| 摘要 |
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. |
