Combat aircrafts have to meet the requirement of operating at reasonably high angle of attack. This often leads to phenomenon of wing rock which is a highly non-linear phenomenon in which an aircraft experiences roll oscillations. In the present work, a fifth order model of wing rock dynamics has been considered which includes the effect of yaw oscillations also. A controller based on back-stepping technique is derived to make the error signal between actual system and the desired state trajectories to converge to zero. Lyapunov theory has been used to perform the stability analysis and for the derivation of controller. Finally, numerical simulations are carried out to show the effectiveness of proposed strategy.
Wing Rock Suppression using Recursive Controller Design Approach
2013
5 Seiten, Bilder, Tabellen, 10 Quellen
Aufsatz (Konferenz)
Englisch
Wing rock suppression using forebody vortex control
AIAA | 1991
|Wing Rock Suppression Using Forebody Vortex Control
British Library Conference Proceedings | 1991
|Performance Evaluation of an L1 Adaptive Controller for Wing-Body Rock Suppression
Online Contents | 2012
|