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AN EXPERIMENTAL INVESTIGATION FOR FLUTTER SUPPRESSION CONTROL OF A HIGH-ASPECT-RATIO FLEXIBLE WING MODEL
Last modified: 2017-05-26
Abstract
Abstract
The interaction between inertial, structural and aerodynamic forces can cause several undesirable phenomena when an elastic body is placed in the fluid stream, such as divergence, flutter, limit cycle oscillations and buffeting. There are the representative topics of aeroelasticity, is a dangerous phenomenon encountered in flexible structures subjected to aerodynamic forces. It occurs in a wide range of the engineering applications in aircraft, buildings, telegraph wires, stop signs, and bridges.
The present paper is devoted to identify the aeroelastic dynamic behaviours of a high-aspect-ratio flexible wing model and explore various active flutter suppression strategies for this wing model with control actions from a trailing edge control surface. Such a high-aspect-ratio flexible wing model is susceptible to dynamic instabilities which can lead to large amplitude limit cycle oscillations (LCO) . Frequency responses of this wing model are measured using accelerometers under the excitations from a shaker and flow-induced vibrations, and then these results are compared with results obtained from the finite element analysis (FEA). It is observed that for this flexible wing model, the flutter phenomenon occurs when the 2nd bending and 1st torsional model coalesce or come together with each other. Furthermore, based on this knowledge, an active control system using trailing edge control surface driven by a servomotor is developed. Various control strategies were tested in the present experiment, it is shown that the present active control system can effectively delay or suppress the flutter behavior at the optimized control parameters.
The interaction between inertial, structural and aerodynamic forces can cause several undesirable phenomena when an elastic body is placed in the fluid stream, such as divergence, flutter, limit cycle oscillations and buffeting. There are the representative topics of aeroelasticity, is a dangerous phenomenon encountered in flexible structures subjected to aerodynamic forces. It occurs in a wide range of the engineering applications in aircraft, buildings, telegraph wires, stop signs, and bridges.
The present paper is devoted to identify the aeroelastic dynamic behaviours of a high-aspect-ratio flexible wing model and explore various active flutter suppression strategies for this wing model with control actions from a trailing edge control surface. Such a high-aspect-ratio flexible wing model is susceptible to dynamic instabilities which can lead to large amplitude limit cycle oscillations (LCO) . Frequency responses of this wing model are measured using accelerometers under the excitations from a shaker and flow-induced vibrations, and then these results are compared with results obtained from the finite element analysis (FEA). It is observed that for this flexible wing model, the flutter phenomenon occurs when the 2nd bending and 1st torsional model coalesce or come together with each other. Furthermore, based on this knowledge, an active control system using trailing edge control surface driven by a servomotor is developed. Various control strategies were tested in the present experiment, it is shown that the present active control system can effectively delay or suppress the flutter behavior at the optimized control parameters.