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US 12,630,302 B2Granted
Automatic diagnostic method for at least one engine equipping an aircraft, aircraft and arrangement implementing the method
AssigneeAirbus Helicopters
InventorFlorent Esterle
Life of this patent
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Abstract
An automatic diagnostic method for monitoring a state of health of at least one engine equipping an aircraft, the method comprising the periodic in-flight acquisition of a plurality of flight data, with sensors, the plurality of flight data being representative of a plurality of physico-chemical parameters, the identification, with a controller, from the plurality of flight data, of at least one predetermined engine health check phase and the isolation, with the controller, of a sequence of significant data from the plurality of flight data produced during the at least one engine health check phase.
Claims20
An automatic diagnostic method for monitoring a state of health of at least one engine equipping an aircraft, the method comprising the following steps:
- periodic in-flight acquisition of a plurality of flight data with sensors, the plurality of flight data being representative of a plurality of physico-chemical parameters;
- identification, with a controller, from the plurality of flight data, of at least one predetermined engine health check phase and isolation, with the controller, of a sequence of significant data from the plurality of flight data produced during the at least one engine health check phase, the significant data of a sequence being acquired successively;
- and
- for each engine health check phase, calculation, with the controller, of at least one engine health index as a function of at least one control parameter of the at least one engine from the plurality of physico-chemical parameters,
- wherein the method comprises the following steps:
- for each engine health index, generation, with the controller, of a point of an at least one-dimensional map, each point associating the engine health index with at least one value of at least one predetermined state parameter from the plurality of physico-chemical parameters, each predetermined state parameter corresponding to a dimension of the map, each value corresponding respectively to a value of the at least one predetermined state parameter at an instant in the sequence of significant data for which the engine health index is calculated;
- grouping together, with the controller, of the points of the map into at least one class of interest, each class of interest corresponding to a group of points spaced apart from each other in the map by a predetermined maximum distance;
- monitoring, with the controller, of the engine health indices corresponding to the points of the at least one class of interest;
- and
- generation, with an alerter, of an information signal depending on the engine health indices monitored during the monitoring step;
- wherein the method comprises, for each class, the determination of a barycenter of the points and a weighting operation assigning a weight to each engine health index, the weight depending at least on a distance separating the at least one point from the barycenter, the monitoring of the engine health indices being carried out depending on the weights of each engine health index by producing a weighted curve representative of the engine health indices and the associated weights, the information signal being generated when a slope of the weighted curve passes a predetermined threshold value, when a discontinuity of the weighted curve is identified or when a weighted value of the engine health indices passes another predetermined threshold value.
8 more elements
An automatic diagnostic method for monitoring a state of health of at least one aircraft engine, the method comprising:
- using sensors to periodically conduct in-flight acquisition of a plurality of flight data representative of a plurality of physico-chemical parameters;
- using a controller to identify from the plurality of flight data, at least one predetermined engine health check phase and to isolate a sequence of significant data from the plurality of flight data produced during the at least one engine health check phase, the significant data of a sequence being acquired successively;
- and
- using the controller to calculate for each engine health check phase at least one engine health index as a function of at least one control parameter of the at least one engine from the plurality of physico-chemical parameters,
- wherein the method further comprises:
- generating with the controller, for each engine health index, a point of an at least one-dimensional map, each point associating the engine health index with at least one value of at least one predetermined state parameter from the plurality of physico-chemical parameters, each predetermined state parameter corresponding to a dimension of the map, each value corresponding respectively to a value of the at least one predetermined state parameter at an instant in the sequence of significant data for which the engine health index is calculated;
- grouping together, with the controller, of the points of the map into at least one class of interest, each class of interest corresponding to a group of points spaced apart from each other in the map by a predetermined maximum distance;
- monitoring, with the controller, of the engine health indices corresponding to the points of the at least one class of interest;
- and
- generating, with an alerter, an information signal depending on the engine health indices monitored during the monitoring step;
- wherein the method comprises, for each class, the determination of a barycenter of the points and a weighting operation assigning a weight to each engine health index, the weight depending at least on a distance separating the at least one point from the barycenter, the monitoring of the engine health indices being carried out depending on the weights of each engine health index by producing a weighted curve representative of the engine health indices and the associated weights, the information signal being generated when a slope of the weighted curve passes a predetermined threshold value, when a discontinuity of the weighted curve is identified or when a weighted value of the engine health indices passes another predetermined threshold value.
8 more elements
Dependencies are inferred from the claim text.