Stability and Control of a Structurally Nonlinear Aeroelastic System
Stability and Control of a Structurally Nonlinear Aeroelastic System
复制标题
DOI：
10.2514/2.4317
复制
发表时间：
1998-09
影响因子：
2.6
通讯作者：
J. Ko;T. Strganac;A. Kurdila
中科院分区：
文献类型：
--
作者：
J. Ko;T. Strganac;A. Kurdila
研究了一类基于反馈线性化技术的结构非线性典型二维机翼截面非线性控制的稳定性。在翼面只有一个后缘操纵面的情况下，研究了部分反馈线性化实现俯冲初级控制的稳定性。在这种情况下，与闭环系统响应有关的零动态在一定的速度和弹性轴位置范围内是局部渐近稳定的。然而，对于这种简单的反馈策略，存在着亚音速/不可压缩流的弹性轴和速度的位置，对于这些位置，存在着广泛的分叉现象。Hopf分叉和干叉分叉都随着低速和弹性轴位置的不同而参数演化。在翼面具有两个操纵面的情况下，研究了基于全反馈线性化的自适应控制方法的全局稳定性。与部分或完全反馈线性化技术相比，所提出的自适应控制策略不需要明确了解结构非线性的形式。
The authors examine the stability properties of a class of nonlinear controls derived via feedback linearization techniques for a structurally nonlinear prototypical two-dimensional wing section. In the case in which the wing section has a single trailing-edge control surface, the stability of partial feedback linearization to achieve plunge primary control is studied. It is shown for this case that the zero dynamics associated with the closed-loop system response are locally asymptotically stable for a range of e ow speeds and elastic axis locations. However, there exist locations of the elastic axis and speeds of the subsonic/incompressible e ow for which this simple feedback strategy exhibits a wide range of bifurcation phenomena. Both Hopf and pitchfork bifurcations evolve parametrically in terms of the e ow speed and elastic axis location. In the case in which the wing section has two control surfaces, the global stability of adaptive control techniques derived from full feedback linearization is studied. In comparison with partial or full feedback linearization techniques, the adaptive control strategies presented do not require explicit knowledge of the form of the structural nonlinearity.