Wing flutter control in S2MA wind-tunnel

ONERA aeroelasticity specialists have confirmed the active control of wing flutter by control surfaces in a wind tunnel (end of 2010). With this control, the appearance of this instability phenomenon has been delayed, allowing a distinct increase in the flight domain.

This demonstration was carried out in the ONERA S2MA wind tunnel in Modane, with a generic model fitted with a trailing edge control surface. The control principle used during these tests is based on the introduction of non-stationary aerodynamic stabilising forces by this control surface.

A measurement of the structure's dynamic response is used as input to the control law that controls the control surface servo-control. The numerical control laws tested using a real time system showed their effectiveness for different structural configurations.

The S2MA wind tunnel duct with a half-aircraft model intended for wing aeroelasticity studies..

Video showing the appearance of the flutter phenomenon in the absence of any control. Active control prevents the phenomenon from starting.