System for evacuating gas from battery boxes of an aircraft comprising synchronized means of connection between each box and means for evacuating gas from the system

Abstract

This gas evacuation system (1) is configured to connect to at least two electrical energy storage battery housings (2) of an aircraft and to connect to a common gas outlet (4) of the aircraft. The system (1) comprises, for each housing (2), a gas evacuation means (3) associated with said housing (2) and connected to the common gas outlet (4). The system (1) comprises synchronized connection means (5) adapted to concomitantly establish connections between each housing (2) and its associated gas evacuation means (3). Figure for abstract: Figure 3

Description

Title of the invention: System for evacuating gas from battery boxes of an aircraft comprising synchronized means of connection between each box and means for evacuating gas from the system Technical field

[0001] The present invention relates to the management of gases emitted during the operation of batteries, in particular in the field of aeronautics. Previous techniques

[0002] Climate change is a major concern for many legislative and regulatory bodies around the world. Indeed, various restrictions on carbon emissions have been, are being, or will be adopted by various States. In particular, an ambitious standard applies both to new types of aircraft and those currently in circulation, requiring the implementation of technological solutions to make them compliant with current regulations. Civil aviation has been mobilizing for several years now to make a contribution to the fight against climate change.

[0003] Technological research efforts have already made it possible to significantly improve the environmental performance of aircraft. The Applicant takes into consideration the factors impacting all phases of design and development to obtain less energy-intensive, more environmentally friendly aeronautical components and products, the integration and use of which in civil aviation have moderate environmental impacts. Consequently, the Applicant is constantly working to reduce its climate impact by using methods and operating virtuous development and manufacturing processes that minimize greenhouse gas emissions to the minimum possible.

[0004] This sustained research and development work focuses in particular on the development of the use of electrical technologies to provide propulsion.

[0005] In this context, the storage of electrical energy on board is carried out for example by means of batteries (typically of the Lithium-Ion type) at low voltage, typically a voltage lower than 120V.

[0006] This type of storage presents particular challenges in terms of safety and performance. In particular, Lithium-Ion batteries have a high energy density relative to mass and require significant monitoring of their operating conditions, such as voltage or temperature, and a cooling system to keep them within a reduced temperature range.

[0007] Beyond a temperature threshold known as "thermal runaway", exothermic internal chemical reactions may begin. When the accumulator is no longer able to dissipate enough heat, the temperature of the cell increases until it is destroyed. In other words, thermal runaway occurs in a battery when the energy released by the exothermic reactions occurring inside the battery exceeds the capacity to dissipate this energy to the outside. This runaway may be followed by the generation of gas and an explosion and / or fire, which risks spreading the reaction to the other electrochemical cells in the battery.

[0008] To contain the phenomenon of thermal runaway, aircraft batteries are generally enclosed in a dedicated containment structure (typically of the box type) and generally associated with a system for managing the gases that may be generated during thermal runaway. Containment and gas management are essential functions for aircraft safety, which make it possible to control the risks linked to overheating and explosion of batteries.

[0009] For example, document FR 313 1454 A1 in the name of the Applicant discloses a battery containment structure, or battery housing, comprising a tray associated with a bell which provides a function of guiding the gases emitted by the battery during its operation, in particular in the event of thermal runaway. The bell comprises for this purpose a profiled opening intended for gas management and provided so that the emitted gases are guided in a desired direction. This design aims to improve safety by directing potentially dangerous gases outwards and away from sensitive components of the aircraft.

[0010] However, document FR 313 1454 A1 only deals with the containment and management of gases emitted by the battery of a single housing. However, in current practice, particularly in the aeronautical industry, electrical energy storage systems generally comprise several batteries placed in several housings and operating in parallel and / or in series. This multiple configuration is adopted to meet high energy requirements and to ensure redundancy, a key element in aeronautical safety. The number of battery housings on board can be significant, for example of the order of several dozen.

[0011] Each of the boxes must then be connected to the gas management system. Due to the large number of battery boxes, it can be tedious to individually check that each box is properly connected to the gas management system.

[0012] Furthermore, it is known to use gas evacuation systems associated with aircraft batteries in order to ensure the evacuation of gases which may be emitted during the deterioration of a battery.

[0013] However, connecting such gas evacuation systems to the housings containing the batteries is a time-consuming activity and subject to safety risks when the connection is not properly established. Statement of the invention

[0014] The invention aims to propose a system for evacuating gas from aircraft battery boxes, the safety and ease of connection of which are increased, in particular during the connection between the boxes and the outlet of the gases to be evacuated to the outside. The desired system must in particular facilitate the connection of several battery boxes to a common gas evacuation system.

[0015] The invention relates to a gas evacuation system configured to connect to at least two electrical energy storage battery boxes of an aircraft, and to connect to a common gas outlet of the aircraft.

[0016] The system comprises for each housing, a gas evacuation means associated with the housing and connected to the common gas outlet.

[0017] The system comprises synchronized connection means adapted to concomitantly establish connections between each housing and its associated gas evacuation means.

[0018] The connection established between each housing and its associated gas evacuation means is preferably reversible, the housing being able to be disconnected from its gas evacuation means using the synchronized connection means.

[0019] Such a gas evacuation system allows centralized connection to multiple boxes and improves safety. In addition, the reversibility of the connections allows centralized disconnection.

[0020] An additional advantage is that it is not necessary, in order to check the correct connection of the gas evacuation means to the housings, to check each housing one after the other.

[0021] For example, the synchronized connection means comprise at least two guide bars each connected at a first end to a common actuator arm and at a second end to a part to be clamped associated with the gas evacuation means.

[0022] Preferably, the number of guide bars is equal to the number of housings, each guide bar being associated with a housing. Such a configuration makes it possible to ensure a centralized connection for all the housings.

[0023] Advantageously, each guide bar is connected to the common actuator arm and to the part to be clamped by ball-joint type connections, so as to constitute a mechanism for guiding the parts to be clamped which can be actuated by the common actuator arm.

[0024] Advantageously, the system comprises parts to be screwed onto each housing, each intended to constitute a space for receiving the parts to be tightened in the vicinity of an opening of each housing.

[0025] According to one characteristic, the common actuator arm is connected by slide-type connections to at least one lever fixed to a structure of the aircraft and the parts to be tightened are connected to a common guide arm.

[0026] According to another characteristic, the gas evacuation means comprise at least one connection associated with each housing, each connection having a first end fixed to the associated part to be clamped and a second end connected to the common gas outlet.

[0027] Advantageously, the system comprises means for locking the synchronized connection means in a locking position. Such locking means prevent any unwanted disconnection.

[0028] According to another aspect, the invention relates to an aircraft comprising at least two housings for an electrical energy storage battery and a gas evacuation system as defined above.

[0029] According to another aspect, the invention relates to a method for connecting a gas evacuation system of an aircraft as defined above to the housings of the aircraft. The method comprises steps of: - connection of the gas evacuation means to the common gas outlet, and - concomitant connection between each box and its means of evacuation of associated gas.

[0030] Such a method allows centralized connection to multiple boxes and improves security.

[0031] Optionally, the method comprises the following steps: - mounting of parts to be screwed onto each housing, so as to constitute a chamber for receiving the parts to be tightened in the vicinity of a profiled opening in each housing, - simultaneous introduction of the parts to be clamped into the receiving chambers by a vertical translation of the common actuator arm from a high position to a low position, - horizontal translation of the common actuator arm from an unlocked position to a locked position, and - locking the common actuator arm in the locked position by activating the locking means. Brief description of the drawings

[0032] Other aims, characteristics and advantages of the invention will appear on reading the following description, given solely by way of non-limiting example, and made with reference to the appended drawings in which:

[0033] [Fig-1] to [Fig.3] illustrate a connection kinematics of an evacuation system of gas according to an example of the invention;

[0034] [Fig.4] and [Fig.5] illustrate respectively a high position and a low position of a lever of the system of [Fig.l] to [Fig.3]; and

[0035] [Fig.6] to [Fig.8] illustrate the kinematics of [Fig.1] to [Fig.3] at a connection of the evacuation means of the gas evacuation system. Detailed description of at least one embodiment

[0036] It should be noted that throughout the following, identical or similar elements bear the same references, from one figure to another.

[0037] Figures 1 to 3 show a system 1 for evacuating gas from electric battery boxes, according to an exemplary embodiment of the invention. The system 1 is here integrated on board an aircraft. It will be noted that a similar evacuation system could be used for any other type of vehicle or installation equipped with electric batteries.

[0038] More specifically, Figures 1 to 3 illustrate a kinematics for setting up a connection of the gas evacuation system 1 to housings 2 for an electrical energy storage battery of an aircraft. This kinematics is detailed later in the description. The energy storage battery may be, for example, a propulsion battery, or any other type of electric battery that may in certain cases produce toxic gases to be evacuated. The gases to be evacuated may, for example, be associated with a thermal runaway event of the battery.

[0039] A straight orthonormal reference frame illustrates the orientation of the elements relative to the X, Y and Z axes, from one figure to another.

[0040] A housing 2 is a structure called “casing” in English, intended to receive a battery and which is capable of containing any thermal runaway of the battery cells.

[0041] In an exemplary embodiment, each housing 2 comprises a plate on which the battery cells are fixed, a bell covering the plate and means for mechanically fixing the bell to the plate. The plate preferably further comprises means for electrically connecting the battery, means for connecting communication means, and means for thermally managing the power elements. Each housing 2 constitutes a containment structure and comprises means for guiding gases emitted by the battery allowing the management of the risks of thermal runaway of the battery. For example, the bell of the housing comprises a profiled opening, visible in FIGS. 6 to 8, intended for gas management and provided so that the emitted gases are guided in a desired direction. For example, the profiled opening is kept closed by a cover configured to rupture in the event of overpressure.

[0042] The gas evacuation system 1 comprises gas evacuation means 3 from inside at least two boxes 2, here three boxes in number, to a common gas outlet 4.

[0043] The gas evacuation system 1 comprises synchronized connection means 5 adapted to establish, preferably concomitantly, connections between each housing 2 and the gas evacuation means 3. The connection established between each housing 2 and its associated gas evacuation means 3 is preferably reversible, the housing being able to be disconnected from its gas evacuation means using the synchronized connection means 5.

[0044] The gas evacuation means 3 here comprise at least two guide bars 6, here three in number. Each guide bar 6 comprises a first end 6a and a second end 6b, opposite one another. The first end 6a is connected to a common actuator arm 7 which is oriented along the Z axis. The second end 6b is connected to a clamping part 8 associated with each guide bar 6. Each clamping part 8 is connectable to a housing 2.

[0045] According to the example illustrated, each guide bar 6 is connected to the common actuator arm 7 and to the associated part to be clamped 8 by ball-joint type connections 9, so as to constitute a mechanism for guiding the parts to be clamped 8 actuable by the actuator arm 7. Thus, each guide bar 6 is movable in rotation about the X axis between an unlocked position and a locked position. The guide bars 6 are in the unlocked position ([Fig.2]) when they are oriented along the Y axis and in a locked position ([Fig.3]) when they are inclined at an angle α relative to the Y axis.

[0046] Preferably, the number of guide bars 6 is equal to the number of housings 2, each guide bar 6 being associated with a housing 2.

[0047] As illustrated in Figures 1 to 3, the parts to be clamped 8 are connected to a common guide arm 10, preferably by ball-and-socket type connections.

[0048] The actuator arm 7 is connected by slide-type connections to at least one lever 11, here two levers 11. Each lever 11 is articulated to a structural part 12 of the aircraft (i.e., for example, to a frame), as seen in [Fig. 4]. The levers 11 are movable in rotation about the Z axis between a high position and a low position illustrated respectively in FIGS. 4 and 5. The high and low positions are positions representing respectively a disconnection and a connection of the system 1 to the housings 2.

[0049] The levers 11 are preferably provided with means for holding them in the low position, such as indexing fingers, latches, locks or magnets.

[0050] As indicated previously, figures 1 to 3 illustrate a kinematics of setting up the connection of the gas evacuation system 1 to the housings 2. In [Fig.l], the levers 11 are in the high position and the system 1 is disconnected from the housings 2. In Figures 2 and 3, the levers 11 are in the low position and the system 1 is connected to the housings 2. In Figures 1 and 2, the synchronized connection means 5 are in the unlocked position, that is to say that the guide bars 6 are oriented along the Y axis. In [Fig. 3] the synchronized connection means 5 are in the locked position, that is to say that the guide bars 6 form an angle a with the Y axis.

[0051] The angle a has a predetermined value, for example between 5° and 25°, chosen so as to allow the activation of locking means 12 of the system 1. The locking means 12 may in particular comprise at least one through hole 13 formed on the thickness of the actuator arm 7 and oriented along the X axis. Each hole 13 is associated with a locking pin which cooperates with the adjacent lever 11 to block a movement of the actuator arm 7 along the Z axis. In the example illustrated in FIGS. 1 to 3, the locking means 12 comprise two holes 13 each formed at an opposite end of the actuator arm 7. Such a configuration prevents any movement along the Z axis of the actuator arm 7 when the locking means 12 are activated and the synchronized connection means 5 are in the locked position.

[0052] Figures 6 to 8 illustrate in more detail the kinematics of Figures 1 and 2 at the location of the connection of the gas evacuation means 3 to the housing 2.

[0053] The gas evacuation means 3 comprise at least one connection 14 associated with each housing 2, the connection 14 preferably taking the form of a pipe. The pipe is for example of an angled shape. Each connection 14 has a first end fixed to an associated clamping part 8 and a second end connected to the common gas outlet 4.

[0054] As indicated above, each housing 2 preferably comprises an opening 15, here a profiled opening. The opening 15 is intended for gas management and provided so that the emitted gases are guided in a desired direction, for example towards areas far from the people present in the aircraft. Here, the profiled opening 15 is preferably kept closed by a cover 16 capable of breaking in the event of overpressure.

[0055] The system 1 comprises parts to be screwed 16 onto each housing 2 and each intended to constitute a space 17 for receiving the parts to be tightened 8 in the vicinity of the profiled opening 15 of each housing 2.

[0056] The connection of the gas evacuation means 3 to the housing 2 is carried out when the parts to be clamped 8 are inserted into their respective receiving space 17, putting the receiving spaces 17 and the gas evacuation means 3 into fluid communication. Thus, each connection 14 constitutes, when it is connected to a housing 2 and to the common gas outlet 4, a gas evacuation path from the inside of the housing 2 to the common gas outlet 4.

[0057] An example embodiment of a method for connecting the system 1 to the battery boxes 2 of an aircraft is detailed below. This method implements, for example, the evacuation system described above.

[0058] The method begins here with a preliminary step of mounting the parts to be screwed 16 on each housing 2, so as to constitute a space 17 for receiving the parts to be tightened 8 in the vicinity of an opening 15 of each housing 2.

[0059] The method continues with a step of concomitant introduction of the parts to be clamped 8 into the receiving spaces 17 by a translation of the common actuator arm 7 from a high position to a low position. During this translation, the gas evacuation means 3 are simultaneously connected to the housings 2 of the batteries. Alternatively, the gas evacuation means 3 can be connected to the housings 2 one after the other, so that all the evacuation means 3 are connected to their respective housings 2 once the parts to be clamped 8 have been introduced.

[0060] After the introduction step, the actuator arm 7 is translated from an unlocked position to a locked position.

[0061] The method preferably ends with a step of locking the actuator arm 7 in the locked position by activating the locking means 12.

Claims

Claims

1. Gas evacuation system (1) configured to connect to at least two housings (2) for an electrical energy storage battery of an aircraft, and to connect to a common gas outlet (4) of the aircraft, characterized in that said system (1) comprises: - for each housing (2), a gas evacuation means (3) associated with said housing (2) and connected to the common gas outlet (4), and - synchronized connection means (5) adapted to concomitantly establish connections between each housing (2) and its associated gas evacuation means (3).

2. System according to claim 1, wherein the synchronized connection means (5) comprise at least two guide bars (6) each comprising a first end (6a) connected to a common actuator arm (7) of the evacuation system, and each comprising a second end (6b) connected to a respective clamping part (8) of the evacuation system associated with the gas evacuation means (3).

3. System according to claim 2, in which the number of guide bars (6) is equal to the number of housings (2), each guide bar (6) being associated with a housing (2).

4. System according to claim 2 or 3, in which each guide bar (6) is connected to said common actuator arm (7) and to said part to be clamped (8) by ball-joint type connections (9), so as to constitute a mechanism for guiding the parts to be clamped (8) actuable by the common actuator arm (7).

5. System according to any one of claims 2 to 4, comprising parts to be screwed (16) on each housing (2), each intended to constitute a space (17) for receiving the parts to be tightened (8) in the vicinity of an opening (15) of each housing (2).

6. System according to any one of claims 2 to 5, in which the common actuator arm (7) is connected by slide-type connections to at least one lever (11) configured to be fixed to a structure (12) of the aircraft, the parts to be clamped (8) being connected to a common guide arm (10).

7. System according to any one of claims 2 to 6, in which the gas evacuation means (3) comprise at least one connection (14) associated with each housing (2), each connection (14) having a first end fixed to the associated clamping part (8) and a second end connected to the common gas outlet (4).

8. System according to any one of claims 1 to 7, comprising locking means (12) of the synchronized connection means (5) in a locking position.

9. Aircraft comprising at least two housings (2) for an electrical energy storage battery and a gas evacuation system (1) according to any one of claims 1 to 8.

10. A method of connecting a gas evacuation system (1) of an aircraft according to claim 9 to the housings (2) of the aircraft, comprising steps of: - connecting the gas evacuation means (3) to the common gas outlet (4), and - concomitant connection between each housing (2) and its associated gas evacuation means (3).

Images