Abstract: Techniques to compensate non-radiation hardened components for changes or degradation in performance that result from exposure to radiation. During testing and modeling phase, a component's performance may be characterized as a result of the exposure to radiation. In some examples, some performance characteristics, such as voltage response, frequency response, gain, leakage or other characteristics, may change as the component's exposure to an amount of radiation increases. During normal operation, a system may include one or more devices that measure the amount of radiation to which the system may be subjected, such as a radiation dosimeter. The system may compensate the non-radiation hardened component based on the amount of radiation received the known component performance change caused by radiation as determined during the modeling phase.

Abstract: Techniques to compensate non-radiation hardened components for changes or degradation in performance that result from exposure to radiation. During testing and modeling phase, a component's performance may be characterized as a result of the exposure to radiation. In some examples, some performance characteristics, such as voltage response, frequency response, gain, leakage or other characteristics, may change as the component's exposure to an amount of radiation increases. During normal operation, a system may include one or more devices that measure the amount of radiation to which the system may be subjected, such as a radiation dosimeter. The system may compensate the non-radiation hardened component based on the amount of radiation received the known component performance change caused by radiation as determined during the modeling phase.

Abstract: Techniques to compensate non-radiation hardened components for changes in performance that result from exposure to radiation. The techniques of this disclosure apply a predetermined bias signal to a representative non-radiation hardened component while a system is in use. The system determines whether there is a performance change in characteristics, such as voltage response, frequency response, gain, or other characteristics. The system may determine a compensation factor that may restore the desired signal output from the component. The system may compensate a second identical component that is in use in the system with the compensation factor. The component receiving the predetermined bias signal acts as a characterization dosimeter of the component in use in the system. A number of radiation vulnerable components may be characterized simultaneously with exact representative parts. The system may compensate identical component in use in the system with the appropriate compensation factor for each.

Abstract: An exoatmospheric device comprises an inertial measurement unit comprising a spin axis gyroscope adapted to obtain data regarding angular rotation of the exoatmospheric device about a spin axis, and at least one off-spin axis gyroscope adapted to obtain data regarding angular oscillation of the spin axis. The exoatmospheric device further comprises a processing unit coupled to the inertial measurement unit and adapted to detect attitude error by analyzing correlations between the measured rotation about the spin axis and the measured angular oscillation of the spin axis.

Abstract: A method of determining the integrity of a gyro in a navigation system is provided. The method includes detecting a relatively sudden change in one of a pitch, yaw and roll signal from a respective pitch, yaw and roll gyro and reviewing at least one other of the pitch, yaw and roll signals to verify the relatively sudden change.

Abstract: A method of implementing a fault-tolerant-avionic architecture in a vehicle includes using parity logic to monitor the functionality of at least three non-fault-tolerant inertial measurement units during a parity check and calculating a threshold from expected inertial measurement unit performance during a parity check. If a failure of an inertial measurement unit is detected based on the calculated threshold, then the method further includes identifying the failed inertial measurement units based on a direction of a parity vector in parity space. Each inertial measurement unit comprises at least one triad of sensors.

Abstract: Methods and apparatus for controlling frequency in a crystal oscillator are provided that allows for continued reception of GPS signal solution in a continuous high G environment. One method comprises measuring G-forces asserted on the crystal oscillator, determining a shift in frequency of the crystal oscillator due to the measured G-forces, determining a temperature that would shift the crystal oscillator's frequency back to a rate that would occur without the measured G-forces, and changing the temperature of the crystal oscillator based on the determined temperature to shift the crystal oscillator's frequency back to a rate that would occur if the G-forces were not present.

Abstract: A method of implementing a fault-tolerant-avionic architecture in a vehicle includes using parity logic to monitor the functionality of at least three non-fault-tolerant inertial measurement units during a parity check and calculating a threshold from expected inertial measurement unit performance during a parity check. If a failure of an inertial measurement unit is detected based on the calculated threshold, then the method further includes identifying the failed inertial measurement units based on a direction of a parity vector in parity space.

Abstract: Methods and apparatus for controlling frequency in a crystal oscillator are provided that allows for continued reception of GPS signal solution in a continuous high G environment. One method comprises measuring G-forces asserted on the crystal oscillator, determining a shift in frequency of the crystal oscillator due to the measured G-forces, determining a temperature that would shift the crystal oscillator's frequency back to a rate that would occur without the measured G-forces, and changing the temperature of the crystal oscillator based on the determined temperature to shift the crystal oscillator's frequency back to a rate that would occur if the G-forces were not present.

Abstract: Systems and methods for monitoring and tracking transients caused by geological events are provided. In one embodiment, a geological event monitoring system is provided. The system comprises a sensor array having a plurality of geologic activity sensors adapted to receive positioning signals from one or more Earth orbiting satellites and further adapted to receive a resolution enhancement signal from at least one reference station, the geologic activity sensors further adapted to measure motion activity; and a central monitoring system adapted to communicate with the sensor array, wherein the sensor array measures motion activity at a plurality of locations and transmits time stamped data characterizing the motion activity at the plurality of locations to the central monitoring system, the central monitoring system further adapted to correlate the time stamped data and track movement and inertial forces experienced by the plurality of geologic activity sensors over time.

Abstract: An exoatmospheric device comprises an inertial measurement unit comprising a spin axis gyroscope adapted to obtain data regarding angular rotation of the exoatmospheric device about a spin axis, and at least one off-spin axis gyroscope adapted to obtain data regarding angular oscillation of the spin axis. The exoatmospheric device further comprises a processing unit coupled to the inertial measurement unit and adapted to detect attitude error by analyzing correlations between the measured rotation about the spin axis and the measured angular oscillation of the spin axis.

Abstract: Systems and methods for monitoring and tracking transients caused by geological events are provided. In one embodiment, a geological event monitoring system is provided. The system comprises a sensor array having a plurality of geologic activity sensors adapted to receive positioning signals from one or more Earth orbiting satellites and further adapted to receive a resolution enhancement signal from at least one reference station, the geologic activity sensors further adapted to measure motion activity; and a central monitoring system adapted to communicate with the sensor array, wherein the sensor array measures motion activity at a plurality of locations and transmits time stamped data characterizing the motion activity at the plurality of locations to the central monitoring system, the central monitoring system further adapted to correlate the time stamped data and track movement and inertial forces experienced by the plurality of geologic activity sensors over time.

Abstract: A method and system for object characterization based on image volumetric determination are provided. The method comprises capturing frames of image data for a moving object in an area from at least two different angles. The later occurring frames of image data are subtracted from previous occurring frames of image data for each of the different angles to obtain object movement information. The object movement information is correlated from the different angles over the area, and a volume of the object is determined from the object movement information.

Abstract: Systems and methods for monitoring and tracking transients caused by geological events are provided. The system comprises a sensor array and a central monitoring system. The central monitoring system is adapted to communicate with the sensor array. The sensor array measures motion at a plurality of locations and transmits time stamped data characterizing the geologic activity at the plurality of locations to the central monitoring system. The central monitoring system is further adapted to correlate the time stamped data and map geological disturbances in real time.

Abstract: An electronic module is provided. The electronic module includes a first system and a second, redundant system. The first and second redundant systems include at least three processors having health management tasks that operate independently to perform a voting function to identify faults within the electronic module.