Abstract: A power supply has first and second ac voltage generators. Both of the first and second ac voltage generators are connected to one or more loads and a respective 6-pulse rectifier unit for rectifying ac voltage from each of the first and second power generators to a dc voltage output for the loads, Both of the first and second ac voltage generators includes two 3-phase voltage sources separated by a phase shift. The voltage output from each rectifier unit is coupled to the loads via a respective interphase inductor.

Abstract: A power supply has first and second ac voltage generators. Both of the first and second ac voltage generators are connected to one or more loads and a respective 6-pulse rectifier unit for rectifying ac voltage from each of the first and second power generators to a dc voltage output for the loads, Both of the first and second ac voltage generators includes two 3-phase voltage sources separated by a phase shift. The voltage output from each rectifier unit is coupled to the loads via a respective interphase inductor.

Abstract: Apparatus for controlling the excitation current of a variable frequency generator (VFG) including means to create a voltage-regulated DC link using PMG power and frequency information, the latter being the image of the VFG mechanical input speed. A step-down voltage-controlled chopper is inserted between the passive rectifier stage and the excitation current control chopper. The control law of this voltage-controlled source is such that when the mechanical input speed of the VFG increases, its output (controlled DC-link voltage) decreases non-linearly, leading to DC link voltage varying from V (engine at idle) to V/2 (engine at take-off speed). The DC voltage becomes inverse-proportional to input mechanical speed.

Abstract: The invention concerns an aircraft comprising a reversible rotary electrical machine 30), a wheel (35) for imparting movement to a stream of air, linked to said machine (30), a first ventilation duct (10, 15) configured to supply said wheel (35) with air, an electricity distribution network (70), a reversible power converter (40) connected to said machine (30) and to said network (70), and a control circuit (50) configured to control said converter (40) for, in a motor operating mode of said machine (30), taking a supply current from said network (70) to supply said machine (30) and drive said wheel (35), and, in an alternator operating mode of said machine (30), in which a stream of air flows in said first ventilation duct (15) and imparts movement to said wheel (35), to provide supply power to said network (70) which is generated by said machine (30) driven by said wheel (35).

Abstract: Apparatus for controlling the excitation current of a variable frequency generator (VFG) including means to create a voltage-regulated DC link using PMG power and frequency information, the latter being the image of the VFG mechanical input speed. A step-down voltage-controlled chopper is inserted between the passive rectifier stage and the excitation current control chopper. The control law of this voltage-controlled source is such that when the mechanical input speed of the VFG increases, its output (controlled DC-link voltage) decreases non-linearly, leading to DC link voltage varying from V (engine at idle) to V/2 (engine at take-off speed). The DC voltage becomes inverse-proportional to input mechanical speed.

Abstract: Power takeoff means (46, 47, 60, 61) for this flight control system adjacent to the aircraft engines (41, 42) are all-electric and this makes it possible to reduce the length of hydraulic connections leading to actuators of the controlled devices (54, 55, 66). Electrical generators are of different types to minimize the risk of a generic failure. Characteristically of the invention, some generators (60, 61) have a constant voltage to frequency ratio and directly or almost directly control electro-hydraulic pumps (64, 65), without modifying the current characteristic and with no power electronics. Furthermore, system reconfigurations are made possible by additional electrical connections (69, 70, 71, 72) in case of failure.

Abstract: A device and a method for supplying electrical power to at least one induction machine on board an aircraft. This device includes at least one CVFR type source, in which the voltage and frequency are both variable but in a constant ratio, that supplies power to at least one induction machine.

Abstract: The invention concerns an aircraft comprising a reversible rotary electrical machine 30), a wheel (35) for imparting movement to a stream of air, linked to said machine (30), a first ventilation duct (10, 15) configured to supply said wheel (35) with air, an electricity distribution network (70), a reversible power converter (40) connected to said machine (30) and to said network (70), and a control circuit (50) configured to control said converter (40) for, in a motor operating mode of said machine (30), taking a supply current from said network (70) to supply said machine (30) and drive said wheel (35), and, in an alternator operating mode of said machine (30), in which a stream of air flows in said first ventilation duct (15) and imparts movement to said wheel (35), to provide supply power to said network (70) which is generated by said machine (30) driven by said wheel (35).

Abstract: A system for electrical generation, conversion, distribution and starting on board an aircraft, of “bleedless” type, that is, with an electrical power architecture with no pneumatic circuits. The electrical distribution channels for high power loads specific to aircraft of “bleedless” type, and the electrical distribution channels for conventional loads, including technical loads, such as avionics, lighting, fuel pumps and commercial loads are separated, and are supplied with power by separate generators driven by the aircraft's engines.

Abstract: A system for electrical generation, conversion, distribution and starting on board an aircraft, of “bleedless” type, that is, with an electrical power architecture with no pneumatic circuits. The electrical distribution channels for high power loads specific to aircraft of “bleedless” type, and the electrical distribution channels for conventional loads, including technical loads, such as avionics, lighting, fuel pumps and commercial loads are separated, and are supplied with power by separate generators driven by the aircraft's engines.

Abstract: The invention relates to a system and a process for direct current power supply of electrical networks. This system comprises a system for direct current power supply of electrical networks comprising at least two generators (G1, G2), an alternating current power distribution bar (11), a direct current power distribution bar (10), wherein these two power distribution bars (11, 10) are connected to one another by a rectifier unit (12) and a battery (13). The alternating current bar (11) is connected to the generators (G1, G2) via a transfer contactor (20). The direct current power distribution bar (10) is connected to the battery (13) via a first contactor (S1) in series with a second contactor (S2) positioned in parallel with a power diode (21).

Abstract: Power takeoff means (46, 47, 60, 61) for this flight control system adjacent to the aircraft engines (41, 42) are all-electric and this makes it possible to reduce the length of hydraulic connections leading to actuators of the controlled devices (54, 55, 66). Electrical generators are of different types to minimise the risk of a generic failure. Characteristically of the invention, some generators (60, 61) have a constant voltage to frequency ratio and directly or almost directly control electro-hydraulic pumps (64, 65), without modifying the current characteristic and with no power electronics. Furthermore, system reconfigurations are made possible by additional electrical connections (69, 70, 71, 72) in case of failure.

Abstract: A device and a method for supplying electrical power to at least one induction machine on board an aircraft. This device includes at least one CVFR type source, in which the voltage and frequency are both variable but in a constant ratio, that supplies power to at least one induction machine.

Abstract: This invention relates to a device for supplying electrical power to an aircraft and for electrically starting a jet engine on board an aircraft, including a multi-phased starter-generator, a multi-phased transformer-rectifier unit, a multi-phased DC-AC converter, a multi-phased rectifier unit, and at least one three-phase inverter, wherein the number of phases is equal to or greater than 5.

Abstract: This invention relates to a device for supplying electrical power to an aircraft and for electrically starting a jet engine on board an aircraft, including a multi-phased starter-generator, a multi-phased transformer-rectifier unit, a multi-phased DC-AC converter, a multi-phased rectifier unit, and at least one three-phase inverter, wherein the number of phases is equal to or greater than 5.

Abstract: The invention relates to a system and a process for direct current power supply of electrical networks. This system comprises a system for direct current power supply of electrical networks comprising at least two generators (G1, G2), an alternating current power distribution bar (11), a direct current power distribution bar (10), wherein these two power distribution bars (11, 10) are connected to one another by a rectifier unit (12) and a battery (13). The alternating current bar (11) is connected to the generators (G1, G2) via a transfer contactor (20). The direct current power distribution bar (10) is connected to the battery (13) via a first contactor (S1) in series with a second contactor (S2) positioned in parallel with a power diode (21).

Abstract: A magnetic field generated by a primary winding (1) in which the current (i1) to be measured flows is balanced by a magnetic field of opposing direction generated by a secondary winding (2) in which a compensating current (i2) flows. The device includes a member (3) sensitive to the field resulting from the addition of the magnetic fields of opposing directions to regulate the compensating current (i2) in closed loop mode. According to the invention, the, sensitive member (3) is sensitive only to the direction of the resultant field and, in return, controls the reversal of the direction of circulation of the compensating current (i2) in the secondary winding (2). This sensitive member (3) can be formed by a Hall effect probe with bipolar output signal. The device is suitable for the measurement of a current inautomotive electronics.

Abstract: A fixed frequency electrical generation system includes an induction coupler. The system includes an electricity generator with no rings or brushes, and an induction speed regulator, mechanically coupled, so as to transform mechanical energy input from a shaft rotating at a variable speed into output electricity in the form of at least one alternating voltage with a constant rms value and constant frequency.

Abstract: The invention relates to a fixed frequency electrical generation system with an induction coupler comprising: an electricity generator with no rings or brushes, an induction speed regulator, mechanically coupled, so as to transform mechanical energy input from a first shaft rotating at a variable speed into output electricity in the form of at least one alternating voltage (15) with a constant rms value and constant frequency.

Abstract: The invention relates to a fixed frequency electrical generation system that can be placed at the variable load engine output, which includes: an initial stage (30), which is a permanent magnet generator that provides energy to said system, making it autonomous, a secondary stage (21,) which is an excitation stage that controls the magnetisation of a third stage, this third stage (24,) which is a main generator, is the electrical energy production power stage.