Spin stabilized ring-wing canard controlled missile

DESCRIPTION OF THE INVENTION

A missile generally indicated by reference numeral 1 includes an aft fin 2, a longitudinal centerline axis 3, a center of gravity 4 and a nose 5. A boom 6 projects forward of the missile and is provided with a spherical bearing 7 extending around the boom surface for support of spin stabilized ringwing canard 8. The canard includes an aerodynamic lift ring 9 connected by ring support struts 10 to a bearing 11 which is mounted on bearing 7 for rotation. The canard is mounted with its spin axis pivoted about a point in the longitudinal axis of the missile. As the missile leaves the tube launcher, the canard may be spun up by riflings in the tube or by high-pressure gas carried by the canard itself to be spin stabilized for gyroscopic action to maintain the spin axis thereof in the trajectory of the missile. When a disturbing force causes rotation of the missile axis from the canard axis, an aerodynamic force acts on lift ring 9 and a restoring torque is applied to the missile having a lever arm that is the effective length from the center of the spherical bearing to the missile center of gravity thereby restoring coincidence of the missile and canard axes.