Successive Generalized Dynamic Inversion Control of Lateral Fighter Aircraft Dynamics

Abstract

The successive generalized dynamic inversion (SGDI) control design methodology is used to control the linearized underactuated three degrees of freedom lateral motion of the F-16 fighter aircraft. The lateral kinematical state variables are analyzed first for the property of mutual direct controllability (MDC) to decide on the best SGDI control design configuration. The MDC analysis reveals that the yaw and sideslip angles do not form together an MDC subset of state variables. The MDC analysis also reveals that the sideslip and roll angles form together an MDC subset of state variables. However, it is shown that the SGDI control system design that is based on the roll and sideslip angles suffers from an excessively stable zero dynamics, which implies a large control effort and an undesirably fast closed loop transient response. Finally, the MDC analysis reveals that the roll and yaw angles form together an MDC subset of state variables and that the associated SGDI control design configuration is the most favorable in terms of the zero dynamics characteristics. Hence, the SGDI control design configuration that is based on the roll and yaw angles is exploited to synthesize a multivariable lateral stability augmentation system (SAS).