The invention discloses a vertical take-off and landing aircraft and a tilting rotor pneumatic control method thereof, and aims to solve the problems that the tilting angle of a rotor tilting mechanism of an existing tilting rotor aircraft is controlled through a motor, so that the reliability is poor, the attitude of the aircraft is difficult to control, the fault rate is high, and the damage degree caused by faults is large. According to the aircraft, wings are fixed to a fuselage, rotor wing tilting mechanisms at the tail ends of the wings can rotate on hinge shafts, fan-shaped worm wheels are fixedly connected with the inner walls of the wings, worms with motor control are fixed to nacelle frames of the rotor wing tilting mechanisms, and universal joints connected with the hinge shafts are located at the roots of the wings; the two empennage tilting mechanisms are symmetrically arranged on the two sides of the tail of the fuselage and fixedly connected with the empennage shaft. The method comprises the steps that the direction of the rotor propeller is adjusted by adjusting the circulating pitch and the collective pitch of the rotor propeller, and the rotation angular speed is limited through the fan-shaped worm gear and the worm. The reliability of the aircraft can be improved, the weight of the aircraft is reduced, and the aerodynamic performance is improved.
一种垂直起降飞行器及其可倾转旋翼气动控制方法,以解决现有倾转旋翼飞行器是通过电动机控制旋翼倾转机构倾转的角度,存在可靠性差、飞行器姿态难以控制、故障率高、故障发生危害程度大的问题。飞行器:机翼固定在机身上,机翼末端的旋翼倾转机构可在铰链轴上旋转,扇形蜗轮与机翼内壁固接,带有电机控制的蜗杆固定在旋翼倾转机构的短舱框架上,连接铰链轴的万向节位于机翼根部,两个尾翼倾转机构对称设置在机身尾部的两侧,尾翼倾转机构与尾翼轴固接。方法:通过调节旋翼螺旋桨的循环螺距和集体螺距的方式调整旋翼螺旋桨的方向,通过扇形蜗轮和蜗杆限制旋转角速度。本发明可以提高飞行器的可靠性,减轻飞行器的重量以及提升气动性能。
Vertical take-off and landing aircraft and tilting rotor pneumatic control method thereof
一种垂直起降飞行器及其可倾转旋翼气动控制方法
02.07.2024
Patent
Elektronische Ressource
Chinesisch
IPC: | B64C AEROPLANES , Flugzeuge |
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