The invention belongs to the field of aircraft control system design, and particularly relates to an aircraft control system with a trimming mechanism. Comprising a main driving control device, a co-driving control device, a left-side balancing execution mechanism, a right-side balancing execution mechanism, a balancing motor and a linkage pull rod. The main driving control device is provided with a first load mechanism and a first rocker arm; the co-driver control device is provided with a second load mechanism and a second rocker arm; the first end of the left balancing execution mechanism is connected with the fixed end of the first load mechanism, and the second end is connected with the first end of the left flexible shaft; the first end of the right balancing execution mechanism is connected with the fixed end of the second load mechanism, and the second end is connected with the first end of the right flexible shaft; the balancing motor is provided with a left output shaft and a right output shaft, the left output shaft is connected with the second end of the left flexible shaft, and the right output shaft is connected with the second end of the right flexible shaft; the first end of the linkage pull rod is connected with the first rocker arm, and the second end is connected with the second rocker arm.
本申请属于飞机操纵系统设计领域,特别涉及一种带配平机构的飞机操纵系统。包括:主驾驶操纵装置、副驾驶操纵装置、左侧配平执行机构、右侧配平执行机构、配平电机以及连动拉杆。主驾驶操纵装置配置有第一载荷机构以及第一摇臂;副驾驶操纵装置配置有第二载荷机构以及第二摇臂;左侧配平执行机构的第一端与第一载荷机构的固定端连接,第二端与左侧软轴的第一端连接;右侧配平执行机构的第一端与第二载荷机构的固定端连接,第二端与右侧软轴的第一端连接;配平电机具有左输出轴以及右输出轴,左输出轴与左侧软轴的第二端连接,右输出轴与右侧软轴的第二端连接;连动拉杆的第一端与第一摇臂连接,第二端与第二摇臂连接。
Aircraft control system with balancing mechanism
一种带配平机构的飞机操纵系统
2022-03-25
Patent
Elektronische Ressource
Chinesisch
IPC: | B64C AEROPLANES , Flugzeuge |
FUSELAGE POSITIONING MECHANISM (VERSIONS), AIRCRAFT AND AIRCRAFT BALANCING METHOD (VERSIONS)
Europäisches Patentamt | 2019
|Balancing of aircraft propellers
Engineering Index Backfile | 1941
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