AIRBUS HELICOPTERS

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.

An aircraft comprising a power plant provided with at least one combustion engine, and with a system for detecting polluting emissions, that comprises: i) at least one engine sensor per combustion engine that emits an engine measurement signal carrying a measured value of an engine parameter of the associated combustion engine; ii) at least one aircraft sensor that emits an aircraft measurement signal carrying a measured value of an aircraft parameter; and iii) a controller determining at least one produced amount of a pollutant emitted during the mission, as a function of the engine measurement signal and the aircraft measurement signal.

The present disclosure relates to a system and a method for assisting the piloting of an aircraft, said method comprising, during a flight phase of said aircraft, at least two steps of measuring at least two current values of at least two respective operating parameters of said aircraft. The method comprises, for each of said at least two operating parameters, the following steps: generating an item of digital data representative of a current value of this operating parameter; identifying a current range within which an index lies, each range from said at least two ranges of indices being associated with a specific display configuration of said item of digital data; and displaying said item of digital data on at least one page of symbologies according to said specific display configuration corresponding to said current range.

A method and a device for detecting a fault in a mechanical system comprising a rotating member and a vibration sensor transmitting a temporal vibration signal. The method comprises processing the temporal vibration signals transmitted over a predetermined period in order to transform the temporal vibration signals firstly into angular vibration signals, then into frequency vibration signals. Next, series of amplitudes are generated, each series being associated with a specific frequency channel and comprising the amplitudes of the frequency vibration signals for this frequency channel. The frequency channels displaying an increasing trend consistent with the fault of interest are then identified. The frequency channels that display an increasing trend are then compared with characteristic frequencies of a known fault of interest in order to check for the possible presence of such a fault in the mechanical system.

The present disclosure relates to a method for detecting a hard landing comprising: i) determining three ground components of a ground reaction force, and determining, for each connector of a landing gear, three attachment components of a force applied to this connector, ii) determining whether a ground stress point defined by the three ground components lies within or outside a ground dimensioning envelope, and, for each connector, whether an attachment stress point defined by the three corresponding attachment components lies within or outside an attachment dimensioning envelope, iii) determining that a hard landing has been made when at least the ground stress point lies outside the ground dimensioning envelope or at least one attachment stress point lies outside the corresponding attachment dimensioning envelope.

A method for monitoring an energy level of an electrical energy source capable of delivering a reference electrical power PRef for a reference time period DTRef for a reference charge level NRef. Said source comprises at least one electrical energy storage device and several sensors. Said method comprises using the sensors to acquire parameters of the electrical energy source, then calculating a main consumption time period DTprin wherein the source is able to supply an electric current carrying the reference electrical power PRef, as a function of the parameters of the source. Next, a main display of main symbols indicating the main consumption time period DTprin is displayed in order to indicate to an operator how long the source can supply the reference electrical power PRef.

A method for monitoring the operation of a power plant of a rotorcraft and a rotorcraft comprising at least one lift rotor rotated by the power plant comprising at least one engine. Such a rotorcraft comprises a monitoring system comprising at least one failure sensor detecting a regulation failure affecting a regulation system of the at least one engine, a speed sensor measuring a current speed of rotation of the at least one lift rotor and a controller determining whether there is a condition of compatibility or a condition of incompatibility between a current flight phase and the speed of rotation.

A method for checking a level of damage of at least one part of an aircraft. According to the disclosure, such a method comprises at least: a collection step for receiving data representative of measurements of at least one flight parameter, the data being generated during a mission of the aircraft by at least one embedded sensor; a projection step for projecting points onto a map in order to form an image point; an identification step for identifying, for each image point, an image zone in which the image point is located; and an analysis step for statistically analyzing the identified image zones and determining the level of damage of the at least one aircraft part.

A method for assisting the piloting of an aircraft comprising a head-up display and an automatic flight control system that comprises a human-machine selection interface for choosing an operating mode from among several predetermined operating modes comprising a disengaged mode and an engaged mode, the automatic flight control system being configured, in the engaged mode, to control at least one actuator in order to bring a current value of a controlled parameter towards a setpoint value. The method comprises: i) detecting, with a control system, an applied current mode from among the several predetermined operating modes; and ii) controlling and displaying, on the head-up display, a symbol carrying the current value according to a graphic charter specific to the current mode, a first graphic charter applied during the disengaged mode being different from a second graphic charter applied during the engaged mode.

A height indicator for an aircraft, the height indicator being provided with a controller controlling a display means to display a height scale and a pointer. The height scale is able to move in relation to the pointer along an axis on the display means, the height scale being a piecewise linear scale comprising several graduated sections, each graduated section having its own linear scale, each graduated section having a scale factor different from a scale factor of another graduated section, each scale factor representing the quotient between a distance on the graduated section along axis and a corresponding actual height.