Vibration Control of Flexible Aircraft with Respect to Passengers Comfort

The paper deals with the development of the active vibration suppression of fuselage of flexible aircraft of BWB (blended wing body) type with respect to comfort criterions. The independent system of the proof mass actuators within the fuselage is considered as actuators, accelerometers throughout the fuselage are considered as the sensors. The placement of actuators and sensors is optimized through the special norms minimization. The feedback control design is done by H∞ method. The robustness of the controller is tested with respect to the fuel and passengers mass variations.