Abstract: A navigation system includes a Coriolis vibratory gyroscope, a voltage input supply, and a controller. The voltage input supply is configured to supply a first voltage input to the Coriolis vibratory gyroscope at a first bias voltage, and supply a second voltage input to the Coriolis vibratory gyroscope at a second bias voltage, the second bias voltage being different than the first bias voltage. The controller is configured to detect a difference in responses of the Coriolis vibratory gyroscope to the first bias voltage and the second bias voltage, and determine a gyro rate of the Coriolis vibratory gyroscope as a function of the difference in responses and a correction term.

Abstract: A navigation system includes a Coriolis vibratory gyroscope, a voltage input supply, and a controller. The voltage input supply is configured to supply a first voltage input to the Coriolis vibratory gyroscope at a first bias voltage, and supply a second voltage input to the Coriolis vibratory gyroscope at a second bias voltage, the second bias voltage being different than the first bias voltage. The controller is configured to detect a difference in responses of the Coriolis vibratory gyroscope to the first bias voltage and the second bias voltage, and determine a gyro rate of the Coriolis vibratory gyroscope as a function of the difference in responses and a correction term.

Abstract: A method comprises supplying an optical input to an interferometric fiber optic gyro (IFOG) at a first frequency and then a different second frequency; detecting a difference in responses of the IFOG to the optical input at the first and second frequencies; and computing a gyro rate as a function of the difference and a correction term.

Abstract: In accordance with one or more aspects of the present disclosure, a method including supplying a first voltage input to a Coriolis vibratory gyroscope at a first bias voltage; supplying a second voltage input to the Coriolis vibratory gyroscope at a second bias voltage, the second bias voltage being different than the first bias voltage; detecting a difference in responses of the Coriolis vibratory gyroscope due to the first bias voltage and the second bias voltage; and determining a gyro rate of the Coriolis vibratory gyroscope as a function of the difference in responses and a correction term.

Abstract: In accordance with one or more aspects of the present disclosure, a method including supplying a first voltage input to a Coriolis vibratory gyroscope at a first bias voltage; supplying a second voltage input to the Coriolis vibratory gyroscope at a second bias voltage, the second bias voltage being different than the first bias voltage; detecting a difference in responses of the Coriolis vibratory gyroscope due to the first bias voltage and the second bias voltage; and determining a gyro rate of the Coriolis vibratory gyroscope as a function of the difference in responses and a correction term.

Abstract: Conductive cooled gimbaled inertial measurement units are disclosed herein. An example apparatus includes an inertial measurement unit, a gimbal assembly in which the inertial measurement unit is disposed, the gimbal assembly having gaps between each gimbal of the gimbal assembly, the gaps including a gas to conduct heat from the gimbal assembly, and an isothermal dome at least partially surrounding the gimbal assembly, the isothermal dome having a cooling tube disposed on an external surface of the isothermal dome to transfer heat from the gimbal assembly via conduction.

Abstract: Conductive cooled gimbaled inertial measurement units are disclosed herein. An example apparatus includes an inertial measurement unit, a gimbal assembly in which the inertial measurement unit is disposed, the gimbal assembly having gaps between each gimbal of the gimbal assembly, the gaps including a gas to conduct heat from the gimbal assembly, and an isothermal dome at least partially surrounding the gimbal assembly, the isothermal dome having a cooling tube disposed on an external surface of the isothermal dome to transfer heat from the gimbal assembly via conduction.

Abstract: A method comprises supplying an optical input to an interferometric fiber optic gyro (IFOG) at a first frequency and then a different second frequency; detecting a difference in responses of the IFOG to the optical input at the first and second frequencies; and computing a gyro rate as a function of the difference and a correction term.

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.