Abstract: A precision linear actuator (10, 120, 140) is provided particularly adapted for accurately controlling the positioning of a lens element in the optical system of a guided vehicle such as a missile. The actuator includes a frame (12, 130, 142) rigidly affixed to the missile structure which includes a pair of bearing supports (30, 32) and a pair of separated guide pockets (24, 26). A lever (14, 122, 150) is installed within the frame (12, 130, 142) and is fixed to the frame by bearings (44, 46) which enable the lever to undergo slight rotation with respect to the frame. An actuator mechanism in the form of a voice coil (56), drive motor or other device is employed to drive the lever (14, 122, 150) to undergo its rotational motion. A lens holder (16) is installed within an open area inside the lever (14, 122, 150) and defines separated guide rails (76, 78, 80, 82) which enable it to be moved linearly with respect to the frame (12, 130, 142).

Abstract: A lens focusing mechanism 10 including a bracket 18 for retaining a lens 14. The bracket 18 has a bearing 22 attached thereto or integral therewith. The bearing 22 is eccentric relative to the leans 14 and is effective to move the lens 14 along an optical axis 16 thereof. Movement is effectuated by a drive mechanism 34 in a smooth manner and without lubrication. In a specific embodiment, the bearing 22 is eccentric and external to a cylindrical volume defined by the periphery of the lens 14.

Abstract: An improved mirror pointing method and apparatus which stabilizes a mirror relative to the line-of-sight of the input image. The invention includes an outer gimbal pivotally mounted on a pedestal which is in turn attached to a reference frame. An inner gimbal is pivotally mounted on the outer gimbal and the mirror is separately pivotally mounted on the outer gimbal. A linkage is provided between the inner gimbal and the mirror to stabilize the mirror relative to the line-of-sight of the input image. In a more specific embodiment, the outer gimbal and the inner gimbal are stabilized. Thus, a rate detector is provided for detecting angular turning rates of the inner and outer gimbals in conjunction with torquers and resolvers as is known in the art.

Abstract: A multiple phase electronically commutated torque motor including an annular stator element having at least two coils or windings on the periphery thereof and a magnetic rotor disposed concentrically within the stator for relative coplanar rotational motion. Means are provided for selectively energizing and de-energizing the windings as a function of the instantaneous rotor angle on command to generate a desired torque.

Abstract: A two-axis gyroscope in which precession may be effected by application of a DC current to the stationary precession windings. The rotor assembly has a pair of ring-shaped permanent magnets with their magnetic vectors aligned parallel with the gyro spin axis. This structure presents a magnetic field to the precession windings which does not change as the rotor assembly rotates. Thus the gyroscope may be precessed by application of a DC current to the precession windings. The precession windings are located along two orthogonal axes to allow precession of the gyro in two orthogonal directions.