AIRCRAFT AND COAXIAL DUAL-ROTOR ASSEMBLY

WIPO Patent Application WO/2023/060678

A1

An aircraft (1), comprising a fuselage (10), a wing assembly (20), a tilt rotor assembly (50), and a coaxial dual-rotor assembly (60). The wing assembly (20) is connected to the fuselage (10); the tilt rotor assembly (50) is tiltably connected to the wing assembly (20); the coaxial dual-rotor assembly (60) comprises a mounting shaft (61), a first blade (63), and a second blade (65); the mounting shaft (61) is connected to the fuselage (10); the first blade (63) and the second blade (65) are respectively rotatably connected to two opposite ends of the mounting shaft (61); and the rotation direction of the first blade (63) is opposite to the rotation direction of the second blade (65). By means of the aircraft, the coaxial dual-rotor assembly is provided, and the rotation direction of the first blade of the coaxial dual-rotor assembly is opposite to the rotation direction of the second blade, so that a counter torque generated by the aircraft can be counteracted, the heading stability of the aircraft is improved, and the flight safety of the aircraft is guaranteed. Further provided is a coaxial dual-rotor assembly.

WANG TAN (CN)
LIANG YICHENG (CN)
LOU JINYUAN (CN)
SHI YICHEN (CN)
CAO XUEYU (CN)
WANG WEIMIN (CN)

PCT/CN2021/129532

April 20, 2023

November 09, 2021

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GUANGDONG HUITIAN AEROSPACE TECH CO LTD (CN)

B64C27/22; B64C11/48

WO2020247148A2

2020-12-10

CN106628163A	2017-05-10
CN210912855U	2020-07-03
DE102013001852A1	2014-07-31

SHENZHEN ZHIQUAN INTELLECTUAL PROPERTY OFFICE (CN)

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