Automatic diagnostic method for at least one engine equipping an aircraft, aircraft and arrangement implementing the method
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.
1 . 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.
2 . The method according to claim 1 ,
wherein the method comprises identification, with an identification controller, of the at least one class of interest from at least two distinct classes, the at least one class of interest being identified as a function of at least one identification parameter chosen from the group comprising a frequency of appearance of a point in the at least one class of interest in question and a distribution of the points in the map.
3 . The method according to claim 1 ,
wherein the method comprises predetermining the at least one predetermined state parameter, the predetermination comprising the following sub-steps:
preliminary periodic acquisition, during at least one preliminary flight, of a plurality of preliminary flight data with sensors, the plurality of preliminary flight data being representative of a plurality of physico-chemical parameters;
calculation, with the predetermination controller, of a plurality of preliminary engine health indices as a function of a plurality of values of at least one preliminary control parameter of the at least one engine from the plurality of physico-chemical parameters;
generation, with the predetermination controller, of a database comprising the plurality of values of the at least one preliminary control parameter associated with the corresponding plurality of preliminary engine health indices;
generation, with the predetermination controller, from a correlation between the plurality of preliminary engine health indices and the plurality of values of the at least one preliminary control parameter of the at least one engine contained in the database, of a plurality of linear regression models, each linear regression model being associated with a preliminary control parameter or with a combination of several preliminary control parameters; and
identification, with the predetermination controller, of the predetermined state parameter(s) from the preliminary control parameter or the combination of several preliminary control parameters corresponding to each linear regression model, the identification depending on a goodness of fit of the plurality of linear regression models and a number of control parameters.
4 . The method according to claim 3 ,
wherein the at least one preliminary flight comprises a plurality of flights performed with one or more aircraft.
5 . The method according to claim 1 ,
wherein the monitoring of the engine health indices comprises the calculation of a slope of a curve described by the engine health indices of a given class of interest as a function of time and the comparison of the slope with a predetermined threshold value, the information signal being generated when the slope passes the predetermined threshold value.
6 . The method according to claim 1 ,
wherein the monitoring of the engine health indices comprises the identification of a discontinuity of a curve described by the engine health indices of a given class of interest as a function of time, the information signal being generated when the discontinuity is identified.
7 . The method according to claim 1 ,
wherein the monitoring of the engine health indices comprises the comparison between a value of the engine health indices and another predetermined threshold value, the information signal being generated when the value of the engine health indices passes the other predetermined threshold value.
8 . The method according to claim 1 ,
wherein the monitoring of the engine health indices is carried out periodically with a predetermined period.
9 . The method according to claim 1 ,
wherein the monitoring of the engine health indices is carried out following each calculation of the engine health indices.
10 . The method according to claim 1 ,
wherein the method comprises the storing of the plurality of flight data in a memory installed on board the aircraft during the flight phase of the aircraft.
11 . The method according to claim 1 ,
wherein the method comprises the transmission of the plurality of flight data from the aircraft to at least one ground station.
12 . An aircraft equipped with at least one engine, sensors for acquiring a plurality of flight data, a controller and an alerter,
wherein the sensors, the controller and the alerter of the aircraft are configured to implement the automatic diagnostic method according to claim 1 .
13 . An arrangement comprising at least one ground station and at least one aircraft equipped with at least one engine and sensors for acquiring a plurality of flight data, the at least one ground station comprising a controller and an alerter,
wherein the sensors, the controller and the alerter of the arrangement are configured to implement the automatic diagnostic method according to claim 1 .
14 . 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.
15 . The method according to claim 14 ,
wherein the method comprises identification, with an identification controller, of the at least one class of interest from at least two distinct classes, the at least one class of interest being identified as a function of at least one identification parameter chosen from the group comprising a frequency of appearance of a point in the at least one class of interest in question and a distribution of the points in the map.
16 . The method according to claim 14 ,
wherein the method comprises predetermining the at least one predetermined state parameter, the predetermination comprising the following sub-steps:
preliminary periodic acquisition, during at least one preliminary flight, of a plurality of preliminary flight data with sensors, the plurality of preliminary flight data being representative of a plurality of physico-chemical parameters;
calculation, with the predetermination controller, of a plurality of preliminary engine health indices as a function of a plurality of values of at least one preliminary control parameter of the at least one aircraft engine from the plurality of physico-chemical parameters;
generation, with the predetermination controller, of a database comprising the plurality of values of the at least one preliminary control parameter associated with the corresponding plurality of preliminary engine health indices;
generation, with the predetermination controller, from a correlation between the plurality of preliminary engine health indices and the plurality of values of the at least one preliminary control parameter of the at least one aircraft engine contained in the database, of a plurality of linear regression models, each linear regression model being associated with a preliminary control parameter or with a combination of several preliminary control parameters; and
identification, with the predetermination controller, of the predetermined state parameter(s) from the preliminary control parameter or the combination of several preliminary control parameters corresponding to each linear regression model, the identification depending on a goodness of fit of the plurality of linear regression models and a number of control parameters.
17 . The method according to claim 16 ,
wherein the at least one preliminary flight comprises a plurality of flights performed with one or more aircraft.
18 . The method according to claim 14 ,
wherein the monitoring of the engine health indices comprises the calculation of a slope of a curve described by the engine health indices of a given class of interest as a function of time and the comparison of the slope with a predetermined threshold value, the information signal being generated when the slope passes the predetermined threshold value.
19 . An aircraft equipped with at least one of flight data, engine, sensors for acquiring a plurality a controller and an alerter,
wherein the sensors, the controller and the alerter of the aircraft are configured to implement the automatic diagnostic method according to claim 14 .
20 . An arrangement comprising at least one ground station and at least one aircraft equipped with at least one engine and sensors for acquiring a plurality of flight data, the at least one ground station comprising a controller and an alerter,
wherein the sensors, the controller and the alerter of the arrangement are configured to implement the automatic diagnostic method according to claim 14 .