Tail Rudder Optimization Design and Dynamics Modeling for the Small Flexible Membrane Wing Aircraft

In this paper, for one of the research problems of the small flexible membrane wing (FMW) unmanned aerial vehicles (UAV), which is how to make the aircraft have enough fast maneuverability, several different control schemes have been proposed. The controlling aerodynamics were calculated in the different combinations of multiple control surfaces from the rolling, pitching and yawing motion aspect respectively. Through optimization analysis of these types of schemes and establishing an evaluation standard, a design scheme suitable for our demand was determined. Then the nonlinear state-variation model of aircraft dynamics is linearized with the small-disturbance theory and the equation in the state-space form of the aircraft was established. Finally, the result was obtained by analyzing the longitudinal and lateral modes and stability characteristics of the flight as reference for follow-up controller design.