Nonlinear Control Methods for High-Energy Limit-Cycle Oscillations
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abstract
Limit-cycle oscillations, as they appear in high-performance fighter aircraft, remain an area of scrutiny by the aerospace community. Tools for the simulation and prediction of the onset for limit-cycle oscillations have matured significantly. Surprisingly, less progress has been made in active control methodologies for these inherently nonlinear dynamic phenomena. Even in the cases where it is known that limit-cycle oscillations may be observed in particular flight regimes, and active control methodologies are employed to attenuate response, there are very few analytical results that characterize the stability of the closed-loop system. In part, this may be attributed to the difficulty in understanding the nature of the contributing nonlinear structural and nonlinear aerodynamic interactions that account for the motion. Recent progress made by the authors in the derivation, development, and implementation of nonlinear control methodologies appropriate for a class of flutter problems is reviewed. Both analytical and experimental results are summarized. Directions for future study and, in particular, remaining technical barriers that must be overcome, are summarized.
