Patent ID: 9026277
Filing Date: 2015-05-05
Classification: B64C

Abstract:
1. A method for reducing vibrations in an airframe of an aircraft, comprising: determining, with a processor, information indicative of an initial error value between a desired vibration level and a measured vibration level in the airframe; determining, with the processor, an initial adjustment solution for the aircraft in response to the determining of the information for the initial error value; receiving, with the processor, information indicative of a flight response to the initial adjustment solution; combining, with the processor, disturbance signals indicative of vibration noise with the information for the flight response; determining, with the processor, a subsequent error value between the desired vibration level and a subsequent measured vibration level; and determining, with the processor, a predicted adjustment solution in response to the determining of the subsequent error value comprising (i) determining an initial control adjustment matrix in response to the determining of the initial adjustment solution and (ii) determining a measured vibration matrix from the initial control adjustment matrix.