Electric propulsion chain for aircraft and method of charging battery of aircraft

Abstract

An apparatus for charging a battery (15, 16) of an aircraft (1) comprises a reversible electrical power converter (13) comprising a power inlet (132) configured to be connected to the battery (16) and a power outlet (134) configured to be connected to a propulsion rotating electric machine (5) driving a propeller (100) of the aircraft, such that the power converter transfers electrical energy between the electric machine and the battery. The charging device further comprises means for deactivating the propeller configured to prevent rotation of the propeller (100), and a parking socket (42) connected between the charging contactor and the power outlet.

Description

Technical Field

[0001] The present invention relates to aircraft electric propulsion systems and, more particularly, to an apparatus for charging propulsion batteries and a battery charging method.

[0002] The invention also relates to a propulsion chain comprising such a device and to an aircraft comprising such a propulsion chain. Background Art

[0003] Climate change is a major concern for many legislative and regulatory bodies around the world. In fact, countries have, are or will adopt various measures to limit carbon emissions. In particular, an ambitious standard applies both to new aircraft and to aircraft already in service, requiring the implementation of technical solutions to bring them into compliance with current regulations. For many years, civil aviation has been committed to contributing to the fight against climate change.

[0004] Technical research has significantly improved the environmental performance of aircraft. Applicants have taken into account influencing factors at all stages of design and development to obtain aviation components and products that consume less energy, are more environmentally friendly, and have little impact on the environment when integrated and used in civil aviation, so as to improve the energy efficiency of aircraft.

[0005] Therefore, the Applicant is continuously working to reduce the environmental impact of its operations by lowering its negative impact on the climate through the use of benign development and manufacturing methods and processes that minimize greenhouse gas emissions as much as possible.

[0006] This ongoing research and development work is focused on new generation aircraft engines, lighter aircraft and, in particular, lighter onboard equipment, and the use of electric technology to ensure propulsion.

[0007] The electric propulsion aircraft includes at least one electric motor driving a pusher propeller, at least one battery storing electric energy required to power the electric motor, and a power converter for supplying power to the electric motor using an AC voltage converted from a DC voltage provided by the battery.

[0008] The battery is charged while the aircraft is on the ground.

[0009] For this purpose, a ground unit (groupe de parc) supplying an alternating voltage is connected to the aircraft in order to charge the batteries.

[0010] However, since the grounding unit generally provides a three-phase AC voltage, the voltage needs to be converted into a DC voltage to charge the battery.

[0011] It is known to implement a power converter in the ground unit to convert the AC voltage provided by the ground unit into a DC voltage for charging the battery.

[0012] However, it is necessary to develop a new ground unit architecture and add a communication module between the ground unit and a battery charge management module of a battery implemented in an aircraft in order to regulate the charging of the battery.

[0013] It is also known to install a power converter in an aircraft to convert the alternating voltage provided by a ground unit into a direct voltage for charging the battery.

[0014] However, the implementation of a power converter and a wiring harness for providing a three-phase voltage to the power converter, which is used exclusively for charging the battery, increases the weight of the aircraft, resulting in an increase in the energy consumption of the aircraft. Summary of the invention

[0015] The object of the present invention is to overcome all or part of these disadvantages.

[0016] To this end, the present invention is the result of technical research aimed at most significantly improving the performance of aircraft and correspondingly contributing to reducing the impact of aircraft on the environment. To this end, the present invention relates to a device for charging the battery of an aircraft, thus comprising a reversible electric power converter comprising a power input terminal configured to be connected to the battery and a power output terminal configured to be connected to a propulsion rotary electric machine driving a propulsion propeller of the aircraft, so that the power converter transfers electrical energy between the electric machine and the battery.

[0017] The charging device also comprises means for deactivating the pusher propeller, configured to prevent the propeller from rotating, and a ground connection connected to the power output.

[0018] This charging device enables the batteries of the aircraft to charge a ground unit known from the prior art, without having to implement a power converter dedicated to charging the batteries in the aircraft, thereby increasing the weight of the aircraft.

[0019] Charging the batteries utilizes the power converters already present in the aircraft to control the aircraft's propulsion rotary motors.

[0020] There is also provided an electric propulsion chain for an aircraft, comprising a charging device as defined above, a propulsion rotating motor configured to drive a propeller of the aircraft, a power distribution device and a battery, the power distribution device comprising a power supply line comprising an input connected to the battery and an output connected to the power input of a converter, and wherein the device for deactivating the propulsion propeller comprises a charging contactor which connects the power output of the converter to the rotating motor.

[0021] Preferably, the power converter comprises a first reversible conversion module connecting the power input terminal to the power output terminal and a second conversion module connecting the second power input terminal to the second power output terminal, the conversion modules being independent of each other, the power distribution device comprising a second power supply line comprising an input terminal connected to a battery and an output terminal connected to a second power input terminal of the converter, the rotating motor comprising two groups of redundant stator coils, the first group of stator coils being connected to a charging contactor, and the second group of stator coils being connected to a second power output terminal of the converter.

[0022] Alternatively, an electric propulsion chain for an aircraft comprises a charging device as defined above, a propulsion rotary motor, a power distribution device and a battery, the propulsion rotary motor comprising a shaft configured to drive a propulsion propeller of the aircraft, the power distribution device comprising a power supply line comprising an input end connected to the battery and an output end connected to a power input end of a converter, and wherein the device for deactivating the propulsion propeller comprises a clutch configured to disengage the propulsion propeller from the shaft of the rotary motor to prevent rotation of the propulsion propeller.

[0023] Preferably, the power converter includes a first reversible conversion module connecting the power input terminal to the power output terminal and a second conversion module connecting the second power input terminal to the second power output terminal, and the conversion modules are independent of each other. The power distribution device includes a second power supply line, which includes an input terminal connected to the battery and an output terminal connected to the second power input terminal of the converter. The rotating motor includes two groups of redundant stator coils, the first group of stator coils is connected to the power output terminal, and the second group of stator coils is connected to the second power output terminal of the converter.

[0024] Advantageously, each power supply line comprises a power supply bus, a first voltage sensor, a second voltage sensor and a control circuit, the power supply bus being connected to the input end of the power supply line via a first contactor and to the output end of the power supply line via a second contactor, the first voltage sensor measuring the voltage between the input end and the first contactor, the second voltage sensor measuring the voltage between the second contactor and the converter, the control circuit being configured to control the converter and the first contactor and the second contactor according to the values ​​measured by the first voltage sensor and the second voltage sensor.

[0025] Preferably, the electric propulsion chain further comprises a redistribution contactor connecting the power supply bus of the power supply line to the power supply bus of the second power supply line, and the control circuit is further configured to control the redistribution contactor.

[0026] Advantageously, the control circuit is further configured to control the ground power supply unit to supply power to the ground power connection piece when the pusher propeller is prevented from rotating.

[0027] Preferably, the electric propulsion chain includes a second propulsion rotary motor, a second power converter, and a second battery. The power distribution device includes a third power supply line, which includes an input end connected to the second battery and an output end connected to the input end of the second power converter. The power distribution device also includes a distribution contactor, which connects the power supply bus of the power supply line to the power supply bus of the third power supply line, and the control circuit is configured to control the distribution contactor.

[0028] An aircraft is also provided, comprising an electric propulsion chain as defined above and the same number of propulsion nacelles as propulsion rotary electric machines, each motor being arranged in a different nacelle, means for deactivating the pusher propellers and a ground connection being arranged in one of the nacelles.

[0029] The grounding connector is disposed in one of the multiple cabins of the aircraft, such as in the bottom of the cabin, eliminating the need for a charging harness connecting the grounding connector to a power distribution device, thereby further reducing the weight of the aircraft.

[0030] Furthermore, a method for charging a battery of an aircraft, the aircraft comprising a reversible electric power converter comprising a power input connected to the battery and a power output connected to a propulsion rotary motor of the aircraft, such that the power converter transfers electrical energy between the motor and the battery, is particularly advantageous for reducing the environmental impact of the aircraft.

[0031] The method includes activating a device for disabling the pusher propeller to prevent rotation of the pusher propeller, and when the pusher propeller is prevented from rotating, supplying power to a ground connection connected to a power output so that a power converter transfers power from the ground connection to a battery.

[0032] Preferably, the aircraft includes a second propulsion rotary motor, a second power converter, a second battery and a power distribution device, the power distribution device including: a power supply line including an input end connected to the battery and an output end connected to the power input end of the converter; a second power supply line including an input end connected to the second battery and an output end connected to the power input end of the second converter; and a distribution contactor, each power supply line including: a power supply bus connected to the input end of the power supply line through a first contactor and connected to the output end of the power supply line through a second contactor; a first voltage sensor, the first voltage sensor measures the voltage between the input end and the first contactor; and a second voltage sensor, the second voltage sensor measures the voltage between the second contactor and the converter; the distribution contactor connects the power supply bus of the first power supply line to the power supply bus of the second power supply line; the method also includes: closing the second contactor and the redistribution contactor of the power supply line, disconnecting the second contactor of the second power supply line, and controlling the power converter according to the values ​​measured by the first current sensor and the first voltage sensor, the second current sensor and the second voltage sensor of the power supply line and the second power supply line, so that the power converter transmits electrical energy from the grounding connector to the second battery. BRIEF DESCRIPTION OF THE DRAWINGS

[0033] Other objects, characteristics and advantages of the invention will appear on reading the following description, given by way of non-limiting example only, and made with reference to the accompanying drawings, in which:

[0034] [ Figure 1 ] schematically shows an aircraft according to the invention;

[0035] [ Figure 2 ] schematically shows an example embodiment of a power distribution device according to the present invention;

[0036] [ Figure 3 ] schematically shows a first exemplary embodiment of a charging device according to the present invention;

[0037] [ Figure 4 ] schematically shows a second exemplary embodiment of a charging device according to the present invention,

[0038] [ Figure 5 ] schematically illustrates another example embodiment of a charging device. DETAILED DESCRIPTION

[0039] refer to Figure 1 , Figure 1 An aircraft 1 is schematically shown comprising an electric propulsion chain 2 connected to a ground unit 3 .

[0040] This propulsion chain 2 comprises two multiphase propulsion rotary electric machines 4 , 5 , each arranged in a nacelle 6 , 7 on either side of the longitudinal axis of the aircraft 1 , and comprising a respective shaft 101 , 102 , each equipped with a propeller 100 , in order to propel the aircraft 1 .

[0041] The first rotating electrical machine 4 is disposed in the first nacelle 6 , and the second rotating electrical machine 5 is disposed in the second nacelle 7 .

[0042] For example, the motors 4 , 5 are of three-phase type.

[0043] For example, the aircraft 1 is an airplane.

[0044] Alternatively, the aircraft 1 may comprise more than two rotary electric machines 4 , 5 , which are arranged in equal numbers on both sides of the longitudinal axis of the aircraft 1 .

[0045] According to another alternative, aircraft 1 may comprise a single rotating electrical machine.

[0046] The aircraft 1 may also comprise at least one turboprop or turbojet driven by a fuel-burning turbine, so that the aircraft 1 has hybrid propulsion.

[0047] Each rotating electrical machine 4 , 5 comprises a first set of stator coils 8 , 9 and a second set of stator coils 10 , 11 .

[0048] For example, the coils in each set of coils 8, 9, 10, 11 are connected together in a star configuration.

[0049] The propulsion chain 2 further comprises two power converters 12 , 13 , a power distribution device 14 , two batteries 15 , 16 connected to the power distribution device 14 , and a control circuit 43 for controlling the propulsion chain 2 .

[0050] The first converter 12 provided in the first nacelle 6 is connected to the first rotating electrical machine 4 , and the second converter 13 provided in the second nacelle 7 is connected to the second rotating electrical machine 5 .

[0051] The batteries 15, 16 are located in the additional fuselage, for example at the bottom of the aircraft fuselage, so that if one of the batteries 15, 16 releases gas, the gas will be ejected from the additional fuselage in the direction of the ground to protect the aircraft.

[0052] The location of the batteries 15 , 16 makes it possible to simplify the fuselage structure by avoiding the need to install chimneys inside the fuselage for degassing the batteries 15 , 16 .

[0053] Each converter 12 , 13 includes a first power input terminal 121 , 131 , a second power input terminal 122 , 132 , a first power output terminal 123 , 133 , and a second power output terminal 124 , 134 .

[0054] The power distribution device 14 comprises the same number of identical power supply lines 21 , 22 , 23 , 24 as power input terminals 121 , 122 , 131 , 132 , each power supply line 21 , 22 , 23 , 24 being connected to a different power input terminal 121 , 122 , 131 , 132 .

[0055] A first power input 121 of the first converter 12 is connected to the output terminals 25 , 26 of the first power supply line 21 , and a second power input 122 of the first converter 12 is connected to the output terminals 27 , 28 of the second power supply line 22 .

[0056] The first three-phase power output terminal 123 of the first converter 12 is connected to the first set of stator coils 8 of the first rotating electric machine 4 , and the second three-phase power output terminal 124 of the first converter 12 is connected to the second set of stator coils 10 of the first rotating electric machine 4 .

[0057] The first converter 12 comprises two independent conversion modules 17 , 18 , so that if one of the conversion modules 17 , 18 fails, the other conversion module 18 , 17 continues to operate in an optimal manner.

[0058] The conversion modules 17 , 18 are both made of semiconductors (eg, diodes and transistors).

[0059] The first conversion module 17 connects the first power input terminal 121 to the first power output terminal 123 , and the second conversion module 18 connects the second power input terminal 122 to the second power output terminal 124 .

[0060] Each conversion module 17 , 18 receives a DC voltage at a power input terminal 121 , 122 , and provides a three-phase voltage system at a power output terminal 124 , 123 to power the first motor 4 and control the first motor 4 .

[0061] Input terminals 29 , 30 , 31 , 32 of the first power supply line 21 and the second power supply line 22 are connected to the first battery 15 .

[0062] The first power supply line 21 and the second power supply line 22 provide a DC voltage from the first battery 15 to the conversion modules 17 , 18 .

[0063] Each group of stator coils 8 , 11 is powered by a power supply circuit, which includes conversion modules 17 , 18 of a first converter 12 and a first power supply line 21 and a second power supply line 22 .

[0064] The power supply circuits enable the rotary electrical machine 4 to be supplied redundantly in order to compensate for a failure of one of the power supply circuits.

[0065] A first power input 131 of the second converter 13 is connected to the output terminals 33 , 34 of the third power supply line 23 , and a second power input 132 of the second converter 13 is connected to the output terminals 35 , 36 of the fourth power supply line 24 .

[0066] Input terminals 37 , 38 , 39 , 30 of the third power supply line 23 and the fourth power supply line 24 are connected to the second battery 16 .

[0067] The first three-phase power output terminal 133 of the second converter 13 is connected to the first group of stator coils 9 of the second rotating electric machine 5 .

[0068] The second three-phase power output terminal 133 of the second converter 13 is connected to the second group of stator coils 11 of the second rotating electric machine 5 through the charging contactor 41 .

[0069] In addition, the ground power connection element 42 is connected between the charging contactor 41 and the second power output terminal 134 .

[0070] The charging contactor 41 and the ground connection 42 are disposed in the nacelle 7 accommodating the second electric machine 5 .

[0071] The grounding connector 42 is connected to the power output terminal of the grounding unit 3, so that the grounding unit 3 provides electrical energy to the grounding connector 42, for example, the grounding unit provides a three-phase voltage system.

[0072] When the charging contactor 41 is disconnected, all phases of the second group of stator coils 11 of the second motor 5 are isolated from the ground connection 42 , so that the ground unit 3 exclusively supplies power to the second converter 13 .

[0073] Since no power is supplied to the second set of stator coils 11 of the second motor 5, the shaft 102 of the motor is not driven.

[0074] Since the propeller 100 connected to the shaft 102 does not rotate, an operator working on the second nacelle 7 is less likely to be injured by the propeller.

[0075] The control circuit 43 controls the first and second converters 12 and 13 , the power supply lines 21 , 22 , 23 , 24 , and the charging contactor 41 , and includes, for example, a redundant processing unit.

[0076] The supply lines 21 , 22 , 23 , 24 can also be connected to one another via redistribution contacts and distribution contacts which are not shown in this figure.

[0077] When the aircraft is flying, the second converter 13 supplied with a DC voltage at the power input terminals 131 , 132 provides a three-phase voltage system at the power output terminals 133 , 134 to supply power to and control the second motor 4 .

[0078] The first power output terminal 133 supplies power to the first group of coils 9 .

[0079] The charging contactor 41 is closed, so that the second power output terminal 134 supplies power to the second group of coils 11 .

[0080] The third power supply line 23 and the fourth power supply line 24 supply a DC voltage from the second battery 16 to the second converter 13 .

[0081] The second reversible converter 13 includes a conversion module 19 connecting the first power input terminal 131 to the first power output terminal 133 , and a reversible conversion module 20 connecting the second power input terminal 132 to the second power output terminal 134 .

[0082] The second reversible converter 13 , the charging contactor 41 and the ground connection 42 form a charging device.

[0083] When the aircraft is on the ground, Figure 1 As shown, the grounding unit 3 is connected to the grounding connector 42 , and the charging contactor 41 is disconnected by the control circuit 43 , so that the second power output terminal 134 and the grounding connector 42 are not electrically connected to the second group of coils 11 .

[0084] During the flight, each group of stator coils 9 , 11 is powered by a power supply circuit, which includes conversion modules 19 , 20 of the second converter 13 and a third power supply line 23 and a fourth power supply line 24 .

[0085] The power supply circuits enable the rotary electric machine 5 to be supplied redundantly to compensate for a failure of one of the power supply circuits.

[0086] Figure 2 An exemplary embodiment of a power distribution device 14 comprising power supply lines 21 , 22 , 23 , 24 is shown.

[0087] Each power supply line 21 , 22, 23, 24 comprises a power supply bus 50, 51 , 52, 53 connected via a first contactor 54, 55, 56, 57 to an input terminal 29, 30, 31 , 32, 37, 38, 39, 40 forming the input of the line.

[0088] Each power supply line 21 , 22, 23, 24 comprises a second contactor 58, 59, 60, 61 connecting the bus 50, 51 , 52, 53 to an output terminal 25, 26, 27, 28, 33, 34, 35, 36 forming the output end of the line.

[0089] Each supply line 21, 22, 23, 24 also comprises a first voltage sensor 62, 63, 64, 65 measuring the voltage between the input of the supply line and the first contactor 54, 55, 56, 57, and a second voltage sensor 70, 71, 72, 73 measuring the voltage between the second contactor 58, 59, 60, 61 and the converter 12, 13 connected to the line.

[0090] Each power supply line 21, 22, 23, 24 may also include a first current sensor 66, 67, 68, 69 measuring the current between the first contactor 54, 55, 56, 57 and the bus 50, 51, 52, 53, and a second current sensor 74, 75, 76, 77 measuring the current between the second contactor 58, 59, 60, 61 and the converter 12, 13 connected to the line.

[0091] The power distribution device 14 may also include two redistribution contactors 78 , 79 .

[0092] The first redistribution contactor 78 connects the bus bars 50 , 51 of the first and second lines 21 , 22 to one another, and the second redistribution contactor 79 connects the bus bars 52 , 53 of the third and fourth lines 23 , 24 to one another.

[0093] Each redistribution contactor 78 , 79 ensures that both sets of coils 8 , 10 , 9 , 11 of the motor 4 , 5 are supplied with power via a single supply line.

[0094] The power distribution device 14 may also include a distribution contactor 80 that connects the bus 51 of the second line 22 to the bus 53 of the fourth line 24 connected to the reversible conversion module 20 .

[0095] The control circuit 43 controls the converters 12, 13, the first contactors 54, 55, 56, 57 and the second contactors 58, 59, 60, 61, the redistribution contactors 78, 79 and the distribution contactor 80 according to the values ​​measured by the first current sensors 66 to 69, the second current sensors 74 to 77, the first voltage sensors 62 to 65 and the second voltage sensors 70 to 73.

[0096] Figure 3 A first exemplary embodiment of a charging device for charging the second battery 16 is schematically shown.

[0097] Assume that the grounding unit 3 is connected to the grounding connection 42, the first contactors 54, 55, 56, 57 and the second contactors 58, 59, 60, 61 of each of the lines 21, 22, 23, 24 and the charging contactor 41 are closed, the redistribution contactors 78, 79 and the distribution contactor 80 are opened, and the converters 12, 13 are turned off (no electrical energy is transferred between their power input and output terminals).

[0098] During a step 90 , the control circuit 43 opens the charging contactor 41 .

[0099] During the charging step 91 , when the charging contactor 41 is open, the control circuit 43 controls the reversible conversion module 20 of the second converter 13 so that the converter 13 transfers electrical energy from the ground connection 42 to the second battery 16 .

[0100] The control circuit 43 controls the reversible conversion module 20 so that the difference between the voltages measured by the first voltage sensor 65 and the second voltage sensor 73 of the fourth line 24 is equal to a predetermined threshold voltage, and the voltage measured by the first sensor is lower than the voltage measured by the second sensor 73, so that the second battery 16 stores the electrical energy transmitted by the second converter 13 while limiting the current consumption of the second battery 16 during charging.

[0101] When the value measured by the first voltage sensor 65 is equal to the predetermined charge value, the second battery is considered to be charged. The control circuit 43 controls the second converter 13 to stop charging the second battery 16.

[0102] During the charging step 91 , the control circuit 43 reads the current values ​​measured by the first current sensor 69 and the second current sensor 77 to detect a fault.

[0103] The control circuit 43 compares the measured current value with a predetermined alarm threshold value.

[0104] If one of the measured current values ​​is greater than the alarm threshold associated with said value, during a step 92 the control circuit 43 controls the reversible conversion module 20 such that the voltage read by the first voltage sensor 65 is greater than the voltage read by the second voltage sensor 73 .

[0105] The second battery 16 delivers electric energy to prevent heat dissipation of the second battery 16 , and then the control circuit 43 disconnects at least one of the first contactor 57 and the second contactor 61 of the fourth line 24 .

[0106] Alternatively, the control circuit 43 communicates with a control device of the grounding unit 3 .

[0107] The control circuit 43 transmits the set value of the voltage delivered by the grounding unit 3 to the control device.

[0108] Figure 4 A second example embodiment of a charging device is schematically shown.

[0109] In this embodiment, the charging device charges the first battery 15 .

[0110] Assume that the grounding unit 3 is connected to the grounding connection 42, the first contactors 54, 55, 56, 57 and the second contactors 58, 59, 60, 61 of each of the lines 21, 22, 23, 24 and the charging contactor 41 are closed, the redistribution contactors 78, 79 and the distribution contactor 80 are opened, and the converters 12, 13 are turned off (no electrical energy is transferred between their power input and output terminals).

[0111] Repeat step 90.

[0112] Then, during a step 95 , the control circuit 43 closes the distribution contactor 80 so that the bus bars 51 , 53 of the second line 22 and the fourth line 24 are connected to one another, opening the first contactor 57 of the fourth line 24 and the second contactor 59 of the second line 22 .

[0113] During the charging step 96, when the charging contactor 41 is disconnected and the distribution contactor 80 is closed, the first contactor 57 of the fourth line 24 and the second contactor 59 of the second line 22 are disconnected, and the control circuit 43 controls the reversible conversion module 20 of the second converter 13 so that the converter 13 transmits electrical energy from the ground connection 42 to the first battery 15.

[0114] The control circuit 43 controls the reversible conversion module 20 so that the difference between the voltages measured by the second voltage sensor 73 of the fourth line 24 and the first voltage sensor 63 of the second line 22 is equal to a predetermined threshold voltage, and the voltage measured by the first sensor 63 is lower than the voltage measured by the second sensor 73, so that the first battery 15 stores the electrical energy transmitted through the second converter 13 while limiting the current consumption of the first battery 15 during charging.

[0115] The control circuit 3 reads the current values ​​measured by the first current sensor 67 of the second wire 22 and the second current sensor 77 of the fourth wire 24 to detect a fault as described above.

[0116] Alternatively, after the first switch 57 on the fourth line 24 is closed, the converter 13 charges the first battery 15 and the second battery 16 simultaneously.

[0117] When the aircraft is on the ground, the first battery 15 and the second battery 16 may be charged sequentially or simultaneously by the charging device.

[0118] This charging device makes it possible to charge the batteries in the aircraft 1 from a ground unit known in the prior art, without having to implement a power converter dedicated to charging the batteries in the aircraft 1 , thereby increasing the weight of the aircraft.

[0119] The batteries are charged using the power converters already present in the aircraft to control the aircraft's propulsion rotary motors.

[0120] In addition, since the grounding connector is arranged in one of the multiple cabins of the aircraft, for example, at the bottom of the cabin, the charging harness connecting the grounding connector to the power distribution device is eliminated compared to the charging devices known in the prior art, thereby further reducing the weight of the aircraft and simplifying the wiring of the harness.

[0121] The charging contactor 41 forms a means for deactivating the propeller, so as to prevent the propeller 100 from rotating while at least one of the batteries 15 , 16 is being charged.

[0122] Figure 5 Another example embodiment of a charging device is schematically shown.

[0123] In this embodiment, the means for deactivating the propeller comprise a clutch 103 connecting the shaft 102 of the second rotary electric machine 5 to the propeller 100 .

[0124] When the means for deactivating the pusher propeller includes the clutch 103 , the control circuit 43 controls the clutch 103 so that the shaft 102 is decoupled from the propeller 100 to prevent the pusher propeller 100 from rotating.

[0125] When the propeller is decoupled from the shaft 102 , the ground connection 42 is powered by the ground unit and the control circuit 43 controls the reversible conversion module 20 of the second converter 13 as described above.

[0126] All phases of the second group of stator coils 11 of the second motor 5 are powered by the second converter 13 , thereby driving the shaft 102 to rotate.

[0127] Since the propeller is decoupled from the shaft 102 , the second electric machine 5 rotates without load.

[0128] Since the second motor 5 rotates without load, the energy consumed by the second motor 5 is reduced.

[0129] Since the propeller is not rotating, an operator working on the second nacelle 7 is less likely to be injured by the propeller.

Claims

1. An electric propulsion chain (2) for an aircraft (1), comprising means for charging batteries (15, 16), a propulsion rotary electric machine (5) configured to drive a propulsion propeller (100) of the aircraft, a power distribution device (14) and batteries (16), - the charging device comprises a reversible electric power converter (13) comprising a power input (132) configured to be connected to the battery (16) and a power output (134) connected to the propulsion rotary motor (5), such that the power converter transfers electric energy between the motor and the battery, - The charging device also includes: means for deactivating the pusher propeller configured to prevent rotation of the pusher propeller (100); and a ground connection member (42) connected to the power output terminal; - the power distribution device comprises a power supply line (24) comprising an input (39, 40) connected to the battery (16) and an output (35, 36) connected to a power input (132) of the converter (13), Features - the propulsion chain comprises a second propulsion rotary motor (4), a second power converter (12), a second battery (15), the power distribution device (14) comprises a third power supply line (22), the third power supply line (22) comprises an input terminal (31, 32) connected to the second battery (15) and an output terminal (27, 28) connected to an input terminal (122) of the second power converter (12), - Each power supply line (21, 22, 23, 24) comprises a power supply bus (50, 51, 52, 53), a first voltage sensor (62, 63, 64, 65), a second voltage sensor (70, 71, 72, 73) and a control circuit (43), wherein the power supply bus (50, 51, 52, 53) is connected to the input end (29, 30, 31, 32, 37, 38, 39, 40) of the power supply line through a first contactor (54, 55, 56, 57) and is connected to the input end (29, 30, 31, 32, 37, 38, 39, 40) of the power supply line through a second contactor (58, 59, 60, 61) The output end (25, 26, 27, 28, 33, 34, 35, 36) of the power supply line, the first voltage sensor (62, 63, 64, 65) measures the voltage between the input end and the first contactor, the second voltage sensor (70, 71, 72, 73) measures the voltage between the second contactor and the converter (12, 13), the control circuit (43) is configured to control the converter and the first contactor and the second contactor according to the values ​​measured by the first voltage sensor and the second voltage sensor, The power distribution device further comprises a distribution contactor (80) which connects the power supply bus (53) of the power supply line (23) to the power supply bus (51) of the third power supply line (22), and the control circuit (43) is configured to control the distribution contactor.

2. The electric propulsion chain (2) for an aircraft (1) according to claim 1, wherein: The device for deactivating the pusher propeller (100) comprises a charging contactor (41) which connects the power output of the converter (13) to the rotating electrical machine (5).

3. The electric propulsion chain (2) according to claim 2, wherein: The power converter (13) comprises a first reversible conversion module (20) connecting the power input terminal (132) to the power output terminal (134) and a second reversible conversion module (19) connecting the second power input terminal (131) to the second power output terminal (133), the conversion modules being independent of each other, the power distribution device comprising a second power supply line (23), the second power supply line (23) comprising an input terminal (37, 38) connected to the battery (16) and an output terminal (33, 34) connected to the second power input terminal (131) of the converter (13), the rotating electric machine (5) comprising two groups of redundant stator coils (9, 11), the first group of stator coils (11) being connected to the charging contactor (41), and the second group of stator coils (9) being connected to the second power output terminal (133) of the converter (13).

4. The electric propulsion chain (2) for an aircraft according to claim 1, wherein: The device for deactivating the propulsion propeller (100) comprises a clutch (103), wherein the clutch (103) is configured to disengage the propulsion propeller (100) from the shaft (102) of the rotating motor (5) to prevent the propulsion propeller (100) from rotating.

5. The electric propulsion chain (2) according to claim 4, wherein: The power converter (13) comprises a first reversible conversion module (20) connecting the power input terminal (132) to the power output terminal (134) and a second conversion module (19) connecting the second power input terminal (131) to the second power output terminal (133), the conversion modules being independent of each other, the power distribution device comprising a second power supply line (23), the second power supply line (23) comprising an input terminal (37, 38) connected to the battery (16) and an output terminal (33, 34) connected to the second power input terminal (131) of the converter (13), the rotating electric machine (5) comprising two groups of redundant stator coils (9, 11), the first group of stator coils (11) being connected to the power output terminal (134), and the second group of stator coils (9) being connected to the second power output terminal (133) of the converter (13).

6. The electric propulsion chain according to claim 3 or 5, further comprising a redistribution contactor (79), wherein the redistribution contactor (79) connects the power supply bus (53) of the power supply line (24) to the power supply bus (52) of the second power supply line (23), and the control circuit (43) is further configured to control the redistribution contactor.

7. The electric propulsion chain (2) according to any one of claims 1 to 6, wherein: The control circuit (43) is further configured to control the grounding unit (3) to supply power to the grounding connector (42) when the pusher propeller (100) is prevented from rotating.

8. An aircraft (1), comprising an electric propulsion chain (2) according to any one of claims 1 to 7 and the same number of propulsion nacelles (6, 7) as propulsion rotary electric machines (4, 5), each electric machine being arranged in a different nacelle, the device for deactivating the propulsion propeller and the ground connection (42) being arranged in one of the nacelles (7).

9. A method for charging a battery (15, 16) of an aircraft (1), the aircraft (1) comprising: A reversible electric power converter (13), the reversible electric power converter (13) comprising a power input terminal (132) connected to the battery (16) and a power output terminal (134) connected to the propulsion rotary motor (5) of the aircraft, so that the power converter transmits electric energy between the motor and the battery; a second propulsion rotary motor (4); a second power converter (12); a second battery (15); and a power distribution device (14), the power distribution device (14) comprising a power supply line (23), the power supply line (23) comprising an input terminal (37, 38) connected to the battery (16) and an output terminal (134) connected to the power input terminal (132) of the converter (13). 35, 36), a second power supply line (22), the second power supply line including an input terminal (31, 32) connected to the second battery (15) and an output terminal (27, 28) connected to a power input terminal (122) of a second converter, and a distribution contactor (80), each power supply line including a power supply bus (53, 52), a first voltage sensor (65, 63), a second voltage sensor (73, 71), a first current sensor (67, 69) and a second current sensor (75, 77), the power supply bus (53, 52) being connected to the input terminal of the power supply line through a first contactor (57, 55) and connected to the power supply bus through a second contactor (61, 59). The method comprises: a first voltage sensor (65, 63) measuring a voltage between the input terminal and the first contactor, a second voltage sensor (73, 71) measuring a voltage between the second contactor and the converter, a first current sensor (67, 69) measuring a current between the first contactor and the bus, and a second current sensor (75, 77) measuring a current between the second contactor and the converter connected to the power supply line, the distribution contactor connecting the power supply bus of the first power supply line to the power supply bus of the second power supply line, the method comprising: activating a device for deactivating a propulsion propeller to prevent the propulsion propeller (1 00), and when the rotation of the pusher propeller is prevented, power is supplied to the grounding connector (42) connected to the power output terminal so that the power converter transmits the electric energy from the grounding connector to the battery, closes the second contactor (61) of the power supply line (24) and the redistribution contactor (80), opens the second contactor (59) of the second power supply line (22), and controls the power converter (13) according to the values ​​measured by the first current sensor and the first voltage sensor and the second current sensor and the second voltage sensor of the power supply line and the second power supply line so that the power converter transmits the electric energy from the grounding connector to the second battery.

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