Abstract: One example includes a navigation system. The navigation system includes an inertial navigation system (INS) that is configured to provide a coordinate frame corresponding to an inertial reference of the INS relative to a geodetic coordinate system. The coordinate frame includes a reference axis that defines a reference orientation of the INS. The system also includes an optical tracking device configured to obtain a reference image to determine an orientation of a boresight axis of the optical tracking device. The system further includes an alignment controller configured to compare the reference axis based on the coordinate frame and the boresight axis based on the reference image to determine an angular misalignment between the reference axis and the boresight axis, and to adjust the reference orientation to align the reference axis to the boresight axis based on the determined angular misalignment.

Abstract: The invention is related to a method and an inertial navigation system for combining continuous signal output from a first inertial sensor (14) with discontinuous signal output from a second inertial sensor (12). The first inertial sensor (14) acquires continuous data with respect to a navigation frame of reference for a parameter used in inertial navigation and the continuous data is processed to produce estimated values of the parameter. The second inertial sensor (12) acquires discontinuous data with respect to a case frame of reference indicative of the parameter with respect to a case (25) containing the second inertial sensor (12). The discontinuous data is processed to produce measurements of the parameter at selected times, —and the estimated values of the parameter and the measurements of the parameter are processed at selected times with a Kalman filter to provide corrections to the estimated values of the parameter at the selected times.

Abstract: One example includes a FOG assembly including a spool that includes a flattened portion corresponding to a flange comprising an axial center corresponding to a sensitive axis about which an associated FOG system is configured to measure rotation. The FOG assembly also includes a magnetic shield arranged as a capped concentric cover about the sensitive axis and coupled to the spool and the flange to create a toroidal cavity between the magnetic shield and the flange. A fiber coil is disposed within the toroidal cavity and coupled to the flange. The fiber coil includes an optical fiber which is counter-wound in first and second orientations. The fiber coil has an axial dimension along the sensitive axis that is less than or equal to approximately 160% of a radial width corresponding to a difference between an outer radius and an inner radius of the fiber coil.

Abstract: One example includes a fiber-optic gyroscope (FOG) system that includes a fiber coil. The coil includes an optical fiber wound around a spool of a FOG. The optical fiber includes a first input and a second input. The system also includes an optical beam controller comprising an optical switch that provides a first optical beam to the first input and a second optical beam to the second input during a first switching state, and provides the first optical beam to the second input and the second optical beam to the first input during a second switching state. The system further includes a controller that mitigates bias error in determining rotation of the FOG based on comparing the first and second optical beams output from the FOG during the first and second switching states.

Abstract: One example includes a FOG assembly including a spool that includes a flattened portion corresponding to a flange comprising an axial center corresponding to a sensitive axis about which an associated FOG system is configured to measure rotation. The FOG assembly also includes a magnetic shield arranged as a capped concentric cover about the sensitive axis and coupled to the spool and the flange to create a toroidal cavity between the magnetic shield and the flange. A fiber coil is disposed within the toroidal cavity and coupled to the flange. The fiber coil includes an optical fiber which is counter-wound in first and second orientations. The fiber coil has an axial dimension along the sensitive axis that is less than or equal to approximately 160% of a radial width corresponding to a difference between an outer radius and an inner radius of the fiber coil.

Abstract: A control system includes a processor that operates one or more control loops that enable gyroscopic angular measurement for an inertial measurement unit (IMU). Each of the one or more control loops operates over a range of set points defined for each of the respective control loops. A dynamic loop adjuster receives environmental input data to determine environmental conditions for the IMU. The dynamic loop adjuster alters at least one of the set points for at least one of the one or more control loops operated by the processor based on the determined environmental conditions.

Abstract: A fiber optic gyroscope (FOG) is provided. The FOG comprises a depolarizer that receives light from a light source, a multifunction integrated optic chip (MIOC) and a sensing coil coupled to outputs of the MIOC. The FOG also includes a polarizer coupled between an output of the depolarizer and an input of the MIOC. The polarizer mitigates polarization non-reciprocity (PNR) bias error and enhances the polarization extinction ratio (PER) of the FOG.

Abstract: A control system includes a processor that operates one or more control loops that enable gyroscopic angular measurement for an inertial measurement unit (IMU). Each of the one or more control loops operates over a range of set points defined for each of the respective control loops. A dynamic loop adjuster receives environmental input data to determine environmental conditions for the IMU. The dynamic loop adjuster alters at least one of the set points for at least one of the one or more control loops operated by the processor based on the determined environmental conditions.

Abstract: A control system includes a processor that operates one or more control loops that enable gyroscopic angular measurement for an inertial measurement unit (IMU). Each of the one or more control loops operates over a range of set points defined for each of the respective control loops. A dynamic loop adjuster receives environmental input data to determine environmental conditions for the IMU. The dynamic loop adjuster alters at least one of the set points for at least one of the one or more control loops operated by the processor based on the determined environmental conditions.

Abstract: A control system includes a processor that operates one or more control loops that enable gyroscopic angular measurement for an inertial measurement unit (IMU). Each of the one or more control loops operates over a range of set points defined for each of the respective control loops. A dynamic loop adjuster receives environmental input data to determine environmental conditions for the IMU. The dynamic loop adjuster alters at least one of the set points for at least one of the one or more control loops operated by the processor based on the determined environmental conditions.

Abstract: A system is provided for controlling the amplitude of a vibrating resonant sensor through a drive signal applied to the resonator. The system comprises a controller that provides the drive signal to a forcer coupled to the resonator to excite the resonator into vibration at its resonant frequency. The system further comprises a buffer having an input node that receives charge of a pickoff capacitor of the resonator that is a measure of the resonator vibration and a current reference waveform. The buffer provides an output that is a difference signal that represents an error of the resonator vibration that corresponds to a difference between the measured resonator vibration and the current reference waveform, wherein the controller adjusts the drive signal in order to null the difference signal.

Abstract: A system is provided for controlling the amplitude of a vibrating resonant sensor through a drive signal applied to the resonator. The system comprises a controller that provides the drive signal to a forcer coupled to the resonator to excite the resonator into vibration at its resonant frequency. The system further comprises a buffer having an input node that receives charge of a pickoff capacitor of the resonator that is a measure of the resonator vibration and a current reference waveform. The buffer provides an output that is a difference signal that represents an error of the resonator vibration that corresponds to a difference between the measured resonator vibration and the current reference waveform, wherein the controller adjusts the drive signal in order to null the difference signal.

Abstract: A fiber optic gyroscope (FOG) is provided. The FOG comprises a depolarizer that receives light from a light source, a multifunction integrated optic chip (MIOC) and a sensing coil coupled to outputs of the MIOC. The FOG also includes a polarizer coupled between an output of the depolarizer and an input of the MIOC. The polarizer mitigates polarization non-reciprocity (PNR) bias error and enhances the polarization extinction ratio (PER) of the FOG.

Abstract: An exemplary navigation system uses a master navigation component at a first location in a vehicle and a slave navigation component at a second location that is a variable displacement to the first location due to physical deformation of the vehicle. Static and dynamic location components provide static and dynamic information of the displacement between the first and second locations. An error estimator estimates errors in the navigational measurement data generated by the slave navigation component based on the navigational measurement data generated by the master navigation component and the displacement information provided by the static and dynamic location components. The master navigation component corrects the navigation measurement data of the slave navigation component based on the determined error and translates the corrected navigation measurement data of the slave navigation component into navigational measurement data in its coordinate system.

Abstract: A gyroscope having photonic crystals for sensing rotation uses the Sagnac effect to determine angular motion. The gyroscope comprises a photonic crystal capable of guiding counter-propagating light beams in a closed path. A light source, coupling, and detection apparatus permits detection of phase changes between the counter-propagating beams, thereby permitting measurement of angular rotation. The photonic crystal comprises a periodic structure of pillars and voids which creates a photonic bandgap waveguide within which light waves in the proper wavelength range propagate with low loss.

Abstract: A gyroscope having photonic crystals for sensing rotation uses the Sagnac effect to determine angular motion. The gyroscope comprises a photonic crystal capable of guiding counter-propagating light beams in a closed path. A light source, coupling, and detection apparatus permits detection of phase changes between the counter-propagating beams, thereby permitting measurement of angular rotation. The photonic crystal comprises a periodic structure of pillars and voids which creates a photonic bandgap waveguide within which light waves in the proper wavelength range propagate with low loss.

Abstract: A gyroscope having photonic crystals for sensing rotation uses the Sagnac effect to determine angular motion. The gyroscope comprises a photonic crystal capable of guiding counter-propagating light beams in a closed path. A light source, coupling, and detection apparatus permits detection of phase changes between the counter-propagating beams, thereby permitting measurement of angular rotation. The photonic crystal comprises a periodic structure of pillars and voids which creates a photonic bandgap waveguide within which light waves in the proper wavelength range propagate with low loss.

Abstract: An automatic gain control system for a fiber optic gyroscope control loop includes an adjustable gain applied to the gyro output signal. A pilot signal is injected into the fiber optic gyroscope control loop. A compensation loop receives signals output from the control loop and also receives pilot signals. The compensation loop processes the pilot signal to produce a compensation signal that is combined with signals output from the control loop to provide a compensated fiber optic gyroscope output signal. An automatic gain control loop is connected between the compensation loop and the adjustable gain applied to the fiber optic gyroscope output signal. The automatic gain control loop includes a gain error demodulator that multiplies the compensated fiber optic gyroscope output signal and the compensation signal together to produce a gain error signal used to control the adjustable gain in order to stabilize the gain of the gyro control loop.

Abstract: An automatic gain control system for a fiber optic gyroscope control loop includes an adjustable gain applied to the gyro output signal. A pilot signal is injected into the fiber optic gyroscope control loop. A compensation loop receives signals output from the control loop and also receives pilot signals. The compensation loop processes the pilot signal to produce a compensation signal that is combined with signals output from the control loop to provide a compensated fiber optic gyroscope output signal. An automatic gain control loop is connected between the compensation loop and the adjustable gain applied to the fiber optic gyroscope output signal. The automatic gain control loop includes a gain error demodulator that multiplies the compensated fiber optic gyroscope output signal and the compensation signal together to produce a gain error signal used to control the adjustable gain in order to stabilize the gain of the gyro control loop.

Abstract: A fiber optic gyroscope signal process dither system permits application of a low amplitude dither signal for many sampling periods without increasing the noise in the sampled outputs due to residual dither signals. A dither loop and an accumulator are added to a closed loop fiber optic gyroscope rotation sensing system. The dither loop has a delay and a gain that are adjusted to match the gain and delay of the fiber gyro loop. A zero mean dither of amplitude sufficient to break up the deadband is injected into to gyro and the dither loop. The dither loop filters the dither signal in the same manner as the gyro loop to provide a signal that is input to a differencing circuit to remove the dither signal from the gyro output.