TY - JOUR
AU - Prakash, Shashikala
AB - The reduction of vibration in Aircraft/Aerospace structures as well as helicopter fuselage is becoming increasingly important. A traditional approach to vibration control uses passive techniques which are relatively large, costly and ineffective at low frequencies. Active Vibration Control (AVC), apart from having benefits in size, weight, volume and cost, efficiently attenuates low frequency vibration. Hitherto this was being achieved using high speed Digital Signal Processors (DSPs). But the throughput requirements of general purpose DSPs have increased very much and the Field Programmable Gate Arrays (FPGAs) have emerged as an alternative. The silicon resources of an FPGA lead to staggering performance gains i.e. they are 100 times faster than DSPs. In the present paper Active Vibration Control of a Composite Research Wing Model is investigated using Piezo electric patches as sensors and PZT bimorph actuators collocated on the bottom surface as secondary actuators. Attempt has been made to realize the State - of - the - Art Active Vibration Controller using the Xilinx System Generator on VIRTEX - 4 FPGA. The control has been achieved by implementing the Filtered-X Least Mean Square (FXLMS) based adaptive filter on the FPGA. Single channel real time control has been successfully implemented & tested on the composite research wing model.
TI - Active vibration control of a composite wing model using PZT sensors/actuators and virtex: 4 FPGAs
JF - Proceedings of SPIE
DO - 10.1117/12.844673
DA - 2009-07-25
UR - https://www.deepdyve.com/lp/spie/active-vibration-control-of-a-composite-wing-model-using-pzt-sensors-LYfycOIKwc
SP - 74931O
EP - 74931O-8
VL - 7493
IS - 1
DP - DeepDyve
ER -