Abstract: A method and a device for automatically detecting an incorrect measurement of a total temperature on an aircraft. The detection device comprises several monitoring units configured to monitor the variations of the measured total temperature, provided by a temperature probe, and current values of the Mach number and of the altitude of the aircraft over a predetermined monitoring period of time, and a detection unit configured to detect an incorrect measurement of the total temperature when said monitoring units simultaneously detect particular conditions relative to said variations.

Abstract: A method for detecting erroneous air data on an aircraft includes determining a current air parameter and a current altitude pressure parameter which collectively define a current point of control for the aircraft. The method also includes verifying whether the current point of control is situated in a characteristic envelope indicating operating limits for the aircraft. When the current point of control is outside the characteristic envelope, then a detection piece of information identifying at least one of the parameters as an erroneous parameter is emitted, which causes that erroneous parameter to be invalidated and an alarm signal to be sent to the crew. Therefore, an erroneous air data parameter is readily addressed and discarded using the method and associated device.

Abstract: An aircraft is equipped with engines, each engine having at least one pod and one compressor/turbine hitch. The aircraft has at least one data processing unit and at least one system at the engine level. At least one engine is equipped with at least one static pressure probe for measuring the ambient air under the pod. Also, air static pressure probes are arranged at the engine levels, with one pressure probe at the output of the compressor, at least one rotation speed sensor, for example of a blower, and ambient air temperature probes at the air input or in any compression point. The processing unit is able, from measurements performed by such probes at the engine level, to supply to at least one of the systems at the engine level, determination data for the air speed of the aircraft.

Abstract: A method and a device for automatically detecting an incorrect measurement of a total temperature on an aircraft. The detection device comprises several monitoring units configured to monitor the variations of the measured total temperature, provided by a temperature probe, and current values of the Mach number and of the altitude of the aircraft over a predetermined monitoring period of time, and a detection unit configured to detect an incorrect measurement of the total temperature when said monitoring units simultaneously detect particular conditions relative to said variations.

Abstract: An electronic circuit, and a system including such a circuit, for determining a datum representative of a parameter of air surrounding an aircraft, including: a mechanism receiving, from a plurality of sources, a plurality of respective measurement data representative of a measured value of the parameter; a mechanism determining the datum representative of the parameter based on the measurement data; and a mechanism transmitting the datum representative of the parameter to a computer associated with an aircraft engine.

Abstract: A system and method for selecting a datum representative of an air parameter, including a plurality of sources each capable of delivering a datum representative of a measured value of the parameter. The system includes: a mechanism for determining, for at least some sources, a number of other sources from the plurality of sources in agreement with a source in question; and a mechanism for selecting the datum selected from the data delivered by the sources for which the determined agreement number is the maximum. An engine control system, or an aircraft can include such a system or implement such a method.

Abstract: A device for a motorized aircraft includes at least one avionic component positioned in the aircraft, at least one engine interface positioned in the aircraft and at least one engine controller positioned in or near an engine of the aircraft. The at least one engine interface is designed to exchange data between the at least one avionic component and the at least one engine controller. The at least one engine interface is generic and able to communicate with engine controllers of various types that may be mounted on the aircraft. The at least one engine controller is specific to a particular engine.

Abstract: A device for electrical distribution in an ignition system of an engine of an aircraft provided with a primary electrical supply and a secondary electrical supply, a primary igniter, and a secondary igniter, is provided with an electrical supply system adapted to supply at least one of the igniters alternately via one or the other of the electrical supplies. The electrical supply system is provided with a switch adapted to supply one of the igniters to which it is connected via one or the other of the electrical supplies. A detecting means detects if the igniter that is connected to the switch is also connected to the other electrical supply. The switch may have a relay supplied via one of the electrical supplies so that, in the event of defect of this supply, the igniter to which the switch is connected will be connected to the other electrical supply.

Abstract: An aircraft is equipped with engines, each engine having at least one pod and one compressor/turbine hitch. The aircraft has at least one data processing unit and at least one system at the engine level. At least one engine is equipped with at least one static pressure probe for measuring the ambient air under the pod. Also, air static pressure probes are arranged at the engine levels, with one pressure probe at the output of the compressor, at least one rotation speed sensor, for example of a blower, and ambient air temperature probes at the air input or in any compression point. The processing unit is able, from measurements performed by such probes at the engine level, to supply to at least one of the systems at the engine level, determination data for the air speed of the aircraft.

Abstract: The device (1) comprises means (2) for checking that a couple of parameters, namely a current air parameter and a current altitude pressure parameter, is situated in a characteristic envelope indicating operating limits for the aircraft.

Abstract: A system for selecting a datum among a set of data representing an air parameter, this set comprising at least two engine data obtained by measurement respectively in the zone of two engines of an aircraft and at least two reference data obtained by measurement in the zone of the fuselage of the aircraft, the system comprising: means for verifying pairwise agreement of three data of the set of data; means for selecting a reference datum among the said three data if such agreement is verified. A process and a computer program relating thereto are also proposed.

Abstract: A system and method for selecting a datum representative of an air parameter, including a plurality of sources each capable of delivering a datum representative of a measured value of the parameter. The system includes: a mechanism for determining, for at least some sources, a number of other sources from the plurality of sources in agreement with a source in question; and a mechanism for selecting the datum selected from the data delivered by the sources for which the determined agreement number is the maximum. An engine control system, or an aircraft can include such a system or implement such a method.

Abstract: An electronic circuit, and a system including such a circuit, for determining a datum representative of a parameter of air surrounding an aircraft, including: a mechanism receiving, from a plurality of sources, a plurality of respective measurement data representative of a measured value of the parameter; a mechanism determining the datum representative of the parameter based on the measurement data; and a mechanism transmitting the datum representative of the parameter to a computer associated with an aircraft engine.

Abstract: The device for electrical distribution in an ignition system of an engine (100) of an aircraft provided with a primary electrical supply (105) and a secondary electrical supply (115), a primary igniter (110) and a secondary igniter (120) is provided with an electrical supply system (205, 225) adapted to supply at least one of the said igniters alternately via one or the other of the said electrical supplies. The electrical supply system is provided with a switch (205) adapted to supply the igniter to which it is connected via one or the other of the electrical supplies, and to simulate a defect of the electrical supply of these supplies. A detecting means makes it possible to detect if the igniter that is connected on the one hand to the switch is connected on the other hand to the other electrical supply.

Abstract: The invention relates to a device for motorized aircraft comprising at least one avionic component (300) positioned in the said aircraft, at least one engine interface (310) positioned in the said aircraft and at least one engine controller (315) positioned in or near an engine (320) of the said aircraft. According to the device of the invention, the said at least one engine interface (310) is designed to exchange data between the said at least one avionic component (300) and the said at least one engine controller (315). The said at least one engine interface (310) is generic and able to communicate with engine controllers (315) of various types that may be mounted on said aircraft. The said at least one engine controller is specific to a particular engine.

Abstract: A system for selecting a datum among a set of data representing an air parameter, this set comprising at least two engine data obtained by measurement respectively in the zone of two engines of an aircraft and at least two reference data obtained by measurement in the zone of the fuselage of the aircraft, the system comprising: means for verifying pairwise agreement of three data of the set of data; means for selecting a reference datum among the said three data if such agreement is verified. A process and a computer program relating thereto are also proposed.