Active flutter suppression is used to prevent flutter throughout the flight envelope by supplying active control forces in response to vehicle motions. In recent years, studies have been conducted on active flutter suppression using the receptance method. The advantage of the receptance method is that the feedback control gains are purely based upon measured receptances, without any need to evaluate or know the mass, damping, and stiffness matrices of the system. However, determination of the desired closed-loop poles is a unsolved problem. The goal of this work is to determine the pole-assignment in the receptance method, enabling the extension of flutter boundaries by combining the receptance method with the flutter margin technique. The design of an output feedback control for a multi-degree-of-freedom uniform wing numerical model with a trailing-edge control surface is demonstrated. Numerical results show that the presented approach can effectively extend the flutter boundary without the usual diculties of pole-assignment.
|Title of host publication||57th AIAA/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference|
|Publisher||American Institute of Aeronautics and Astronautics Inc. (AIAA)|
|Number of pages||18|
|Publication status||Published - 4 Jan 2016|