Abstract: High aspect ratio positioning systems are disclosed herein. A high aspect ratio positioning system can be packaged in a thin package that can eliminate some bulky components typically associated with positioning systems such as pancake motors or other motors, geared resolvers, gear trains, and the like. Thus, the high aspect ratio positioning system can be used in applications where volume is limited, without sacrificing accuracy.

Abstract: Inertial measurement unit apparatus for use with guidance systems are disclosed herein. An example guidance system includes an inertial measurement unit removably coupled in a cavity of a guidance wafer via an access port of the guidance wafer defining a port axis that is non-parallel relative to a longitudinal axis of the guidance wafer.

Abstract: An azimuth determination system has a platform. A plurality of gimbals is attached to the platform to allow the platform to rotate about multiple axes. A pair of gryos is attached to the platform. A leveling device is attached to the platform to indicate when the platform is at a desired position. A control device attached to the plurality of gimbals to move the platform to the desired position indicated by the leveling device. An electronics system is to provide power to the azimuth determination system and to determine azimuth by positioning the gyros in a first position with an input axis of the gyros in the horizontal plane and orthogonal to the Earth Rate vector to calculate a first output and rotating the gyros 180° about the vertical to a second position to calculate a second output, the platform is then inverted and an additional set of two readings is taken. The four outputs are combined to produce the azimuth value and a gyro induced bias error.

Abstract: In accordance with at least one embodiment of the present invention, a system includes a gyroscope and a flight vehicle operatively connected to the gyroscope. The gyroscope includes a length of fiber optic cable arranged in loop and configured to surround an interior loop region. The gyroscope further includes a control unit configured to send and receive light through the fiber optic cable and measure a rate of rotation of the gyroscope. A portion of the flight vehicle is located within the interior loop region.

Abstract: In accordance with at least one embodiment of the present invention, a system includes a gyroscope and a flight vehicle operatively connected to the gyroscope. The gyroscope includes a length of fiber optic cable arranged in loop and configured to surround an interior loop region. The gyroscope further includes a control unit configured to send and receive light through the fiber optic cable and measure a rate of rotation of the gyroscope. A portion of the flight vehicle is located within the interior loop region.

Abstract: A method and apparatus for determining an absolute angular velocity of a vehicle that rotates during operation about an axis of rotation. The vehicle includes a vehicle body and a gyroscope rotatably mounted on the body for rotation with respect to the body about a gyroscope axis generally aligned with the axis of rotation. The gyroscope is rotated with respect to the vehicle body about the gyroscope axis in a direction opposite to rotation of the vehicle so an absolute angular velocity of the gyroscope about the gyroscope axis tends to remain about zero. A rotational speed of the gyroscope is measured about the gyroscope axis with respect to the vehicle body. The rotational speed of the gyroscope corresponds to the absolute angular velocity of the vehicle about the axis of rotation.