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A cooling system for a multi-rotor aircraft engine

A multi-rotor aircraft and cooling system technology, applied in the aviation field, can solve problems such as poor heat dissipation, and achieve the effect of solving heat dissipation problems and saving costs

Active Publication Date: 2019-06-07
BEIJING SANKUAI ONLINE TECH CO LTD +1
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0003] The purpose of the present invention is to provide a cooling system for a multi-rotor aircraft engine, which can effectively solve the problem of poor heat dissipation

Method used

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  • A cooling system for a multi-rotor aircraft engine
  • A cooling system for a multi-rotor aircraft engine
  • A cooling system for a multi-rotor aircraft engine

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Experimental program
Comparison scheme
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Embodiment approach 1

[0026] Such as figure 1 As shown, the cooling system of the present invention mainly includes cooling devices 11, 12, a heat exchange device 3, a circulation device 2, and connecting passages connecting the above devices. Wherein the cooling device includes a first liquid inlet and a first liquid outlet; the heat exchange device 3 includes a second liquid inlet and a second liquid outlet, wherein the second liquid inlet is connected to the first liquid outlet of the cooling device; The circulation device 2 includes a third liquid inlet and a third liquid outlet, wherein the third liquid inlet is connected to the second liquid outlet of the heat exchange device, and the third liquid outlet is connected to the first liquid inlet of the cooling device; And the connecting channel connected between the above-mentioned devices.

[0027] A circulating cooling liquid is arranged in the connecting channel. The cooling liquid includes organic or inorganic solutions such as water, ethy...

Embodiment approach 2

[0036] On the basis of the previous embodiments, this embodiment further designs the heat exchange device.

[0037] Such as image 3 As shown, the heat exchange device 3 is located under the cantilever beam under the rotor of the UAV, including a liquid storage container, pipelines and a folded aluminum foil radiator. The radiator uses folded aluminum foil to increase the heat dissipation area, bear the system heat dissipation load, and cool the working fluid. Fully heat exchange with the aluminum row through the pipeline.

[0038] One end of the heat exchanger is respectively provided with a liquid inlet 301 and a liquid outlet 302 . The heat exchanger uses the downwash airflow generated by the rotation of the rotor to perform forced convection. To achieve the ideal heat dissipation effect, the forced convection wind speed passing through the heat exchanger should not be lower than 8m / s.

[0039] The heat exchange device also includes a first control device; the first contr...

Embodiment approach 3

[0044] On the basis of the previous embodiments, this embodiment further designs the circulation device. The circulation device includes a circulation pump 2, a liquid storage container 5, and a second control device. The second control device includes a pressure sensing unit 10, a second threshold comparison unit and a switch unit 6, see Figure 4 shown.

[0045] The pressure sensing unit is used to measure the pressure in the second liquid storage container, which may be a pressure measuring mechanism such as a pressure gauge; When the threshold is reached, a second control signal is sent; the switch unit 6, which can be, for example, a valve 6, opens the valve when receiving the second control signal sent by the second threshold comparison unit, so that the second liquid storage container communicates with the atmosphere, release stress. This allows the system to trigger valves in the event of excess pressure, releasing the pressure to atmosphere to keep the system safe....

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Abstract

The invention discloses a cooling system for an engine of a multi-rotor aircraft. A small aviation piston engine is mainly applied to a fixed-wing unmanned aerial vehicle in practice, heat dissipation is carried out by virtue of a high-speed airflow generated by level flight of the fixed-wing unmanned aerial vehicle, and a design for the heat dissipation of the engine is simple. The small aviation piston engine is used in the multi-rotor aircraft, and has no heat dissipation conditions of high-speed level flight of the fixed-wing unmanned aerial vehicle, and the heat dissipation need of the engine cannot be met by using a common air-cooling fan for heat dissipation. The invention designs an efficient small air-cooling system for solving the problem of heat dissipation of the small aviation piston engine. The small air-cooling system is low in weight, high in heat dissipation power, and capable of improving the reliability and stability of the unmanned aerial vehicle and prolonging the endurance time of the unmanned aerial vehicle. With the adoption of a cylinder sleeve coating a cylinder of the engine, a cooling working solution is in direct contact with the cylinder, and efficient heat exchange is realized. In addition, a special heat dissipation fan is replaced by a forced-convection aluminium row heat exchanger adopting a rotor downwash airflow, thus the overall efficiency is improved.

Description

technical field [0001] The invention belongs to the technical field of aviation, and in particular relates to a cooling system for an engine of a flying multi-rotor aircraft. Background technique [0002] In practice, small aviation piston engines are mainly used in fixed-wing unmanned aerial vehicles. The high-speed airflow generated by the fixed-wing aircraft in level flight is used to dissipate heat, and the heat dissipation design of the engine is simple. In recent years, multi-rotor UAVs have developed rapidly. With their stable flight, simple structure, and easy manipulation, they have been widely used in aerial photography, reconnaissance, exploration, logistics, plant protection and other fields. Gasoline-powered multi-rotor drones break through the shortcomings of electric multi-rotor drones in terms of battery life and load, and open up broader application prospects for multi-rotor drones. The multi-rotor uses a small aviation piston engine, which does not have th...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): F01P3/02F01P3/18
CPCF01P3/02F01P3/18F01P2003/021
Inventor 姜欣宏徐志雄赵恒
Owner BEIJING SANKUAI ONLINE TECH CO LTD