The invention discloses a flapping-hinge-free helicopter rotor wing capable of automatically adjusting rotor wing lift force, and belongs to the technical field of helicopter rotor wing design, the flapping-hinge-free helicopter rotor wing comprises a helicopter main shaft, a large rotor wing, a small adjusting rotor wing, a large rotor wing connecting rod, a small rotor wing connecting rod, a rotor wing rotating shaft and a rotor wing deflection limiting block, and the large rotor and the small adjusting rotor are connected through a large and small rotor connecting rod. The rotor wing rotating shafts are symmetrically installed on the helicopter main shaft, one ends of the rotor wing rotating shafts are fixedly connected to the large rotor wings, the other ends of the rotor wing rotating shafts are rotationally connected into the helicopter main shaft, rotor wing deflection limiting blocks are further arranged between the large rotor wings and the helicopter main shaft, and one ends of the rotor wing deflection limiting blocks are fixedly arranged on the large rotor wings. The other end of the rotor wing deflection limiting block is connected into the helicopter spindle in a limited rotating mode. According to the invention, the flying stability of the helicopter can be improved, and the rotor hub structure is greatly simplified.
本发明公开了一种能自动调整旋翼升力的无挥舞铰直升机旋翼,属于直升机旋翼设计技术领域,包括直升机主轴、大旋翼、调节小旋翼、大小旋翼连接杆、旋翼转轴和旋翼偏转限位块,大旋翼的后缘上方设有调节小旋翼,大旋翼和调节小旋翼之间通过大小旋翼连接杆连接。旋翼转轴对称安装在直升机主轴上,旋翼转轴的一端固定连接于大旋翼上,旋翼转轴的另一端转动连接于直升机主轴内,大旋翼和直升机主轴之间还设有旋翼偏转限位块,旋翼偏转限位块的一端固定设于大旋翼上,旋翼偏转限位块的另一端限制转动连接在直升机主轴内。本发明既能提高直升机飞行的稳定平稳性,又大大简化了旋翼桨毂结构。
No-flapping-hinge helicopter rotor wing capable of automatically adjusting rotor wing lift force
一种能自动调整旋翼升力的无挥舞铰直升机旋翼
2022-12-09
Patent
Electronic Resource
Chinese
IPC: | B64C AEROPLANES , Flugzeuge |
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