This paper presents the gain design process for a nonlinear control algorithm used in a conceptual electrical vertical-take-off-and-landing (eVTOL) vehicle with a fixed wing configuration. The control strategy is based on the incremental nonlinear dynamic inversion (INDI) approach, which ensures effective control throughout all flight phases. This research endeavors to develop the controller further into a primary flight controller (PFC) by considering real-world scenarios involving measurement errors and availability. To address these challenges, the estimation of measurements and computation of necessary controller states are performed using various filters, which are incorporated into the controller design. Moreover, the gain design considers the presence of these filters. By optimizing the gain configuration within the error controller (EC), a robust and performance controller design is achieved, allowing for comprehensive investigations in both the time and frequency domains without decoupling the aircraft dynamics. The results of the gain design process are then validated through nonlinear simulations, providing empirical evidence of the effectiveness of the gain and filter concepts.    «

This paper presents the gain design process for a nonlinear control algorithm used in a conceptual electrical vertical-take-off-and-landing (eVTOL) vehicle with a fixed wing configuration. The control strategy is based on the incremental nonlinear dynamic inversion (INDI) approach, which ensures effective control throughout all flight phases. This research endeavors to develop the controller further into a primary flight controller (PFC) by considering real-world scenarios involving measurement...    »