Decoupled Incremental Nonlinear Dynamic Inversion Control for Aircraft Spin Recovery

Obtaining information about the aircraft's dynamics while spinning is extremely difficult, especially at high angles of attack. Due to the complex nature of such a viable problem and unknow model restricts the applicability of model dependent control law for spin recovery. This paper presents an incremental nonlinear dynamic inversion (INDI)-based control law for spin recovery and addresses the dependency control law problem. The primary contribution of this paper is to arrest an aircraft's spin motion by reducing its reliance on aerodynamic derivatives. Furthermore, the cross couple aerodynamic derivative problem addressed by decoupling the deigned INDI control law. The controller efficacy is tested on F 18 High Alpha Research Vehicle and according to simulation results, even in the presence of wind, INDI guarantees a safe spin-out. By altering the control effectiveness matrix, Monte Carlo simulation is used to assess the robustness of the INDI. The validation process culminates with a comparison between the spin recovery profile derived from the INDI control and an earlier spin recovery article.