Abstract: A device and a method for calibrating load sensors which are provided at least one load cross-section of an aerofoil or control surface of an aircraft, the load sensors being calibrated on the basis of load coefficients (?i) of the load sensors, which load coefficients a calculation unit calculates by evaluating a linear system of equations formed by means of mechanical loading of the aerofoil or control surface.

Abstract: The present invention provides a structural element, in particular for an aircraft and spacecraft, comprising a core, the rigidity of which varies at least in portions for optimising the aeroelastic characteristics of the structural element The present invention also provides a method for producing a structural element, in particular for an aircraft and spacecraft, which comprises the following steps: provision of a structural element comprising a core; determination of the aeroelastic behavior of the structural element; and variation, at least in portions, of the rigidity of the core of the structural element such that the aeroelastic behavior of the structural element is optimised. The present invention further provides an aircraft and spacecraft comprising a structural element of this type, and a rotor blade, in particular for a wind turbine, comprising a structural element of this type.

Abstract: A device and a method for calibrating load sensors which are provided at least one load cross-section of an aerofoil or control surface of an aircraft, the load sensors being calibrated on the basis of load coefficients (?i) of the load sensors, which load coefficients a calculation unit calculates by evaluating a linear system of equations formed by means of mechanical loading of the aerofoil or control surface.

Abstract: A method and a system for the integrated determination of aerodynamic data, dynamic load distributions and local accelerations in an aircraft, in particular in an airplane, in flight. Sensors for directly and indirectly detecting aerodynamic parameters, local acceleration and/or structural loads of the aircraft are provided at the aircraft. A calculation unit, which is provided within the aircraft or at the ground station, calculates based on a non-linear simulation model of the aircraft the aerodynamic data, local accelerations and dynamic load distributions of the aircraft depending on the detected aerodynamic parameters of the aircraft. The calculation may take place in real time.

Abstract: The present invention provides a structural element, in particular for an aircraft and spacecraft, comprising a core, the rigidity of which varies at least in portions for optimising the aeroelastic characteristics of the structural element The present invention also provides a method for producing a structural element, in particular for an aircraft and spacecraft, which comprises the following steps: provision of a structural element comprising a core; determination of the aeroelastic behaviour of the structural element; and variation, at least in portions, of the rigidity of the core of the structural element such that the aeroelastic behaviour of the structural element is optimised. The present invention further provides an aircraft and spacecraft comprising a structural element of this type, and a rotor blade, in particular for a wind turbine, comprising a structural element of this type.