Abstract: A method for alleviating and protecting loads of a lifting surface of an aircraft based on control of structural distortions of the lifting surface. The lifting surface includes a control surface, a maneuvering system for displacing the control surface and sensors which measure a dimensional characteristic linked to the distortion of the lifting surface. The method acquires characteristic data linked to the distortion of the lifting surface, determines a set of values of the shape, analyzes the value of the strain attribute and compares the set of values characterizing the shape to the values of the tolerance interval associated with the lifting surface. If the set of values characterizing the shape is outside of the interval, the process triggers an activation of the maneuvering system to displace the control surface from an initial position in order to alleviate the loads on the lifting surface.

Abstract: A method for alleviating and protecting loads of a lifting surface of an aircraft based on control of structural distortions of the lifting surface. The lifting surface includes a control surface, a maneuvering system for displacing the control surface and sensors which measure a dimensional characteristic linked to the distortion of the lifting surface. The method acquires characteristic data linked to the distortion of the lifting surface, determines a set of values of the shape, analyzes the value of the strain attribute and compares the set of values characterizing the shape to the values of the tolerance interval associated with the lifting surface. If the set of values characterizing the shape is outside of the interval, the process triggers an activation of the maneuvering system to displace the control surface from an initial position in order to alleviate the loads on the lifting surface.

Abstract: An aircraft with active control of the warping of its wings may include at the outer end of each wing an articulating additional aerodynamic plane that is swept back with respect to the wing. The pivoting of the additional aerodynamic plane is controlled in such a way that, at certain flight points of the aircraft, the aerodynamic forces engendered by the additional aerodynamic plane modify the reference warp of the wing into an aerodynamically optimal warp for the relevant flight point.

Abstract: According to the invention, at the outer end (10) of each wing of the aircraft is articulated an additional aerodynamic plane (14) swept back with respect to said wing. The pivoting of said plane (14) is controlled in such a way that, at at least certain flight points of said aircraft, the aerodynamic forces engendered by said plane (14) modify the reference warp of the wing into an aerodynamically optimal warp for the relevant flight point.