Aircraft propulsion apparatus

Abstract

The invention relates to an aircraft propulsion apparatus (E) having first and second nacelles (1a, 1b), each nacelle comprising a thrust reversal system comprising at least two movable cowls (4a, 4b, 5a, 5b) which are movable under the action of at least one means for actuating the given nacelle between a closed position and an open position. The means for actuating the first nacelle comprises a first electric motor (80a) for moving some of the cowls of the first nacelle, and the means for actuating the second nacelle comprises at least a first electric motor (80b) for moving at least some of the cowls (4b, 5b), the apparatus also comprising a power control unit (90) for powering the electric motors of the two nacelles (1a, 1b).

Description

[0001] EQUIPMENT FOR AIRCRAFT PROPULSION

[0002] The present invention relates to the field of equipment for the propulsion of an aircraft, such equipment comprising at least two nacelles each intended to receive a turbojet engine, each nacelle having a rear section equipped with at least one thrust reverser system.

[0003] BACKGROUND OF THE INVENTION

[0004] We know, for example from patent document FR2927310A1, from the same applicant, of equipment for the propulsion of an aircraft comprising at least a first nacelle 1a to receive a first turbojet 3a and a second nacelle 1b to receive a second turbojet 3b.

[0005] Each given nacelle comprises: a forward air intake section, - a midsection designed to surround and house a fan of the turbojet engine associated with the given nacelle; and

[0006] a rear section equipped with at least one thrust reversing system.

[0007] Each thrust reversal system includes: - on the one hand, means for diverting at least part of an airflow from the turbojet associated with the given nacelle; and - on the other hand, at least two movable cowlings.

[0008] Each movable hood of the given nacelle is capable of moving, under the action of at least one electromechanical actuation means of the given nacelle, alternately from a closed position, in which it ensures the aerodynamic continuity of the given nacelle and in which the deflection means are inactive, to an open position in which it opens a passage in the given nacelle and in which the deflection means are active. The electromechanical actuation means of the given nacelle is controlled by a power control unit associated with the given nacelle which allows the movement of the hoods of the given nacelle to be controlled according to a control signal delivered by a computer.

[0009] The computer commands the power control units of the two nacelles to move the cowlings to their respective closed positions adopted for example during the flight of the aircraft (the propulsion delivered by the turbojets is then essentially directed towards the rear of the aircraft to propel it) or to their open positions when it is desired that at least part of the flow generated by the turbojets be directed towards the front of the aircraft to assist its deceleration.

[0010] The cowlings are in their open positions during the aircraft braking phase, once the aircraft is moving on the ground.

[0011] Thrust reversal systems are therefore useful for reducing the aircraft's braking distance, limiting brake and wheel wear, and reducing fuel consumption due to the decrease in the time required to brake the aircraft.

[0012] Such equipment for aircraft propulsion is particularly useful and efficient.

[0013] It would be useful to optimize such equipment to reduce production costs and / or simplify maintenance.

[0014] SUBJECT OF THE INVENTION

[0015] An object of the present invention is to provide equipment for the propulsion of an aircraft which resolves or at least mitigates some or all of the aforementioned disadvantages of prior art equipment.

[0016] SUMMARY OF THE INVENTION To this end, the invention relates to equipment for the propulsion of an aircraft comprising at least one first nacelle for receiving a first turbojet engine and a second nacelle for receiving a second turbojet engine, each given nacelle comprising:

[0017] a forward air intake section, - a mid-section designed to surround and house a fan of the turbojet engine associated with the given nacelle; and

[0018] a rear section equipped with at least one thrust reversal system comprising, on the one hand, means for diverting at least part of an airflow from the turbojet associated with the given nacelle, and on the other hand, at least two movable cowlings, each movable cowling of the given nacelle being capable of passing, under the action of at least one electromechanical actuation means of the given nacelle, alternately from a closed position, in which it ensures the aerodynamic continuity of the given nacelle and in which the diverting means are inactive, to an open position in which it opens a passage in the given nacelle and in which the diverting means are active.

[0019] The equipment according to the invention is essentially characterized in that the electromechanical actuation means of the first nacelle includes at least one first electric motor for moving at least one of the hoods of the first nacelle between the closed and open positions, and the electromechanical actuation means of the second nacelle includes at least one first electric motor for moving at least one of the hoods of the second nacelle between the closed and open positions, the equipment also comprising a power control unit capable of transforming an external power supply (for example a high voltage supply and / or a direct current supply) into at least one power supply (for example an alternating current) for the electric motors of the electromechanical actuation means of the first and second nacelles.

[0020] External power supply is for example a high voltage and / or direct current power supply, while the power supply for electric motors is for example a medium voltage and / or alternating current power supply.

[0021] Thanks to the invention, a single power control unit is used to power all the electric motors of the electromechanical actuation means of the first and second nacelles.

[0022] Thus, thanks to the invention, the single power control unit is shared to power the electric motors of the two nacelles.

[0023] The invention makes it possible to optimize the power supply architecture of the motors since it allows to connect external power supply, for example a power supply delivered by an electrical generation system of the aircraft (for example high voltage direct current) to a single power control unit of the propulsion equipment which is dedicated to supplying all the electric motors of the two nacelles to move the movable cowlings of at least two nacelles.

[0024] This single power control unit allows for the selective control of the deflection of at least a portion of the airflow from the first turbojet and the selective control of the deflection of at least a portion of the airflow from the second turbojet. The invention also allows for architectural optimization of the equipment for the propulsion of an aircraft and consequently for architectural optimization at the aircraft / plane level.

[0025] Preferably, the power control unit is adapted to deliver power to the electric motors of the first nacelle independently of power to the electric motors of the second nacelle, so as to be able to move one or more of the hoods of one of said nacelles independently of a movement of one or more of the hoods of the other of said nacelles.

[0026] Thus, the power control unit of the equipment according to the invention can, depending on the need to control the electromechanical actuation means of the first and second nacelles: - move one or more of the hoods of one of the nacelles while keeping one or more of the hoods of the other nacelle immobile (the movements of the hoods of the nacelles can be carried out hood by hood or nacelle by nacelle according to a desired sequence of hood movements); or supply all the motors at the same time to synchronize the movements of the hoods of the first nacelle with the movements of the hoods of the second nacelle.

[0027] In this respect, the power control unit, even if it is adapted to electrically power the motors of both nacelles, also allows each electric motor of any one of the nacelles to be powered independently of the power supply of any other electric motor of any one of the nacelles.

[0028] The power supply for the thrust reversal system motors of the first and second nacelles is thus optimized since it only requires a single power control unit capable of supplying all the electric motors of the reversal systems of both nacelles on its own.

[0029] The invention allows for a mass reduction in the power control function for motor supply.

[0030] The equipment according to the invention is simplified and optimized without compromising the services provided by each thrust reversal system.

[0031] Maintenance of the equipment according to the invention is also simplified because the number of power control units to be maintained is reduced to a minimum (the same control unit can control both nacelles).

[0032] Furthermore, in the event of failure of the power control unit, this does not generate an additional critical risk to the aircraft compared to an aircraft which would have propulsion equipment with a first power control unit dedicated to the actuation of electric motor(s) of the first nacelle and a second power control unit dedicated to the actuation of electric motor(s) of the second nacelle.

[0033] With the equipment according to the invention, the power supply of the motors of the two thrust reversal systems of the nacelles is optimized, the power control unit being common to both nacelles.

[0034] In the event of a failure of this power control unit, the failure applies simultaneously to both thrust reversal systems, which eliminates any risk of unintentional asymmetrical actuation of the hoods of the first and second nacelles.

[0035] The equipment according to the invention is therefore optimized without adding any critical risk to the aircraft. Furthermore, as the power control unit is not integrated into the nacelle and is developed to power electric motors from several nacelles, it can be developed to power different types of motors from different nacelle architectures.

[0036] A power control unit adaptable to several types of motors or adaptable to several types of nacelles can be certified on its own, independently of the certification of the nacelles or the motors.

[0037] The certification operations of a nacelle can thus be simplified / carried out at a lower cost, because the same power control unit can be certified from the outset for a whole range of nacelles and / or a whole range of electric motors.

[0038] BRIEF DESCRIPTION OF THE DRAWINGS

[0039] Other features and advantages of the invention will become clear from the description given below, by way of example and not limitation, with reference to the accompanying drawings, in which:

[0040] [Fig. 1] Figure 1 is a schematic representation of a first embodiment of the equipment E according to the invention in which each nacelle la, 1b comprises a single electric motor 80a, 80b, the electric motors being controlled by the power control unit 90 common to both nacelles;

[0041] [Fig. 2] Figure 2 is a schematic representation of a second embodiment of the equipment E according to the invention in which each nacelle la, 1b comprises a single electric motor 80a, 80b, the electric motors being controlled by the power control unit 90, each hood given 4a, 5a, 4b, 5b of a nacelle given la, 1b is connected to the single motor given 80a, 80b of the nacelle given via two mechanical cylinders 6a, 6a2, 7a, 7a2, 6b, 6b2, 7b, 7b2 per hood to be moved (in other words each nacelle comprises an electric motor to actuate two hoods by means of two cylinders per hood to be actuated);

[0042] [Fig. 3] Figure 3 is a schematic representation of a third embodiment of the equipment E according to the invention in which each nacelle la, 1b has two electric motors per nacelle (80a, 80a2 for the first nacelle la and 80b, 80b2 for the second nacelle 1b), each of these motors is dedicated to the actuation of only one of the hoods associated with it, by means of two mechanical cylinders per hood to be actuated / moved;

[0043] [Fig. 4] Figure 4 illustrates an aircraft 1000 according to the invention equipped with equipment E according to the invention.

[0044] DETAILED DESCRIPTION OF THE INVENTION

[0045] With reference to figures 1, 2 and 3, the invention relates to equipment E for the propulsion of an aircraft 1000 comprising at least a first nacelle 1a for receiving a first turbojet 3a and a second nacelle 1b for receiving a second turbojet 3b.

[0046] Each nacelle given la, 1b comprises: a forward air intake section, - a midsection intended to surround and receive a fan of the turbojet associated with the given nacelle (a fan of the first turbojet 3a being positionable in the midsection of the first nacelle la and a fan 3b of the second turbojet 3b being positionable in the midsection of the second nacelle 1b); and a rear section equipped with at least one thrust reverser system. Each thrust reverser system is specific to only one of the nacelles and comprises: - on the one hand, means for diverting at least a part of an airflow from the turbojet associated with the given nacelle; and - on the other hand, at least two movable cowlings 4a, 4b (for the first nacelle la) and 5a, 5b (for the second nacelle 1b).

[0047] Each movable hood of the given nacelle is capable of passing, under the action of at least one electromechanical actuation means of the given nacelle (6a, 6b, 7a, 7b) alternately from a closed position, in which it ensures the aerodynamic continuity of the given nacelle and in which the deflection means are inactive, to an open position in which it opens a passage in the given nacelle and in which the deflection means are active.

[0048] The thrust reverser system can be of the grid reverser type (also called "transcowl", in which case each movable cowl selectively closes a passage through which the airflow from the turbojet passes, after this flow has passed through a grid to deflect the airflow towards the front of the aircraft) or of the door reverser type (in this case, a movable cowl is a steerable door to selectively close the passage of the airflow generated by the turbojet, the cowl in the open position also being positioned to deflect the airflow flowing through the passage towards the front of the aircraft).

[0049] In other words: when a given cowl of a given nacelle is in the closed position (for example during the takeoff or flight phases of the aircraft), this given cowl then ensures the aerodynamic continuity of the given nacelle and the means of deflecting the given nacelle are inactive so as to prohibit the deflection of a flow generated by the turbojet associated with the given nacelle and maximize a flow towards the rear of the aircraft equipped with the given nacelle;

[0050] when a given cowling of a given nacelle is in the open position (for example during the landing of the aircraft, during a braking phase of the aircraft), the given cowling then opens a passage in the given nacelle and the means of deflecting the given nacelle are active so as to deflect at least a part of an airflow from the turbojet associated with the given nacelle to generate a reverse thrust directed towards the front of the aircraft.

[0051] In this description, references with the letter "a" denote elements belonging to the first nacelle 1a and references with the letter "b" denote elements belonging to the second nacelle 1b.

[0052] According to the invention, in accordance with the equipment illustrated in figures 1 to 3, the electromechanical actuation means of the first nacelle comprises at least a first electric motor 80a to move at least one of the hoods of the first nacelle between the closed and open positions.

[0053] Similarly, the electromechanical actuation means of the second nacelle includes at least one first electric motor 80b to move at least one of the hoods 4b, 5b of the second nacelle 1b between the closed and open positions.

[0054] Equipment E also includes a power control unit 90 capable of transforming an external power supply 20 into at least one power supply 31a, 31b, 32a, 32b for the electric motors 80a, 80a2, 80b, 80b2 of the electromechanical actuation means of the first and second nacelles la, 1b. As indicated above, thanks to the invention, a single power control unit 90 is used to power all the electric motors 80a, 80a2, 80b, 80b2 of the electromechanical actuation means of the first and second nacelles la, 1b, which allows a reduction in the number of power control units, a reduction in mass, a limitation of production costs and a simplification of the maintenance of equipment E, without compromising the overall reliability of the equipment for the propulsion of the aircraft.

[0055] Equipment E for aircraft propulsion 1000 according to the invention is therefore optimized without adding critical risk to the aircraft.

[0056] In each of the embodiments illustrated in figures 1 to 3, the equipment E also includes at least one control unit 100 to control said power control unit 90.

[0057] The pilot unit 100 includes: - at least one control input 91a, 91b to receive at least one control signal SI from the thrust reversing systems; and - at least one pilot output 41 connected to a pilot input 42 of the power control unit 90.

[0058] The control unit 100 is adapted to deliver to the power control unit 90, via said control output 41 and said at least one control input 42, a control signal S2.

[0059] This control signal S2 is generated by the control unit 100 as a function of at least said control signal SI.

[0060] The power control unit 90 is here adapted to deliver said at least one power supply to the electric motors 80a, 80a2, 80b, 80b2 according to the control signal S2 generated by the control unit 100.

[0061] This embodiment allows for a control unit 100, which is powered via its own power supply input 10, electrically separate from the power control unit 90 which is powered by another external power supply 20.

[0062] This is particularly useful because the control unit 100 generally requires for its operation a first electric current (passing through the power supply input 10) whose characteristics differ from the values ​​of the external power supply 20 received by the power control unit 90 to power the electric motors 80a, 80b, 80a2, 80b2.

[0063] With this embodiment, depending on the control signal SI of the thrust reversal systems of the first and second nacelles la, 1b, the control unit 100 generates a control signal S2 which is transmitted to the power control unit 90 which, in turn, depending on the control signal S2 transforms an external power supply 20 into power supplies 31a, 31b, 32a, 32b for the electric motors 80a, 80a2, 80b, 80b2 of the nacelles.

[0064] This power supply to the nacelle motors is adapted to induce a movement of the motors to move the movable hoods of the two nacelle thrust reversal systems between their respective open and closed positions.

[0065] In this embodiment, when the conditions for controlling the movement of the hoods 4a, 5a, 4b, and 5b from their closed positions to their respective open positions are met (i.e., at least when the landing gear 101 of the aircraft 1000 has extended and a taxi speed of the aircraft below a predetermined threshold is detected), the control signal SI can be generated by at least one control unit 22, 23 external to the piloting unit 100 of the equipment E according to the invention. Depending on the embodiment, the control signal can take several alternative forms depending on whether it is desired to control the movement of all the hoods or, where applicable, the movement of at least some of the hoods of the equipment E.

[0066] In certain equipment architectures, it is possible to arrange the control signal SI to control the movement of one or more hoods while one or more other hoods of the equipment E remain stationary.

[0067] In other architectures of the equipment E, it is possible to arrange the control signal SI to control a symmetrical movement between the hoods of the first nacelle 1a and the hoods of the second nacelle 1b.

[0068] The control unit 22 or 23 can be arranged so that the SI control signal is generated only if a thrust reverser command has been activated at the flight deck / cockpit of aircraft 1000.

[0069] A control unit 22, 23 could be either an aircraft main computer or an aircraft FADEC-type computer, having two symmetrical communication channels 22, 23 each connected to the control unit 100 to deliver the SI signal.

[0070] The term FADEC is an acronym for "Full Authority Digital Engine Control," which is a system that interfaces between the cockpit's human-machine interface controls and an aircraft engine to pilot it (by aircraft engine, we mean the turbojet and the nacelle containing the engine, including the thrust reverser system).

[0071] This embodiment allows redundancy in the transmission and reception capacity of the SI control signal which can be transmitted by the FADEC to the control unit 100, indifferently via channel 22 and / or channel 23.

[0072] The pilot unit 100 can be arranged to command the power control unit 90 to generate the S2 signal to move the hoods 4a, 5a, 4b, 5b of the thrust reversing systems, provided that it receives at least one SI signal.

[0073] Preferably, the power control unit 90 and said at least one control unit 100 are placed in a housing 9 having connection means for selectively connecting, electrically, the power control unit 90 to the first electric motor 80a of the actuation means of the first nacelle via first electrical conductors (i.e. the conductors of the supply 31a) and to the first electric motor 80b of the actuation means of the second nacelle 1b via second electrical conductors (i.e. the conductors of the supply 31b).

[0074] With this embodiment of the invention, the housing which receives the piloting units 100 and power control units 90 makes it possible to increase the level of electrical safety in the aircraft since on the one hand it protects these units 100 and 90 against electrical risk factors coming from the external environment of the housing and on the other hand it protects the external environment of the housing 9 against electrical risk factors generated by the units 90, 100 contained in the housing 9.

[0075] Furthermore, with such an arrangement of units 90, 100 in the same case 9, maintenance operations are greatly simplified since in the event of failure of one of the units contained in the case 9, it is simply possible to disconnect the connecting means to remove the case 9 and replace it with a new case containing similar functional units.

[0076] This saves maintenance time and the most complex maintenance operations can be carried out in the workshop, with specialized benches, while limiting the downtime for maintenance of the aircraft 1000.

[0077] In a particular mode, unit 100 can be arranged to directly receive the external power supply 20 and to serve both as a power transformation stage and as a logic stage delivering the signal S2 to the power control unit 90 with the energy required to actuation the motors, unit 90 being dedicated to motor control.

[0078] In this example: - unit 100 ensures the transformation of the energy supplied by an external source via the power supply 20, by converting a current received from the power supply 20 (for example a direct current) into a current suitable for supplying the electric motors (for example an alternating current); - unit 100 also develops the control logic of the inverters based on the SI signals coming from channels 22 and 23 (Each inverter is preferably independent in this logic development); - unit 90 receives the energy from unit 100 and the motor control commands (signal S2) in order to control, preferably independently of each other, the motors 80a and 80b according to the signal S2.

[0079] Preferably, the thrust reversal system of the first nacelle la includes a first mechanical cylinder 6a mechanically linking the first electric motor 80a of the first nacelle la to a first of said movable hoods 4a of the first nacelle la to move it in response to an actuation of the first electric motor 80a.

[0080] Similarly, the thrust reversal system of the second nacelle 1b preferentially includes a first mechanical cylinder 6b mechanically linking the first electric motor 80b of the second nacelle 1b to a first of said movable hoods 4b of the second nacelle 1b to move it in response to an actuation of the first electric motor 80b of the second nacelle 1b.

[0081] The use of a mechanical jack to connect a given electric motor to a given hood makes it possible to amplify an actuation force generated by the motor to control the movement of the given hood, while prohibiting the possibility of the motor moving in response to a force applied to the given hood.

[0082] To this end, the mechanical jack may include, for example, a screw-nut system, or another system such that a force generated by the movable hood connected to the jack cannot move the electric motor connected to the jack, while any movement of the motor induces a rotation of the screw relative to the nut to move the corresponding movable hood.

[0083] In a particular embodiment, each cylinder can be configured so that, in the absence of actuation of the motor to which it is connected, it opposes any movement of the hood to which it is connected.

[0084] Furthermore, each given nacelle of the equipment according to the invention may also include a movable locking device (not shown) between:

[0085] a locking configuration in which the locking device opposes any movement of the hoods of the given nacelle relative to the rest of the nacelle; and a release configuration in which the locking device permits movement of the hoods of the given nacelle under the effect of the actuation of the electric motor(s) of the given nacelle.

[0086] This locking device is preferably monostable in the locking configuration and is driven by an element contained in the housing 9 (for example the control unit 100 or another computing unit) to switch from the locking configuration to the release configuration.

[0087] In the embodiments of figures 1 to 2, the thrust reversal system of the first nacelle la includes a second mechanical actuator 7a mechanically linking the first electric motor 80a of the first nacelle la to a second of said movable hoods 5a of the first nacelle la to move it in response to an actuation of the first electric motor 80a of the first nacelle la.

[0088] Similarly, the thrust reversal system of the second nacelle 1b includes a second mechanical actuator 7b mechanically linking the first electric motor 80b of the second nacelle 1b to a second of said movable hoods 5b of the second nacelle 1b to move it in response to an actuation of the first electric motor 80b of the second nacelle 1b.

[0089] According to this embodiment illustrated in Figures 1 and 2, each given motor of a given nacelle is mechanically connected to two mechanical cylinders to actuate:

[0090] - on the one hand the first movable hood of this given nacelle by means of the first cylinder of this given nacelle; and - on the other hand the second movable hood of this given nacelle by means of the second cylinder of this given nacelle.

[0091] In this way, a single power control unit 90, which supplies at least one electrical supply to the first motors 80a, 80b of the first and second nacelles 1a, 1b, can by itself control:

[0092] on the one hand the simultaneous movement of the first and second hoods 4a, 5a of the first nacelle 1a; and - on the other hand the simultaneous movement of the first and second hoods 4b, 5b of the second nacelle 1b.

[0093] This method of implementation is particularly economical and secure because it allows:

[0094] on the one hand to prohibit any possibility of having asynchronous actuation between the first and second hoods of the same nacelle (all hoods connected to the same motor of a nacelle necessarily move together, the mechanical cylinders prevent a desynchronization of the movements between the hoods of the same nacelle); and - on the other hand to synchronize, or at least sequence, using the same control unit 90, which controls the motors 80a, 80b of the two nacelles la, 1b, the movements of the hoods of one of the nacelles with respect to the movements of the hoods of the other of the nacelles.

[0095] In the embodiment illustrated in Figure 2, the thrust reversal system of the first nacelle la includes a third mechanical cylinder 6a2 mechanically linking the first electric motor 80a of the first nacelle la to the first of said movable hoods 4a of the first nacelle la to move it, the first and third cylinders 6a, 6a2 being actuated together by the first electric motor 80a of the first nacelle la to move the first hood 4a of the first nacelle la together under the effect of the actuation of the first electric motor 80a of the first nacelle la. Also in the embodiment illustrated in Figure 2, the thrust reversal system of the second nacelle 1b includes a third mechanical cylinder 6b2 mechanically linking the first electric motor 80b of the second nacelle 1b to the first of said movable hoods 4b of the second nacelle 1b to move it.

[0096] The first and third cylinders 6b, 6b2 are actuated together by the first electric motor 80b of the second nacelle 1b to move together the first hood 4b of the first nacelle 1b under the effect of the actuating of the first electric motor 80b of the second nacelle 1b.

[0097] Thus, as illustrated in Figure 2, the first motor 80a of the first nacelle is connected to the first and third mechanical cylinders 6a, 6a2 which are themselves connected to the first hood 4a to move it between its closed and open positions by actuation of the first motor 80a.

[0098] In this way, the forces of displacement of the first hood 4a of the first nacelle la are applied to this hood by two separate cylinders which allows the forces to be distributed on the hood.

[0099] This hood can therefore withstand significant external forces without risk of deformation.

[0100] The same characteristics and advantages apply mutatis mutandis to the second nacelle 1b illustrated in Figure 2, whose first hood 4b is also actuated by the motor 80b via the first and third cylinders 6b, 6b2 of the second nacelle 1b.

[0101] This embodiment allows the same hood to be operated by means of two mechanical cylinders driven by the same motor.

[0102] The two mechanical jacks are driven together by the same electric motor, sized so that it can provide sufficient mechanical power to simultaneously move both hoods of the nacelle.

[0103] As illustrated in Figure 2, the thrust reversal system of the first nacelle la includes a fourth mechanical actuator 7a2 mechanically linking the first electric motor 80a of the first nacelle la to the second of said movable hoods 5a of the first nacelle la to move it.

[0104] The second and fourth jacks 7a, 7a2 are actuated together by the first electric motor 80a of the first nacelle la to move together the second hood 5a of the first nacelle la under the effect of the actuation of the first electric motor 80a of the first nacelle la.

[0105] With reference to the embodiment illustrated in Figure 2, the thrust reversal system of the second nacelle 1b includes a fourth mechanical cylinder 7b2 mechanically linking the first electric motor 80b of the second nacelle 1b to the second of said movable hoods 5b of the second nacelle 1b to move it.

[0106] The second and fourth jacks 7b, 7b2 are actuated together by the first electric motor 80b of the second nacelle 1b to move together the second hood 5b of the second nacelle 1b under the effect of the actuating of the first electric motor 80b of the second nacelle 1b.

[0107] In this embodiment illustrated in Figure 2, the second hood 5a, 5b of a given nacelle la, 1b is actuated by means of two cylinders 7a, 7a2 (for the first nacelle) or 7b 7b2 (for the second nacelle 1b) which are driven together by the same electric motor of the given nacelle.

[0108] As mentioned above, driving a given hood by means of two cylinders coupled to that given hood allows the forces applied to the hood to be distributed between the cylinders, thus limiting the risk of deformation of the hood and / or the cylinders.

[0109] In this embodiment, each nacelle has a single motor enabling the movement of two hoods 4a, 5a (for the first nacelle 1a) or 4b, 5b (for the second nacelle 1b) by means of two mechanical cylinders per hood.

[0110] This results in an economy of means since only one motor is needed per nacelle and since only one power control unit 90 is needed to operate these two electric motors 80a, 80b of the two nacelles la, 1b.

[0111] This embodiment allows synchronization of the movements of all the hoods 4a, 4b, 5a, 5b of the nacelles while having a reduced on-board mass (a single power control unit 90 is used to control the motors).

[0112] With reference to the embodiment of Figure 2, the first electric motor 80a of the first nacelle la is connected to the first mechanical cylinder 6a and to the third cylinder 6a2 of the first nacelle la via a first primary shaft 93a and via a first torque distribution device 6al0 of the first nacelle la distributing a mechanical torque transferred by the first primary shaft 93a to: - on the one hand an actuation shaft of the first mechanical cylinder 6a; and to - on the other hand an actuation shaft of the third mechanical cylinder 6a2.

[0113] The first electric motor 80a of the first nacelle la is also connected to the second mechanical cylinder 7a and the fourth cylinder 7a2 of the first nacelle la via a second primary shaft 92a and via a second torque distribution device 6a20 distributing a mechanical torque transferred by the second primary shaft 92a to: - on the one hand an actuating shaft of the second mechanical cylinder 7a; and to - on the other hand an actuating shaft of the fourth mechanical cylinder 7a2.

[0114] This particular embodiment of the first nacelle illustrated in Figure 2, allows, with a single electric motor 80a controlled by a single power control unit 90, to control in a synchronized manner the movements of the two hoods 4a, 5a of the first nacelle, each given hood of the nacelle being driven in movement between its opening and closing positions by two cylinders connected to this given hood and driven by the single electric motor of the nacelle.

[0115] This improves operational reliability since all the hoods of the same nacelle are necessarily synchronized in their movements because they are mechanically operated by a single motor itself controlled by the single power control unit 90.

[0116] As illustrated on equipment E in Figure 2, the first and second gondolas are arranged symmetrically.

[0117] Thus, the first electric motor 80b of the second nacelle 1b is connected to the first mechanical cylinder 6b of the second nacelle 1b and to the third cylinder 6b2 of the second nacelle 1b via a first primary shaft 93b of the second nacelle 1b and via a first torque distribution device 6bl0 of the second nacelle 1b.

[0118] The first torque distribution device 6bl0 of the second nacelle 1b distributes a mechanical torque transferred by the first primary shaft 93b of the second nacelle 1b to: - on the one hand an actuation shaft of the first mechanical cylinder 6b of the second nacelle 1b; and to - on the other hand an actuation shaft of the third mechanical cylinder 6b2 of the second nacelle 1b.

[0119] The first electric motor 80b of the second nacelle 1b is also connected to the second mechanical cylinder 7b of the second nacelle 1b and to the fourth cylinder 7b2 of the second nacelle 1b via a second primary shaft 92b of the second nacelle 1b and via a second torque distribution device 6b20 of the second nacelle 1b.

[0120] This second torque distribution device 6b20 of the second nacelle 1b is arranged to distribute a mechanical torque transferred by the second primary shaft 92b to: - on the one hand an actuating shaft of the second mechanical cylinder 7b of the second nacelle 1b; and to - on the other hand an actuating shaft of the fourth mechanical cylinder 7b2 of the second nacelle 1b.

[0121] A torque distribution device may include one or more universal joints coupled with a gear transfer box, the box having an input coupled to the engine-side shaft and two distribution outputs, each coupled to its corresponding cylinder.

[0122] The second gondola 1b illustrated in figure 2 is of symmetrical design to the first gondola la, this gondola 1b presenting, mutatis mutandis, the same advantages as those indicated above in relation to the first gondola la.

[0123] The fact that the electric motors 80a, 80b of the two nacelles 1a and 1b are controlled by the same power control unit 90 contributes to the quality of the synchronization of the movements of the hoods of the two nacelles while minimizing the number of power control units 90, which is advantageous in terms of mass and cost. We will now describe the particular embodiment of the equipment E according to the invention illustrated in Figure 3.

[0124] The electromechanical actuation means of the first nacelle includes here, in addition to the said first electric motor 80a, a second electric motor 80a2.

[0125] Similarly, the electromechanical actuation means of the second nacelle 1b includes, in addition to the said first electric motor 80b, a second electric motor 80b2.

[0126] In this particular mode of Figure 3, the thrust reversal system of the first nacelle la includes a first mechanical actuator 6a mechanically linking the first electric motor 80a of the first nacelle la to a first of said movable hoods 4a of the first nacelle la to move it between the open and closed positions in response to an actuation of the first electric motor 80a by the power control unit 90.

[0127] The thrust reversal system of the first nacelle la includes a second mechanical actuator 7a which mechanically links the second electric motor 80a2 of the first nacelle la to a second of said movable hoods 5a of the first nacelle la to move it between the open and closed positions in response to an actuation of the second electric motor 80a2 by the power control unit 90.

[0128] Similarly, the thrust reversal system of the second nacelle 1b includes a first mechanical actuator 6b mechanically linking the first electric motor 80b of the second nacelle 1b to a first of said movable hoods 4b of the second nacelle 1b to move it between the open and closed positions in response to an actuation of the first electric motor 80b of the second nacelle 1b by the power control unit 90. The thrust reversal system of the second nacelle 1b also includes a second mechanical actuator 7b mechanically linking the second electric motor 80b2 of the second nacelle 1b to a second of said movable hoods 5b of the second nacelle 1b to move it between the open and closed positions in response to an actuation of the second electric motor 80b2 of the second nacelle 1b by the power control unit 90.

[0129] With this embodiment illustrated in Figure 3, a single power control unit 90 is capable of controlling the first and second electric motors 80a, 80a2 of the first nacelle la (via the power supply 31a for the first electric motor 80a of the first nacelle la and via the power supply 32a for the second electric motor 80a2 of the first nacelle la) and the first and second electric motors 80b, 80b2 of the second nacelle 1b (via the power supply 31b for the first electric motor 80b of the second nacelle 1b and via the power supply 32b for the second electric motor 80b2 of the second nacelle 1b) in order to, on the one hand,that the hoods of the first nacelle (1a) move simultaneously to their open or closed positions, and that, on the other hand, the hoods of the second nacelle (1b) move simultaneously to their open or closed positions.

[0130] As mentioned above, the hoods of the first gondola may or may not be moved at the same time as the hoods of the second gondola.

[0131] In a particular case, the power control unit 90, for example as a function of said pilot signal S2 emitted by the pilot unit 100, can command the simultaneous movement of the hoods of the two nacelles towards their closed position or towards their open positions.

[0132] The said control signal S2 is for example emitted by the control unit 100 as a function of a control signal SI of the thrust reversal systems received by the control unit 100.

[0133] In this embodiment of the invention, each given motor of the equipment E is associated with a single hood which it moves between its opening and closing positions by means of two mechanical cylinders connecting the given motor to the hood which it moves.

[0134] So :

[0135] - the first motor 80a of the first nacelle la is connected to the first hood 4a of the first nacelle by means of two mechanical cylinders 6a, 6a2 actuated together by this motor 80a; - the second motor 80a2 of the first nacelle la is connected to the second hood 5a of the second nacelle 1b by means of two other mechanical cylinders 7a, 7a2 actuated together by this motor 80a2; - the first motor 80b of the second nacelle 1b is connected to the first hood 4b of the second nacelle 1b by means of two mechanical cylinders 6b, 6b2 actuated together by this motor 80b; - the second motor 80b2 of the second nacelle 1b is connected to the second hood 5b of the second nacelle 1b by means of two other mechanical cylinders 7b, 7b2 operated together by this motor 80b2.

[0136] Finally, with reference to each of the embodiments illustrated in figures 1 to 3, the equipment E according to the invention also includes a plurality of sensors Cia, C2a, Clb, C2b each communicating with the power control unit 90 to deliver signals S3 representative of current positions adopted by the hoods 4a, 5a, 4b, 5b of the first and second nacelles la, 1b.

[0137] The position, nature and number of sensors may vary depending on considerations relating to overall integration and the expected performance in terms of detection functions by these sensors.

[0138] For example, some of these sensors could be integrated into electric motors so that a given sensor can directly measure the displacements of the motor in which it is integrated.

[0139] In each of these embodiments: - the current position of the first hood 4a of the first nacelle la (which can be the open and / or closed position) is detected by at least one first sensor Cia of the first nacelle la; - the current position of the second hood 5a of the first nacelle la (which can be the open and / or closed position) is detected by at least one second sensor C2a of the first nacelle la; - the current position of the first hood 4b of the second nacelle 1b which can be the open and / or closed position is detected by at least one first sensor Clb of the second nacelle 1b; - the current position of the second hood 5b of the second nacelle 1b which can be the open and / or closed position is detected by at least one second sensor C2b of the second nacelle 1b.

[0140] The power control unit 90 controls the electric motors of the nacelles and moves all the hoods to their closed or open positions according to the pilot signal.

[0141] The power control unit can use the S3 signals representing current positions respectively adopted by the hoods 4a, 5a, 4b, 5b to interrupt the power supply to the motor(s) of a given nacelle when the position of the hoods of that given nacelle reaches the expected open or closed position and conforms to the control signal SI.

[0142] In other words, the power control unit 90 is arranged to drive the nacelle motors by a closed loop servo using at least the S3 signals generated by the sensors Cia, C2a, Clb, C2b.

[0143] The plurality of sensors may include other types of sensors such as proximity sensors of hoods relative to their open and / or closed positions, locking sensors of each hood in its closed and / or open positions, electrical power sensors consumed by the motors, electrical voltage and / or current sensors, motor temperature sensors, the closed loop control being able to use signals generated by all or part of these sensors.

[0144] It should be noted that if the said S3 signals representing current positions respectively adopted by the hoods 4a, 5a, 4b, 5b, are here delivered to the power control unit 90, in certain particular embodiments, it could be made that they are delivered to the pilot unit 100.

[0145] Figure 4 depicts an aircraft 1000 according to the invention comprising:

[0146] - said equipment E according to any one of the embodiments illustrated above or claimed; - the first turbojet 3a is received in the first nacelle 1a; - the second turbojet 3b is received in the second nacelle 1b.

[0147] The power control unit 90 is here integrated into a housing 9 which is at a distance from the two nacelles la, 1b, i.e. in an area of ​​the aircraft protected from the main vibrations generated by the turbojets 3a, 3b.

[0148] In this instance, housing 9 is located closer to the aircraft cockpit than to the nacelles.

[0149] This aircraft 1000 has all the aforementioned advantages with reference to equipment E according to the invention.

[0150] The invention thus allows a mass saving for the aircraft, without compromising the possibility of controlling a synchronized and safe movement of all the engines and cowlings.

[0151] Of course, the power control unit can also be arranged so that when it receives a particular signal generated by the pilot unit 100, it only powers some of the thrust reverser motors.

[0152] This capability is useful, for example, for testing engines independently of each other, for example during aircraft ground maintenance operations.

[0153] Finally, even though the aircraft propulsion equipment presented above comprises two nacelles, it should be noted that the invention also extends to aircraft propulsion equipment that comprises more than two nacelles (for example 3 nacelles or 4 nacelles or more), each nacelle of the equipment according to the invention conforming to the definition given above, for example in the "summary of the invention" section.

[0154] Each given nacelle of the equipment according to the invention includes an electromechanical actuation means for the given nacelle comprising at least a first electric motor for moving at least one of the hoods of the given nacelle between the closed and open positions.

[0155] The said power control unit of the equipment according to the invention is suitable, i.e. adapted, to transform said external power supply into at least one power supply for the electric motors of the electromechanical actuation means of said nacelles of the equipment.

[0156] It should be noted that the arrangement on the aircraft of the pods of the equipment according to the invention may conform to the arrangement illustrated in Figure 4 (i.e. the first pod fixed under the right wing of the aircraft and the second pod fixed under the left wing of the aircraft), or may be different without departing from the scope of the invention.

[0157] For example, several nacelles can be fixed under a given wing of the aircraft, a given nacelle can be fixed on a structure of the aircraft, away from the wings (for example one or more nacelles can be placed in a plane of longitudinal symmetry of the fuselage and / or on either side of this plane of longitudinal symmetry of the fuselage, for example at a portion of the aircraft behind the wings).

[0158] Thus, the equipment according to the invention may comprise more than two nacelles, all of these nacelles being distributed in various locations of the aircraft in order to be able to selectively generate thrust or thrust reversal forces.

[0159] Finally, a means of actuation of a given nacelle may be of the "electromechanical means of actuation" type, as described previously, possibly being equipped with an electronic controller coupled with the electric motor(s) of the means of actuation or possibly including a pneumatic type controller.

[0160] The invention is intended for equipment with electromechanical actuators but it could also be extended to equipment with other types of actuators controlled by said power control unit, such as electropneumatic actuators.

Claims

DEMANDS 1. Equipment (E) for the propulsion of an aircraft (1000) comprising at least a first nacelle (la) for receiving a first turbojet engine (3a) and a second nacelle (1b) for receiving a second turbojet engine (3b), each given nacelle comprising: a forward air intake section, - a mid-section designed to surround and house a fan of the turbojet engine associated with the given nacelle; and a rear section equipped with at least one thrust reversal system comprising, on the one hand, means for diverting at least a portion of the airflow from the turbojet associated with the given nacelle, and on the other hand, at least two movable cowlings (4a, 4b, 5a, 5b), each movable cowling (4a, 4b, 5a, 5b) of the given nacelle being capable of passing, under the action of at least one actuating means of the given nacelle (6a, 6b, 7a, 7b), alternately from a closed position, in which it ensures the aerodynamic continuity of the given nacelle and in which the diverting means are inactive, to an open position in which it opens a passage in the given nacelle and in which the diverting means are active, characterized in that the actuating means of the first nacelle comprises at least a first electric motor (80a) for move at least one of the hoods of the first nacelle between the closed and open positions,and the actuation means for the second nacelle includes at least one first electric motor (80b) for moving at least one of the hoods (4b, 5b) of the second nacelle (1b) between the closed and open positions, the equipment also including a power control unit (90) capable of transforming an external power supply (20) into at least one power supply (31a, 31b, 32a, 32b) for the electric motors (80a, 80a2, 80b, 80b2) of the actuation means for the first and second nacelles (1a, 1b).

2. Equipment (E) according to claim 1, wherein: - the thrust reversal system of the first nacelle (la) comprises a first mechanical actuator (6a) mechanically connecting the first electric motor (80a) of the first nacelle (la) to a first of said movable hoods (4a) of the first nacelle (la) to move it in response to an actuation of the first electric motor (80a) by the power control unit (90); and wherein - the thrust reversal system of the second nacelle (lb) includes a first mechanical jack (6b) mechanically linking the first electric motor (80b) of the second nacelle (1b) to a first of said movable hoods (4b) of the second nacelle (1b) to move it in response to an actuation of the first electric motor (80b) of the second nacelle (1b) by the power control unit (90).

3. Equipment (E) according to any one of claims 1 or 2, wherein said power control unit (90) is placed in a housing (9) having connection means for selectively connecting, electrically, the power control unit (90) to the first electric motor (80a) of the first nacelle (la) via first electrical conductors (31a) and to the first electric motor (80b) of the second nacelle (1b) via second electrical conductors (31b).

4. Equipment (E) according to claim 3, also comprising at least one control unit (100) for controlling said power control unit (90), the control unit (100) being placed in said housing (9) and comprising: - at least one control input (91a, 91b) to receive at least one control signal (SI) from the thrust reversing systems; and - at least one pilot output (41) connected to a pilot input (42) of the power control unit (90); the control unit (100) being adapted to deliver to the power control unit (90), via said control output (41) and said at least one control input (42), a control signal (S2) function of at least said control signal (SI), the power control unit (90) being adapted to deliver said at least one power supply to the electric motors (80a, 80a2, 80b, 80b2) according to the control signal (S2) generated by the control unit (100).

5. Equipment (E) according to any one of the preceding claims combined with claim 2, wherein: - the thrust reversal system of the first nacelle (la) comprises a second mechanical actuator (7a) mechanically linking the first electric motor (80a) of the first nacelle (la) to a second of said movable hoods (5a) of the first nacelle (la) for moving it in response to an actuation of the first electric motor (80a) of the first nacelle (la), and wherein - the thrust reversal system of the second nacelle (lb) comprises a second mechanical actuator (7b) mechanically linking the first electric motor (80b) of the second nacelle (1b) to a second of said movable hoods (5b) of the second nacelle (1b) for moving it in response to an actuation of the first electric motor (80b) of the second gondola (1b).

6. Equipment (E) according to claim 5, wherein: - the thrust reversal system of the first nacelle (la) comprises a third mechanical cylinder (6a2) mechanically linking the first electric motor (80a) of the first nacelle (la) to the first of said movable hoods (4a) of the first nacelle (la) for moving it, the first and third cylinders (6a, 6a2) being actuated together by the first electric motor (80a) of the first nacelle (la) to move the first hood (4a) of the first nacelle (la) together under the effect of the actuation of the first electric motor (80a) of the first nacelle (la), and wherein - the thrust reversal system of the second nacelle (lb) comprises a third mechanical cylinder (6b2) mechanically linking the first electric motor (80b) of the second gondola (1b) to the first of said movable hoods (4b) of the second gondola (1b) to move it,the first and third cylinders (6b, 6b2) being actuated together by the first electric motor (80b) of the second nacelle (1b) to move together the first hood (4b) of the first nacelle (1b) under the effect of the actuating of the first electric motor (80b) of the second nacelle (1b).

7. Equipment (E) according to claim 6, wherein: - the thrust reversal system of the first nacelle (la) comprises a fourth mechanical cylinder (7a2) mechanically linking together the first electric motor (80a) of the first nacelle (la) to the second of said movable hoods (5a) of the first nacelle (la) to move it, the second and fourth cylinders (7a, 7a2) being actuated together by the first electric motor (80a) of the first nacelle (la) to move together the second hood (5a) of the first nacelle (la) under the effect of the actuation of the first electric motor (80a) of the first nacelle (la),and wherein - the thrust reversal system of the second nacelle(1b) comprises a fourth mechanical jack (7b2) mechanically linking together the first electric motor (80b) of the second nacelle (1b) to the second of said movable hoods (5b) of the second nacelle (1b) for moving it, the second and fourth jacks (7b, 7b2) being actuated together by the first electric motor (80b) of the second nacelle (1b) to move together the second hood (5b) of the second nacelle (1b) under the effect of the actuation of the first electric motor (80b) of the second nacelle (1b).

8. Equipment (E) according to claim 7, wherein: - the first electric motor (80a) of the first gondola (la) is connected to the first mechanical cylinder (6a) and to the third cylinder (6a2) of the first gondola (la) via a first primary shaft (91a) and via a first torque distribution device (6al0) of the first gondola (la) distributing a mechanical torque transferred by the first primary shaft (91a) to on the one hand an actuating shaft of the first mechanical cylinder (6a) and to on the other hand an actuating shaft of the third mechanical cylinder (6a2);and in which - the first electric motor (80a) of the first nacelle (la) is also connected to the second mechanical cylinder (7a) and to the fourth cylinder (7a2) of the first nacelle (la) via a second primary shaft (92a) and via a second torque distribution device (6a20) distributing a mechanical torque transferred by the second primary shaft (92a) to, on the one hand, an actuating shaft of the second mechanical cylinder (7a) and to, on the other hand, an actuating shaft of the fourth mechanical cylinder (7a2).

9. Equipment (E) according to any one of claims 1 to 4 combined with claim 2, wherein: the means of actuation of the first nacelle (the) comprises, in addition to said first electric motor (80a), a second electric motor (80a2); The actuation means for the second nacelle (1b) comprises, in addition to said first electric motor (80b), a second electric motor (80b2); - the thrust reversal system for the first nacelle (la) comprises a second mechanical actuator (7a) mechanically connecting the second electric motor (80a2) of the first nacelle (la) to a second of said movable hoods (5a) of the first nacelle (la) to move it between the open and closed positions in response to an actuation of the second electric motor (80a2) by the power control unit (90); and in which - the thrust reversal system of the second nacelle (lb) includes a second mechanical actuator (7b) mechanically linking the second electric motor (80b2) of the second nacelle (1b) to a second of said movable hoods (5b) of the second nacelle (1b) to move it between the open and closed positions in response to an actuation of the second electric motor (80b2) of the second nacelle (1b) by the power control unit (90).

10. Aircraft (1000) comprising said equipment (E) according to any one of claims 1 to 9, in which the first turbojet (3a) is received in the first nacelle (la) and the second turbojet (3b) is received in the second nacelle (1b).

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