Nonlinear Control Laws Design for Generic Fighter Jet in Transonic Regime

This work explores control alternatives for a generic fighter jet, focusing on handling qualities enhancement in the transonic flight regime. The aerodynamic coefficients of the aircraft exhibit abrupt variations due to shock wave interference, so nonlinear control strategies are suggested. MATLAB simulations are employed to analyze the influence of these control laws on aircraft dynamics, including automated routines for equilibrium calculations, linearization, and the design of a conventional gain-scheduled Stability Augmentation System (SAS). Preliminary results demonstrate the SAS's lack of effectiveness in mitigating transonic nonlinearities when sensor measurement errors occur. Therefore, the application of two nonlinear control techniques is proposed and investigated: Nonlinear Dynamic Inversion (NDI) and an output-based Incremental Nonlinear Dynamic Inversion (INDI). The controlled variable of the flight control system is selected based on analysis of the Zero Dynamics Matrix calculated for load factor on pilot, C-star and a combination of C-star, true airspeed, and altitude. Whereas NDI and INDI techniques result in adequate performance and stability characteristics in nominal conditions, the INDI controller is confirmed to be more robust to sensor measurement errors.