Design of nonlinear flight control law based on bifurcation tailoring
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摘要: 应用分支裁剪和特征结构配置的方法进行了飞行控制律的全局连续设计.以飞机本体动力学系统平衡图为基础,采用连续方法设计前馈控制律,修改平衡图的分支形状,使系统输出跟踪操纵输入指令.应用特征结构配置的方法设计全局调参的纵、横航向解耦反馈控制律,满足飞行品质要求,裁剪非指令运动对应的平衡分支.对开环前馈控制以及闭环反馈控制的控制分叉进行了分析.针对某静不稳定飞机进行控制律设计和数值仿真,结果表明不期望分叉得到抑制,飞机稳定飞行范围得以扩展.Abstract: The global and continuous flight control law was designed via the bifurcation tailoring and eigenstructure assignment methods. Based on the equilibrium branches of aircraft flight dynamics, the feedforward control law was designed by utilizing the continuous method, by which the shape of the equilibrium branches was modified to make the output variables trace the input commands. The uncoupled gain-scheduled feedback control law was designed via the eigenstructure assignment technique to meet the requirement of flying qualities, and the equilibrium branches of the uncommand motion were tailored. Control bifurcation was analyzed for the feedforward open-loop control system and the feedback closed-loop control system. The control law design and computer simulation for a static unstable aircraft were presented to demonstrate that the unexpected bifurcation behaviors were restrained and the stable flight envelope was extended.
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Key words:
- flight dynamics /
- bifurcation /
- eigenvalues /
- nonlinear control system
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