A method for identifying aircraft faults, comprising: receiving a dataset comprising a plurality of low priority messages and a plurality of high priority messages, each low priority message identifying a minor aircraft fault and each high priority message identifying a major aircraft fault; for each low priority message, generating an embedding vector which maps the low priority message in an embedding space; for each high priority message, generating an embedding vector which maps the high priority message in the embedding space; providing, to a machine learning unit, the embedding vector for each low priority message of the plurality of low priority messages and the embedding vector for each high priority message of the plurality of high priority messages; and obtaining, from the machine learning unit, a probability of a target high priority message occurring based on each low priority message of the plurality of low priority messages.

Flight guidance systems and methods that provide an airport selection in response to an EO condition in a single engine plane. The airport selection takes into consideration factors such as optimal approach type, runway length, weather, terrain, remaining battery time, and the like. Additionally, various also generate and display a visual indication of a remaining glide range when the EO condition is happening; the remaining glide range determination is based, at least in part, on terrain.

An example method includes receiving, by one or more processors and via a sensor, a signal representing operational characteristics of a device included in an aircraft; determining, by the one or more processors and based on the signal, a partial discharge intensity value; receiving, by the one or more processors and via an environmental sensor, at least one environmental measurement of the device; modifying, by the one or more processors and based on the at least one environmental measurement, the partial discharge intensity value to determine a modified partial discharge intensity value; and responsive to determining that the modified partial discharge intensity value satisfies a threshold, outputting an alert signal for the device.

A device for monitoring a state of a propulsion engine includes an acquisition module that acquires data of flights of the propulsion engine, comprising, for each flight, values of input variables, environment variables, and output variables of the propulsion engine during the flight, a learning module that computes, by learning from the data of each flight, an individual flight model for the flight, a using module that computes, for each flight, estimates of the values of the output variables, by applying the individual flight model to reference values of the input variables and the environment variables, and an error associated with the estimates of the values of the output variables that is obtained by applying the individual flight model to the reference values of the input variables and the environment variables. The reference values belong to a set of reference data, which are identical for the individual flight models.

The invention relates to a device for connecting parts of an aircraft engine. The connection device comprises connectors suitable for connecting a first and a second part so as to establish a physical transfer link between these parts and means which enable it to monitor the state of the connection in particular by means of an impedance measurement carried out in a circuit formed by components integrated into said connectors.

Techniques for employing a smart sensor device (102) that has a primary sensing function for sensing a state of a physical component and can concurrently enable one or more backup functions for sensing one or more states of one or more other physicals components in response to one or more other smart sensor devices (102 and/or 116) not being able to perform their primary function of sensing and/or reporting on the one or more states of the one or more other physical components.

A method for detecting wear before failure of a free-wheel, the free-wheel comprising a driving part integrated into an upstream mechanical power transmission system and a driven part integrated into a downstream mechanical power transmission system. The method comprises determining an oscillation measurement of a monitoring parameter within the upstream or downstream mechanical power transmission system, determining a value of at least one dynamic parameter characteristic of the oscillation measurement or of a transform of the oscillation measurement in a frequency reference frame, and generating an alarm when the value of the dynamic parameter reaches at least one wear threshold.

A method of inspecting an air data probe for damage or misalignment on a mounting surface includes retrieving reference data for the air data probe from a database, capturing images of the air data probe via a camera and generating dimensions from the captured images of the air data probe via a feature extractor. An alignment calculator analyzes the generated dimensions from the captured images of the air data probe and the reference data for the air data probe from the database to identify misalignment of the air data probe, and analyzes the generated dimensions from the captured images of the air data probe and the reference data for the air data probe from the database to identify damage of the air data probe. A maintenance recommendation for the air data probe is generated and outputted, based on the identified misalignment or damage of the air data probe.

A method for brake health monitoring may include sending, by a brake control unit (BCU), a brake command signal to initiate a braking maneuver, and receiving a first wheel speed signal and a second wheel speed signal corresponding to the speed of first and second wheels, respectively, during the braking maneuver. The BCU may detect that the speed of the first wheel is greater than the speed of the second wheel by a predetermined threshold, and, in response thereto, post an alert indicating a failure in a brake control component associated with the first wheel based upon the detection of the speed of the first wheel being greater than the speed of the second wheel by the predetermined threshold.

A method, system, and device for predicting parachuting time in case of a sudden failure are provided to resolve a prior art problem that parachuting time of a parachutist in case of a sudden failure of an aircraft cannot be predicted accurately and efficiently. The method includes: obtaining input data; preprocessing the input data; determining whether an aircraft is in a sudden failure state; generating a movement track and a landing point range of parachuting; calculating a movement track and a falling point range of the aircraft after a parachutist performs parachuting, and impact force and a damage range after the aircraft falls; and obtaining a prediction result of parachuting time of the parachutist by a pre-constructed parachuting time prediction model. The method, system, and device can accurately and efficiently predict the parachuting time of the parachutist in case of the sudden failure of the aircraft.