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Adaptive Control of Aircraft Wing Oscillations with Stiffness and Damping Nonlinearities in Pitching Mode

  • L. Prabhu
  • J. Srinivas
Conference paper
Part of the Advances in Intelligent Systems and Computing book series (AISC, volume 701)

Abstract

This paper presents an adaptive control strategy for aircraft wing structure based on a nonlinear aeroelastic model with plunge and pitch degrees of freedom. System nonlinearities in terms of pitching degree of freedom are accounted in stiffness and damping terms of the model. The closed-loop response of the model is studied under two cases: (i) polynomial form of nonlinearities and (ii) combined free play and polynomial form of nonlinearities. The adaptive control strategy with wing flap based on partial feedback linearization is designed to suppress the instabilities occurring at certain freestream velocities. Objective of controller is to stabilize the system within the flutter boundary. A neural network based observer is used to estimate the uncertain parameters in control law. The designed control system with neural network estimator is effective in suppressing the limit cycle oscillations considerably.

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Copyright information

© Springer Nature Singapore Pte Ltd. 2018

Authors and Affiliations

  1. 1.Department of Mechanical EngineeringNational Institute of TechnologyRourkelaIndia

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