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Fuel-electric hybrid four-rotor power unit and control method thereof

A power unit and hybrid power technology, which is applied in the field of oil-electric hybrid four-rotor power unit and its control, can solve the problems of complex control of oil-powered quad-rotor aircraft and small load of electric quad-rotor aircraft, so as to improve application value and extend battery life Time, the effect of expanding the scope of application

Inactive Publication Date: 2017-04-19
北京天宇新超航空科技有限公司
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AI Technical Summary

Problems solved by technology

[0004] The purpose of the present invention is to provide a kind of aircraft that can effectively solve the contradiction between the small load of the electric quadrotor aircraft and the complex control of the oil-driven quadrotor aircraft, and simultaneously provide a control method for the hybrid quadrotor aircraft

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  • Fuel-electric hybrid four-rotor power unit and control method thereof
  • Fuel-electric hybrid four-rotor power unit and control method thereof

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Embodiment Construction

[0021] The present invention will be further described below in conjunction with drawings and embodiments.

[0022] figure 1 The overall block diagram of the hybrid quadrotor power unit is shown, in which the dotted lines represent communication cable connections, and the solid lines represent mechanical connections. refer to figure 1 , The hybrid four-rotor power unit includes a fuel engine, a transmission system, a generator, a propeller, and a traction motor arranged between the propeller and the transmission system. When the power unit needs extra torque to start, the electric motor can directly generate traction torque to start the engine. In this embodiment, the traction motor is located between the transmission system and the propeller, which is beneficial to the structural design of the power unit.

[0023] According to an embodiment of the present invention, the engine converts heat energy generated by fuel combustion into kinetic energy of moving parts such as pis...

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Abstract

The invention discloses a hybrid four-rotor unmanned aerial vehicle and a control method thereof. The hybrid unmanned aerial vehicle comprises a fuel engine (1), a traction motor (2), a drive system (3) and a whole machine control unit (4). The system and the method are characterized in that the actual torque of an input shaft of the drive system is controlled or compensated by controlling the torque source of the traction motor on the basis of the measured input torque of the drive system. According to the four-rotor unmanned aerial vehicle, the fuel engine provides most of the driving force for propellers, and the traction motor provides the acceleration driving force and the regenerative braking force for the propellers, so that the attitude of the unmanned aerial vehicle is controlled. The hybrid four-rotor unmanned aerial vehicle has the advantages of high energy density of the fuel engine and simple control of electric multi-rotors.

Description

technical field [0001] The invention relates to an oil-electric hybrid four-rotor power unit and a control method thereof, belonging to the technical field of aviation products. Background technique [0002] The four-rotor aircraft is operated and controlled by the radio remote control system and the autonomous flight control system to realize the aircraft's take-off and landing, forward and backward flight, acceleration and deceleration, and direction control. Maneuverability, stability, effective mission load and endurance time are important indicators for examining quadrotor aircraft. Under the same maneuverability and stability conditions, users pursue greater effective mission load and long-term endurance flight capability. [0003] In traditional quadrotor aircraft, motors are installed on the rotating shafts of the propellers to drive the propellers to achieve the purpose of flight, and the lift force of each rotor is changed by changing the motor speed to control the...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64D27/24B64D27/02B64C27/32
CPCB64C27/32B64D27/02B64D27/24B64D27/026Y02T50/60
Inventor 胡龙王一博
Owner 北京天宇新超航空科技有限公司
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