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.
