Applied flight dynamics modeling and stability analysis of a nonlinear time-periodic mono-wing aerial vehicle

This paper presents fly-ability, trim-ability, stability, and control ability of a mono-wing aerial vehicle as an under-actuated multi-body system. A nonlinear mathematical model of this vehicle with translational and rotational movements is developed. Based on early simulations, a conceptual prototype of the monowing is initially designed and constructed. A comprehensive nonlinear simulation is then performed by modeling aerodynamic forces and moments using the Blade Element Momentum (BEM) theory. Modeling and simulation are validated against experimental data to satisfy research needs. Twenty-three efficient dynamic parameters of the mono-wing are studied in ninety-seven simulation scenarios. Robustness against external disturbances in various trim conditions is examined. Flight test experiments reveal not only fly-ability but also high attitude stability in hovering-climb flight despite the imprecise model. This vehicle has a complex dynamic behavior that urges precise identification to reach stable flight performance. The model helps to achieve a deeper understanding of the flight characteristics of such vehicles. Wing area and incidence angle, position vectors of the aerodynamic center and rotation center, and the moment of inertia tensors are identified to be the most significant parameters on the flight stability of this vehicle. It is observed that the mono-wing has multiple trim conditions and is robust against external disturbances regardless of the control surfaced deflection, the center of gravity position, or even the wing geometry, because of the rotational stability and aerodynamic performance. Moreover, it is found both by simulation and experiment that although this vehicle is not full-state controllable and observable, it can be stabilized and guided to follow the desired trajectory and perform complex flight maneuvers. (C) 2020 Elsevier Masson SAS. All rights reserved.