Abstract: An inductive look angle sensor for a guided missile radiation seeker in which the optical system of the seeker is secured to a gimbal ring that is mounted by bearing mounts to a gimbal post that is stationary with respect to the missile airframe, and the gimbal ring is adapted for rotating back and forth relative to the airframe during a missile roll cycle when the look angle of the radiation seeker relative to the airframe is not zero degrees, is disclosed. The sensor includes a first coil wound on the gimbal post; a second coil wound on the gimbal ring for inductive coupling to the first coil; a signal generator coupled to one of the two coils for providing a first alternating signal having a predetermined frequency; and a demodulator coupled to the other coil and the signal generator. The first and second coils are located relative to each other for enabling the other one of the two coils to inductively respond to the first signal by providing a second signal.

Abstract: A steering rate sensing device for use in the control of a rotating air frame comprises a base member adapted to be secured to the frame for rotation therewith about its rotary axis, a magnetic member pivotally mounted for pivotal movement about an axis transverse to the rotary axis and a coil encircling the magnetic body for sensing and picking up a signal induced by relative angular movement of the magnetic member with the coil. The device responds to gyroscopic effect induced by rotation thereof upon movement of the air frame from its axial orientation to cause the magnetic member to move relative to the sensing coil for generating a signal.

Abstract: A steering rate sensing device for rolling air frames includes a base member for attachment to the air frame, a magnetic member fixed to the base member, and a pick up coil pivotally mounted to the base in close proximity to the magnet such that movement of the coil relative to the magnet generates a signal proportional to the steering rate of the rotating body.