CN105298617A - Engine dissipating structure of small single-rotor-wing unmanned helicopter - Google Patents
Engine dissipating structure of small single-rotor-wing unmanned helicopter Download PDFInfo
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- CN105298617A CN105298617A CN201510873741.5A CN201510873741A CN105298617A CN 105298617 A CN105298617 A CN 105298617A CN 201510873741 A CN201510873741 A CN 201510873741A CN 105298617 A CN105298617 A CN 105298617A
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Abstract
An engine dissipating structure of a small single-rotor-wing unmanned helicopter comprises a cylinder body and a water jacket; a plurality of dissipating fins are connected to the outer wall of the cylinder body, and an annular gap belt not connected with the dissipating fins is arranged on the outer wall of the cylinder body; the water jacket is mounted on the annular gap belt of the cylinder body in a sealed manner, and an annular water cavity is formed between the water jacket and the cylinder body; and a water inlet joint and a water outlet joint which are communicated to the annular water cavity are arranged on the water jacket. The engine dissipating structure has the beneficial effects that when an engine works, cooling water is led into the annular water cavity through the water inlet joint, the cooling water absorbs heat of the cylinder body in the process of flowing inside a cooling water cavity, and then is drained out through the water outlet joint, the dissipating effect of the dissipating structure is superior to that of a small aero-engine purely depending on air cooling dissipating, the working stability of the engine is ensured, and the continuous flying time of the unmanned helicopter is prolonged.
Description
Technical field
The present invention relates to engine cylinder body structure, particularly a kind of small-sized single rotor unmanned helicopter heat dissipation structure of engine.
Background technique
Existing small aero is often applied on depopulated helicopter, such as, take photo by plane on unmanned plane or agricultural spray agricultural chemicals unmanned plane or small-sized model airplane and military fixed-wing target drone.Consider its weight and applying working condition, its cooling mechanism comprises the radiating fin be disposed in parallel on engine body, namely adopt air-cooled mode to dispel the heat, the convection current wind by producing when the propeller cavitation High Rotation Speed that is connected with arbor and high-speed flight during unmanned helicopter flight cools engine body.
But in use there is following problem: when the reduction of propeller rotating speed or the flying speed reduction of unmanned plane, the abatement of wind, the cooling effectiveness of cooling mechanism will reduce greatly, cause engine operation unstable, if do not raised speed, will cause cylinder body (piston cylinder) temperature will be too high and power dropping will cause air crash.If motor is lowered the temperature by refueling to raise speed under being in the condition of high temperature again, the faster of cylinder body (piston cylinder) temperature increase can be made on the contrary.So the existing unmanned helicopter continuous flight time is all shorter, long-time continuous flight can not be realized.
Summary of the invention
The object of the invention is to overcome the deficiencies in the prior art, and a kind of small-sized single rotor unmanned helicopter heat dissipation structure of engine is provided.It adopts water-cooled and the air-cooled radiating mode combined, good heat dissipation effect, solves the various drawbacks that existing small aero adopts wind-cooling heat dissipating to bring.
Technological scheme of the present invention is: small-sized single rotor unmanned helicopter heat dissipation structure of engine, comprises cylinder body and water jacket; Outer wall of cylinder block is provided with multi-disc radiating fin, and outer wall of cylinder block is provided with the annular vacancy band not connecting radiating fin; Water jacket sealing is arranged on the annular vacancy band of cylinder body, and and form annular water chamber between cylinder body, which is provided with the water supply connector and water output connector that are communicated to annular water chamber.
The further technological scheme of the present invention is: water jacket comprises arc sleeve and arc lower cover; The annular vacancy band that upper and lower arc sleeve is arranged on cylinder body is bolted into an annular, and the tank on both intrados is communicated with and circularizes tank, forms annular water chamber between annular water tank and cylinder body.
The present invention further technological scheme is: sealed by sealing gasket between the surface of contact of upper arc sleeve and arc lower cover; Sealed by seal ring A and seal ring B between water jacket and the surface of contact of cylinder body, seal ring A, B are located at the both sides of annular water chamber.
The present invention further technological scheme is: the outer arced surface of upper and lower arc sleeve is evenly equipped with multi-disc radiating fin.
The present invention further technological scheme is: water supply connector is located on arc sleeve, and water output connector is located at arc lower and puts.
The present invention compared with prior art tool has the following advantages:
1, on the cylinder body of existing small aero, part radiating fin is removed, form the annular vacancy band installed for water jacket, water jacket sealing is arranged on annular vacancy band, during engine operation, in annular water chamber, cooling water is passed into by water supply connector, the heat of cylinder body is absorbed in the process that cooling water flows in cooling water chamber, discharged by water output connector again, radiating effect is better than the small aero relying on merely wind-cooling heat dissipating, ensure engine operation stability, extend the follow-on mission time of depopulated helicopter and the working life of motor.
2, cylinder body comprises high-temperature zone, air inlet area and ventilation district, and annular vacancy band is positioned at the high-temperature zone of cylinder body, and radiating effect is better, effectively prevents engine body temperature too high.
3, sealed by sealing gasket between the surface of contact that upper arc sleeve and arc lower overlap, sealed by seal ring A and seal ring B between water jacket and the surface of contact of cylinder body, prevent cooling water from oozing out from cooling water chamber or leaking.
Below in conjunction with figure and embodiment the invention will be further described.
Accompanying drawing explanation
Fig. 1 is perspective view of the present invention;
Fig. 2 is structural representation of the present invention;
Fig. 3 is that the A-A of Fig. 2 is to sectional view;
Fig. 4 is the explosive view of water jacket.
Embodiment
Embodiment 1:
As shown in figures 1-4: small-sized single rotor unmanned helicopter heat dissipation structure of engine, comprises cylinder body 1 and water jacket.
Cylinder body 1 outer wall is provided with multi-disc radiating fin 11, and cylinder body 1 outer wall is provided with the annular vacancy band 12 not connecting radiating fin 11.
Water jacket comprises arc sleeve 21 and arc lower cover 22.The annular vacancy band 12 that upper and lower arc sleeve is arranged on cylinder body 1 is bolted into an annular, and the tank on both intrados is communicated with and circularizes tank, forms annular water chamber 3 between annular water tank and cylinder body 1.Water jacket is provided with the water supply connector 211 and water output connector 221 that are communicated to annular water chamber 3.Water supply connector 211 is located on arc sleeve 21, and water output connector 221 is located on arc lower cover 22.The outer arced surface of upper and lower arc sleeve is evenly equipped with multi-disc radiating fin 23.
Sealed by sealing gasket 24 between the surface of contact of upper arc sleeve 21 and arc lower cover 22.Sealed by seal ring A25 and seal ring B26 between the surface of contact of water jacket and cylinder body 1, seal ring A, B are located at the both sides of annular water chamber 3.
Preferably, annular vacancy band 12 is located at the high-temperature zone 15 (cylinder body comprises high-temperature zone, air inlet area and ventilation district) of cylinder body 1.
Claims (5)
1. small-sized single rotor unmanned helicopter heat dissipation structure of engine, is characterized in that: comprise cylinder body (1) and water jacket; Cylinder body (1) outer wall is provided with multi-disc radiating fin (11), and cylinder body (1) outer wall is provided with the annular vacancy band (12) not connecting radiating fin (11); Water jacket sealing is arranged on the annular vacancy band (12) of cylinder body (1), and and form annular water chamber (3) between cylinder body (1), which is provided with the water supply connector (211) and water output connector (221) that are communicated to annular water chamber (3).
2. small-sized single rotor unmanned helicopter heat dissipation structure of engine as claimed in claim 1, is characterized in that: water jacket comprises arc sleeve (21) and arc lower cover (22); The annular vacancy band (12) that upper and lower arc sleeve is arranged on cylinder body (1) is gone up and is bolted into an annular, tank connection on both intrados circularizes tank, forms annular water chamber (3) between annular water tank and cylinder body (1).
3. small-sized single rotor unmanned helicopter heat dissipation structure of engine as claimed in claim 2, is characterized in that: the upper sealing gasket (24) that passes through between arc sleeve (21) and the surface of contact of arc lower cover (22) seals; Sealed by seal ring A (25) and seal ring B (26) between the surface of contact of water jacket and cylinder body (1), seal ring A, B are located at the both sides of annular water chamber (3).
4. small-sized single rotor unmanned helicopter heat dissipation structure of engine as claimed in claim 2 or claim 3, is characterized in that: the outer arced surface of upper and lower arc sleeve is evenly equipped with multi-disc radiating fin (23).
5. small-sized single rotor unmanned helicopter heat dissipation structure of engine as claimed in claim 2 or claim 3, it is characterized in that: water supply connector (211) is located on arc sleeve (21), and water output connector (221) is located on arc lower cover (22).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510873741.5A CN105298617A (en) | 2015-12-03 | 2015-12-03 | Engine dissipating structure of small single-rotor-wing unmanned helicopter |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510873741.5A CN105298617A (en) | 2015-12-03 | 2015-12-03 | Engine dissipating structure of small single-rotor-wing unmanned helicopter |
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| Publication Number | Publication Date |
|---|---|
| CN105298617A true CN105298617A (en) | 2016-02-03 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201510873741.5A Pending CN105298617A (en) | 2015-12-03 | 2015-12-03 | Engine dissipating structure of small single-rotor-wing unmanned helicopter |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106988855A (en) * | 2017-05-11 | 2017-07-28 | 廖兴池 | Special engine heat dissipating device on a kind of unmanned plane |
Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104047717A (en) * | 2014-06-17 | 2014-09-17 | 湖南金骏农业科技有限公司 | Wind-water cooling double-cylinder two-stroke gasoline engine for radio-controlled helicopter |
| CN104696095A (en) * | 2014-06-19 | 2015-06-10 | 安阳全丰航空植保科技有限公司 | Water cooling system for engine of unmanned helicopter |
| CN206319948U (en) * | 2015-12-03 | 2017-07-11 | 衡阳云雁航空科技有限公司 | Small-sized single rotor unmanned helicopter heat dissipation structure of engine |
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2015
- 2015-12-03 CN CN201510873741.5A patent/CN105298617A/en active Pending
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104047717A (en) * | 2014-06-17 | 2014-09-17 | 湖南金骏农业科技有限公司 | Wind-water cooling double-cylinder two-stroke gasoline engine for radio-controlled helicopter |
| CN104696095A (en) * | 2014-06-19 | 2015-06-10 | 安阳全丰航空植保科技有限公司 | Water cooling system for engine of unmanned helicopter |
| CN206319948U (en) * | 2015-12-03 | 2017-07-11 | 衡阳云雁航空科技有限公司 | Small-sized single rotor unmanned helicopter heat dissipation structure of engine |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106988855A (en) * | 2017-05-11 | 2017-07-28 | 廖兴池 | Special engine heat dissipating device on a kind of unmanned plane |
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