PASSIVE ELECTRICAL POWER GENERATION SYSTEM FOR AN AIRCRAFT

Abstract

The system (2) for passively generating electrical energy for an aircraft (1) comprises a support (4), at least one mobile platform (5) arranged on said support (4) and capable of moving under the effect of a variation in apparent gravity in a direction perpendicular to the support (4), at least one guidance device (6) which connects the support (4) to said platform (5) and which is configured to guide the movement of the platform (5) relative to the support (4), and at least one module (8) for transforming the movement of the platform (5) in the or each guidance means (6) into electrical energy. Figure for the abstract: Figure 1

Description

Title of the invention: PASSIVE ELECTRICAL ENERGY GENERATION SYSTEM FOR AN AIRCRAFT Technical field of the invention

[0001] The present invention relates to the general field of aeronautics. It relates in particular to a system for passively generating electrical energy for an aircraft, an aircraft comprising such a system, as well as a method for passively generating electrical energy. Technical background

[0002] An aircraft, whether a civil transport aircraft or a military aircraft of any type, is equipped with a number of turbomachines that generate the propulsion and maintain the lift of the aircraft necessary for its flight. These turbomachines are generally thermal engines which, depending on the type of propulsion of the aircraft, operate by combustion (and / or afterburning) of large quantities of different fuels, all derived from fossil fuels. During their operation on the ground as well as in the air, aircraft turbomachines emit gases such as carbon dioxide, sulfur dioxide, nitrogen oxide, etc.

[0003] However, these emissions are polluting gases, some of which have a greenhouse effect. The sole use of thermal turbomachines for the propulsion and maintenance of the lift of an aircraft therefore constitutes a source of air pollution through the emissions they emit and also contributes to the depletion of non-renewable resources such as fuels.

[0004] One way of reducing these polluting emissions could be to equip each aircraft with a so-called "hybrid" engine, meaning that the propulsion and maintenance of the aircraft's lift would be ensured by combining an electric motor with the usual thermal engine.

[0005] Generally, the electricity required to operate the electric motor is available in electrical energy accumulators, also called batteries. These batteries are charged before the aircraft takes off and their electrical energy storage capacity depends directly on the number of accumulator cells they contain. Thus, the more cells a battery contains, the more electricity it will be able to supply to the electric motor, but the greater its dimensions and mass will be.

[0006] However, when elements constituting the aircraft have dimensions and / or a mass that is too large, they imply the use of a larger quantity of fossil fuels such as electricity to enable the aircraft to fly. This is also one of the reasons why the dimensions and weight of the elements making up an aircraft, including turbomachines, are constantly being optimized.

[0007] The presence and use of batteries charged before takeoff of the aircraft to provide energy to the electric motor leads to a slight reduction in the consumption of polluting fuels.

[0008] There are autonomous energy storage and release devices, such as that described by document WO 2017 / 013.342-A1, but whose capacities remain limited by their sizes which do not allow them to supply electrical energy to a hybrid engine for example. Summary of the invention

[0009] The present invention aims to overcome this drawback by providing an energy generation system making it possible to directly produce electrical energy during the flight of the aircraft.

[0010] To this end, the invention relates to a system for passively generating electrical energy for an aircraft, in particular a civil or military aircraft.

[0011] According to the invention, the system comprises: - a support extending along a longitudinal axis, - at least one mobile platform arranged on said support and capable of moving relative to said support under the effect of a variation in apparent gravity in a direction perpendicular to said longitudinal axis, - at least one guidance device which connects the support to said platform and which is configured to guide the movement of said platform relative to said support, and - at least one module for transforming the movement of the platform in the or each guidance device into electrical energy.

[0012] Thus, thanks to the invention, the electrical energy produced by the relative movement of the platform with respect to the support can be directly used by an electric motor as by any other electrical equipment on board the aircraft. Furthermore, its production depends only on the variations in speed of the aircraft during its flight. The electrical energy is thus generated passively and depends only on the way in which the crew pilots the aircraft. Furthermore, the production of electrical energy can be repeatable as many times as the aircraft experiences such variations in speed.

[0013] The passive electrical energy generation system may also have one or more of the following characteristics, taken alone or in combination with each other: - it also includes at least one storage unit for said electrical energy generated by the or each transformation module, - the or each guide device comprises a slide-type connection configured to guide said movement of said platform relative to said support by translation in said direction perpendicular to the longitudinal axis, - the or each guide device comprises a ball-joint type connection configured to guide said movement of said platform relative to said support in the direction perpendicular to the longitudinal axis by rotation around the longitudinal axis, - the or each transformation module comprises a dynamo and / or an electrostatic generator, - the or each transformation module can be a linear motor and / or a rotary motor, - it comprises a plurality of guidance devices, a plurality of transformation modules, or even a plurality of platforms, arranged on said support.

[0014] The present invention also relates to an aircraft, in particular a civil or military transport aircraft, comprising a passive energy generation system such as that mentioned above, said system being located inside the fuselage of the aircraft.

[0015] Advantageously, the support of the passive electrical energy generation system is fixed to a floor of a passenger cabin of the aircraft, and the platform(s) of this system support(s) passenger seats.

[0016] Preferably, the support of the passive electrical energy generation system is fixed to a floor of a hold of the aircraft, and the platform(s) of said system support(s) the inert masses on board the hold.

[0017] The present invention further relates to a method for passively generating electrical energy by means of an aircraft such as that described above and consisting of carrying out a succession of ascent and descent phases so as to: - generate a variation in apparent gravity of the system located in the fuselage in a direction perpendicular to the longitudinal axis of the support, - guide the movement of the or each mobile platform relative to said support in one or more guidance devices, - transform the displacement of the platform relative to the support in the direction perpendicular to the longitudinal axis into electrical energy, and - transmitting said generated electrical energy for powering electrical equipment and / or storing said generated electrical energy in a storage unit. Brief description of the figures

[0018] Other characteristics and advantages of the invention will appear during the reading of the detailed description which follows for the understanding of which reference will be made to the appended drawings in which:

[0019] [Fig-1] [Fig.l] shows an axial schematic view of a generation system passive electrical energy in an aircraft according to one embodiment;

[0020] [Fig.2] [Fig.2] shows an axial schematic view of an aircraft comprising a system for passively generating electrical energy during a climb phase according to one embodiment;

[0021] [Fig.3] [Fig.3] shows an axial schematic view of an aircraft comprising a system for passively generating electrical energy during a descent phase according to one embodiment. Detailed description of the invention

[0022] The passive electrical energy generation system (hereinafter "system 2"), shown in [Fig. 1], is intended to generate energy to supply electrical equipment 9 on board an aircraft 1, in particular a transport aircraft. A transport aircraft may be civil or military. An electrical equipment 9 may be, for example, an electric motor in the context of a hybrid motorization of the propulsion means of the aircraft 1.

[0023] By convention, in the present application, the terms "front" and "rear" are used with reference to a positioning relative to the fuselage 3 of the aircraft 1 which extends along a longitudinal axis XX, from the nose towards the empennages. Furthermore, the terms "above" and "below" are defined relative to a transverse axis YY which is perpendicular to the longitudinal axis XX from the hold of the aircraft 1 towards the top of the fuselage 3. Thus, "longitudinal" or "longitudinally" means any direction parallel to the axis XX, and "transversely" or "transverse" means any direction parallel to the axis YY.

[0024] In a preferred embodiment, and as shown schematically in [Fig.l], the system 2 is mounted in the fuselage 3 of the aircraft 1.

[0025] The system 2 according to the invention comprises a support 4 which is preferably rigid and which extends along the longitudinal axis XX. This rigid support 4 can be fixed to one of the floors of the aircraft 1 which are arranged in the fuselage 3 of the aircraft 1. In a particular embodiment, the support 4 is fixed to a cabin floor which usually supports the rows of passenger seats, or even the cockpit. Alternatively, the support 4 is fixed to a hold floor on which the baggage and various equipment on board the aircraft 1 are arranged. The support 4 is fixed to the floor whatever it is by any well-known means.

[0026] The system 2 also comprises one or more platforms 5. The or each platform 5 may be a rigid plate. One or each platform 5 is arranged above the support 4 and extends parallel to it along the longitudinal axis XX. Preferably, only one platform 5 is arranged above a support 4, although the number of platforms 5 above a support 4 may be greater than 1. If several platforms 5 are located above the support 5, they may be arranged one on top of the other. behind the others along the axis XX or next to each other along a lateral axis perpendicular to the longitudinal XX and transverse YY axes. Alternatively, the platforms 5 are arranged above the support 4 along the lateral and longitudinal XX axes.

[0027] Furthermore, according to the embodiment in which the support 4 is fixed to the floor of a passenger or cockpit cabin, the platform(s) 5 support(s) the passenger seats which are arranged above it(s), for example, a row of seats. As a variant of this particular embodiment, the platform(s) 5 support(s) a single passenger or cockpit seat.

[0028] According to the embodiment in which the support 4 is fixed to the hold floor, the platform(s) 5 support(s) the inert masses, for example, the luggage or various materials on board the aircraft 1.

[0029] According to a preferred embodiment, the platform 5 is movable relative to the support 4 when the system 2 located inside the fuselage 3 of the aircraft 1 experiences a variation in apparent gravity.

[0030] In the context of the invention, the term “apparent gravity” refers to the gravity felt inside the aircraft 1 when it is in flight. In the event of engine thrust, for example, the lift of the aircraft 1 increases and becomes greater than Earth's gravity so that the aircraft 1 rises in the air. This increase in lift corresponds to an acceleration in the direction of the arrow F1 which increases the apparent gravity felt in the aircraft 1 along the YY axis, as shown in Figures 1 and 2.

[0031] In the event of a reduction in the thrust of the engines, for example, the lift of the aircraft 1 decreases and becomes less than Earth's gravity so that the aircraft 1 descends. The descent of the aircraft 1 corresponds to an acceleration along the YY axis in the direction of the arrow F2, as shown in [Fig. 3] which reduces the apparent gravity in the aircraft 1.

[0032] According to a preferred embodiment, the or each platform 5 can move towards the support 4 in the direction of the arrow F2 when the apparent gravity increases. Furthermore, the or each platform 5 can move away from the support 4 in the direction of the arrow F1 when the apparent gravity decreases.

[0033] The system 1 further comprises at least one guide device 6. As shown in [Fig.l], the or each guide device 6 connects the support 4 to the or each mobile platform 5. Each guide device 6 makes it possible to guide the rectilinear movement along the transverse axis YY of a platform 5 relative to the support 4. For reasons of mechanical strength, the or each guide device 6 can be fixed to each of the front and rear ends of a platform 5 and of the support 4 to which it is connected. Alternatively, the guide device 6 can be fixed to sides of the platform 5 and the support 4 along the lateral axis. In each of these embodiments, the guide device 6 guides the movement of the platform 5 only along the transverse YY axis.

[0034] According to a first particular embodiment, the guide device 6 is formed by rails 7 so that they allow a slide-type connection between the support 4 fixed to the floor and the mobile platform 5. As shown in [Fig.l], these rails 7 are arranged in a plane perpendicular to the plane in which the support 4 and the platform 5 are located so that they guide the sliding of the platform 5 towards the support 4 or away from the support 4 depending on the variation in apparent gravity along the YY axis.

[0035] In a second particular embodiment, the guiding device 6 comprises a plurality of ball joints fixed on either side to the platform 5 and to the support 4. These ball joints (not shown) can be arranged on the front and rear ends of the platform 5 and of the support 4 so that the rotation of each of the ball joints along the lateral axis guides the rectilinear movement of the platform 5 towards or away from the support 4 along the transverse axis YY.

[0036] The ball joints can also be arranged on the lateral sides of the platform 5 and the support 4 so that the movement of the platform 5 relative to the support 4 along the transverse axis YY is generated by the rotation of the ball joint along the longitudinal axis XX.

[0037] The system 2 is also provided with at least one transformation module 8 which is capable of transforming the relative displacement of the platform 5 with respect to the support 4 into electrical energy. Preferably, the number of transformation modules 8 is equal to the number of guidance devices 6.

[0038] As shown in [Fig.l], a transformation module 8 is arranged against or near each guidance device 6 so as to recover and transform the work of moving the or each platform 5 relative to the support 4 into electrical energy.

[0039] According to a preferred embodiment, the transformation module 8 comprises at least one dynamo motor which converts this work into electrical energy. The dynamo motor may be a rotary motor or a linear motor.

[0040] Alternatively, the transformation module 8 comprises at least one motor in electrostatic generator mode configured to convert work into electrical energy. This or these electrostatic generators may be linear or rotary motors.

[0041] According to a particular embodiment, each of the transformation modules 8 is connected to the electric motor 9 allowing the propulsion of the aircraft 1 by connecting means 10, for example cables.

[0042] As shown in [Fig.l], the system 2 also comprises a storage unit 11 for electrical energy. The storage unit 11 is connected by connecting means 12, for example one or more cables, to the transformation module 8 so as to receive and store the electrical energy produced by the transformation module 8 and transmitted by the connecting means 12. This storage unit 11 forms a battery comprising a plurality of cells which are charged during the flight by the energy passively generated by the variations in speed of the aircraft 1 along the transverse axis YY. The electrical energy thus stored can be used at any time to power the electric motor 9, in the case of a hybrid motorization of the aircraft 1, or any other electrical equipment 9 to which the storage unit 11 can be connected.

[0043] In a particular embodiment, the aircraft 1 comprises a plurality of passive electrical energy generation systems 2. These systems 2 can be arranged one behind the other along the fuselage 3 of the aircraft 1. They can also be arranged separately in the hold and under the passenger and / or pilot seats.

[0044] The aircraft 1, in which the system 2 is arranged, makes it possible to implement a method for passively generating electrical energy comprising a succession of steps, implemented by the system 2 during successive phases of ascent and descent.

[0045] In the context of the invention, the term “climb phase” means any phase of flight during which the aircraft 1 is piloted so that the lift force along the YY axis exceeds Earth's gravity.

[0046] The term “descent phase” means any phase of flight during which the aircraft 1 is piloted so that the lift force along the YY axis decreases and becomes less than Earth's gravity. The aircraft 1 undergoes an acceleration in the direction of the arrow F2.

[0047] Piloting modes allowing climb and descent phases may include increasing or decreasing engine thrust, taking air currents, etc.

[0048] As shown in [Fig.2], during a climb phase, the pilot causes, by a particular piloting mode, a climb of the aircraft 1 represented by the arrows M. This piloting mode leads to an increase in the lift relative to Earth's gravity which generates an acceleration in the direction of the arrow FL. This produces an increase in the apparent gravity inside the aircraft 1 which causes the relative displacement of the platform(s) 5 towards the support 4 in the direction of the arrow F2. The or each platform 5 being connected to the support 4 by slide-type connections 7 or ball-joint type connections, its displacement is rectilinear along the transverse axis YY. The transformation modules 8 which are connected to each guidance device 6 recover the work representing the variation in apparent gravity along each guidance device 6. This work is transformed into electrical energy by the motor(s) present in each transformation module 8.

[0049] Connection means 11 connect each transformation module 8 to an electric motor 9 or electrical equipment 9 so that the transformed electrical energy is transmitted to them. Alternatively, other connection means 12 connect each transformation module 8 to a storage unit 11 comprising a plurality of cells so as to store the electrical energy generated by the system 2 for later use by the electric motor 9 or any other on-board electrical equipment 9.

[0050] As shown in [Fig. 3], during the following descent phase, the pilot generates, by a second particular piloting mode, a descent of the aircraft 1 represented by the arrows D. This piloting mode generates an acceleration in the direction of the arrow F2 which produces a reduction in the apparent gravity inside the aircraft 1. Under the effect of this variation in apparent gravity, the or each platform 5 which was near the support 4 moves away from it by moving along the YY axis in the direction of the arrow F1. The rectilinear movement of the or each platform 5 is guided along the YY axis by the guidance devices 6 which connect it to the support 4. As during the previous ascent phase, the work linked to the relative movement of the platform 5 is converted into electrical energy by the motor(s) of each transformation module 8. However, the motors operate in reverse in the ascent and descent phases.The passively generated electrical energy is then either stored in the storage units 11 or transmitted to the electric motor and / or the on-board electrical equipment 9 for immediate power supply.

[0051] The system 2 according to the invention has in particular the advantage of passively generating electrical energy depending on the manner of piloting the aircraft 1.

Claims

Claims

1. Aircraft (1) comprising a passive electrical energy generation system for an aircraft, said system (2) being characterized in that it comprises: - a support (4) extending along a longitudinal axis, and fixed on one of the floors of the aircraft (1) which are arranged in a fuselage (3) of the aircraft (1), - at least one mobile platform (5) arranged above said support (4) and capable of moving relative to the support (4) under the effect of a variation in apparent gravity in a direction perpendicular to said longitudinal axis (XX), - at least one guidance device (6) which connects the support (4) to said platform (6) and which is configured to guide the movement of said platform (5) relative to said support (4), and - at least one module (8) for transforming the movement of the platform (5) in the or each guidance device (6) into electrical energy.

2. Aircraft (1) according to the preceding claim, characterized in that the system (2) for passive generation of electrical energy also comprises at least one storage unit (11) for said electrical energy generated by the or each transformation module (8).

3. Aircraft (1) according to one of the preceding claims, characterized in that the or each guide device (6) comprises a slide-type connection (7) configured to guide said movement of said platform (5) relative to said support (4) by translation in said direction perpendicular to the longitudinal axis (XX).

4. Aircraft (1) according to one of the preceding claims, characterized in that the or each guidance device (6) comprises a ball-joint type connection configured to guide said movement of said platform (5) relative to said support (4) in the direction perpendicular to the longitudinal axis (XX) by rotation around the longitudinal axis.*

5. Aircraft (1) according to one of the preceding claims, characterized in that the or each transformation module (8) comprises a dynamo and / or an electrostatic generator.

6. Aircraft (1) according to one of the preceding claims, characterized in that the or each transformation module (8) can be a linear motor and / or a rotary motor.

7. Aircraft (1) according to one of the preceding claims, characterized in that the system (2) for passive generation of electrical energy comprises a plurality of guidance devices (6), a plurality of transformation modules (8), or even a plurality of platforms (5) arranged on said support (4).

8. Aircraft (1) according to one of the preceding claims, characterized in that the floor is a floor of a passenger cabin of the aircraft (1), and in that the platform(s) (5) of the passive electrical energy generation system (2) support(s) passenger seats.

9. Aircraft (1) according to one of claims 1 to 7, characterized in that the floor is a floor of a hold of the aircraft (1), and in that the platform(s) (5) of said system (2) for passive generation of electrical energy support(s) the inert masses on board the hold of the aircraft (1).

10. Method for passively generating electrical energy by means of an aircraft (1) according to one of the preceding claims, characterized in that it consists of carrying out a succession of ascent and descent phases so as to: - generate a variation in apparent gravity of the system (2) located in the fuselage (3) in a direction perpendicular to the longitudinal axis of the support (4), - guide the movement of the or each mobile platform (5) relative to said support (4) in one or more guide devices (6), - transform the movement of the platform (5) relative to the support (4) in the direction perpendicular to the longitudinal axis (XX) into electrical energy, and - transmit said generated electrical energy for the supply of electrical equipment (9) and / or store said generated electrical energy in a storage unit (H).

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