Patent ID: 7598657

Claim:
A structural element for an aircraft, the structural element comprising: an active element; and a passive element; wherein the active element is adapted for controllable or regulable active introduction of forces into the passive element; wherein the passive element is selected from the group consisting of a floor structure, frame in the floor region of the aircraft, traversal beam in the floor region, and Samer rod; and wherein the structural element is adapted to reduce bending of a fuselage in a floor region of the aircraft which is due to a flight maneuver or a gust load; wherein the structural element is connected to a control- or regulating electronics adapted for registering internal forces, flight maneuvers and a gust load that trigger said internal forces and for predicting a load state of the fuselage such that corresponding counter forces can be introduction into the passive element well in time in order to reduce bending of the fuselage.