The characterization of the behaviour of nonlinear aeroelastic systems has become a very important research topic in the Aerospace Industry. However, most work carried to-date has concentrated upon systems containing structural or aerodynamic nonlinearities. The purpose of this paper is to study the stability of a simple aeroservoelastic system with nonlinearities in the control system and power control unit. The work considers both structural and control law nonlinearities and assesses the stability of the system response using bifurcation diagrams. It is shown that simple feedback systems designed to increase the stability of the linearized system also stabilize the nonlinear system, although their effects can be less pronounced. Additionally, a nonlinear control law designed to limit the control surface pitch response was found to increase the flutter speed considerably by forcing the system to undergo limit cycle oscillations instead of fluttering. Finally, friction was found to affect the damping of the system but not its stability, as long as the amplitude of the frictional force is low enough not to cause stoppages in the motion.
Characterization of the behavior of a simple aeroservoelastic system with control nonlinearities
Verhalten eines aeroservoelastischen Systems mit nichtlinearer Regelung
Journal of Fluids and Structures ; 14 , 8 ; 1173-1193
2000
21 Seiten, 25 Bilder, 3 Tabellen, 25 Quellen
Article (Journal)
English
Aeroservoelastic Response Simulation with Geometric Nonlinearities Using Full Finite-Element Models
British Library Conference Proceedings | 2016
|Adaptive aeroservoelastic control
TIBKAT | 2016
|Aeroservoelastic Sensor-Based Control
NTIS | 2012
|Rigid-Body Issues in FFT-Based Dynamic Loads Analysis with Aeroservoelastic Nonlinearities
British Library Conference Proceedings | 2012
|