Gust Load Alleviation of an Aeroelastic System Using Nonlinear Control Conference Paper uri icon

abstract

  • The authors develop a nonlinear longitudinal model of an aircraft modeled by rigid fuselage, tail, and wing, where the wing is attached to the fuselage with a torsional spring. The main focus is to retain the full nonlinearities associated with the system and to perform gust load alleviation for the model by comparing the impact of a proportional-integral-filter nonzero setpoint linear controller with control rate weighting and a nonlinear Lyapunov- based controller. The four degree of freedom longitudinal system under consideration includes the traditional longitudinal three degree of freedom aircraft model and one ad- ditional degree of freedom due to the torsion from the wing attachment. Computational simulations are performed to show the aeroelastic response of the aircraft due to a gust load disturbance with and without control. Results presented in the paper show that the linear model fails to capture the true nonlinear response of the system and the linear controller based on the linear model does not stabilize the nonlinear system. Copyright 2009 by the authors.

name of conference

  • 50th AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference

published proceedings

  • 50th AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference

author list (cited authors)

  • Lucas, A., Valasek, J., & Strganac, T.

publication date

  • January 1, 2009 11:11 AM