Abstract:
This paper presents the design framework for an integrated Flight Control System (FCS) of a conceptual electric vertical takeoff and landing (eVTOL) vehicle. The aircraft integrates propeller and impeller propulsion systems with tilt deflections. In this paper, the primary FCS based on incremental nonlinear dynamic inversion (INDI) principles, is highlighted, known for its stability and robustness across diverse flight conditions, without encountering disruptive mode switching transients. The paper emphasizes the handling of measurements within the INDI framework, particularly addressing those not directly accessible through sensors. Moreover, an automated gain design tool for the nonlinear controller is introduced, focusing on achieving tuning goals in both time and frequency domains. This involves sequential linearization of the plant model and the implemented controller, facilitating comprehensive analysis to ensure safe and stable performance throughout the mission profile. The design tool further delves into realworld factors like delays, discrete computation, and uncertainties inherent in the integrated onboard plant model (OBPM). Finally, the performance of the design process is validated through nonlinear simulations.