Research Of Distributed Active Vibration Control Based On Aircraft Vertical Tail

The active vibration control aimed at aircraft empennage has huge practical values in the aspects of adding the fatigue life of vertical tail, increasing the capability and availability of the aircraft, reducing the through-life-support costs and so on. This paper aims at model of vertical tail based on certain type aircraft. The method of distributed actively vibration control based on multi DSP has been carried on this model. A distributed actively vibration control system based on DSPs is designed to real timely control the structural vibration of two modes. Further more, related theories and experiments are outspreaded.The main content of this paper are as following,1. The material characteristic and principle of piezoelectric material (PZT) and Macro-Fiber Composite (MFC) is analyzed. Cada-X structural dynamics analytic software is used to carry on the experimental modeling and mode analysis of the vertical tail. Consequently, the disposal scheme of sensor and actuator is confirmed.2. The adaptive filter control arithmetic is systemically analyzed. A Simplified FX-LMS (SFX-LMS) adaptive arithmetic is proposed. Finally, this algorithm is derived in detail.3. The hardware and software design of vibration control system is achieved. The achievement and flow of software design is emphasized in detailed.4. the experiment of distributed actively vibration control is achieved. The ideal experimental results are obtained. The validity and feasibility of this system is validated. Further more, the experiment using MFC bonding PZT as actuator is carried on which validates the advantage of MFC.