International Journal of Aerospace and Lightweight Structures

doi: 10.3850/S2010428614000026

Effects of Active Damping on Parametric Instability of Composite Cylindrical Shells Using Piezo Fiber Composites

Partha Bhattacharya^1,a, Debabrata Podder² and Atanu Sahu^{1 1}Department of Civil Engineering, Jadavpur University, Kolkata – 700 032, India. ^ap_bhatta@yahoo.com ²Department of Ocean Engineering and Naval Architecture, Indian Institute of Technology, Kharagpur – 721 302, India.

ABSTRACT

Parametric instability due to longitudinal forces is becoming a critical issue for lightweight and flexible modern day aerospace vehicles. An attempt is made in the present work to develop a FE model for a piezoelectric actuated laminated composite shell panel subjected to parametric edge excitation. A feedback control strategy is developed with the piezo sensor output being fed back to the IDE-PFC actuators. Employing Hamiltonian principle, governing differential equation taking the form of Mathieu-Hill equation is developed. The resulting equation is solved using the method of strained parameter. Results for various geometries, boundary conditions and lamination sequences are obtained and discussed.

Keywords: Parametric instability, IDE-PFC actuators, Laminated composite shell, Mathieu-Hill equations, Feedback damping.

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