Abstract: Methods and systems are described for increasing the safety of unmanned vehicles. Failure rates of components can be combined and adjusted if necessary given sensor data or statistical or historical data that impacts failure rates. The failure rates of components can be combined to give an overall failure or success rate for a vehicle and can be compared to an accepted failure or success rate in connection with a hazard. Hazards with heightened safety requirements can be avoided by a contingency maneuver if the unmanned vehicle's failure or success rate is not acceptable.

Abstract: Methods and systems are described for increasing the safety of unmanned vehicles. Failure rates of components can be combined and adjusted if necessary given sensor data or statistical or historical data that impacts failure rates. The failure rates of components can be combined to give an overall failure or success rate for a vehicle and can be compared to an accepted failure or success rate in connection with a hazard. Hazards with heightened safety requirements can be avoided by a contingency maneuver if the unmanned vehicle's failure or success rate is not acceptable.

Abstract: Methods and systems are described for increasing the safety of unmanned vehicles. Failure rates of components can be combined and adjusted if necessary given sensor data or statistical or historical data that impacts failure rates. The failure rates of components can be combined to give an overall failure or success rate for a vehicle and can be compared to an accepted failure or success rate in connection with a hazard. Hazards with heightened safety requirements can be avoided by a contingency maneuver if the unmanned vehicle's failure or success rate is not acceptable.

Abstract: A system and algorithm-based method of determining engine health and assuring available propulsion power based on historical data reflecting the individual engine's unique performance “fingerprint.

Abstract: A system and algorithm-based method of determining engine health and assuring available propulsion power based on historical data reflecting the individual engine's unique performance “fingerprint.

Abstract: In one example embodiment, a filter condition measurement device features an engine data repository, one or more sensor units, and a measurement unit. The measurement system is configured to identify a first flow value corresponding to a sensed engine power value from the engine data repository, determine a filter coefficient for the filter as a function of the first flow value and the sensed delta-pressure value; identify a second engine power value from the plurality of stored engine power values and a second flow value corresponding to the second engine power value; and determine a second delta-pressure value for the air filter as a function of the filter coefficient and the second flow value.

Abstract: A system and algorithm-based method of determining engine health and assuring available propulsion power based on historical data reflecting the individual engine's unique performance “fingerprint.

Abstract: In one example embodiment, an engine flow measurement device features an engine data repository, one or more sensor units, and a measurement unit. The measurement system is configured to identify, from performance data, a maneuver performed during operation of the aircraft and to measure, for the identified maneuver, a plurality of maneuver flow values achieved during performance of the maneuver. The plurality of maneuver flow values correspond to a plurality of maneuver engine power values. Each of the plurality of maneuver flow values represent a volume of air flow through the air filter at a particular moment during performance of the maneuver.

Abstract: A system and algorithm-based method of determining engine health and assuring available propulsion power based on historical data reflecting the individual engine's unique performance “fingerprint.

Abstract: In one example embodiment, an engine flow measurement device features an engine data repository, one or more sensor units, and a measurement unit. The measurement system is configured to identify, from performance data, a maneuver performed during operation of the aircraft and to measure, for the identified maneuver, a plurality of maneuver flow values achieved during performance of the maneuver. The plurality of maneuver flow values correspond to a plurality of maneuver engine power values. Each of the plurality of maneuver flow values represent a volume of air flow through the air filter at a particular moment during performance of the maneuver.

Abstract: In one example embodiment, a filter condition measurement device features an engine data repository, one or more sensor units, and a measurement unit. The measurement system is configured to identify a first flow value corresponding to a sensed engine power value from the engine data repository, determine a filter coefficient for the filter as a function of the first flow value and the sensed delta-pressure value; identify a second engine power value from the plurality of stored engine power values and a second flow value corresponding to the second engine power value; and determine a second delta-pressure value for the air filter as a function of the filter coefficient and the second flow value.