Parallel power supply type multi-rotor wing unmanned aerial vehicle hybrid power device based on heavy oil internal combustion engine

Abstract

The invention discloses a parallel power supply type multi-rotor wing unmanned aerial vehicle hybrid power device based on a heavy oil internal combustion engine. The device comprises a heavy oil internal combustion engine, a conditioning unit and a lithium battery, wherein the device is characterized in that an output shaft of the heavy oil internal combustion engine is fixedly connected to a generator rotor; a generator is electrically connected with the conditioning unit; the conditioning unit is electrically connected with the heavy oil internal combustion engine through a controller, a double-way switch is arranged inside the conditioning unit, a first input port of the double-way switch is connected with a rectifying circuit, and a second input port of the double-way switch is connected with the lithium battery.

Description

technical field [0001] The invention relates to an unmanned aerial vehicle hybrid power device, in particular to a parallel power supply type multi-rotor unmanned aerial vehicle hybrid power device based on a heavy oil internal combustion engine. Background technique [0002] A multi-rotor UAV is a special unmanned helicopter with three or more rotor shafts. It is rotated by an electric motor on each shaft to drive the rotor, thereby generating thrust. The collective pitch of the rotors is fixed, not variable like normal helicopters. By changing the relative rotational speed between different rotors, the size of the single-axis propulsion can be changed, thereby controlling the trajectory of the aircraft. [0003] The UAV hybrid power device is powered by two or more drive units that can operate simultaneously. It selects different drive units to provide power independently or jointly according to the actual driving state of the UAV. According to the classification of pow...

AI Technical Summary

Problems solved by technology

Due to the existence of the charging function, this type of structure needs to introduce an additional set of high-power charging circuit, which increases the overall weight of the power unit; at the same time, due to the power loss in the charging process, to maintain the long-term continuous output capacity of the power unit, it is necessary to use a larger power unit. power of the internal combustion engine, undoubtedly increases the cost and quality

[0005] The multi-rotor UAV application platform with high electrical integration has multiple ignition sources hazards, such as electric ignition caused by line faults, or radio frequency sparks caused by radio waves

However, the multi-rotor hybrid power devices in the existing market are all developed based on gasoline internal combustion engines. Gasoline has a low flash point (-50°C) and is volatile. There are potential safety hazards in the actual application process.

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