Aircraft , comprising: - a control computer , - an internal or external load determining unit , - a first, central inertial measurement device and - at least one additional second inertial measurement device at a distance from the first inertial measurement device , wherein the load determining unit is coupled to the first inertial measurement device and at least one second inertial measurement device , wherein the load determining unit is designed to receive instantaneous first accelerations detected by the first inertial measurement device and instantaneous second accelerations detected by at least one second inertial measurement device and from these to determine instantaneous loads acting on the aircraft and to store them in a memory unit and/or to transfer them to an external unit , wherein the load determining unit is designed to determine expected manoeuvre accelerations from the first accelerations and from position information provided by the control computer , wherein the load determining unit is designed to filter out the expected manoeuvre accelerations from the totality of the detected first accelerations and second accelerations and to determine dynamic accelerations on the aircraft from this, wherein the load determining unit is designed to determine expected manoeuvre loads on the aircraft from the expected manoeuvre accelerations by means of a manoeuvre load model, to determine dynamic loads on the aircraft from the induced dynamic accelerations and to determine the sum of the expected manoeuvre loads and the dynamic loads as loads acting on the aircraft , and characterised in that the load determining unit is designed to determine modal accelerations of the aircraft , which include rigid body modes and elastic modes of the aircraft , from the detected first accelerations and the detected second accelerations. - a control computer , - an internal or external load determining unit , - a first, central inertial measurement device and - at least one additional second inertial measurement device at a distance from the first inertial measurement device , wherein the load determining unit is coupled to the first inertial measurement device and at least one second inertial measurement device , wherein the load determining unit is designed to receive instantaneous first accelerations detected by the first inertial measurement device and instantaneous second accelerations detected by at least one second inertial measurement device and from these to determine instantaneous loads acting on the aircraft and to store them in a memory unit and/or to transfer them to an external unit , wherein the load determining unit is designed to determine expected manoeuvre accelerations from the first accelerations and from position information provided by the control computer , wherein the load determining unit is designed to filter out the expected manoeuvre accelerations from the totality of the detected first accelerations and second accelerations and to determine dynamic accelerations on the aircraft from this, wherein the load determining unit is designed to determine expected manoeuvre loads on the aircraft from the expected manoeuvre accelerations by means of a manoeuvre load model, to determine dynamic loads on the aircraft from the induced dynamic accelerations and to determine the sum of the expected manoeuvre loads and the dynamic loads as loads acting on the aircraft , and characterised in that the load determining unit is designed to determine modal accelerations of the aircraft , which include rigid body modes and elastic modes of the aircraft , from the detected first accelerations and the detected second accelerations. <EOS>