Modern commercial aircraft designs are continuously driven towards a light weight and large aspect ratio configurations to meet performance and mission requirements. Consequently, these aircraft are characterised by flexible structures having large structural deformations, and in turn, the frequency separation between the flexible and rigid body modes is greatly reduced. In the presence of nonlinearities, the effects of flexibility on the flight dynamics of such vehicles have been shown to be significant. Conventional methods are not suitable to accurately predict the stability characteristics and handling qualities of such vehicles. This paper demonstrates the effects of flexibility on the dynamics, stability and control of elastic aircraft using a novel analysis framework based on bifurcation and continuation tools linked to classical aeroelastic methods. The robustness of different control law designs to supress nonlinear aeroelastic induced instabilities is also investigated.
|Title of host publication
|Collection of Technical Papers - AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics and Materials Conference
|Published - 2010
|51st AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics and Materials Conference - Orlando, FL, United States
Duration: 12 Apr 2010 → 15 Apr 2010
|51st AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics and Materials Conference
|12/04/10 → 15/04/10