AEROELASTIC LIMIT CYCLE OSCILLATION ANALYSIS OF AIRCRAFT WING WITH MULTIPLE STRUCTURAL NONLINEARITIES

Abstract

The main research topic of this thesis is to investigate the behaviors of flutter and subcritical limit cycle oscillations caused by multiple types of wing structural nonlinearities. Towards this objective, three aeroelastic systems with different types or numbers of structural nonlinearities are introduced for the analysis purposes. The first two aeroelastic systems are established based on the NACA0012 airfoil section with single and two (i.e. trailing- and leading-edge) control surfaces, respectively. The third aeroelastic system is a 3D JAXA Standard Wing Model (JSM) with the installation of the external pylon-mounted engine nacelle. In order to facilitate an efficient and accurate analysis, an adaptive step size control algorithm incorporated in the continuation method (CM) is developed and combined with the filtered impulse function method based on aero-structural solvers and applied to two aeroelastic analysis tasks concerned with modes tracking and parameter variation. The corresponding results based on the proposed methods are compared with that of other methods to elucidate its distinct disadvantages.