DC electrical power distribution device, and associated propulsion system and aircraft

Abstract

A DC electrical power distribution device (6) for an aircraft propulsion duct comprises a main power supply line (36) intended to supply at least one propulsion assembly of the propulsion duct with power from a high-voltage DC electrical power supply source and including main switching means (39) and fast switching means for connecting said source to the propulsion assembly. The device comprises a secondary power supply line (37) intended to be connected to another distribution device (7) and configured to supply the propulsion assembly with power from the other device when the main switching means are open.

Description

[0001] DESCRIPTION

[0002] TITLE: Direct voltage electrical power distribution device, associated propulsion system and aircraft

[0003] Technical field of the invention

[0004] The invention relates to aircraft electric propulsion systems, and more particularly to devices for distributing direct voltage electrical power.

[0005] The invention further relates to an electric propulsion system comprising such devices and an aircraft comprising such a system.

[0006] State of the prior art

[0007] Generally, aircraft are powered by turbomachinery of the turboprop, turbojet or turbine type.

[0008] However, the use of turbomachines is accompanied by significant noise emissions and high consumption of fossil fuel, particularly kerosene, generating equally significant polluting emissions.

[0009] In order to reduce pollutant and noise emissions, aircraft propulsion can be electric, by replacing the turbomachines intended to produce the aircraft's thrust with electric motors.

[0010] Electrical systems on board aircraft typically comprise a combination of an alternating voltage system, for example 115 volts alternating current or 230 volts alternating current, and a low voltage direct current system, for example 28 volts direct current, or a single direct current system, for example 28 volts direct current.

[0011] An on-board AC network in an aircraft provides a total on-board electrical power of between 50 and 500 kW, and up to 1 MW.

[0012] A DC network on board an aircraft provides electrical power of less than 100kW. In addition, the electrical architecture of such a network is usually developed for a given application and for a given type of aircraft, preventing the reuse of the network for another type of aircraft.

[0013] In addition, the electric propulsion system is a critical system of the aircraft so it must meet stringent operational safety requirements to be certified.

[0014] Redundancy of critical elements of the propulsion system is required increasing the mass of the aircraft.

[0015] Documents WO 2020 / 174165 and FR 3 098 663 disclose electric propulsion system architectures.

[0016] Documents EP 3588729, EP 2980946 and FR 3050882 disclose electrical power supply networks for aircraft.

[0017] Document EP 3703220 discloses a method of regulating a voltage delivered by an active rectifier connected to a battery.

[0018] Document EP368391 1 discloses interconnected high voltage direct current electrical networks.

[0019] There is a demand for components capable of operating at a voltage of 800 VDC, and at powers of the order of 100 to 250 kW, allowing the implementation of a high-voltage DC network.

[0020] Such components would be particularly advantageous for electrically powered aircraft with rotating electrical machines driving propulsion propellers.

[0021] Statement of the invention

[0022] The aim of the invention is to overcome all or part of these drawbacks.

[0023] The invention relates to a device for distributing direct voltage electrical power for a propulsion channel of an aircraft, comprising a main power supply line intended to supply at least one propulsion unit of the propulsion channel from a high direct voltage electrical power supply source and comprising main switching means for connecting said source to said propulsion unit. The device further comprises a secondary power supply line intended to be connected to another distribution device and configured to supply said propulsion unit from another device when the main switching means are open.

[0024] Upon detection of a failure of the power source, propulsion assembly or main power line of the device, said device is reconfigured to power the propulsion assembly from another device.

[0025] The architecture of the devices ensures power supply redundancy for the propulsion system connected to the device.

[0026] High DC voltage is defined as DC voltage greater than 270 volts.

[0027] Preferably, the main power supply line extends between input terminals intended to be connected to the source and output terminals intended to be connected to the propulsion unit, the main power supply line comprising a power bus connected to the output terminals and connected to the input terminals via main switching means and fast switching means, and the secondary power supply line is connected to the bus via secondary switching means and comprising input terminals intended to be connected to input terminals of the secondary power supply line of the other device, the device further comprising control means configured to open the main switching means and the fast switching means, and second control means configured to close the secondary switching means upon detection of a failure of the propulsion unit,from the main power line or source.,

[0028] Advantageously, the main power supply line extends between input terminals intended to be connected to the source and output terminals intended to be connected to the propulsion unit, the main power supply line comprising a power bus and a power line, the bus being connected to the output terminals and connected to the input terminals via the main switching means and fast switching means, the power line being connected between the input terminals and the main switching means and being intended to be connected to the secondary power supply line of the other device, and the secondary power supply line is connected to the bus via secondary switching means and comprising input terminals intended to be connected to input terminals of the power line of the other device,the device further comprising control means configured to open the main switching means and the rapid switching means, and second control means to close the secondary switching means upon detection of a failure of the propulsion unit, the main power supply line or the source.,

[0029] Preferably, the device further comprises charging terminals connected between the input terminals and the main switching means or between the main switching means and the fast switching means via charging switching means and intended to charge the reversible power source from a charger, the control means being further configured to close the charging switching means to charge the reversible source.

[0030] Advantageously, the main power supply line extends between input terminals intended to be connected to the source and output terminals intended to be connected to the propulsion unit, the main power supply line comprising a power bus connected to the output terminals via fast switching means and connected to the input terminals via the main switching means and comprising charging terminals connected via the charging switching means between the input terminals and the main switching means and intended to be connected to a charger and to the charging terminals of the other device, and the secondary power supply line comprises second output terminals connected to the bus via secondary switching means and intended to be connected to the output terminals of the other device,the device further comprising control means configured to open the main switching means, the fast switching means and the secondary switching means upon detection of a failure of the propulsion unit, the main power supply line or the source.,

[0031] There is also provided a propulsion system comprising at least two identical devices as defined above, in which the input terminals of the secondary power supply line of a first device are connected to the input terminals of the secondary power supply line of the second device.

[0032] Preferably, the propulsion system comprises at least two identical devices as defined previously, in which the input terminals of the power line of a first device are connected to the input terminals of the secondary power supply line of the second device.

[0033] Advantageously, the propulsion system comprises at least four identical devices as defined previously, in which the input terminals of the power line of a first device are connected to the input terminals of the secondary power supply line of a second device, the input terminals of the secondary power supply line of the first device are connected to the input terminals of the power line of a third device, the input terminals of the power line of the second device are connected to the input terminals of the secondary power supply line of the fourth device, and the input terminals of the power line of the fourth device are connected to the input terminals of the secondary power supply line of the third device.

[0034] Preferably, the propulsion system comprises at least two identical devices as defined above, in which the charging terminals of a first device are connected to the charging terminals of the second device, and in which at least one pair of output terminals of the main power supply line of the first device is connected to a pair of input terminals of the secondary power supply line of the second device.

[0035] There is also provided an aircraft comprising a propulsion system as defined above. Brief description of the drawings

[0036] Other aims, characteristics and advantages of the invention will appear on reading the following description, given solely by way of non-limiting example, and made with reference to the appended drawings in which:

[0037] [Fig 1] schematically illustrates an aircraft according to the invention;

[0038] [Fig 2] schematically illustrates a first embodiment of an electrical distribution module according to the invention;

[0039] [Fig 3] schematically illustrates a second embodiment of the electrical distribution module according to the invention;

[0040] [Fig 4] schematically illustrates a third embodiment of the electrical distribution module according to the invention; and

[0041] [Fig 5] schematically illustrates a fourth embodiment of the electrical distribution module according to the invention.

[0042] Detailed description of at least one embodiment

[0043] We refer to figure 1 which schematically illustrates an aircraft 1 comprising a propulsion system 2.

[0044] The propulsion system 2 comprises two rotating electrical machines 3, 4 each arranged on either side of a longitudinal axis of the aircraft 1 and each equipped with a propeller to propel the aircraft 1.

[0045] Alternatively, the aircraft 1 may comprise more than two rotating electrical machines 3, 4 arranged in equal numbers on either side of the longitudinal axis of the aircraft 1.

[0046] According to yet another variant, the aircraft 1 may comprise a single rotating electrical machine.

[0047] The propulsion system 2 further comprises an electrical distribution module 5 comprising two identical electrical power distribution devices 6, 7, four power converters 8, 9, 10, 11 each supplying one of the rotating electrical machines 3, 4, and two sources 12, 13 of direct electrical voltage.

[0048] A first converter 8 is connected to a first and a second output terminals 14, 15 of a first electrical power distribution device 6, and a second converter 9 is connected to a third and a fourth output terminals 16, 17 of the first electrical power distribution device 6.

[0049] The first converter 8 supplies the first machine 3 and the second converter 9 supplies the second machine 4.

[0050] A first source 12 is connected to input terminals 18, 19 of the first device 6.

[0051] A third converter 10 is connected to a first and a second output terminals 20, 21 of the second electrical power distribution device 7, and the fourth converter 11 is connected to a third and a fourth output terminals 22, 23 of the second electrical power distribution device 7.

[0052] The third converter 10 supplies the first 3 and the fourth converter 11 supplies the second machine 4.

[0053] The second source 13 is connected to input terminals 24, 25 of the second device 7.

[0054] Alternatively, the first converter 8 and the third converter 10 can be integrated into the first rotating electrical machine 3, and the second converter 9 and the fourth converter 11 can be integrated into the second rotating electrical machine 4.

[0055] Each source 12, 13 comprises, for example, a fuel cell, a battery or a direct voltage generator.

[0056] Each source 12, 13 may be reversible so that it may be recharged from an electrical power supply network at the aircraft 1 or from electrical energy produced by an electrical generator arranged in the aircraft 1 or outside the aircraft 1 and connected to the source 12, 13.

[0057] The first device 6 is powered by the first source 12, and supplies the first and second converters 8, 9 with direct voltage.

[0058] The second device 7 is powered by the second source 13, and supplies the third and fourth converters 10, 11 with direct voltage.

[0059] The first converter 8 supplies the first machine 3 and the second converter 9 supplies the second machine 4. The third converter 10 supplies the first machine 3 and the fourth converter 11 supplies the second machine 4.

[0060] The first and second machines 3, 4 are each powered independently by two converters 8, 10, 9, 11 so that if one of the two converters fails, said machine is powered by the other converter.

[0061] Alternatively, each machine can be powered by more than two independent power converters.

[0062] The converters 8 to 11 are of the inverter type and transform a direct voltage received from the first and second devices 6, 7 into a variable voltage to control the machines 3, 4.

[0063] The first and second machines 3, 4 powered by the first and second converters 8, 9 form a first propulsion unit.

[0064] The first device 6, the first source 12, and the first propulsion assembly form a first propulsion channel 26.

[0065] The first and second machines 3, 4 powered by the third and fourth converters 10, 11 form a second propulsion unit.

[0066] The second device 7, the second source 13, and the second propulsion assembly form a second propulsion channel 27.

[0067] Of course, system 2 can include more than two propulsion channels.

[0068] Each propulsion channel 26, 27 operates independently so that if one of the channels 26, 27 fails, the other channel allows the aircraft 1 to be kept in flight.

[0069] Figure 2 schematically illustrates a first embodiment of the electrical distribution module 5.

[0070] The first and second devices 6, 7 further comprise second input terminals 28, 29, 30, 31.

[0071] The second input terminals 28, 29 of the first device 6 are connected to the second input terminals 30, 31 of the second device 7.

[0072] Each device 6, 7 may further comprise charging terminals 32, 33, 34, 35. As the first and second devices 6, 7 are identical, only the first device 6 is detailed.

[0073] The first device 6 comprises a main supply line 36, a secondary supply line 37, and control means 38.

[0074] The control means 38 are produced for example from an aeronautical controller.

[0075] The main power supply line 36 comprises main switching means 39 comprising for example a main contactor, fast switching means 40 made from semiconductors, and a power bus 41 of the high direct voltage type.

[0076] High DC voltage is defined as DC voltage greater than 270 volts.

[0077] The control means 38 are interfaced with the main switching means 39 and the fast switching means 40.

[0078] The main switching means 39 are connected to the input terminals 18, 19 and to input terminals of the fast switching means 40.

[0079] Output terminals of the fast switching means 40 are connected to the bus 41 supplying the output terminals 14 to 17.

[0080] The output terminals 14 to 17 can each be connected to the bus 41 via protection means 80 comprising, for example, a pyrotechnic switch or a contactor.

[0081] The protection means 80 make it possible to electrically isolate one of the faulty converters 8, 9 while continuing to supply the other converter 9, 8.

[0082] The fast switching means 40 known by the acronym “SSPC” “Solid state power controller” control and protect the electrical supply of the output terminals 14 to 17 from the first source 12 connected to the input terminals 18, 19, and are connected to the control means 38. The secondary supply line 37 comprises secondary switching means 42 comprising for example a contactor connected to the second input terminals 28, 29 and to the bus 41.

[0083] The fast switching means 40 comprise a device for precharging the capacitors connected to the bus 41. The precharging device is active when the fast switching means 40 closes in order to ensure a sufficiently slow rise in voltage of the bus 41 to minimize the current draws from the source 12 connected to the input terminals 18, 19.

[0084] The secondary switching means 42 comprise a device for precharging the capacitors connected to the bus 41. The precharging device is active when the secondary switching means 40 closes in order to ensure a sufficiently slow rise in voltage of the bus 41 to minimize the current draws from the source 12 connected to the second input terminals 28, 29.

[0085] The secondary switching means 42 are controlled by the control means 38.

[0086] Each terminal 14 to 19, 28, 29, 32 and 33 is equipped with a voltage sensor and a current sensor connected to the control means 38.

[0087] It is assumed that the main switching means 39 and the fast switching means 40 are closed so that the first source 12 supplies the output terminals 14 to 17, and the secondary switching means 42 are open.

[0088] When the control means 38 detect a failure of the first propulsion unit, of the main power supply line 36 or of the first source 12, for example a short circuit or an overload, from the quantities measured by the voltage sensors, the current sensors, and the information transmitted by the rapid switching means 39, the control means 38 control the main switching means 39 and the rapid switching means 40 so that the main switching means 39 and the rapid switching means 40 open.

[0089] The main switching means 39 and the rapid switching means 40 make it possible to isolate the first propulsion unit or the first source in order to prevent propagation of the failure to other components of the aircraft 1.

[0090] Bus 41 is no longer supplied with direct voltage by the first source 12.

[0091] Each device 6, 7 further comprises second control means 43 produced for example from an aeronautical controller.

[0092] The second control means 43 of the first and second devices 6, 7 communicate with each other.

[0093] If the fault is located upstream of the main switching means 39, between the switching means 39 and the input terminals 18, 19, the control means 38 can control the secondary switching means 42 so that it is in the closed position when the main switching means 39 are open, and communicate with the second control means 43 so that the control means of the second device 7 close the secondary contactor of the second device 7.

[0094] Furthermore, the fault upstream of the main switching means 39 is isolated by the source 12 supplying the first device 6 so that the fault does not propagate in the propulsion channel.

[0095] The main switching means 39 and the secondary switching means 42 are not simultaneously closed to prevent the sources 12, 13 from being connected in parallel to the input terminals 18, 19 and to the second input terminals 28, 29.

[0096] Closing the secondary switching means of the first and second devices 6, 7 makes it possible to supply the bus 41 of the first device 6 from the second source 13 so as to redundantly supply the first and second machines 3, 4 when the first source 12 fails.

[0097] Of course, if the second source 13 fails, the devices 6, 7 are configured so that the first device 6 supplies the power bus of the second device 7.

[0098] The reconfiguration of the first and second devices 6, 7 upon detection of a failure of one of the sources 12, 13 makes it possible to supply the propulsion unit connected to the faulty source by the functional source.

[0099] The rapid switching means 40 and the secondary main switching means 42 are of different technology so as to obtain an asymmetry of the switching members to improve the reliability of the devices 6, 7.

[0100] The main switching means 39 and secondary switching means 42 will be controlled independently to ensure dissimilarity of the control of the device 6, 7. The main switching means 39 are controlled by the control means 38 while the secondary switching means 42 are controlled by the second control means 43.

[0101] The first device 6 further comprises load switching means 44 ensuring the charging of the reversible source 12 controlled by the means 38 and connecting the load terminals 32, 33 to the main supply line 36 between the input terminals 18, 19 and the main switching means 39.

[0102] The load switching means 44 comprise, for example, a contactor.

[0103] When the charging switching means 44 are closed, the charging terminals 32, 33 recharge the first source 12 from a charger 100 connected to a ground-based electrical supply network when the aircraft 1 is on the ground, the first source 12 each comprising a reversible battery.

[0104] Alternatively, the load switching means 44 are connected between the main switching means 39 and the fast switching means 40.

[0105] According to another variant, the first device 6 does not comprise charging terminals 32, 33 and charging contactor 44. The charging of the source 12 is then carried out through the secondary switching means 42.

[0106] Figure 3 schematically illustrates a second embodiment of the electrical distribution module 5.

[0107] We find the first and second devices 6, 7 comprising the main supply line 36, the secondary supply line 37, the load terminals 32, 33, 34, 35, and the protection means 80 as described previously.

[0108] The first and second devices 6, 7 further comprise power terminals 45, 46, 47, 48 connected to the input terminals 18, 19, 30, 31 via a power line 49.

[0109] The power terminals 45, 46 of the first device 6 are connected to the second input terminals 30, 31 of the second device 7, and the power terminals 47, 48 of the second device 7 are connected to the second input terminals 28, 29 of the first device 6.

[0110] In a manner similar to the first embodiment illustrated in FIG. 2, when the control means 38 detect a failure of the first propulsion unit or of the first source 12, the control means 38 control the main switching means 39 and the rapid switching means 40 so that the main switching means 39 and the rapid switching means 40 are open.

[0111] If the fault is located upstream of the bus 41, between the bus 41 and the input terminals 18, 19, the control means 38 control the secondary switching means 42 so that they are in the closed position.

[0112] Closing the secondary switching means 42 of the first device 6 makes it possible to supply the bus 41 of the first device 6 from the second source 13 so as to redundantly supply the first and second machines 3, 4 when the first source 12 fails.

[0113] In this embodiment, the total electrical power exchanged between the two devices 6, 7 passes through the main power supply line 36 and the power line 49, making it possible to size the main switching means 39 and the fast switching means 40, and the bus 41 of the main power supply line 36, and furthermore the secondary switching means 42 according to the electrical powers delivered to the output terminals 14 to 17 and 20 to 23 of the two devices 6, 7, reducing the size and weight of the switching means 39, 40, 42 and the bus 41.

[0114] The mass and volume of the two devices 6, 7 are reduced. Figure 4 schematically illustrates a third embodiment of the electrical distribution module 5.

[0115] The module 5 comprises four identical devices 6, 7, 50, 51 as defined in the second embodiment of the electrical distribution module 5 illustrated in Figure 3.

[0116] In this embodiment, the four devices 6, 7, 50, 51 are connected to each other by circular permutation.

[0117] Each device 6, 7, 50, 51 supplies a different propulsion unit.

[0118] Each device 6, 7, 50, 51 and its associated propulsion assembly form a propulsion channel so that the four propulsion channels power, for example, four rotating electrical machines.

[0119] Only the input terminals 28, 29, 30, 31, 52, 53, 54, 55 of the secondary power supply line of the devices 6, 7, 50, 51 and the input terminals 45, 46, 47, 48, 56, 57, 58, 59 of the power line of the devices 6, 7, 50, 51 are illustrated.

[0120] The input terminals 45, 46 of the power line of the first device 6 are connected to the input terminals 30, 31 of the secondary power supply line of the second device 7.

[0121] The input terminals 28, 29 of the secondary power supply line of the first device 6 are connected to the input terminals 56, 57 of the power line of a third device 50.

[0122] The input terminals 47, 48 of the power line of the second device 7 are connected to the input terminals 54, 55 of the secondary power supply line of the fourth device 51.

[0123] The input terminals of the power line 58, 59 of the fourth device 51 are connected to the input terminals 52, 53 of the secondary power supply line of the third device 50.

[0124] Figure 5 schematically illustrates a fourth embodiment of the electrical distribution module 5.

[0125] We find the first and second identical devices 6, 7 comprising the output terminals 14 to 17 and 20 to 23, the input terminals 18, 19, 24, 25, the load terminals 32, 33, 34, 35. As the devices 6 and 7 are identical, only the architecture of the first device 6 is described.

[0126] The first device 6 comprises a main power supply line 60 extending between input terminals 18, 19 and the output terminals 14 to 17.

[0127] The main power supply line 60 comprises the power bus 41 connected to the output terminals 14 to 17 via two SSPC semiconductor type fast switching means 61, 62 each controlling a different pair of output terminals 14 to 17, and connected to the input terminals 18, 19 via the main switching means 39.

[0128] The load terminals 32, 33 are connected to the main supply line 60 between the input terminals 18, 19 and the main switching means 39 via the load switching means 44.

[0129] The fast switching means 61 and 62 comprise the precharging device to prevent overcurrent when connecting the rotating electrical machines 3, 4 to the bus 41.

[0130] The first device 6 further comprises a secondary power supply line 63 comprising second output terminals 64 to 67 connected to the bus 41 by first and second secondary switching means 68, 69, the first secondary switching means 68 connecting the second output terminals 64, 65 to the bus 41, and the second secondary switching means 69 connecting the second output terminals 66, 67 to the bus 41.

[0131] The switching means 68 and 69 comprise a device for precharging capacitors of the rotating electrical machines 3, 4 making it possible to slowly charge the capacitors of said electrical machines to prevent an overcurrent when connecting the motors to the bus 41.

[0132] The fast switching means 61 and 62 on the one hand and the secondary switching means 68 and 69 on the other hand are of dissimilar technology and are dissimilar in their control in order to protect against common modes of the fast switching means and the secondary switching means. The first device 6 further comprises control means 70 produced for example from a controller.

[0133] The input terminals of the secondary power supply line of the second device 7 are denoted 71, 72, 73, 74.

[0134] The load terminals 32, 33 of the first device 6 are connected to the load terminals 34, 35 of the second device 7.

[0135] A first pair of second output terminals 64, 65 connected to the first secondary switching means 68 is connected to a second pair of output terminals 22, 23 of the second device 7.

[0136] The second pair of output terminals 66, 67 connected to the second secondary switching means 69 is connected to the first pair of output terminals 21, 22 of the second device 7.

[0137] A first pair of output terminals 71, 72 of the secondary power supply line of the second device 7 is connected to a first pair of output terminals 14, 15.

[0138] The second pair of output terminals 73, 74 of the secondary power supply line of the second device 7 is connected to the second pair of output terminals 16, 17.

[0139] The main switching means 39, the fast switching means 61, 62 of the devices 6 and 7 are closed while the first and second secondary switching means 68, 69 of the devices 6 and 7 are open during normal operation.

[0140] The load switching means 44 of the first and second devices 6, 7 are initially open.

[0141] When the source 12 or the propulsion unit of the first device 6 fails, the control means 70 open the main switching means 39, the rapid switching means 61, 62, and the secondary switching means 68, 69.

[0142] Since the output terminals 14 to 17 of the first device 6 are connected to the input terminals 71, 72, 73, 74 of the secondary supply line of the second device 7, the first propulsion unit is supplied by the second device 7.

[0143] Furthermore, if the source 12 is not faulty, the means 70 close the load switching means 44 making it possible to parallelize the sources 12, 13. When a failure of a source or of the main power supply line is detected, the first and second devices 6, 7 are reconfigured to supply the propulsion unit from a functional source. When the reversible source 12 is charged by the charger 100, the control means 70 close the load switching means.

[0144] When a fault is detected during the charging of the source 12, the control means 70 open the charging switching means.

[0145] The architecture of the devices 6, 7 makes it possible to ensure redundancy in the supply of the propulsion units from identical sources or from sources of different types, the first device 6 being for example supplied by a fuel cell and the second device 7 being for example supplied by a direct voltage generator.

Claims

DEMANDS 1. A device (6, 7) for distributing direct current electrical power to a propulsion channel (26, 27) of an aircraft (1), comprising a main supply line (36, 60) for supplying at least one propulsion unit of the propulsion channel from a high-voltage direct current power source (12, 13) and comprising main switching means (39) for connecting said source to said propulsion unit, the device comprising a secondary supply line (37, 63) for connection to another distribution device (7, 6) and configured to supply said propulsion unit from the other device when the main switching means are open, the main supply line (36) extending between input terminals (18, 19) for connection to the source (12) and output terminals (14, 15, 16, 17) for connection to the propulsion assembly (26),the main power supply line comprising a power bus (41) connected to the output terminals and connected to the input terminals via the main switching means (39) and fast switching means (40), and the secondary power supply line (37) being connected to the bus via secondary switching means (42) and comprising input terminals (28, 29) intended to be connected to input terminals (30, 31) of the secondary power supply line of the other device (7), the device further comprising control means (38) configured to open the main switching means and the fast switching means, and second control means (43) configured to close the secondary switching means upon detection of a failure of the propulsion assembly, the main power supply line or the source, characterized in that the device further comprises load terminals (32,33) connected between the input terminals (18, 19) and the main switching means (39) or between the main switching means (39) and the fast switching means (40) via load switching means (44) and, intended for charging the reversible power source (12) from a charger (100), the control means being further configured to close the charging switching means to charge the reversible source.

2. Propulsion system (2) comprising at least two identical devices (6, 7) according to claim 1, wherein the input terminals (28, 29) of the secondary power line (37) of a first device (6) are connected to the input terminals (30, 31) of the secondary power line of the second device (7).

3. Aircraft (1) comprising a propulsion system (2) according to claim 2.

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