Using wing articulation, or dynamic dihedral, as a flight control mechanism offers the potential for very large control authority which in turn can be used to greatly improve the maneuverability of small unmanned aircraft, as well as reduce their sensitivity to gusts. This paper investigates how changing design parameters of the wings and hinges affect the stability and dynamic characteristics of articulated aircraft Trade studies of the design parameters are also performed on the control response of such an aircraft Parameters that are varied include articulation hinge elastic properties and location on the body, along with mass properties of the different bodies that constitute the overall aircraft. A unique multibody flight dynamic simulation tool is used to simulate the cases. This tool is also used for calculation of linear dynamic models about different trim conditions. Eigen analysis is performed on linear models to deduce stability and dynamic characteristics. It is shown that the spiral mode is affected the most by all of the design parameters. A reversal in roll direction is noted when the hinge is located below the center of gravity of the vehicle rather than above. The ratio of applied torque to spring stiffness determines the angle between the wings and fuselage, which then determines the lateral response of the vehicle.
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