Piston engine cooling circulating structure for parachuting recovery unmanned aerial vehicle

Abstract

The invention discloses a piston engine cooling circulating structure for a parachuting recovery unmanned aerial vehicle. The structure consists of an engine, a radiator, an expansion box, a pressurerelief cap, an overflow nozzle, an overflow bottle, a water pump, a cylinder block and a pipeline, wherein the radiator is mounted on the upper side of the engine. The radiator and the expansion box form an integral structure; the bottom of the expansion box communicates with a radiator cooling liquid runner; the expansion box is positioned in a high point inlet of one side of the radiator; and alow point outlet on the other side of the radiator communicates with the water pump through a connecting pipeline. The water pump and the expansion box communicate by the cylinder block and the connecting pipeline; the overflow bottle is positioned on the outer side of an engine main body; and an overflow nozzle is mounted on the overflow bottle, and communicates with the pressure relief cap on the expansion box through a connecting pipeline. When the engine works, an engine camshaft drives the water pump to convey cooling liquid to a cylinder block water jacket for cooling, and the cooling liquid flows out from the top of the cylinder block to enter the expansion box and the radiator for heat exchange, and flows out from the radiator to enter the water pump to realize closed cooling circulation.

Description

technical field [0001] The invention relates to the technical field of unmanned aerial vehicle piston engines, in particular to a piston engine cooling cycle structure for parachuting and recovering unmanned aerial vehicles. Background technique [0002] The engine cooling system is a device that dissipates the heat absorbed by the cylinder block in time when the engine is working, so as to ensure that it works at the most suitable temperature state. [0003] The existing cooling system for aviation piston engines for small unmanned aerial vehicles usually arranges the radiator on the lower side of the engine, the expansion tank is arranged on the uppermost side of the engine, and the whole engine is exposed to the atmospheric environment. This arrangement is suitable for low-speed and low-altitude flight, downhill type aircraft. [0004] In the existing public literature "Research on the Characteristics and Optimum Matching of Aviation Turbocharged Gasoline Engines" ("Beij...

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Problems solved by technology

[0004] In the existing public literature "Research on the Characteristics and Optimum Matching of Aviation Turbocharged Gasoline Engines" ("Beijing Jiaotong University", 2008 master's thesis, Chen Hong), the cooling system design for the ROTAX 914 aviation piston engine matching a certain type of aircraft , arrange the radiator on the lower side of the engine, and for medium-sized UAVs that fly at high speed and are parachuted and recovered, the engine compartment cover needs to be rectified, and in order to avoid damage to cooling components such as radiators during the recovery process of the UAV, The conventional layout of the cooling system is no longer suitable and needs to be redesigned

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