Engine combined-cooling system on small single-rotor-wing unmanned helicopter

An unmanned helicopter and hybrid cooling technology, applied in machine/engine, engine components, engine sealing devices, etc., can solve the problems of single engine cooling method and good heat dissipation effect, and achieve extended flight time, excellent heat dissipation effect, etc. Optimum cooling effect

Pending Publication Date: 2016-03-23
衡阳云雁航空科技有限公司
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

It adopts a heat dissipation method combining water cooling and air cooling, which has a good heat dissipation effect and solves various disadvantages caused by the single engine cooling method of the existing unmanned helicopter

Method used

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  • Engine combined-cooling system on small single-rotor-wing unmanned helicopter
  • Engine combined-cooling system on small single-rotor-wing unmanned helicopter
  • Engine combined-cooling system on small single-rotor-wing unmanned helicopter

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Embodiment 1

[0029] Such as figure 1 , 2 Shown: The hybrid engine cooling system on a small single-rotor unmanned helicopter, including cylinder block A1, water cooling jacket A, cylinder block B3, water cooling jacket B, water cooling evaporator 5, water storage tank 6 and water pump 7;

[0030] The outer wall of the cylinder body A1 is provided with a plurality of heat dissipation fins 11, and the outer wall of the cylinder body A1 is provided with an annular vacancy zone 12 that is not connected to the heat dissipation fins (such as image 3 , 4 shown). The water-cooling jacket A includes an upper arc-shaped sleeve 21 and a lower arc-shaped sleeve 22; the upper and lower arc-shaped sleeves are installed on the annular vacant belt 12 of the cylinder A1 and connected into a ring by bolts, and the water tanks on the inner arc surfaces of the two are connected. An annular water tank is formed, and an annular water cavity A13 is formed between the annular water tank and the cylinder A1. ...

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Abstract

The invention discloses an engine combined-cooling system on a small single-rotor-wing unmanned helicopter. The engine combined-cooling system comprises a cylinder A, a water cooled jacket A, a cylinder B, a water cooled jacket B, a water cooling evaporator, a water storage tank and a water pump. When a double-cylinder-oppositely-arranged type air cooled engine works, cooling water enters an annular water cavity A through a water inlet connector of the water cooled jacket A, absorbs heat of the cylinder A and is then drained out through a water outlet connector of the water cooled jacket A; the drained cooling water enters an annular water cavity B through a pipe and a water inlet connector of the water cooled jacket B, absorbs heat of the cylinder B, is then drained out through a water outlet connector of the water cooled jacket B, enters the water cooling evaporator through a pipe and is forcedly cooled through wind generated by a propeller and wind generated by flight; and the cooled water then enters the annular water cavity A through a hose, the water storage tank, a hose, the water pump, a hose and the water inlet connector of the water cooled jacket A in sequence and circulates according to the above path.

Description

technical field [0001] The invention relates to an engine cooling system, in particular to an engine hybrid cooling system on a small single-rotor unmanned helicopter. Background technique [0002] Existing small aeroengines are often used in unmanned helicopters, such as aerial photography drones or agricultural spraying pesticides, or small aircraft models and military fixed-wing target aircraft. Considering its weight and operating conditions, its heat dissipation mechanism includes heat dissipation fins arranged side by side on the engine body, that is, it uses air cooling to dissipate heat. The generated convective air cools the engine body. [0003] However, there are the following problems in the process of use: when the propeller speed of the UAV decreases or the flight speed decreases, the wind force will weaken, and the cooling efficiency of the heat dissipation mechanism will be greatly reduced, resulting in unstable engine operation. If the speed is not increase...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F02F1/06F02F1/14F02F11/00
CPCF02F1/06F02F1/14F02F11/005
Inventor 王国初
Owner 衡阳云雁航空科技有限公司
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