Compact-type multi-rotor fuel-electric hybrid unmanned aerial vehicle

A technology of unmanned aerial vehicles and rotor oil, which is applied in the direction of rotorcraft, unmanned aircraft, fuselage, etc., can solve the problems of inconvenient carrying and placement, large volume, etc., and achieve compact structure, stable flight, and reduced interference Effect

Pending Publication Date: 2018-10-02
GUANGZHOU WALKERA TECH CO LTD
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  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0006] The invention provides a compact multi-rotor oil-electric hybrid unmanned aerial vehicle, which is used to solve the problems in t

Method used

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  • Compact-type multi-rotor fuel-electric hybrid unmanned aerial vehicle
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  • Compact-type multi-rotor fuel-electric hybrid unmanned aerial vehicle

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Embodiment

[0082] A compact multi-rotor oil-electric hybrid UAV, such as figure 1 As shown, it includes a fuselage 1 and a plurality of rotors 2 evenly spaced on the side of the fuselage. The bottom of the fuselage 1 is provided with an engine module 3, a generator module 4 and a pan-tilt assembly 5, such as figure 2 As shown, the top of the fuselage 1 is provided with a fuel tank 6; the inside of the fuselage 1 is provided with a control system, the fuselage 1 includes a first fixed plate 11 and a second fixed plate 12, and the engine module 3, The generator module 4 and the cloud platform assembly 5 are located at the lower end of the first fixed plate 11, the engine module 3 is connected to the generator module 4, the engine module 3 can drive the generator module 4 to run, and the The generator module 4 and the pan / tilt assembly 5 are electrically connected to the control system respectively;

[0083] Such as figure 2 As shown, the rotor 2 is hinged to the side of the first fixed...

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Abstract

The invention provides a compact-type multi-rotor fuel-electric hybrid unmanned aerial vehicle. The compact-type multi-rotor fuel-electric hybrid unmanned aerial vehicle comprises a fuselage and a plurality of rotors evenly arranged on the side surface of the fuselage at intervals. An engine module, an electric generator module and a pan-tilt assembly are arranged at the bottom of the fuselage, afuel tank is arranged at the top end of the fuselage, and a control system is arranged in the fuselage. The fuselage includes a first fixed plate and a second fixed plate, the engine module, the electric generator module and the pan-tilt assembly are arranged at the lower end of the first fixed plate, the engine module is connected with an electric generator, the engine module can drive the electric generator to operate, and the electric generator and the pan-tilt assembly are separately and electrically connected to the control system. The rotors are hinged to the side surface of the first fixed plate, and folding of the rotors is realized. The ends, close to the fuselage, of the rotors are proximal ends, and the ends, away from the fuselage, of the rotors are distal ends. Motors and propellers are arranged at the distal ends of the rotors, and the motors are electrically connected to the control system and the propellers and can drive the propellers to rotate.

Description

technical field [0001] The invention relates to the technical field of a hybrid electric drone, in particular to a compact multi-rotor hybrid drone. Background technique [0002] With the development of high-tech, unmanned aerial vehicle technology continues to make breakthroughs, unmanned aerial vehicle will be developed rapidly and more widely used. In the field of drones, although a series of advanced technologies such as visual positioning, high-definition image transmission, and sensory barriers continue to develop, the fundamental problem of battery life has not been effectively resolved. [0003] The multi-rotor UAV relies on the lift generated by multiple rotors to balance the gravity of the aircraft, so that the aircraft can fly, and the stability and attitude of the aircraft can be controlled by changing the speed of each rotor. Therefore, the multi-rotor aircraft can hover and fly at any speed within a certain speed range. It is basically a platform for flying in...

Claims

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Application Information

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IPC IPC(8): B64C27/08B64D27/26B64D47/08B64D37/04B64C1/30
CPCB64C1/30B64C27/08B64D27/26B64D37/04B64D47/08B64U50/19B64U10/10
Inventor 罗之洪李奔夏烨罗强
Owner GUANGZHOU WALKERA TECH CO LTD
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