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Electronic control system and control method for electricity-oil hybrid unmanned aerial vehicle energy system

An electronic control system and energy system technology, applied in battery/battery traction, electric vehicles, vehicle energy storage, etc., can solve problems such as insufficient power, flameout, insufficient reliability and stability, and achieve stable power generation voltage, The effect of high energy conversion efficiency

Pending Publication Date: 2018-06-22
南京婆娑航空科技有限公司
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AI Technical Summary

Problems solved by technology

However, the reliability and stability of fuel engines are insufficient compared to batteries, and they are prone to failures leading to insufficient power or even flameout, and poor speed stability. Therefore, a good electronic control system is needed to improve the stability and reliability of the energy system, and Reduce energy consumption and improve energy conversion efficiency

Method used

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Embodiment Construction

[0024] The present invention will be further described below in conjunction with the accompanying drawings. The following examples are only used to illustrate the technical solution of the present invention more clearly, but not to limit the protection scope of the present invention.

[0025] Such as figure 1 As shown, an electronic control system of an oil-electric hybrid unmanned aerial vehicle energy system, the energy system includes an engine connected to the oil cylinder, a generator connected to the engine, a backup battery and a lift motor, and the electronic control system includes an engine working condition acquisition module, Analog signal sampling circuit, engine control unit, electric energy mixing module and bidirectional rectification module, the engine working condition acquisition module can collect the throttle signal output from the flight controller to the electronic governor, the engine magneto ignition signal or CDI ignition signal, throttle opening tem...

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Abstract

The invention discloses an electronic control system and control method for an electricity-oil hybrid unmanned aerial vehicle energy system. The energy system comprises an engine, a power generator, astandby battery and a lift motor, and the power generator is connected with the engine which is connected with an oil tank. The electronic control system comprises an engine operating condition acquisition module, a power generator voltage and current sampling module, an electric energy mixing module, a bidirectional rectifying module and an engine control unit. The engine control unit comprisesan engine throttle opening control module and an engine injection quality control module. Accurate control of the electricity-oil hybrid unmanned aerial vehicle energy system can be realized, energy conversion efficiency is improved, fault redundancy is provided, and stability and reliability of the energy system can be remarkably improved.

Description

technical field [0001] The invention relates to an electronic control system and a control method of an oil-electric hybrid unmanned aerial vehicle energy system, and belongs to the technical field of energy system control. Background technique [0002] The multi-rotor drone is a kind of unmanned aerial vehicle that has emerged in recent years. It rotates the motor on each axis to drive the rotor to generate thrust. 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. Its structure is simple, maintenance is convenient, and the price is relatively low, so it is used in many occasions, such as aerial photography, plant protection, power line inspection and other fields. However, the existing multi-rotor drones are mainly driven by electricity, and the source of electric energy is the onboard battery. Due to the impact of battery technology, the battery lif...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64D27/02B64D27/24B64D31/06B60L11/18
CPCB64D27/02B64D27/24B64D31/06B60L50/50Y02T50/60Y02T10/70
Inventor 尹彦卿
Owner 南京婆娑航空科技有限公司
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