A method is provided for diagnosing a failure on an aircraft that includes aircraft systems and monitors configured to report effects of failure modes of the aircraft systems. The method includes receiving a fault report that indicates one or more of the monitors that reported the effects of a failure mode in an aircraft system of the aircraft systems, and accessing a fault pattern library that describes relationships between possible failure modes and patterns of those of the monitors configured to report the effects of the possible failure modes. The method also includes diagnosing the failure mode of the aircraft system from the one or more of the monitors that reported, and using the fault pattern library and a greedy selection algorithm, determining a maintenance action for the failure mode; and generating a maintenance message including at least the maintenance action.

A computer is configured to enable a rapid, consistent, ply-by-ply, quantitative analytical assessment of various Finite Element Method (FEM) material models based on metrics defined for impact damage. Additionally, the computer is configured to provide a method for determining the accuracy of such FEM material model(s) by comparing the output of those models to non-destructive evaluation (NDE) test data.

A computer is configured to enable a rapid, consistent, ply-by-ply, quantitative analytical assessment of various Finite Element Method (FEM) material models based on metrics defined for impact damage. Additionally, the computer is configured to provide a method for determining the accuracy of such FEM material model(s) by comparing the output of those models to non-destructive evaluation (NDE) test data.

In some embodiments, a method for determining a location of an unmanned system (UMS) can include: receiving data from a plurality of data sources, wherein the data sources include a geolocation sensor and at least one of an RF receiver, a RADAR system, a LIDAR system, a SONAR system, an infrared camera, a Simultaneous Location and Mapping Algorithm (SLAM) system, an inertial sensor, or an acoustic sensor; determining a reliability of one or more of the data sources based on the received data; assigning weights to the data sources based at least in part on the determination of the reliability of the one or more data sources; and determining the location of the UMS using the received data and the assigned weights.

In some embodiments, a method for determining a location of an unmanned system (UMS) can include: receiving data from a plurality of data sources, wherein the data sources include a geolocation sensor and at least one of an RF receiver, a RADAR system, a LIDAR system, a SONAR system, an infrared camera, a Simultaneous Location and Mapping Algorithm (SLAM) system, an inertial sensor, or an acoustic sensor; determining a reliability of one or more of the data sources based on the received data; assigning weights to the data sources based at least in part on the determination of the reliability of the one or more data sources; and determining the location of the UMS using the received data and the assigned weights.

A method, apparatus, and system for managing a supplemental cooling unit. The process receives data for a supplemental cooling unit. The data comprises a pressure, a temperature, and a speed. The process generates a set of alerts based on the data for the supplemental cooling unit and a signature in the data.

A method, apparatus, and system for managing a supplemental cooling unit. The process receives data for a supplemental cooling unit. The data comprises a pressure, a temperature, and a speed. The process generates a set of alerts based on the data for the supplemental cooling unit and a signature in the data.

A driveshaft misalignment measurement system for a drivetrain of an aircraft includes a driveshaft having a first end forming a driveshaft spline and a drivetrain subsystem including a spline adapted to connect to the driveshaft spline to form a splined connection. Rotational energy is transferred between the drivetrain subsystem and the driveshaft via the splined connection. The driveshaft misalignment measurement system also includes accelerometers coupled to the drivetrain configured to detect acceleration data and a flight control computer configured to measure misalignment at the splined connection using the acceleration data.

A driveshaft misalignment measurement system for a drivetrain of an aircraft includes a driveshaft having a first end forming a driveshaft spline and a drivetrain subsystem including a spline adapted to connect to the driveshaft spline to form a splined connection. Rotational energy is transferred between the drivetrain subsystem and the driveshaft via the splined connection. The driveshaft misalignment measurement system also includes accelerometers coupled to the drivetrain configured to detect acceleration data and a flight control computer configured to measure misalignment at the splined connection using the acceleration data.

An aircraft performance analysis system and method include a performance analysis control unit that receives original performance model data, receives flight data from an aircraft, and determines a current performance model for the aircraft based on the original performance model data and the flight data.