Signal Blending in Control Systems Structural Interactions

摘要

Flexible modes of vibration must be removed from the feedback control system ofan aircraft. A computer model of a rig, which was being used to model an aircraft fuselage as a simple beam, was created in order to calculate the gains required to remove these modes of vibration using signal blending, instead of notch filters with their associated problems. This was achieved successfully, and the effects of variations of stiffness and damping, that occur when an aircraft is in flight, on signal blending were investigated using the computer model.