Design and Experiment of Adaptive Active Vibration Control System for Aircraft Framework

Hypersonic aircraft with a high velocity and super maneuverability has become a hot spot in current research of near space aircraft. To suppress the aircraft’s vibration during its running process, an active vibration control system for aircraft framework is designed in this paper based on the adaptive filtering algorithm. To start with, an adaptive filtering algorithm – filter-x least mean square (FXLMS) algorithm is presented. Then the hardware configuration and software development are introduced in detail. Meanwhile, the piezoelectric smart structure is used for detecting and driving. The measurement and control system designed in this experiment has 8 input channels and 8 output channels which are able to process off-line identification, on-line identification and real-time control. By choosing reasonable parameters and distributing channels logically, an adaptive active vibration control is imposed. Finally, the experimental performance verifies the feasibility of FXLMS algorithm and the validity of the designed control system.