is arranged above the cooling cylinder body; the water outlet is arranged below the cooling cylinder body. Most of the existing aviation aircraft cylinder bodies are designed in a mode of an upper water inlet and a horizontal water outlet. Therefore, part of cooling liquid forms vortex in a water channel, the local part of the cooling liquid cannot be cooled in place, a supercooling or overheating area is formed, the coating on the inner wall of the cylinder body is heated unevenly, and cylinder pulling is caused in serious cases.
The utility model discloses the water inlet of cylinder body adopts the overhead type, and the cylinder cap vertical below is located to the delivery port, makes the rivers resistance reduce, has improved the flow rate of water, and the effective heat that unit volume hosepipe was walked increases. Specifically, the second circulating water cavity comprises an annular cavity and a side cavity, wherein the upper end of the annular cavity is connected with the water inlet and covers the periphery of the cylinder body, and the side cavity is arranged on the outer side of the free end of the cylinder body; the water outlet is arranged at the lower end of the side cavity.
Electric water pump can select for use to the water pump, carries out closed-loop control as the controlled variable with the coolant temperature, crosses when low at ambient temperature, closes the water pump, when the temperature is high, opens the water pump, simultaneously, when the engine cold start, the water pump is closed, the temperature rises very fast, has shortened engine start-up time greatly, has improved the operating efficiency.
In order to improve the wear resistance of the cylinder body, a ceramic coating is arranged on the surface of the cylinder body. The cylinder body of the existing aviation aircraft mostly adopts a chromium plating or ceramic infiltration process, so that the problems of poor coating bonding force, local coating falling and the like are often caused when an engine works for a long time, and cylinder scuffing is caused in serious cases. The utility model discloses a coating pottery layer, joint reticulation flower drawing make the cylinder body wall effectively obtain lubricated, have improved the wearability of cylinder body, and a life exceeds 1000 hours.
Can set up 1~3 spark plugs according to the design demand on the cylinder cap, the spark plug mounting hole runs through whole cylinder body lid, and the certain wall thickness is set for to the mounting hole, if install a plurality of spark plugs, a plurality of installation pore walls with leave enough water cavity clearance between the outer wall in second circulating water cavity side chamber.
Has the advantages that: the utility model discloses locate main rotor below with the radiator, utilize paddle and flight air current to realize the forced air cooling and combine the water-cooling circulation that the improvement was optimized fully to improve unmanned aerial vehicle's radiating efficiency. The cooling cylinder body adopts water-cooling circulation and fin heat dissipation to realize double heat exchange, and improves the water flow speed and the heat exchange efficiency in the circulating water cavity.
Drawings
Fig. 1 is a schematic structural diagram of the present invention;
FIG. 2 is a schematic view of the cooling cylinder of FIG. 1;
FIG. 3 is a partial schematic view of the cooling cylinder;
fig. 4 is a schematic structural view of a heat sink according to embodiment 3.
Detailed Description
The invention will be further explained with reference to the drawings and the specific embodiments.
Example 1
As shown in fig. 1 and 2, a hybrid cooling device for an engine of an unmanned aerial vehicle comprises a pair of cooling cylinder bodies 100, a water pump 200, a radiator 300, and a pair of cooling cylinder bodies 100, wherein the cooling cylinder bodies 100 are respectively arranged on two sides of a crankcase of an opposed engine 400, each cooling cylinder body 100 comprises a cylinder body 120, a water inlet 140, a water outlet 160, and a cylinder cover 180, a first heat dissipation fin 122 is arranged on the surface of the cylinder body 120, and the first heat dissipation fin 122 is formed by wrapping a plurality of annular fins on the surface of the cylinder body 120. The surfaces of the cylinder body 120, the first heat dissipating fins 122 and the cylinder cover 180 are provided with a ceramic coating.
As further shown in fig. 3, the cylinder cover 180 is disposed at an end of the cylinder body 120 near the outer side, a hollow second circulating water cavity 110 is formed between the cylinder cover 180 and the cylinder body 120, the second circulating water cavity 110 includes an annular cavity 112 covering the periphery of the cylinder body 120 and a side cavity 114 disposed at an outer side of a free end of the cylinder body 120, a water inlet 140 is formed on the surface of the cylinder body 120 above the annular cavity 112, and a water outlet 160 is formed below the cylinder cover 180 below the side cavity 114. Be equipped with two spark plugs 182 on cylinder body lid 180, the spark plug mounting hole runs through whole cylinder body lid 180, keeps apart second circulating water chamber 110, and the spark plug mounting hole is equipped with certain wall thickness, leaves sufficient water cavity clearance between the outer wall in installation pore wall and second circulating water chamber 110 side chamber 114. The cylinder body 120 is provided with an exhaust port 184 for stabilizing the internal pressure of the first circulating water chamber.
Radiator 300 is located unmanned aerial vehicle owner rotor below, and the incoming flow when making the rotatory downwash air current that forms of unmanned aerial vehicle paddle and unmanned aerial vehicle flight is fully cooled off radiator 300, increases substantially the supercooling effect. The radiator 300 includes a first water tank 320, a second heat dissipating fin 340 and a second water tank 360 which are connected in sequence, the second heat dissipating fin 340 is a hollow cavity capable of containing cooling water, and a first circulating water cavity is formed by the second heat dissipating fin 340, the first water tank 320 and the second water tank 360.
The water inlet direction of the first circulating water cavity is connected to the water outlet of the water pump 200 through a first pipeline 220; the first circulating water cavity is provided with two water outlets in the water outlet direction, which are arranged on two sides of the first water tank 320, connected to the water inlets 140 at the upper ends of the two cooling cylinder bodies 100 through the two second pipelines 240, and converged to the water inlet of the water pump 200 through the two third pipelines 260 after passing through the water outlets 160 at the lower end of the second circulating water cavity 110, respectively, so as to form a water cooling pipeline. The first water tank 320 is provided with a water filling port 324.
The protrusion shape of the second heat dissipating fin 340 includes, but is not limited to, any one or combination of grid type, vertical stripe type, diagonal stripe type, spiral type and other irregular shape protrusions, and those skilled in the art can modify the shape of the second heat dissipating fin to increase the heat exchanging surface area based on the above inventive principle, and the present invention is within the protection scope of the present invention.
Example 2
In this embodiment, the internal pressure control of the first circulating water chamber and the second circulating water chamber 110 and the control of the coolant temperature can be further optimized based on embodiment 1.
For temperature control, a temperature sensor 186 is provided within the cylinder cover 180 for monitoring the temperature within the cylinder. Water pump 200 can select for use electric water pump, for example (masses 1K 0965561J), carries out closed-loop control as the controlled variable with the coolant temperature, crosses when low at ambient temperature, closes electric water pump, and when the temperature was high, opens electric water pump, and simultaneously, when the engine cold start, electric water pump closed, and the temperature rise is very fast, has shortened engine start-up time greatly, has improved the operating efficiency.
For the control of the internal pressure, a pressure reducing valve 188 may be provided at the exhaust port of the cylinder head 180. The pressure relief valve begins to operate when the pressure within the engine cylinder caused by high temperatures exceeds a pressure relief valve threshold. The design is also applicable to the first circulating water chamber.
Example 3
This embodiment provides a preferred hollow second fin design. Referring to fig. 4, the second heat dissipation fin of the present embodiment is disposed between the first water tank and the second water tank, the second heat dissipation blade includes a plurality of hollow bars, the hollow cavities of the first water tank and the second water tank are communicated into a whole, and a plurality of S-shaped aluminum foils for increasing the heat exchange surface area are disposed between each hollow bar.
Claims (10)
1. The utility model provides an unmanned aerial vehicle engine hybrid cooling device assembles its characterized in that with the opposition engine: the cooling device comprises a radiator, a cooling cylinder body and a water cooling pipeline;
the cooling cylinder body is arranged on the left side and the right side of the engine in an opposite mode respectively, the cooling cylinder body comprises a cylinder body, a water inlet, a water outlet and a cylinder body cover arranged on the surface of the cylinder body, and first radiating fins are arranged on the surface of the cylinder body and/or the surface of the cylinder body cover;
the water cooling pipeline comprises a water pump, a first circulating water cavity in the radiator, a second circulating water cavity formed between the cylinder body cover and the cooling cylinder body, and a plurality of water pipes.
2. The hybrid cooling device of the engine of the unmanned aerial vehicle of claim 1, wherein: the heat sink includes a hollow second heat dissipating fin.
3. The hybrid cooling device of the engine of the unmanned aerial vehicle of claim 2, wherein: the radiator comprises a first water tank communicated with the water inlet of the cooling cylinder body and a second water tank communicated with the water pump; and a second heat radiating fin is arranged between the first water tank and the second water tank to jointly form a first circulating water cavity.
4. The hybrid cooling device of the engine of the unmanned aerial vehicle of claim 3, wherein: and a water filling port is arranged on the first water tank or the second water tank.
5. The hybrid cooling device of the engine of the unmanned aerial vehicle of claim 4, wherein: the cylinder body is provided with an exhaust port, and the exhaust port is provided with a pressure reducing valve for adjusting the internal pressure of the second circulating water cavity.
6. The hybrid cooling device of the engine of the unmanned aerial vehicle of claim 1, wherein: the radiator is arranged below the main rotor of the unmanned aerial vehicle.
7. The hybrid cooling device of the engine of the unmanned aerial vehicle of claim 1, wherein: the water inlet is arranged above the cooling cylinder body; the water outlet is arranged below the cooling cylinder body.
8. The hybrid cooling device of the engine of the unmanned aerial vehicle of claim 7, wherein: the second circulating water cavity comprises an annular cavity and a side cavity, wherein the upper end of the annular cavity is connected with the water inlet and covers the periphery of the cylinder body, and the side cavity is arranged on the outer side of the free end of the cylinder body; the water outlet is arranged at the lower end of the side cavity.
9. The hybrid cooling device of the engine of the unmanned aerial vehicle of claim 7 or 8, wherein: the cylinder body lid is equipped with the temperature sensor who is used for monitoring temperature in the cylinder body.
10. The hybrid cooling device of the engine of the unmanned aerial vehicle of claim 1, wherein: the surface of the cylinder body is provided with a ceramic coating.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201921900062.2U CN211500781U (en) | 2019-11-06 | 2019-11-06 | Hybrid cooling device for engine of unmanned aerial vehicle |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201921900062.2U CN211500781U (en) | 2019-11-06 | 2019-11-06 | Hybrid cooling device for engine of unmanned aerial vehicle |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN211500781U true CN211500781U (en) | 2020-09-15 |
Family
ID=72408504
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201921900062.2U Active CN211500781U (en) | 2019-11-06 | 2019-11-06 | Hybrid cooling device for engine of unmanned aerial vehicle |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN211500781U (en) |
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2019
- 2019-11-06 CN CN201921900062.2U patent/CN211500781U/en active Active
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| TR01 | Transfer of patent right |
Effective date of registration: 20231229 Address after: 210000 building 12-537, 29 buyue Road, Qiaolin street, Pukou District, Nanjing City, Jiangsu Province Patentee after: Nanjing aerospace Guoqi Intelligent Equipment Co.,Ltd. Address before: 210000 4th floor, block B, photoelectric science and Technology Park, No.6 Yuhe Road, Jiangbei new district, Nanjing City, Jiangsu Province Patentee before: NANJING LIJIAN UNMANNED PLANE TECHNOLOGY Co.,Ltd. Patentee before: NANJING GUOQI INTELLIGENT EQUIPMENT Co.,Ltd. |
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| TR01 | Transfer of patent right |