Abstract: An electrical supply system (10) with first and second electrical sourced (S1, S2), coupled together to electrically supply electrical loads (Z1, Z2, Z3 . . . Zn) of an aircraft. The first electrical source (S1) is mechanically coupled to a primary energy source (12), to which at least one other energy consumer (16) is coupled. A controller (30) controls the first and second electrical sources (S1, S2) so that the power drawn by the first electrical source from the primary energy source (12) corresponds to a difference between an instantaneous nominal power capable of being delivered by the primary energy source and an instantaneous power drawn by the energy consumer (16), and an electrical power delivered by the second electrical source is a sum of an electrical power delivered by the first and second electrical sources which corresponds to an instantaneous electrical consumption of the electrical loads.

Abstract: An electric power supply system for an aircraft includes: a first electric source and a second electric source coupled together to supply electric power to a set of electrical loads, and a controller configured to acquire a piece of information on the current electric consumption consumed by the set of electrical loads; acquire a piece of information corresponding to a target ratio of the distribution, between the first and second electric sources, of the current electric consumption consumed by the set of electrical loads; perform frequency filtering of the current electric consumption to determine a transient consumption portion of the current electric consumption; determine control setpoints for the first electric source and for the second electric source in accordance with the target distribution ratio and with the transient consumption portion; and apply the control setpoints to the first and second electric sources.

Abstract: A data analysis system comprises an artificial intelligence of the machine learning type. The data analysis system collects reference data relating to measurements made and recorded during previous flights of aircraft. A training of the artificial intelligence of the machine learning type is implemented by virtue of reference data, with a first classification run for training to detect potential malfunctions suffered by integrated drive generators and a second classification run for training to determine causes of the malfunctions, where relevant. After using in production, the data analysis system collects data to be analyzed relating to measurements made and recorded during flights of the aircraft comprising an integrated drive generator to be monitored, and uses the artificial intelligence of the machine learning type to predict a potential malfunction and, where relevant, predict its cause using data to be analyzed.

Abstract: In an aircraft, a fuel return valve (FRV) controls a flow of fuel, used to cool an oil feeding a propulsion engine and an oil of an integrated drive generator (IDG). A first sensor supplies measurements of the oil temperature at an output port of the IDG and a second sensor supplies measurements of oil temperature of the propulsion engine. An FRV operation monitoring system: determines, for each flight of the aircraft, an oil temperature maximum at an output port of the IDG and/or a maximum oil temperature of the propulsion engine; assesses a trend of one and/or the other of the oil temperature maxima over several flights; and generates an alarm when the trend of one and/or the other of the oil temperature maxima shows that a predetermined threshold has been exceeded.

Abstract: An electrical supply system (10) with first and second electrical sourced (S1, S2), coupled together to electrically supply electrical loads (Z1, Z2, Z3 . . . Zn) of an aircraft. The first electrical source (S1) is mechanically coupled to a primary energy source (12), to which at least one other energy consumer (16) is coupled. A controller (30) controls the first and second electrical sources (S1, S2) so that the power drawn by the first electrical source from the primary energy source (12) corresponds to a difference between an instantaneous nominal power capable of being delivered by the primary energy source and an instantaneous power drawn by the energy consumer (16), and an electrical power delivered by the second electrical source is a sum of an electrical power delivered by the first and second electrical sources which corresponds to an instantaneous electrical consumption of the electrical loads.

Abstract: An electric power supply system for an aircraft includes: a first electric source and a second electric source coupled together to supply electric power to a set of electrical loads, and a controller configured to acquire a piece of information on the current electric consumption consumed by the set of electrical loads; acquire a piece of information corresponding to a target ratio of the distribution, between the first and second electric sources, of the current electric consumption consumed by the set of electrical loads; perform frequency filtering of the current electric consumption to determine a transient consumption portion of the current electric consumption; determine control setpoints for the first electric source and for the second electric source in accordance with the target distribution ratio and with the transient consumption portion; and apply the control setpoints to the first and second electric sources.

Abstract: The invention relates to an aircraft steering system using an aircraft ground taxi drive system whereby electrical power generated by a first motor-generator of a landing gear wheel drive system in a regenerative braking mode is supplied to a second motor-generator of a landing gear wheel drive system in a motorized driving mode.

Abstract: A taxiing system for an aircraft including an undercarriage having a wheel, includes an electric motor associated with the wheel, an electric controller of the electric motor, connected to an output of an electrical power supply, and a taxiing control computer configured to determine control instructions for the electric motor and to transmit these instructions to the electric controller. The taxiing control computer is configured to receive braking of the aircraft commands during the taxiing of the aircraft and to determine control instructions for the electric motor corresponding to operation of the motor in generator mode when it receives a braking command. The electric controller is connected to an energy absorber making it possible to absorb the electric energy produced by the electric motor when the latter is operating in generator mode.

Abstract: The invention relates to an aircraft steering system using an aircraft ground taxi drive system whereby electrical power generated by a first motor-generator of a landing gear wheel drive system in a regenerative braking mode is supplied to a second motor-generator of a landing gear wheel drive system in a motorized driving mode.

Abstract: A taxiing system for an aircraft including an undercarriage having a wheel, includes an electric motor associated with the wheel, an electric controller of the electric motor, connected to an output of an electrical power supply, and a taxiing control computer configured to determine control instructions for the electric motor and to transmit these instructions to the electric controller. The taxiing control computer is configured to receive braking of the aircraft commands during the taxiing of the aircraft and to determine control instructions for the electric motor corresponding to operation of the motor in generator mode when it receives a braking command. The electric controller is connected to an energy absorber making it possible to absorb the electric energy produced by the electric motor when the latter is operating in generator mode.