Failure Handling on a Split-Flap Ultralight General Aviation Aircraft with Hybrid Nonlinear Dynamic Inversion

Kurzfassung

Ultralight general aviation aircraft provide an accessible gateway to aviation for both manufacturers and pilots. However, due to their reduced weight, requirements, certifications, and costs, these aircraft are more susceptible to hazardous failures than airliners. While they are equipped with a parachute, this is a last resort that is irreversible and can result in a rough landing or the aircraft drifting off. Additionally, the relaxation of medical requirements may result in pilot failures of severe nature. To address these concerns, we propose a semi-electronic flight control concept with split flaps and tailored flight control laws to enable automatic flight during abnormal situations. The simulation results indicate that the closed-loop system performs acceptably in these scenarios. This undermines the intention to use the system in abnormal situations and possibly for augmentation.