Abstract
This work deals with the reduction of aircraft interior noise using active sidewall panels (linings). Research work done in the past showed that considerable reductions of the sound pressure level (SPL) in the cabin are possible using structural actuators mounted on the lining and error microphones distributed in front of the linings. However, microphones are undesirable for error sensing because they are not suitable for the realisation of an integrated and autonomous active lining (smart lining module). Therefore, the goal of the present work is the replacement of the microphones by structural sensors. Using the structural sensors as remote sensors in combination with an acoustic filter, virtual microphones can be defined. The present study relies on experimental data of a double-walled fuselage system which is mounted in a sound transmission loss facility. Simulation results based on measured time data and identified frequency response functions are provided. Different configurations of virtual microphones are investigated regarding the SPL reduction and the induced vibration of the lining panel.
Highlights
The problem of active noise control in propeller-driven aircraft has been thoroughly investigated in research during the last few decades
The sound pressure results are based on the acoustic residual e a, which is calculated from the measured acoustic disturbance d a and from the anti-sound from the active system ŷ a
The vibration results are based on the vibratory residual es that is calculated from the measured vibratory disturbance ds and from the actuator vibration feedback on the remote sensors ŷs
Summary
The problem of active noise control in propeller-driven aircraft has been thoroughly investigated in research during the last few decades. Several systems have been successfully implemented for example in the aircraft Saab 2000 or Bombardier DHC-8 Q400. One approach applies active noise control (ANC) using anti-sound generated by loudspeakers to reduce the sound pressure in the cabin. Results of ANC in aircraft are published by Elliott et al [1]. The interior sound pressure level (SPL) associated with the blade passing frequency (88 Hz) is reduced up to 13 dB. A different method to reduce interior SPL is the active structural acoustic control (ASAC). There, shakers or piezoelectric patch actuators are used to control the sound radiating structural vibration
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