Abstract: An aircraft including a fuselage, a lateral support wing (1) and a propulsion assembly (100) mounted under the wing. The wing includes at least two structural spars (11ba, 11bf) extending from the fuselage toward the tip of the wing, one of these (11ba) being upstream and the other (11bf) downstream. The propulsion assembly includes a gas generator (106) and at least two offset fans (102, 104) arranged on either side of the axis of the gas generator. The offset fans (102, 104) are attached directly to one of the spars (11ba, 11bf) and the gas generator (106) is attached directly to the two spars. The leading edge of the wing forms a given sweep of angle (?) with the axis of the fuselage. The two offset fans (102, 104) are axially offset from one another.

Abstract: A turbomachine fuel circuit including: a low pressure pump; a high pressure pump; a low pressure conduit connecting the low pressure pump to the high pressure pump; a high pressure conduit supplied by the high pressure pump, in which a component is arranged; a mechanism for testing operation of the component; a check valve capable of closing off a segment of the conduit when the pressure in the low pressure conduit is less than a predetermined threshold value; and the testing mechanism is capable of detecting that the check valve at least partly closes off the segment.

Abstract: The present invention relates to an aircraft comprising a fuselage, a lateral support wing (1) and propulsion assembly (100) mounted under the wing, the wing comprising at least two structural spars (11ba, 11bf) extending from the fuselage toward the tip of the wing, one of these (11ba) being upstream and the other (11bf) downstream, and the propulsion assembly comprising a gas generator (106) and at least two offset fans (102, 104) arranged on either side of the axis of the gas generator. The aircraft is characterized in that the offset fans (102, 104) are attached directly to one of the said spars (11ba, 11bf) and the gas generator (106) is attached directly to the two spars. In particular, with the leading edge of the wing forming a given sweep of angle (?) with the axis of the fuselage, the two offset fans (102, 104) are axially offset from one another.

Abstract: A fuel feed circuit for an aeroengine, the circuit including a high-pressure pumping system for delivering fuel at high pressure to combustion chamber injectors, the high-pressure pumping system including first and second positive displacement gear pumps driven simultaneously by the engine. A hydraulic switch member is interposed between respective outlets of the pumps, which makes it possible, in one state, to combine outlet flows from the two pumps to deliver fuel at high pressure to the combustion chamber injectors, and in another state, to discharge some or all of outlet flow from the first pump to a low-pressure feed line, an electrical control member serving to cause the hydraulic switch member to pass from one state to the other.

Abstract: The invention proposes a method for determining the capacity of an aircraft pump to deliver a predetermined fuel flow rate, characterised in that it comprises a step of rotating the pump at a predetermined speed; a step of supplying at least one cylinder with the totality of the fuel coming out of the pump; a step of determining the fuel flow rate supplying said cylinder, and a diagnostic step which consists in determining whether the pump is able to supply a sufficient flow rate as a function of the determined value of the flow rate supplying the cylinder. The invention also proposes a device implementing the method.

Abstract: An aircraft electrical supply circuit including: a power distribution network, onboard the aircraft, for electrical devices located in an engine of the aircraft or near the engine; and a power supply generator built into the engine of the aircraft to supply AC voltage power to a deicing or anti-icing system. The power supply generator is connected to a thrust reverser electromechanical actuator by a rectifier for supplying DC voltage power to the actuator.

Abstract: A fuel feed circuit for an aeroengine, the circuit including a high-pressure pumping system including first and second positive displacement pumps, a hydraulic actuator, and a fuel metering unit. As a function of a position of a slide of the actuator, a feed orifice of the actuator may be connected to a high-pressure delivery orifice connected to an outlet of the second pump, or to a low-pressure delivery orifice connected to a low-pressure feed line. The fuel metering unit includes through sections, one of these through sections being connected to an outlet of the high-pressure pumping system and the other through section being connected to an outlet of the high-pressure pumping system and leading to a high-pressure pilot chamber of the hydraulic actuator.

Abstract: A control system for controlling a plurality of distinct functions of a turbojet engine, each function being associated with a respective actuation device. The system includes: an electric motor adapted to supply mechanical energy to each of the actuation devices; an electronic control unit for the electric motor; and at least one switching device interposed between the motor and the actuation devices, the switching device(s) serving to distribute the mechanical energy supplied by the electric motor selectively to one of the actuation devices.

Abstract: A turbomachine fuel circuit including: a low pressure pump; a high pressure pump; a low pressure conduit connecting the low pressure pump to the high pressure pump; a high pressure conduit supplied by the high pressure pump, in which a component is arranged; a mechanism for testing operation of the component; a check valve capable of closing off a segment of the conduit when the pressure in the low pressure conduit is less than a predetermined threshold value; and the testing mechanism is capable of detecting that the check valve at least partly closes off the segment.

Abstract: An aircraft electrical supply circuit including: a power distribution network, onboard the aircraft, for electrical devices located in an engine of the aircraft or near the engine; and a power supply generator built into the engine of the aircraft to supply AC voltage power to a deicing or anti-icing system. The power supply generator is connected to a thrust reverser electromechanical actuator by a rectifier for supplying DC voltage power to the actuator.

Abstract: The invention relates to a device for regulating the flow rate of fuel taken from a fuel circuit of an aircraft propelled by an engine. The device comprises: a positive displacement pump receiving fuel from a fuel circuit of the aircraft and delivering fuel at a flow rate that is proportional to its speed of rotation; a differential gear having a predefined transmission ratio, a first inlet mechanically coupled to the aircraft engine, a second inlet mechanically coupled to an electric motor/generator, and an outlet mechanically coupled to the positive displacement pump to drive it in rotation; and an electronic control system for regulating the speed of rotation of the electric motor/generator as a function of a setpoint value for the flow rate of fuel to be injected.

Abstract: A device monitors an obstruction of two fluid filters of a fluid circulation system of a gas turbine engine of an aircraft. A first obstruction sensor sends a first detection signal of an obstruction of a first filter. A second obstruction sensor sends a second detection signal of an obstruction of a second filter. A processor includes a monitoring input to measure the first and second detection signals. The first obstruction sensor includes a Wheatstone bridge including a strain gauge resistor. The second obstruction sensor is connected in parallel with the strain gauge resistor. The first detection signal is sent over a first predetermined variation range. The second detection signal is sent over a second predetermined variation range, distinct from the first variation range. The processor identifies the obstruction of one of the fluid filters as a function of one of the variation ranges of the detection signals.

Abstract: A fuel feed circuit for an aeroengine, the circuit including a high-pressure pumping system including first and second positive displacement pumps, a hydraulic actuator, and a fuel metering unit. As a function of a position of a slide of the actuator, a feed orifice of the actuator may be connected to a high-pressure delivery orifice connected to an outlet of the second pump, or to a low-pressure delivery orifice connected to a low-pressure feed line. The fuel metering unit includes through sections, one of these through sections being connected to an outlet of the high-pressure pumping system and the other through section being connected to an outlet of the high-pressure pumping system and leading to a high-pressure pilot chamber of the hydraulic actuator.

Abstract: A fuel feed circuit for an aeroengine, the circuit including a high-pressure pumping system for delivering fuel at high pressure to combustion chamber injectors, the high-pressure pumping system including first and second positive displacement gear pumps driven simultaneously by the engine. A hydraulic switch member is interposed between respective outlets of the pumps, which makes it possible, in one state, to combine outlet flows from the two pumps to deliver fuel at high pressure to the combustion chamber injectors, and in another state, to discharge some or all of outlet flow from the first pump to a low-pressure feed line, an electrical control member serving to cause the hydraulic switch member to pass from one state to the other.

Abstract: The method of the invention for monitoring a thrust reverser of a turbojet having an actuator controlled by an electric motor consists in determining a maintenance notice from a weighted combination of provisional notices, each provisional notice relating to a category of parameters associated with at least one phase of an operating cycle of the reverser, the category being selected from a category of parameters representative of a duration of said phase, of an energy seen by the motor during said phase, of a torque seen by the motor at a predefined instant of said phase, and of a duration during which the setpoint speed of rotation and the measured speed of rotation of the motor differ during said phase, each provisional notice being generated by analyzing values obtained during at least one cycle for at least one parameter of said category relative to a degradation threshold.

Abstract: The invention proposes a method for determining the capacity of an aircraft pump to deliver a predetermined fuel flow rate, characterised in that it comprises a step of rotating the pump at a predetermined speed; a step of supplying at least one cylinder with the totality of the fuel coming out of the pump; a step of determining the fuel flow rate supplying said cylinder, and a diagnostic step which consists in determining whether the pump is able to supply a sufficient flow rate as a function of the determined value of the flow rate supplying the cylinder. The invention also proposes a device implementing the method.

Abstract: A device for monitoring the obstruction of at least two fluid filters of a fluid circulation system of a gas turbine engine of an aircraft, the device comprising a first obstruction sensor, intended to monitor a first fluid filter, set up to send a first detection signal of an obstruction of the first filter and a processor comprising a monitoring input linked to said first sensor to measure the first detection signal. The device also comprises a second obstruction sensor, intended to monitor a second fluid filter, set up to send a second detection signal of an obstruction of the second filter, the monitoring input of the processor being connected to the first obstruction sensor to measure said second detection signal over a single monitoring input.

Abstract: A control system for controlling a plurality of distinct functions of a turbojet engine, each function being associated with a respective actuation device. The system includes: an electric motor adapted to supply mechanical energy to each of the actuation devices; an electronic control unit for the electric motor; and at least one switching device interposed between the motor and the actuation devices, the switching device(s) serving to distribute the mechanical energy supplied by the electric motor selectively to one of the actuation devices.

Abstract: The invention relates to a device for regulating the flow rate of fuel taken from a fuel circuit of an aircraft propelled by an engine. The device comprises: a positive displacement pump receiving fuel from a fuel circuit of the aircraft and delivering fuel at a flow rate that is proportional to its speed of rotation; a differential gear having a predefined transmission ratio, a first inlet mechanically coupled to the aircraft engine, a second inlet mechanically coupled to an electric motor/generator, and an outlet mechanically coupled to the positive displacement pump to drive it in rotation; and an electronic control system for regulating the speed of rotation of the electric motor/generator as a function of a setpoint value for the flow rate of fuel to be injected.

Abstract: A method and machine for testing data processing systems wherein the test result is an acceptance or another condition for the central processing unit of the data processing system. For each data processing system having an intended configuration, the method embodies one or more test programs, each program requiring a predetermined configuration of peripheral devices, the execution of a specific test program being started only after the verification of the presence of the required peripheral. In the absence of an intended peripheral, the test machine has means for simulating the presence of said peripheral device. The determination of the peripherals in a configuration and the selection of a test program from a library of such programs may be automatic or may be chosen by operator input.