The invention relates to the field of aircraft design, in particular to a tilt-wing vertical take-off and landing aircraft and a rotor angle design method, the tilt-wing vertical take-off and landing aircraft comprises an aircraft body unit, the aircraft body unit comprises an aircraft body and an undercarriage, and a first included angle alpha 1 is formed between the minimum air resistance direction of the aircraft body and the bottom plane of the undercarriage; the rotor wing unit comprises a rotor wing assembly, the rotor wing assembly comprises a support, a paddle and a driver, the paddle is rotationally arranged on the support, the support is connected with the fuselage, the output end of the driver is connected to the paddle, a second included angle alpha 2 is formed between a rotating shaft of the paddle and the minimum air resistance direction, and the sum of the first included angle alpha 1 and the second included angle alpha 2 is 90 degrees; the wing unit comprises a wing assembly and a posture adjusting assembly, the posture adjusting assembly is rotationally connected to the fuselage, and the wing assembly is arranged on the posture adjusting assembly.
本发明涉及飞行器设计领域,特别是一种倾转机翼垂直起降飞行器及旋翼角度设计方法,倾转机翼垂直起降飞行器,其包括机体单元,机体单元包括机身和起落架,机身的最小空气阻力方向与起落架底部平面之间形成第一夹角α1;旋翼单元,旋翼单元包括旋翼组件,旋翼组件包括支架、桨叶和驱动器,桨叶转动设置在支架上,支架与机身相连,驱动器的输出端连接于桨叶,桨叶的旋转轴与最小空气阻力方向之间形成第二夹角α2,第一夹角α1和第二夹角α2的角度之和为90度;机翼单元,机翼单元包括机翼组件和姿态调整组件,姿态调整组件转动连接于机身,机翼组件设置于姿态调整组件上。
Tilting wing vertical take-off and landing aircraft and rotor angle design method
一种倾转机翼垂直起降飞行器及旋翼角度设计方法
22.10.2024
Patent
Elektronische Ressource
Chinesisch
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