Control System Analysis in Nonlinear Flight Regimes

摘要

Coupling of the Reynolds-averaged Navier-Stokes equations, rigid-body dynamics, and an optimal state feedback control law is demonstrated with a two-dimensional, two degree-of-freedom airfoil case. The application problem controls the altitude of an airfoil in subsonic flow with a magnitude and rate-limited applied couple. The applied pitch couple is computed using feedback of both attitude and altitude, vertical and angular velocities and integrated altitude error. Comparison of the trajectories showed a longer settling time and slight overshoot for the nonlinear simulation when compared to a linear plant model.