Second Order Nonlinear Dynamic Inversion for Flight Segment Transition

Flight segment transition (FST) is critical in all the phases of aviation. Its fast response and robustness require more efficiency to handle nonlinearities in guidance and control. However, how motion guidance can better serve attitude control rests on error feedback. We propose a feedforward superimposition approach of second order nonlinear dynamic inversion (SONDI) to coordinate the strategic, tactical, and operational timing in guidance, navigation, and control (GNC). We apply the SONDI approach in an autonomous flight mission involving FST tasks. Numerical results show that this approach can be superimposed on cascade control structures to improve the transition performance for admissible segment connections. Our approach represents a route to enhance the control effects of command feedforward superimposed on the original structures.