Aeroelastic problems of light weight structures of modern aerospace vehicles are the result of interactions between aerodynamics, structural and inertial forces. The mathematical model of the aeroelastic problem is based on the Lagrange equations of motion for the structural dynamics and on a quasi-steady approach of the generalized unsteady incompressible aerodynamic forces. The oscillations of such aeroelastic system can be suppressed using linear active control techniques. In the case when the control is saturated the stability domain shrinks. The describing function method is used in this paper to determine the periodic solutions of an experimental aeroelastic system for two control laws.
Stability Analysis of an Aeroelastic System with Actuator Saturation
Advanced Materials Research II, ICAMR, International Conference on Advanced Material Research, 2 ; 1527-1532
Advanced Materials Research ; 463-464
2012
6 Seiten
Aufsatz (Konferenz)
Englisch
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