Cooling structure of air-cooled rotor engine and unmanned aerial vehicle
A technology of rotary engine and cooling structure, applied in the direction of engine cooling, engine components, combustion engine, etc., to achieve the effect of small size, good power-to-weight ratio of the whole machine, and improved heat dissipation efficiency
Pending Publication Date: 2022-08-05
西安空天机电智能制造有限公司
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Problems solved by technology
[0004] The purpose of the present invention is to solve the above-mentioned problems existing in the existing engine, and provide a cooling structure for an air-cooled rotary engine with a reasonable and compact structure design, high engine overall strength, high cooling efficiency, and a solution to the heat load problem of the rotor and drones
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[0030] Example: Reference Figure 1-Figure 6 As shown, this embodiment mainly aims at some problems such as unreasonable heat dissipation structure, poor heat dissipation effect or low overall strength of the existing rotary engine, and provides a cooling structure of an air-cooled rotary engine, figure 1 and Image 6 They are the exploded schematic diagram and the structural schematic diagram of the rotary engine, respectively. The engine includes a cylinder block and a front end cover 1 and a rear end cover 5 that are fixedly connected to both ends of the cylinder block 3 respectively. Therefore, the whole engine is a circular or oval or "8"-shaped annular structure; the outer wall of the cylinder block 3 is provided with an intake port 303, an exhaust port 302 and a spark plug hole 307 that communicate with the working chamber; the engine It also includes a rotor assembly 2 arranged inside the cylinder block 3 and a main shaft assembly 4 which is axially matched with the r...
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The invention discloses a cooling structure of an air-cooled rotor engine and an unmanned aerial vehicle, and belongs to the technical field of engines. The engine comprises a cylinder body, a front end cover and a rear end cover, wherein the front end cover and the rear end cover are fixedly connected to the two ends of the cylinder body respectively. The cooling structure comprises circumferential cooling ribs arranged around the circumferential outer wall of the engine in a radial mode and end cover cooling ribs arranged at the two ends of the engine and extending in the axial direction. The circumferential heat dissipation ribs comprise cylinder body circumferential heat dissipation ribs arranged on the circumferential outer wall of the cylinder body, and the end cover heat dissipation ribs comprise end cover axial heat dissipation ribs arranged on the outer walls of the front end cover and the rear end cover. The cooling structure is applied to the rotor engine and is exquisite and reasonable in structural design, the engine is small in appearance size, and the cooling structure is compact in layout and high in integration level; by means of the various heat dissipation ribs, the heat dissipation efficiency of the engine in the operation process is improved, meanwhile, the overall strength of the engine is improved, and the power-to-weight ratio of the whole engine is increased; the problem of thermal load of the rotor under the conditions that the wheelbase coefficient of the air-cooled rotor engine is large and the rotor is thick is solved.
Description
technical field [0001] The invention belongs to the technical field of rotary engines, and particularly designs a cooling structure of an air-cooled rotary engine and an unmanned aerial vehicle. Background technique [0002] The power-to-weight ratio and fuel consumption of the small aero-rotary engine are between the turbojet turbofan and the piston engine. The small aeronautical rotary engine with high work efficiency, high compactness and stable aerial work is the best power configuration for small UAVs. However, the existing small aviation air-cooled rotary engine has a low degree of commercialization, poor cooling effect, and the design and technology level still remain in the last century. In some application scenarios (such as the volume and structure of cruise missiles), It is even more difficult to meet the application requirements of small aeronautical rotary engines for small size, high compactness, heat dissipation efficiency, and efficient and stable work. [...
Claims
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IPC IPC(8): F02C7/12F02C7/18F01D25/12F01D25/14
CPCF02C7/12F02C7/18F01D25/125F01D25/14Y02T10/12
Inventor 魏智辉刘选科党娅周杜洋王瑞
Owner 西安空天机电智能制造有限公司