Wind tunnel testing of panel flutter control using piezoelectric actuation and iterative gain tuning

Ming-Tsang Ho; Roger R. Chen; Li-Chun Chu

doi:10.1117/12.275679

6 June 1997 Wind tunnel testing of panel flutter control using piezoelectric actuation and iterative gain tuning

Ming-Tsang Ho, Roger R. Chen, Li-Chun Chu

Proceedings Volume 3041, Smart Structures and Materials 1997: Smart Structures and Integrated Systems; (1997) https://doi.org/10.1117/12.275679
Event: Smart Structures and Materials '97, 1997, San Diego, CA, United States

Abstract

This is the second part of a companion paper entitled 'Unified Approach of Active Panel Vibration and Flutter Control using Piezoelectric Actuation and Iterative Root Locus Method.' This paper reports the wind-tunnel test results of panel flutter suppression which is based on the methodology described in the companion paper. Composite panels with one-sided surface- mounted piezoelectric actuators and strain sensors are manufactured. Because the piezoelectric actuators are mounted on one side of the panels only, in plane forces and bending moments are induced simultaneously when the actuators are excited with input voltages. Strain and strain-rate signals picked up by strain gages and electronic differentiators are the system outputs for feedback. Three different configurations are tested and their results are compared, which are: one set of piezo-actuators at leading edge, one set of piezo-actuators at trailing edge, and two independent sets of piezo-actuators at leading and trailing edges respectively. The nonlinear finite element dynamic models for various configurations are introduced. While the experimental setup allows a systematic way of tuning the gains during the test, the theoretical control designs are introduced which comprises the iterative root locus method and the output feedback optimum algorithm. Reasonable details of test procedures are described and major findings of this research are in order. Firstly, strain level at leading edge is about 25% of that at trailing edge. Secondly, actuators at leading edge are more effective than those at trailing edge. Finally, flutter dynamic pressure can be raised by 20 to approximately 30% using active control.

Citation Download Citation

Ming-Tsang Ho, Roger R. Chen, and Li-Chun Chu "Wind tunnel testing of panel flutter control using piezoelectric actuation and iterative gain tuning", Proc. SPIE 3041, Smart Structures and Materials 1997: Smart Structures and Integrated Systems, (6 June 1997); https://doi.org/10.1117/12.275679

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