G. P. Gibbs
C. R. Fuller
Vibration and Acoust. Labs., Dept. of Mech. Eng., VPI & SU, Blacksburg, VA 24061-0238
This paper describes results of experiments in which active control of interior noise in a business aircraft is achieved using piezoceramic actuators bonded to the fuselage structure. The experiments were performed in a real aircraft fuselage (Cessna Citation 3) with engine noise simulated by a point force shaker attached to the engine pylon, and multiple arrays of piezoelectric control actuators in conjunction with an LMS adaptive controller. The cost function used was the summation of the pressure squared at four error microphones located at head height in proximity of the two rear-mounted passenger seats. Results are given for on-resonance and off-resonance cases and sound level reductions from 3 to 15 dB were demonstrated. The global nature of the control and influence of the actuator/sensor positioning is discussed.