Patent ID: 11945604

Abstract:
An aircraft includes a control computer, load determining unit, first central inertial measurement device and a second inertial measurement device. The load determining unit is coupled to the first inertial measurement device and the second inertial measurement device. The load determining unit can receive instantaneous first accelerations detected by the first inertial measurement device and instantaneous second accelerations detected by the at least one second inertial measurement device and from this to determine instantaneous loads acting on the aircraft and to store them in a memory unit and/or to transmit them to an external unit. The load determining unit can determine expected maneuver accelerations. The load determining unit can subtract the expected maneuver accelerations from detected first accelerations and second accelerations and determine externally induced dynamic accelerations. The load determining unit can determine expected maneuver loads on the aircraft to determine dynamic loads on the aircraft and to determine the expected maneuver loads and the dynamic loads.