DescriptionSeminar about the main contents of my master thesis research project. There is currently great interest in innovative aircraft configurations which possibly could lead to a reduction of fuel consumption and an improvement of performances (with no increment of weight). Among them Joined-Wing concept has captured the attention as a possible candidate layout. It is reasonable to wonder about the importance of their inherent structural non-linearities that may invalidate the results obtained with fast lower-fidelity tools; moreover these non-linearities are thought to be particularly concerning when the deformation of the wing is significant. This is a feature of modern aircrafts, where weight reduction has brought to an increase of flexibility. Implementation of dynamic (time-domain) solvers accomplishing non linear modelling with different degrees of accuracy is described. The fluid-structure interaction problem is firstly presented, along with the aerodynamic models adopted and the algorithms employed for the interface (Infinite Plate Spline and Moving Least Square shape functions). Results in terms of aeroelastic response of the selected Joined-Wing layouts are then shown, focusing on the flutter occurrence and analysing post-critical phenomena: Limit Cycle Oscillations (LCOs) are observed as speed is further increased beyond the flutter speed. An attempt of explanation of the complex scenario arising from the non-linear aeroelastic response of Joined-Wings is then attempted by means of a bifurcation diagram describing the multi-stability behaviour of the system when a meaningful parameter (for example the speed in this case) is varied.
|Period||28 Oct 2015|
|Event title||Dynamics and Control Group UoB - Seminar: null|