Abstract: A method in an aircraft of using prognostic indicators for aircraft maintenance includes retrieving aircraft health data for a plurality of aircraft components wherein the aircraft health data includes at least one of mechanical systems condition indicator (CI) data, vibration spectrum data, resampled time-domain (RTD) data, and RTD spectrum data. The method includes estimating component health status information for the plurality of aircraft components using a plurality of prognostic modules wherein each prognostic module is configured to generate health status information for at least one of the aircraft components, the health status information includes at least one of a current health indicator and a prognostic indicator. The method also includes storing the component health status information for the aircraft components in a database onboard the aircraft, and causing the display of the health status information for the specific component on an aircraft display.

Abstract: A computer-implemented method for predicting material properties in an Additive Manufacturing (AM) process is provided.

Abstract: A computer-implemented method for predicting material properties in an Additive Manufacturing (AM) process is provided.

Abstract: A method in an aircraft of using prognostic indicators for aircraft maintenance includes retrieving aircraft health data for a plurality of aircraft components wherein the aircraft health data includes at least one of mechanical systems condition indicator (CI) data, vibration spectrum data, resampled time-domain (RTD) data, and RTD spectrum data. The method includes estimating component health status information for the plurality of aircraft components using a plurality of prognostic modules wherein each prognostic module is configured to generate health status information for at least one of the aircraft components, the health status information includes at least one of a current health indicator and a prognostic indicator. The method also includes storing the component health status information for the aircraft components in a database onboard the aircraft, and causing the display of the health status information for the specific component on an aircraft display.

Abstract: A computer-implemented method for predicting material properties in an Additive Manufacturing (AM) process is provided.

Abstract: A method in an aircraft of using prognostic indicators for aircraft maintenance includes retrieving aircraft health data for a plurality of aircraft components wherein the aircraft health data includes at least one of mechanical systems condition indicator (CI) data, vibration spectrum data, resampled time-domain (RTD) data, and RTD spectrum data. The method includes estimating component health status information for the plurality of aircraft components using a plurality of prognostic modules wherein each prognostic module is configured to generate health status information for at least one of the aircraft components, the health status information includes at least one of a current health indicator and a prognostic indicator. The method also includes storing the component health status information for the aircraft components in a database onboard the aircraft, and causing the display of the health status information for the specific component on an aircraft display.

Abstract: A power line communication and real-time wiring fault location system includes a power distribution system, a plurality of solid-state power controllers, and a communication and fault location determination circuit. The power distribution system includes an upstream power feeder line and a plurality of load-end feeder lines. Each solid-state power controller is associated with a different one of the load-end feeder lines and is configured to selectively couple its associated load-end feeder line to the upstream power feeder line and detect an electrical fault on its associated load-end feeder line or in an electrical load to which the associated load-end feeder line is coupled. The communication and fault location determination circuit is coupled to each of the load-end feeder lines and is configured, in response to a channel selection command, to selectively transmit a fault location stimulation signal onto one of the load-end feeder lines.

Abstract: A system and method for verifying the response capabilities of a control effector include processing, in a test module, at least command data and sensor data associated with the control effector to generate control effector health data representative of control effector health. The control effector health data are processed in a reasoner to selectively indict and clear one or more faults, determine a failure is uncertain based on the one or more indicted faults, determine one or more test excitation signals to supply to the control effector to verify whether the uncertain failure is present or absent, and supply the one or more test excitation signals to a controller that is in operable communication with the control effector.

Abstract: A health monitoring system for monitoring a vehicle and a method for operating the same are provided. The system, for example, may include, but is not limited to, at least one sensor configured to collect data corresponding to the vehicle, an interface system, a memory, and a processor communicatively coupled to the at least one sensor, the interface system and the memory, the processor configured to: determine when the vehicle is experiencing an anomaly, collect, from the interface system, data corresponding to the anomaly from a user of the vehicle, and associate, the data collected from the interface system and the data collected from the at least one sensor.

Abstract: An improved rotorcraft blade tracking system and method is provided. The provided blade tracking system and method projects a focused beam of light with minimal variance in predetermined spectral characteristics at the ranges of distance suitable for rotorcraft blade tracking applications. The provided system and method detects a reflected beam of light that is associated with the projected focused beam of light. The provided system and method maintains eye safety, and performs consistently over a variety of environmental conditions.

Abstract: A health monitoring system for monitoring a vehicle and a method for operating the same are provided. The system, for example, may include, but is not limited to, at least one sensor configured to collect data corresponding to the vehicle, an interface system, a memory, and a processor communicatively coupled to the at least one sensor, the interface system and the memory, the processor configured to: determine when the vehicle is experiencing an anomaly, collect, from the interface system, data corresponding to the anomaly from a user of the vehicle, and associate, the data collected from the interface system and the data collected from the at least one sensor.

Abstract: A system method of estimating health of aircraft brake system friction material includes sensing a temperature of the friction material, and supplying the sensed temperature to a processor-implemented thermal model that is configured to estimate friction material temperatures at one or more locations on the friction material. The estimates of friction material temperatures are supplied to a processor-implemented thermal oxidation model that is configured, based on the estimates of friction material temperatures, to estimate friction material loss due to thermal oxidation. Data representative of runway fluid exposure are supplied to a processor-implemented catalytic oxidation model that is configured, based on the runway fluid exposure, to estimate friction material loss due to catalytic oxidation. The health of the friction material is estimated based on the estimates of friction material loss from the processor-implemented thermal oxidation model and the processor-implemented catalytic oxidation model.

Abstract: A system and method for verifying the response capabilities of a control effector include processing, in a test module, at least command data and sensor data associated with the control effector to generate control effector health data representative of control effector health. The control effector health data are processed in a reasoner to selectively indict and clear one or more faults, determine a failure is uncertain based on the one or more indicted faults, determine one or more test excitation signals to supply to the control effector to verify whether the uncertain failure is present or absent, and supply the one or more test excitation signals to a controller that is in operable communication with the control effector.

Abstract: A system method of estimating health of aircraft brake system friction material includes sensing a temperature of the friction material, and supplying the sensed temperature to a processor-implemented thermal model that is configured to estimate friction material temperatures at one or more locations on the friction material. The estimates of friction material temperatures are supplied to a processor-implemented thermal oxidation model that is configured, based on the estimates of friction material temperatures, to estimate friction material loss due to thermal oxidation. Data representative of runway fluid exposure are supplied to a processor-implemented catalytic oxidation model that is configured, based on the runway fluid exposure, to estimate friction material loss due to catalytic oxidation. The health of the friction material is estimated based on the estimates of friction material loss from the processor-implemented thermal oxidation model and the processor-implemented catalytic oxidation model.