The invention belongs to the technical field of helicopter aerodynamic design, and discloses a large sweepback combined helicopter rotor blade. A blade root joint is arranged at the root of the blade,the blade root joint is provided with two longitudinal connecting holes, the inner walls of the connecting holes are connected with shear bolts, and the blade root joint is connected with a rotor hubsupport arm through the shear bolts. The blade main airfoil section starts from the relative radius of 0.2667 R, and the airfoil thickness from the relative radius of 0.2667 R to the blade tip is 7%-12%. The torsion angles of the helicopter rotor blades from the rotation center to the relative radius of 0.2667 R are kept consistent, the aerodynamic torsion rate from the relative radius of 0.2667R to the blade tip is X, and the forward flight performance is considered while the rotor hovering performance is guaranteed.
本发明属于直升机气动设计技术领域,公开了一种大前后掠组合的直升机旋翼桨叶。述桨叶的根部设有桨根接头,桨根接头有两个纵列式的连接孔,且连接孔的内壁连接有剪力螺栓,桨根接头通过剪力螺栓连接旋翼桨毂支臂。所述桨叶主翼型段起始于相对半径0.2667R,从相对半径0.2667R至桨尖的翼型厚度为7%‑12%。所述直升机旋翼桨叶自旋转中心到相对半径0.2667R的扭转角保持一致,从相对半径0.2667R至桨尖的气动扭转率为X,在保证了旋翼悬停性能的同时兼顾前飞性能。
Large sweepback combined helicopter rotor blade
一种大前后掠组合的直升机旋翼桨叶
2021-01-05
Patent
Elektronische Ressource
Chinesisch
IPC: | B64C AEROPLANES , Flugzeuge |
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