Validation of a linear model for an ultralight helicopter

The thesis presents the development of a flight dynamic linear mathematical model for a single main rotor ultralight helicopter. The main contribution consists in the relative ease in managing the complex dynamic of the helicopters while guaranteeing an adequate accuracy without losing the physical meaning. Helicopter dynamics are treated accordingly to the main literature. Equations of motions are linearized around several equilibriums representing different significant flight conditions: hovering and forward flight. The helicopter dynamics is decoupled and longitudinal and lateral-directional motions are treated independently. Then these proposed models have been compared to corresponding linear models obtained by numerically linearizing a complex nonlinear model. The proposed methodology has been validated by implementing geometrical, inertial and aerodynamic features of an ultralight helicopter.