Flight Stability and Control of Articulated Wing Aircraft

摘要

Using wing articulation, or dynamic dihedral, as a flight control mechanism offers the potential for large control authority which in turn can be used to improve the maneuverability of small unmanned aircraft. This paper investigates the influence of hinge orientations that produce pitch-flap coupling to improve the control response of the vehicle. A unique multibody flight dynamic simulation tool incorporating a numerical lifting line aerodynamics model is used for prediction purposes. Pitch-flap coupling is shown to significantly increase the lateral response of the vehicle. The largest roll response is seen when differential pitching of the wings, without flapping, is used. Pitch-flap hinge angles of even three degrees more than double the roll and yaw response of the vehicle. Less actuator torque is required when pitch-flap coupling is employed to achieve the same lateral response as the nominal, flap-only case.