Manoeuvring flight control

The development of control laws for manoeuvring flight, specifically, a high amplitude velocity vector roll is addressed. The plant model has seventh order nonlinear dynamics with coupled pitch and lateral directional dynamics. Using time scale separation and pointwise linearization, a receding horizon linear quadratic optimal control law with full state feedback is synthesized online. Also online, the pilot inputs are modulated using linear programming to prevent actuator rate saturation over the optimization horizon. The nonlinear control law performance is demonstrated in a fighter aircraft simulation with a rudder failure during a loaded roll manoeuvre