Abstract: A flight control system of an aircraft including a first processing unit, a second processing unit, communication means configured to establish a first two-way digital link and as second two-way digital link between the first processing unit and the second processing unit. The second link is redundant with the first link, and the first link and second link are likely to be active concomitantly. The system further includes backup communication means enabling data exchanges between the first processing unit and the second processing unit in the case of a failure in the first link and second link. The backup communication means includes an array of sensors or actuators and/or a secure onboard network for the avionics.

Abstract: A device for integrity testing a system for rapid reactivation of a turboshaft engine of a helicopter, includes a pneumatic turbine that is mechanically connected to the turboshaft engine and is supplied with gas, upon a command, by a pneumatic supply circuit such that it is possible to rotate the turboshaft engine and ensure that it is reactivated. The testing device has an apparatus configured to withdraw pressurized air from the turboshaft engine and a duct for conveying the withdrawn air to the pneumatic circuit for supplying the pneumatic turbine with gas. The device further includes a sensor for determining the rotational speed of the pneumatic turbine.

Abstract: The invention relates to an overspeed protection device of an aircraft engine.

Abstract: A turbine engine includes a compressor, a combustion chamber, first and second turbines downstream from the combustion chamber, a first rotary shaft constrained to rotate at least with the compressor and the first turbine, a second rotary shaft constrained to rotate with the second turbine, the second rotary shaft nevertheless being free to rotate relative to the first rotary shaft, and a regulator for controlling the feed of fuel to the combustion chamber. The regulator cuts off the feed of fuel to the combustion chamber if the speed of rotation of the second rotary shaft exceeds a maximum threshold that varies as a function of at least one indicative physical parameter associated with mechanical power being extracted from the combustion gas by the second turbine. A method of regulating the turbine engine is also presented.

Abstract: The present invention concerns a method for switching, by a local processing unit (1,2) of a flight control system of an aircraft, configured to control at least one local actuator, connected to at least one local sensor and connected via at least one link (3,4) to an opposite processing unit (2,1) configured to control at least one opposite actuator and be connected to at least one opposite sensor, said local processing unit (1,2) being further configured to be connected to backup communication means (13,14) enabling data exchanges between the local processing unit (1,2) and the opposite processing unit (2,1) in the case of failures of the links connecting same (3,4), said backup communication means comprising an array of sensors or actuators (13) and/or a secure onboard network for the avionics (14), comprising steps of: •—sending, to the opposite processing unit (2,1), acquisition data relative to the at least one local sensor and actuator data relative to the at least one local actuator, •—receiving, from

Abstract: The present invention concerns a method for switching, by a local processing unit (1,2) of a flight control system of an aircraft, configured to control at least one local actuator, connected to at least one local sensor and connected via at least one link (3,4) to an opposite processing unit (2,1) configured to control at least one opposite actuator and be connected to at least one opposite sensor, said local processing unit (1,2) being further configured to be connected to backup communication means (13,14) enabling data exchanges between the local processing unit (1,2) and the opposite processing unit (2,1) in the case of failures of the links connecting same (3,4), said backup communication means comprising an array of sensors or actuators (13) and/or a secure onboard network for the avionics (14), comprising steps of: •—sending, to the opposite processing unit (2,1), acquisition data relative to the at least one local sensor and actuator data relative to the at least one local actuator, •—receiving, from

Abstract: The present invention concerns a flight control system of an aircraft comprising: —a first processing unit (1), —a second processing unit (2), —communication means configured to establish a first two-way digital link (3) and a second two-way digital link (4) between the first processing unit (1) and the second processing unit (2), said second link (4) being redundant with the first link (3), and said first link (3) and second link (4) being likely to be active concomitantly, said system further comprising backup communication means enabling data exchanges between the first processing unit (1) and the second processing unit (2) in the case of a failure in the first link (3) and second link (4), said backup communication means comprising an array of sensors or actuators (13) and/or a secure onboard network for the avionics (14).

Abstract: A device for integrity testing a system for rapid reactivation of a turboshaft engine of a helicopter includes a pneumatic turbine that is mechanically connected to said turboshaft engine and is supplied with gas, upon a command, by a pneumatic supply circuit such that it is possible to rotate the turboshaft engine and ensure that it is reactivated. The testing device has an apparatus configured to withdraw pressurised air from the turboshaft engine; a duct for conveying the withdrawn air to the pneumatic circuit for supplying the pneumatic turbine with gas The device further includes a sensor for determining the rotational speed of the pneumatic turbine.

Abstract: The invention relates to an overspeed protection device of an aircraft engine

Abstract: A turbine engine includes a compressor, a combustion chamber, first and second turbines downstream from the combustion chamber, a first rotary shaft constrained to rotate at least with the compressor and the first turbine, a second rotary shaft constrained to rotate with the second turbine, the second rotary shaft nevertheless being free to rotate relative to the first rotary shaft, and a regulator for controlling the feed of fuel to the combustion chamber. The regulator cuts off the feed of fuel to the combustion chamber if the speed of rotation of the second rotary shaft exceeds a maximum threshold that varies as a function of at least one indicative physical parameter associated with mechanical power being extracted from the combustion gas by the second turbine. A method of regulating the turbine engine is also presented.

Abstract: A metering device for an engine fuel feed circuit, the device including a metering valve, and a pressure regulator device maintaining a constant pressure difference from downstream to upstream across the metering valve, wherein the metering valve includes a seat provided with an inlet orifice and an outlet orifice, a shutter arranged within the seat, and an actuator controlling the position of the shutter, and wherein, between the inlet orifice and the outlet orifice the shutter defines a passage of minimum section that is variable as a function of the position of the shutter along a stroke extending between a bottom abutment and a top abutment and passing via a threshold position.

Abstract: A method improving acceleration efficiency of a gas generator of a gas turbine by reducing take-up of electric power, during transition phases, to conserve a sufficiently large surge margin for an operating line. The method increases acceleration/deceleration power of the gas generator by adjusting voltage of an electric network onboard the aircraft. After a phase of starting the gas turbine, voltage of the onboard network is adjusted by a voltage set value controlled by determining unballasting/ballasting status of a main electricity generation source of the onboard network. The status-determining is executed according to demand for taking power to be supplied for propulsion of the aircraft. The status-determining is followed by selecting a voltage set value from plural levels according to the determining the unballasting/ballasting status, and applying the selected set value to a control loop of the voltage supplied to the onboard network.

Abstract: A method improving acceleration efficiency of a gas generator of a gas turbine by reducing take-up of electric power, during transition phases, to conserve a sufficiently large surge margin for an operating line. The method increases acceleration/deceleration power of the gas generator by adjusting voltage of an electric network onboard the aircraft. After a phase of starting the gas turbine, voltage of the onboard network is adjusted by a voltage set value controlled by determining unballasting/ballasting status of a main electricity generation source of the onboard network. The status-determining is executed according to demand for taking power to be supplied for propulsion of the aircraft. The status-determining is followed by selecting a voltage set value from plural levels according to the determining the unballasting/ballasting status, and applying the selected set value to a control loop of the voltage supplied to the onboard network.

Abstract: A method of identifying a micro-organism and determining the susceptibility of the micro-organism to an antimicrobial agent by inserting a sample of the micro-organism in a primary culture container and allowing the micro-organism to multiply. The primary culture is then divided into a plurality of secondary cultures and the metabolic volatile or semi-volatile compounds (VCs) in the headspace above the cultures are analysed by SIFT-MS to ascertain whether micro-organisms exist in the culture and determine the type of micro-organism. The secondary cultures are then divided into a number of tertiary cultures and an antimicrobial agent is introduced whereupon the VCs in the headspace above the tertiary cultures are analysed by SIFT-MS to determine the susceptibility of the micro-organism to the antimicrobial agent at various concentrations of the antimicrobial agent.

Abstract: The present invention relates to apparatus for reading and writing data to a storage medium, wherein the data is written to the medium in tracks, each track having a predetermined trigger signal pattern, the apparatus comprising: structure for detecting the predetermined trigger signal pattern; an adaptive filter for signals read from the medium; and structure for triggering adaptive filtering for a track of data on detection of the predetermined trigger signal pattern in that track. In this way, during a read operation adaptive filtering is triggered on commencement of data with spectral characteristics suitable for adaption of the filter. In the embodiment to be described, each track comprises data fragments each having a header containing ancillary information wherein at least a header in an initial data fragment in the track comprises the predetermined trigger signal pattern. Preferably, at least the header of the initial data fragment in the track comprises the predetermined trigger signal pattern.