Patent ID: 6646242
Filing Date: 2003-11-11
Classification: F41G,F42B

Abstract:
A system for guiding the flight of a missile in any given direction, the missile having an elongated body and a longitudinal axis; a first movable section and a second movable section; an interface plane positioned between the sections and intersecting the axis at an angle between 0.5Â° and 10Â°; the missile further having a position command generator and a voltage generator; SAID MISSILE GUIDING SYSTEM comprising: a rotatable joint, said joint coupling the first and second movable sections so as to allow rotation of the first section by a pre-selected angle with respect to the second section, said rotatable joint comprising: a drive shaft rigidly attached to the first section and movably attached to the second section, said shaft connecting the sections and being mounted to be perpendicular to the interface plane; a plurality of thrust bearings located in the first section and mounted on said drive shaft, said thrust bearings providing axial support to said guiding system during missile flight; a plurality of roller bearings located in the first section and mounted on said drive shaft, said roller bearings providing radial support to said guiding system during missile flight, said thrust bearings and roller bearings being positioned adjacent to each other; a means for rotating said joint; a means for determining current rotational position of the missile; an electronic controller containing therein a hall pulse counting circuit, said controller being connected to the position command generator and said determining means to receive command signals and current rotational signals, respectively, therefrom and yield error signals in response thereto; a voltage generator coupled between said electronic controller and said rotating means, said voltage generator receiving said error signals from said controller and, in response, generating a proportional voltage command, said voltage command being input to said rotating means to cause the rotation of said joint by a corresponding angle, thereby rotating the first section with respect to the second section, thus effecting a chance in the flight direction of the missile.