The invention discloses a vertical tail hinge moment load shedding method for a high-speed variable vertical tail aircraft, which is used for controlling the hinge moment at the root of a vertical tail to be always kept minimum when the deformation coefficient is continuously changed between 0 and 1 by referring to the thought of extreme value optimization control. The method comprises the following steps: firstly, analyzing hinge moment characteristics of the variable vertical tail structure in high-speed flight to obtain parameters which have great influence on the hinge moment; then, on the basis of an extreme value optimization control thought, the deformation coefficient is used as a scheduling parameter, the rudder deflection angle is used as an independent variable, a control target is a hinge moment amplitude at the root of the vertical empennage, and the deformation coefficient is always kept minimum when continuously changing between 0 and 1; and finally, the self-adaptive variable vertical tail hinge moment load shedding method is formed.
本发明公开了高速变立尾飞行器立尾铰链力矩减载方法,其借鉴极值寻优控制的思路,控制立尾翼根处的铰链力矩在变形系数0~1之间连续变化时始终保持最小。首先对高速飞行中变立尾结构的铰链力矩特性进行分析,获取对铰链力矩影响较大的参数。然后,基于极值寻优控制思路,以变形系数为调度参数,方向舵偏角为自变量,控制目标为立尾翼根处的铰链力矩幅值,使在变形系数在0~1之间连续变化时始终保持最小。最终构成自适应变立尾铰链力矩减载方法。
Vertical tail hinge moment load shedding method for high-speed variable vertical tail aircraft
高速变立尾飞行器立尾铰链力矩减载方法
2024-12-10
Patent
Electronic Resource
Chinese
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