Adaptive Feedback Linearization for the Control of a Typical Wing Section With Structural Nonlinearity Academic Article uri icon

abstract

  • Abstract Earlier results by the authors have derived constructions of Lie algebraic partial feedback linearizing control methods for pitch and plunge primary control utilizing a single trailing edge actuator. In addition, a globally stable nonlinear adaptive control method was derived for a structurally nonlinear wing section with both a leading and trailing edge actuator. However, the global stability result described in a previous paper by the authors, while highly desirable, relied on the fact that the leading and trailing edge actuators rendered the system exactly feedback linearizable via Lie algebraic methods. In this paper, the authors derive an adaptive, nonlinear feedback control methodology for a structurally nonlinear typical wing section. The technique is advantageous in that the adaptive control is derived utilizing an explicit parameterization of the structural nonlinearity, and defining a partial feedback linearizing control via Lie algebraic methods that is parametrically dependent. The closed loop stability of the system is guaranteed to be stable via application of LaSalle‚Äôs in variance principle.

published proceedings

  • 4th International Symposium on Fluid-Structure Interactions, Aeroelasticity, Flow-Induced Vibration and Noise: Volume III

author list (cited authors)

  • Ko, J., Kurdila, A. J., & Strganac, T. W.

citation count

  • 2

complete list of authors

  • Ko, Jeonghwan||Kurdila, Andrew J||Strganac, Thomas W

publication date

  • November 1997