The invention provides a rudder blade hinge moment adjusting method, a hinge moment adjustable rudder blade and a control method thereof, and solves the problem of overlarge hinge moment in the flight process of an aircraft by changing the relative position between the rudder blade and a rudder shaft. The rudder shaft is a movable rudder shaft and can move within a set range in the chord length direction of the rudder sheet; therefore, the relative position between the rudder piece and the rudder shaft is changed (namely, the position of the rudder shaft relative to the rudder piece is changed), the distance between the resultant force point and the rudder shaft is changed, the hinge moment is changed, and the problem that the hinge moment is too large in the flight process of an aircraft is solved.
本发明提供一种舵片铰链力矩调节方法、铰链力矩可调式舵片及其控制方法,通过舵片与舵轴之间相对位置的改变,解决航行器飞行过程中铰链力矩过大的问题。本发明中舵轴为可移动舵轴,能够沿舵片的弦长方向在设定范围内移动;由此实现舵片与舵轴之间相对位置的改变(即改变舵轴相对舵片的位置),进而改变合力点到舵轴的距离,以实现铰链力矩的改变,解决航行器飞行过程中铰链力矩过大的问题。
Rudder piece hinge moment adjusting method, hinge moment adjustable rudder piece and control method
一种舵片铰链力矩调节方法、铰链力矩可调式舵片及控制方法
2025-02-18
Patent
Electronic Resource
Chinese
IPC: | B64C AEROPLANES , Flugzeuge |
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