The invention discloses a helicopter rotor blade based on a seamless trailing edge flap mechanism. The helicopter rotor blade comprises a blade body and a plurality of trailing edge flap modules, wherein the trailing edge flap module comprises a shell, a driver, a push-pull rod, a driving rod, a mounting platform, a first flexible hinge, a second flexible hinge, a trailing edge flap and a sealingpiece; the driver generates dynamic linear displacement output; the driver, the push-pull rod, the driving rod and the trailing edge flap are connected in sequence, and the force and displacement generated by the driver are output and transmitted to the trailing edge flap; and the trailing edge flap is connected with the mounting platform through the second flexible hinge, and the linear reciprocating motion of the push-pull rod is converted into the deflection motion of the trailing edge flap through the second flexible hinge. The helicopter rotor blade is applied to the trailing edge flaps of the helicopter to actively control a rotor wing, the aerodynamic load distribution of the blade is dynamically changed through dynamic deflection of the trailing edge flaps, the vibration load of the rotor wing of the helicopter is inhibited, or the noise of the rotor wing is inhibited through a sound field cancellation method.
本发明公开了一种基于无缝后缘襟翼机构的直升机旋翼桨叶,包含桨叶本体和若干后缘襟翼模块;后缘襟翼模块包含壳体、驱动器、推拉杆、驱动杆、安装平台、第一柔性铰链、第二柔性铰链、后缘襟翼和密封片。驱动器产生动态直线位移输出;驱动器、推拉杆、驱动杆、后缘襟翼依次相连,驱动器产生的力和位移输出传递到后缘襟翼;后缘襟翼通过第二柔性铰链与安装平台相连,并通过第二柔性铰链将推拉杆的直线往复运动转换为后缘襟翼偏转运动。本发明用于直升机后缘襟翼主动控制旋翼,通过后缘襟翼动态偏转,动态改变桨叶气动载荷分布,抑制直升机旋翼振动载荷,或通过声场对消的方法抑制旋翼噪声。
Helicopter rotor blade based on seamless trailing edge flap mechanism
基于无缝后缘襟翼机构的直升机旋翼桨叶
2020-04-10
Patent
Elektronische Ressource
Chinesisch
IPC: | B64C AEROPLANES , Flugzeuge |
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