Abstract: The present invention relates to a fuel metering unit for an aircraft engine, comprising: —a metering member configured to receive a position control signal and to meter the feed of fuel to the engine depending on said position control; —a cutting member configured to cut the feed of fuel to the engine; and characterized in that the fuel metering unit also has a computer for protecting and cutting the engine, said protecting and cutting computer being configured to—detect an overspeeding state of the engine speed and—in response to the detection of an overspeeding state, to transmit a cutting control signal to a cutting control member contained in the cutting member.

Abstract: The present invention relates to a method for controlling an actuator (4) comprising a mobile element (60), the method comprising steps of receiving a set-point signal and two position-measurement signals (A, B) of the mobile element (60) acquired by different position sensors (7), calculating a deviation between the two position-measurement signals (A, B), generating (102) a control signal (S) for controlling a movement of the mobile element (60) on the basis of the set-point signal (E) and at least one of the position-measurement signals (A, B), the method being characterised in that when the deviation between the position-measurement signals (A, B) crosses (201) a predetermined threshold, said method comprises the following steps: setting (202) the control signal (S) to a constant value so as to immobilise the mobile element (60), for each of the two measurement signals (A, B), calculating an interval of positions associated with the measurement signal (A), and detecting an output of the value of a measure

Abstract: The present invention relates to a fuel metering unit for an aircraft engine, comprising: —a metering member configured to receive a position control signal and to meter the feed of fuel to the engine depending on said position control; —a cutting member configured to cut the feed of fuel to the engine; and characterized in that the fuel metering unit also has a computer for protecting and cutting the engine, said protecting and cutting computer being configured to—detect an overspeeding state of the engine speed and—in response to the detection of an overspeeding state, to transmit a cutting control signal to a cutting control member contained in the cutting member.

Abstract: The present invention relates to a method for monitoring the operating state of a turbomachine hydro-mechanical unit (100) of an aircraft comprising: a metering valve (130), comprising a movable metering part (138), a control valve (140), configured to control the flow rate (Q) through the metering valve (130), a flow rate meter (150) able to measure the mass flow rate (Q) of passing fuel, characterized in that a monitoring module (300) is configured for implementing the following steps: (E20?) determining a reconstructed flow rate based on the position of the movable part (138) and on a measurement of the density of the fuel, (E30) calculating a residue, and comparing said residue to a determined threshold value, (E90) determining an abnormal operating state of the hydro-mechanical unit depending on the result of the comparison.

Abstract: The invention relates to a method of monitoring a start-up sequence of a turbomachine that comprises a compressor equipped with a rotor, a starter capable of driving the rotor in rotation and a combustion chamber. The start-up sequence comprises a first phase during which the starter increases the rotation speed of the rotor up to an instant at which fuel is injected into the turbomachine combustion chamber, and a second phase after the first phase that terminates when the starter stops driving the rotor. The method includes: acquisition (ACQ) of a signal representative of the rotation speed of the rotor during the start sequence; detection (DRP1, DRP2, INT) of an instant at which there is a sudden change in the variation of said signal with time, the sudden change instant thus detected being deemed to be the instant at which an air-fuel mix is ignited in the combustion chamber.

Abstract: The present invention relates to a method for controlling an actuator (4) comprising a mobile element (60), the method comprising steps of receiving a set-point signal and two position-measurement signals (A, B) of the mobile element (60) acquired by different position sensors (7), calculating a deviation between the two position-measurement signals (A, B), generating (102) a control signal (S) for controlling a movement of the mobile element (60) on the basis of the set-point signal (E) and at least one of the position-measurement signals (A, B), the method being characterised in that when the deviation between the position-measurement signals (A, B) crosses (201) a predetermined threshold, said method comprises the following steps: setting (202) the control signal (S) to a constant value so as to immobilise the mobile element (60), for each of the two measurement signals (A, B), calculating an interval of positions associated with the measurement signal (A), and detecting an output of the value of a measure

Abstract: The invention relates to a method of monitoring a start-up sequence of a turbomachine that comprises a compressor equipped with a rotor, a starter capable of driving the rotor in rotation and a combustion chamber. The start-up sequence comprises a first phase during which the starter increases the rotation speed of the rotor up to an instant at which fuel is injected into the turbomachine combustion chamber, and a second phase after the first phase that terminates when the starter stops driving the rotor. The method includes: acquisition (ACQ) of a signal representative of the rotation speed of the rotor during the start sequence; detection (DRP1, DRP2, INT) of an instant at which there is a sudden change in the variation of said signal with time, the sudden change instant thus detected being deemed to be the instant at which an air-fuel mix is ignited in the combustion chamber.

Abstract: A method for assisting with the detection of damage to a duct, the duct being designed such as to convey a pressurized air flow collected at the outlet of a high pressure compressor of a turbine engine to a first pressure sensor and a second pressure sensor of a computer, the method including: (A) measuring a first air pressure at the first pressure sensor; (B) measuring a second air pressure at the second pressure sensor; (C) determining a theoretical pressure of the air flow at the outlet of the high-pressure compressor; (D) performing a first test regarding the difference between the first value and the theoretical pressure; (E) performing a second test regarding the difference between the second value and the theoretical pressure; and performing a final test, which is positive if the first difference test and the second difference test are positive, and negative otherwise.

Abstract: A method of determining a duration of a movement of a starter air valve of a turbine engine, the valve for regulating the passage of a flow of pressurized air from upstream to the downstream of pipework, where the downstream side is connected to a pneumatic starter of the turbine engine, the method including determining an instant of initiation and an instant of completion of a movement of the valve during a movement phase of the valve, determining the duration of the movement of the valve, by subtracting the instant of initiation from the instant of completion, calculating a difference between the determined duration of the movement and a theoretical value of the duration.

Abstract: A method for monitoring degradation of an onboard device of an aircraft, implemented by a computer, the degree of degradation of the onboard device being defined by an abnormality score formed by the counting of occurrences of abnormalities noted by a control system of the device, the monitoring method comprising a step of comparing an abnormality score obtained for an observation sequence of given length (n, t) with a decision threshold (ks) and a step of issuing an alarm in the event of the decision threshold (ks) being reached or exceeded, the decision threshold (ks) being determined automatically for a given probability of alarm Pa, corresponding to the probability that an alarm will be issued during the monitoring method whereas the onboard device is sound, by means of the following steps: a step of obtaining an abnormality score (r) on at least one reference sequence corresponding to flights of the aircraft without degradation and with a length (m, tc) equal to a plurality of lengths (n, t) of observ

Abstract: A method for monitoring degradation of an onboard device of an aircraft, implemented by a computer, the degree of degradation of the onboard device being defined by an abnormality score formed by the counting of occurrences of abnormalities noted by a control system of the device, the monitoring method comprising a step of comparing an abnormality score obtained for an observation sequence of given length (n, t) with a decision threshold (ks) and a step of issuing an alarm in the event of the decision threshold (ks) being reached or exceeded, the decision threshold (ks) being determined automatically for a given probability of alarm Pa, corresponding to the probability that an alarm will be issued during the monitoring method whereas the onboard device is sound, by means of the following steps: a step of obtaining an abnormality score (r) on at least one reference sequence corresponding to flights of the aircraft without degradation and with a length (m, tc) equal to a plurality of lengths (n, t) of observ

Abstract: A method for assisting with the detection of damage to a duct, the duct being designed such as to convey a pressurised air flow collected at the outlet of a high pressure compressor of a turbine engine to a first pressure sensor and a second pressure sensor of a computer, the method including: (A) measuring a first air pressure at the first pressure sensor; (B) measuring a second air pressure at the second pressure sensor; (C) determining a theoretical pressure of the air flow at the outlet of the high-pressure compressor; (D) performing a first test regarding the difference between the first value and the theoretical pressure; (E) performing a second test regarding the difference between the second value and the theoretical pressure; and performing a final test, which is positive if the first difference test and the second difference test are positive, and negative otherwise.