Adaptive Aeroservoelastic Control Design for a Flexible-Wing High-Altitude-Long-Endurance Unmanned-Air-Vehicle

Abstract

This work presents the use of adaptive control techniques to design the control system of a flexible-wing HALE aircraft. The structure and Aerodynamic model based on Predator UAV is modeled in NASTRAN, and relevant data is extracted by modifying its solution sequence using DMAP statements. The non-linear elas tic flight dynamics model is developed using the mean axis assumption in Julia’s programming language. AGARD 445.6 Aeroelastic wing is used to verify the developed aeroelastic modeling methodology. Trim conditions are found using non-linear solvers, and automatic differentiation is used to calculate jacobians for linear state space models used for control system design. Model reference adap tive control system using an LQR-based reference model demonstrates adequate tracking performance in the presence of model uncertainties and disturbance re jection to stochastic gust.