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Engine heat insulation structure for oil-powered unmanned aerial vehicle

An engine and drone technology, applied in the cooling system of the power plant, etc., can solve the problem of not considering the engine and so on

Active Publication Date: 2019-03-19
沈阳旋飞航空技术有限公司
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  • Abstract
  • Description
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  • Application Information

AI Technical Summary

Problems solved by technology

[0008] This prior art effectively overcomes the defective of prior art, but still there is room for improvement
This prior art only provides a structure for dissipating heat from the engine, but does not consider the impact of the heat of the engine on other structures inside the UAV, especially for the fuel tank and electronic equipment that are compactly arranged in the narrow space inside the UAV. , need to provide technical solutions to reduce the risk of overheating, and need to consider minimizing the weight gain caused by solving the overheating problem

Method used

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  • Engine heat insulation structure for oil-powered unmanned aerial vehicle
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Embodiment Construction

[0024] In order to have a clearer understanding of the technical features, purposes and effects of the present invention, the specific implementation manners of the present invention will now be described with reference to the accompanying drawings. Wherein, the same parts adopt the same reference numerals.

[0025] As described in the background technology, the present invention aims at the deficiencies of the heat dissipation structure for oil-powered drones disclosed in the prior art Chinese patent application 201711089236.7, and proposes an engine heat insulation structure for oil-powered drones. In order to isolate the engine and its heat dissipation structure from other structures inside the fuselage, to reduce the risk of overheating caused by the heat of the engine to the fuel tank and electronic equipment that are compactly arranged in the small space inside the UAV.

[0026] Specifically, the engine heat insulation structure of the present invention is a further impr...

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Abstract

The invention provides an engine heat insulation structure for an oil-powered unmanned aerial vehicle. The engine heat insulation structure includes a first heat insulation plate and a second heat insulation plate which are arranged in the front and at the rear of an engine respectively. The first heat insulation plate and the second heat insulation plate are formed by a porous carbon fiber supporting plate and heat insulation cotton adhering to the carbon fiber supporting plate in an interlayer mode. The heat insulation cotton is disposed on one side of the carbon fiber supporting plate facing the engine. According to the engine heat insulation structure, the engine and a heat dissipation structure thereof are separated from other structures in a fuselage, and the risk of overheating caused to a fuel tank and an electronic device in compact layout in a narrow space in the unmanned aerial vehicle by engine heat can be reduced.

Description

technical field [0001] The invention relates to the technical field of unmanned aerial vehicles, in particular to a multi-rotor oil-powered unmanned aerial vehicle, and in particular to an engine heat insulation structure for an oil-powered unmanned aerial vehicle. Background technique [0002] Unmanned aircraft, referred to as "UAV", is an unmanned aircraft controlled by radio remote control equipment and its own program control device. According to the application field, UAV can be divided into military and civilian. In terms of military use, UAVs are divided into reconnaissance aircraft and target aircraft. Civilian drones are widely used in aerial photography, agriculture, plant protection, micro-selfies, express delivery, disaster relief, observation of wild animals, monitoring of infectious diseases, surveying and mapping, news reports, power inspections, disaster relief, film and television shooting and other fields. [0003] Existing multi-rotor drones are usually ...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64D33/10
CPCB64D33/10
Inventor 张建飞庞振岳宗宁刘新民鲁明彭璐刘士伟佟亮
Owner 沈阳旋飞航空技术有限公司
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