The invention relates to an aircraft force comprehensive adjusting device, and belongs to the field of flight control. The device comprises an upper rocker arm, a left rocker arm, a right rocker arm, a middle rocker arm, a bolt and a ball bearing, the upper end A of the upper rocker arm is hinged with the control line system; the upper ends of the left rocker arm and the right rocker arm are fixedly connected with two ends of the upper rocker arm respectively; the bolt penetrates through the middle parts E of the left rocker arm, the middle rocker arm and the right rocker arm; the left rocker arm, the middle rocker arm and the right rocker arm rotate around the bolt through respective ball bearings; the upper end F of the middle rocker arm is hinged with the input end of the booster; the lower ends B of the left rocker arm, the right rocker arm and the middle rocker arm are coaxial and concentric, the lower ends B of the left rocker arm and the right rocker arm are hinged to the structure installation support, and the lower end B of the middle rocker arm is hinged to the output end of the stability augmentation steering engine.
本发明涉及一种飞机力综合调节装置,属于飞行控制领域。该装置包括:上摇臂、左摇臂、右摇臂、中摇臂、螺栓、滚珠轴承;上摇臂的上端A与操纵线系铰接,左摇臂、右摇臂的上端分别与上摇臂的两端固连;螺栓穿过左摇臂、中摇臂和右摇臂的中部E,左摇臂、中摇臂和右摇臂通过各自的滚珠轴承绕螺栓旋转;中摇臂的上端F与助力器输入端铰接;左摇臂、中摇臂和右摇臂三者下端共轴同心,其中,左右摇臂下端B铰接在结构安装支架上,中摇臂下端B铰接在增稳舵机输出端。
Aircraft force comprehensive adjusting device
一种飞机力综合调节装置
2025-02-18
Patent
Electronic Resource
Chinese
IPC: | B64C AEROPLANES , Flugzeuge |
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