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Aircraft engine and heat dissipation control method thereof

A control method and engine technology, which is applied in the direction of machine/engine, engine components, engine cooling, etc., can solve problems such as cylinder inner wall strain, engine working efficiency decline, heavy oil combustion is insufficient, etc., to achieve the effect of strengthening and weakening heat dissipation Effect

Active Publication Date: 2022-07-26
珠海天晴航空航天科技有限公司
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0003] However, the operating temperature of the heavy oil engine needs to be controlled within a specific range. If the operating temperature of the engine is lower than the specified temperature range of the engine, it will cause insufficient combustion of the heavy oil and the engine's working efficiency will decrease; if the operating temperature of the engine is higher than the specified temperature range , will cause the engine piston to cooperate too tightly with the cylinder, and the inner wall of the cylinder will be strained; therefore, controlling the working temperature of the heavy oil engine is very important to ensure the work of the heavy oil engine

Method used

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  • Aircraft engine and heat dissipation control method thereof
  • Aircraft engine and heat dissipation control method thereof
  • Aircraft engine and heat dissipation control method thereof

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Embodiment Construction

[0024] Embodiments of the present invention are described in detail below, examples of which are illustrated in the accompanying drawings, wherein the same or similar reference numerals refer to the same or similar elements or elements having the same or similar functions throughout. The embodiments described below with reference to the accompanying drawings are exemplary, only used to explain the present invention, and should not be construed as a limitation of the present invention.

[0025] In the description of the present invention, it should be understood that the azimuth description, such as the azimuth or position relationship indicated by up, down, front, rear, left, right, etc., is based on the azimuth or position relationship shown in the drawings, only In order to facilitate the description of the present invention and simplify the description, it is not indicated or implied that the indicated device or element must have a particular orientation, be constructed and ...

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Abstract

In the field of unmanned aerial vehicles, in order to adjust the working temperature of the engine simply and conveniently, the present invention discloses an aircraft engine, comprising: a cylinder block; a radiator fin, which is connected to the top of the cylinder block; The flow fin can change the flow direction of the airflow that flows through the guide fin and blows to the cylinder block; the adjustment device can adjust the deflection angle of the guide fin relative to the heat sink; the temperature sensor is arranged on the cylinder block; the application of the above aircraft engine can be simple The working temperature of the engine can be adjusted conveniently, and the invention also provides a method for controlling heat dissipation of the engine.

Description

technical field [0001] The invention relates to the field of unmanned aerial vehicles, in particular to an aircraft engine and a heat dissipation control method thereof. Background technique [0002] In the current civil drones, heavy oil engines are more and more used. Compared with gasoline engines, heavy oil engines have good durability, strong load capacity, high cost performance, high safety, and superior high-altitude performance. advantage. [0003] However, the working temperature of the heavy oil engine needs to be controlled within a specific range. If the working temperature of the engine is lower than the specified temperature range of the engine, it will cause insufficient combustion of the heavy oil and reduce the working efficiency of the engine; if the working temperature of the engine is higher than its specified temperature range , it will cause the engine piston and the cylinder to be too tight, and the inner wall of the cylinder will be pulled; therefore...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): F01P1/02F01P5/02F01P7/06F01P11/14
CPCF01P1/02F01P5/02F01P7/06F01P11/14F01P2001/023F01P2050/20
Inventor 贺军房佳琦曲长征张秋毫熊灿松肖宽容邓登宝
Owner 珠海天晴航空航天科技有限公司
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