Maneuverable aircraft flight control using nonlinear dynamic inversion

Feedback linearization is a mature and highly applied control method in aerospace and other industrial applications. The designed control inputs are used to cancel the nonlinear terms using negative feedback of these terms. This paper focuses on designing a fight simulation model for F-16 fighter jet in responding to diverse sharp maneuvers. F-16 model is expressed by fixed-mass rigid-body six-degree-of freedom (6-DOF) equations of motion, which include the detailed aerodynamic coefficients, the engine model and the actuator models that have lags and limits. The two-time scaled concept of dynamic inversion method divides the aircraft states into groups according to their rate of response. Dynamic Inversion (DI) control law is designed for the fast variables using the aerodynamic control surfaces as inputs. Next, DI is applied to the control of the slow states using the outputs of the fast loop as inputs. Simulation results for the nonlinear flight control system have proved the validity and rationality of the proposed technique .