This paper introduces an optimization-based load control strategy suitable for flexible
vehicles with very flexible wings. A model for the coupled flight dynamics/aeroelastic
response of the vehicle is built from geometrically-nonlinear beams using an intrinsic description
and a simple linear 2-D unsteady aerodynamic with no spanwise couplings. The
resulting model has only quadratic nonlinearities and a balanced projection of the dynamic
equations is then practicable and results in a much smaller model that retains the relevant
nonlinear couplings. This is finally used to drive a model-predictive control designed to
suppress wing oscillations in the response to atmospheric gusts. Results are presented on
high-aspect-ratio flying wing undergoing moderately large excursions in the presence of
discrete gusts. They demonstrate the performance of the nonlinear MPC in comparison to
equivalent linear control schemes.