Abstract: Systems and methods to fuse aviation-related data systems for comprehensive aircraft system health monitoring are provided. One example method includes obtaining, by one or more computing devices, fault data indicative of a plurality of fault indications provided by a first plurality of components of an aircraft. The method includes obtaining, by the one or more computing devices, condition indicators describing the respective operational conditions of a second plurality of components of the aircraft. The method includes fusing, by the one or more computing devices, the fault data with the condition indicators to form a comprehensive data set. The method includes identifying, by the one or more computing devices, one or more causes of the plurality of fault conditions based at least in part on the comprehensive data set. One example system includes a data fuser, a cause identifier, and an alert generator.

Abstract: Systems and methods for formatting aviation data for improved aircraft fault detection, diagnosis, and maintenance are provided. One example method includes determining a plurality of available parameters associated with an aircraft. The method includes matching the plurality of available parameters against a plurality of desired parameters to identify a plurality of matched parameters that are both desired and available. The plurality of matched parameters are useful to perform fault diagnosis and prognosis for the aircraft. The method includes determining a priority level for each of the plurality of matched parameters. The method includes creating a standardized maintenance-optimized data frame configuration based at least in part on the plurality of matched parameters and the priority level for each of the plurality of matched parameters.

Abstract: Systems and methods for formatting aviation data for improved aircraft fault detection, diagnosis, and maintenance are provided. One example method includes determining a plurality of available parameters associated with an aircraft. The method includes matching the plurality of available parameters against a plurality of desired parameters to identify a plurality of matched parameters that are both desired and available. The plurality of matched parameters are useful to perform fault diagnosis and prognosis for the aircraft. The method includes determining a priority level for each of the plurality of matched parameters. The method includes creating a standardized maintenance-optimized data frame configuration based at least in part on the plurality of matched parameters and the priority level for each of the plurality of matched parameters.

Abstract: A method of diagnosing a fault in an air-conditioning pack of an aircraft is disclosed, wherein the air-conditioning pack includes one or more sensors. The method includes transmitting data from at least one of the sensors operably coupled to the air-conditioning pack, comparing the transmitted data to a predetermined threshold, and diagnosing a fault in the air-conditioning pack based on the comparison.

Abstract: Systems and methods to fuse aviation-related data systems for comprehensive aircraft system health monitoring are provided. One example method includes obtaining, by one or more computing devices, fault data indicative of a plurality of fault indications provided by a first plurality of components of an aircraft. The method includes obtaining, by the one or more computing devices, condition indicators describing the respective operational conditions of a second plurality of components of the aircraft. The method includes fusing, by the one or more computing devices, the fault data with the condition indicators to form a comprehensive data set. The method includes identifying, by the one or more computing devices, one or more causes of the plurality of fault conditions based at least in part on the comprehensive data set. One example system includes a data fuser, a cause identifier, and an alert generator.

Abstract: A method of predicting a fault in an air-conditioning pack of an aircraft is disclosed. The air-conditioning pack includes one or more sensors outputting data related to air-conditioning pack temperature, air-conditioning pack pressure, or air-conditioning pack valve or actuator positions. The method includes transmitting data from at least one of the sensors operably coupled to the air-conditioning pack, comparing the transmitted data to a predetermined threshold, and predicting a fault in the air-conditioning pack based thereon.

Abstract: Methods of determining an overall performance of air-conditioning system(s) are disclosed. The methods include transmitting data from a sensor operably coupled to at least one air-conditioning pack, comparing the transmitted data, determining an overall performance of the air-conditioning system(s) based on the comparing, and providing an indication of the determined overall performance of the air-conditioning system(s).

Abstract: A method of diagnosing a fault in an air-conditioning pack of an aircraft is disclosed, wherein the air-conditioning pack includes one or more sensors. The method includes transmitting data from at least one of the sensors operably coupled to the air-conditioning pack, comparing the transmitted data to a predetermined threshold, and diagnosing a fault in the air-conditioning pack based on the comparison.

Abstract: A method of predicting a fault in an air-conditioning pack of an aircraft is disclosed. The air-conditioning pack includes one or more sensors outputting data related to air-conditioning pack temperature, air-conditioning pack pressure, or air-conditioning pack valve or actuator positions. The method includes transmitting data from at least one of the sensors operably coupled to the air-conditioning pack, comparing the transmitted data to a predetermined threshold, and predicting a fault in the air-conditioning pack based thereon.

Abstract: A method of predicting a fault in a cabin temperature control system of an air-conditioning system of an aircraft is disclosed. The method includes transmitting data related to a temperature, pressure, valve position, or actuator position of the cabin temperature control system, comparing the transmitted data to a reference value, and predicting a fault in the cabin temperature control system based on the comparing.

Abstract: A method of diagnosing a fault in a cabin temperature control system of an air-conditioning system of an aircraft includes transmitting multiple temperature sensor readings from temperature sensors operably coupled to the air-conditioning system, comparing the transmitted multiple temperature sensor readings to related reference values, and diagnosing a fault in the cabin temperature control system based on the comparing.

Abstract: System and method of identifying a fault in an aircraft having at least one monitored system, including receiving operational data for the at least one monitored system during at least a portion of a flight, receiving user input data from a user input corresponding to the operation of the at least one monitored system, and identifying an actual fault condition, by a controller, when the user input data is determined to be symptomatic of the identified possible fault condition.

Abstract: System and method of identifying a fault in an aircraft having at least one monitored system, including receiving operational data for the at least one monitored system during at least a portion of a flight, receiving user input data from a user input corresponding to the operation of the at least one monitored system, and identifying an actual fault condition, by a controller, when the user input data is determined to be symptomatic of the identified possible fault condition.

Abstract: A method of monitoring hydraulic fluid levels in an aircraft includes identifying segments of operation where the aircraft meets a predetermined stability criteria, receiving output from the fluid sensor, calculating hydraulic fluid levels within the at least one hydraulic storage tank, determining a hydraulic fluid value indicative of the amount of hydraulic fluid in the aircraft based on at least the calculated hydraulic fluid level, and providing an indication of the hydraulic fluid value.

Abstract: A method of monitoring hydraulic fluid levels in an aircraft includes identifying segments of operation where the aircraft meets a predetermined stability criteria, receiving output from the fluid sensor, calculating hydraulic fluid levels within the at least one hydraulic storage tank, determining a hydraulic fluid value indicative of the amount of hydraulic fluid in the aircraft based on at least the calculated hydraulic fluid level, and providing an indication of the hydraulic fluid value.

Abstract: A method for predicting faults in an aircraft thrust reverser system, the method includes receiving a position signal, determining a variation in the position signal relative to a reference position, predicting a fault in the thrust reverser based on the variation, and providing an indication of the predicted fault.