The invention provides a coaxial helicopter capable of reducing kinetic energy loss of spin forced landing. The helicopter comprises an upper rotor assembly, a lower rotor assembly, a central shaft and a rotation driving assembly, the central shaft penetrates through the upper rotor assembly and the lower rotor assembly, the upper rotor assembly comprises an upper blade assembly, the lower rotor assembly comprises a lower blade assembly, and the rotation driving assembly is connected with the central shaft. The rotation driving assembly drives the upper paddle assembly and the lower paddle assembly to rotate and comprises a motor, a speed reduction assembly and at least two one-way bearings, the motor is connected with the speed reduction assembly, and the speed reduction assembly is connected between the upper paddle assembly and the lower paddle assembly. One-way bearings are respectively arranged between the motor and the upper paddle assembly and between the motor and the lower paddle assembly, and by adopting the structure and utilizing the one-way rotation property of the one-way bearings, the one-way bearings enable rigid connection between the power output motor and the rotor wing assembly to be disconnected in a power loss spinning forced landing stage; therefore, kinetic energy loss caused by magnetic damping of the motor in the spin forced landing stage is reduced.
本发明提供一种减少自旋迫降动能损失的共轴直升机,该直升机包括上旋翼组件、下旋翼组件、中心轴和转动驱动组件,中心轴贯穿上旋翼组件和下旋翼组件,上旋翼组件包括上桨叶组件,下旋翼组件包括下桨叶组件,转动驱动组件分别驱动上桨叶组件和下桨叶组件转动,转动驱动组件包括电机、减速组件和至少两个单向轴承,电机与减速组件连接,减速组件分别与上桨叶组件、下桨叶组件之间,电机与上桨叶组件之间和设置在电机与下桨叶组件之间分别设置有单向轴承,采用以上结构,利用单向轴承的单向旋转性,在失去动力自旋迫降阶段中,单向轴承使动力输出电机与旋翼组件之间断开硬性连接,以减少自旋迫降阶段电机的磁阻尼带来的动能损失。
Coaxial helicopter capable of reducing kinetic energy loss of spin forced landing
减少自旋迫降动能损失的共轴直升机
2021-07-23
Patent
Electronic Resource
Chinese
IPC: | B64C AEROPLANES , Flugzeuge |
Engineering Index Backfile | 1946
|METHOD OF FORCED LANDING OF HELICOPTER TYPE UNMANNED AIRCRAFT AT THE VESSEL LANDING PLATFORM
European Patent Office | 2017
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NTIS | 1977
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