A gas venting system from aircraft battery boxes, comprising synchronized means for connecting each box and means for venting gas from the system.

Abstract

This gas venting system (1) is configured to connect to at least two electrical energy storage battery enclosures (2) of an aircraft and to a common gas outlet (4) of the aircraft. The system (1) includes, for each enclosure (2), a gas venting means (3) associated with said enclosure (2) and connected to the common gas outlet (4). The system (1) includes synchronized connection means (5) adapted to simultaneously establish connections between each enclosure (2) and its associated gas venting means (3). (See Figure 3 for abbreviations)

Description

Title of the invention: A gas venting system from aircraft battery boxes comprising synchronized means for connecting each box and means for venting gas from the system technical field

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

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

[0003] Technological research efforts have already significantly improved the environmental performance of aircraft. The Applicant takes into account the factors impacting all phases of design and development to obtain aeronautical components and products that are less energy-intensive, more environmentally friendly, and whose integration and use in civil aviation have moderate environmental impacts. Consequently, the Applicant is constantly working to reduce its climate impact by employing 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 low voltage batteries (typically of the Lithium-Ion type), typically a voltage of less 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 close monitoring of their operating conditions, such as voltage or temperature, and a cooling system to keep them within a narrow temperature range.

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

[0008] To contain the phenomenon of thermal runaway, aircraft batteries are generally enclosed in a dedicated containment structure (typically of the casing type) and generally associated with a gas management system for gases that may be generated during thermal runaway. Containment and gas management are essential functions for aircraft safety, as they allow for the control of risks related to battery overheating and explosion.

[0009] For example, document FR 313 1454 A1 filed on behalf of the Applicant discloses a battery containment structure, or battery housing, comprising a tray associated with a bell that provides a gas guidance function for the gases emitted by the battery during its operation, particularly in the event of thermal runaway. The bell includes, for this purpose, a profiled opening for gas management, designed to guide the emitted gases in a desired direction. This design aims to improve safety by directing potentially hazardous gases outwards and away from sensitive aircraft components.

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

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

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

[0013] However, connecting such gas venting systems to the battery housings is a time-consuming activity and subject to safety risks when the The connection is not properly established. Description of the invention

[0014] The invention aims to provide a gas venting system for aircraft battery boxes with increased safety and ease of connection, particularly when connecting the boxes to the exhaust outlet. The system sought must, in particular, facilitate the connection of several battery boxes to a common gas venting 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 includes, for each box, a gas evacuation means associated with the box and connected to the common gas outlet.

[0017] The system includes synchronized connection means adapted to establish simultaneously connections between each box and its associated gas evacuation means.

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

[0019] Such a gas venting system allows for centralized connection to multiple units and improves safety. Furthermore, the reversibility of the connections allows for centralized disconnection.

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

[0021] For example, the synchronized connection means include at least two guide bars, each connected at one end to a common actuator arm and at one end to a clamping part associated with the gas evacuation means.

[0022] Preferably, the number of guide bars is equal to the number of housings, with each guide bar associated with one housing. Such a configuration ensures a centralized connection for all housings.

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

[0024] Advantageously, the system includes 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 in each housing.

[0025] According to one feature, the common actuator arm is connected by sliding type links to at least one lever fixed to an aircraft structure and the parts to be clamped are connected to a common guide arm.

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

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

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

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

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

[0031] Optionally, the process includes the following steps: - mounting of screw-on parts onto each housing, so as to create a receiving chamber for the parts to be tightened near 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 of the common actuator arm in the locked position by activating the locking means. Brief description of the drawings

[0032] Other objects, features and advantages of the invention will become apparent from the following description, given solely by way of non-limiting example, and made with reference to the accompanying drawings in which:

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

[0034] [Fig.4] and [Fig.5] respectively illustrate a high position and a low position of a lever of the system of [Fig.1] to [Fig.3]; and

[0035] [Fig. 6] to [Fig. 8] illustrate the kinematics of [Fig. 1] to [Fig. 3] at the level of 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 gas evacuation system 1 from electric battery boxes, according to an embodiment of the invention. System 1 is shown here integrated on board an aircraft. It should 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 the kinematics of establishing a connection between the gas evacuation system 1 and battery housings 2 for an aircraft's electrical energy storage battery. This kinematics is detailed later in the description. The energy storage battery could be, for example, a propulsion battery, or any other type of electrical battery that may, in certain cases, produce toxic gases that need to be evacuated. The gases to be evacuated could, for example, be associated with a thermal runaway event in the battery.

[0039] A right orthonormal coordinate system illustrates the orientation of the elements with respect to the X, Y and Z axes, from one figure to another.

[0040] A casing 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 one embodiment, each housing 2 comprises a tray onto which the battery cells are mounted, a bell-shaped cover over the tray, and mechanical means for attaching the bell-shaped cover to the tray. The tray also preferably includes means for electrically connecting the battery, means for connecting communication equipment, and means for thermally managing the power elements. Each housing 2 constitutes a containment structure and includes means for guiding gases emitted by the battery, enabling the management of the risks of thermal runaway of the battery. For example, the housing's bell-shaped cover includes a profiled opening, visible in Figures 6 to 8, for gas management and designed to guide the emitted gases in a desired direction. For example, the profiled opening is held 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, towards a common gas outlet 4.

[0043] The gas evacuation system 1 includes synchronized connection means 5 adapted to establish, preferably simultaneously, 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 each other. 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 piece 8 associated with each guide bar 6. Each clamping piece 8 is connectable to a housing 2.

[0045] According to the illustrated example, each guide bar 6 is connected to the common actuator arm 7 and to the associated clamping workpiece 8 by ball-joint type connections 9, so as to constitute a guide mechanism for the clamping workpieces 8, actuated by the actuator arm 7. Thus, each guide bar 6 is rotatable about the X-axis between an unlocked position and a locked position. The guide bars 6 are in the unlocked position ([Fig. 2]) when oriented along the Y-axis and in a locked position ([Fig. 3]) when inclined at an angle α with respect 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 clamping parts 8 are connected to a common guide arm 10, preferably by ball joint type connections.

[0048] The actuator arm 7 is connected by sliding joints 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 shown in [Fig. 4]. The levers 11 are rotatable about the Z-axis between an upper position and a lower position, illustrated respectively in Figures 4 and 5. The upper and lower positions represent, respectively, a disconnection and a connection of the system 1 to the housings 2.

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

[0050] As previously indicated, Figures 1 to 3 illustrate the kinematics of setting up the connection of the gas evacuation system 1 to the housings 2. In [Fig. 1], the levers 11 are in the raised position and the system 1 is disconnected from the housings 2. On In Figures 2 and 3, the levers 11 are in the lowered 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, i.e., the guide bars 6 are oriented along the Y-axis. In [Fig. 3] the synchronized connection means 5 are in the locked position, i.e., the guide bars 6 form an angle α with the Y-axis.

[0051] The angle a has a predetermined value, for example between 5° and 25°, chosen to allow the activation of locking means 12 of the system 1. The locking means 12 may, in particular, include at least one through hole 13 formed in 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 prevent movement of the actuator arm 7 along the Z-axis. In the example illustrated in Figures 1 to 3, the locking means 12 include two holes 13, each formed at an opposite end of the actuator arm 7. Such a configuration prevents any movement of the actuator arm 7 along the Z-axis when the locking means 12 are activated and the synchronized connecting 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 point of connection of the gas evacuation means 3 to the housing 2.

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

[0054] As previously stated, each housing 2 preferably includes an opening 15, here a profiled opening. The opening 15 is intended for gas management and is designed so that the emitted gases are guided in a desired direction, for example, towards areas away from the persons present in the aircraft. Here, the profiled opening 15 is preferably kept closed by a cover 16 capable of rupturing in the event of overpressure.

[0055] The system 1 includes screw-on parts 16 on each housing 2 and each intended to constitute a receiving space 17 for the clamping parts 8 in the vicinity of the profiled opening 15 of each housing 2.

[0056] The connection of the gas venting means 3 to the housing 2 is made when the clamping parts 8 are inserted into their respective receiving spaces 17, thus establishing fluid communication between the receiving spaces 17 and the gas venting means 3. Therefore, each connection 14, when connected to a housing 2 and the common gas outlet 4, constitutes a gas venting path from the inside of the housing 2 to the common gas outlet 4.

[0057] An example of an embodiment of a method for connecting 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 process begins here with a preliminary step of mounting the screw-on parts 16 onto each housing 2, so as to constitute a receiving space 17 for the clamping parts 8 in the vicinity of an opening 15 of each housing 2.

[0059] The method continues with a step of simultaneously introducing the parts to be clamped 8 into the receiving spaces 17 by means of a translation of the common actuator arm 7 from a high position to a low position. During this translation, the gas venting means 3 are simultaneously connected to the battery housings 2. Alternatively, the gas venting means 3 can be connected to the housings 2 one after the other, so that all the venting 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

Demands

1. A gas venting system (1) configured to connect to at least two electrical energy storage battery boxes (2) of an aircraft, and to connect to a common gas outlet (4) of the aircraft, characterized in that said system (1) comprises: - for each box (2), a gas venting means (3) associated with said box (2) and connected to the common gas outlet (4), and - synchronized connection means (5) adapted to establish concurrently connections between each box (2) and its associated gas venting 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, wherein 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, wherein each guide bar (6) is connected to said common actuator arm (7) and to said clamping part (8) by ball joint type links (9), so as to constitute a clamping part guide mechanism (8) actuable by the common actuator arm (7).

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

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

7. A system according to any one of claims 2 to 6, wherein the gas venting means (3) comprise at least one connection (14) associated with each housing (2), each connection (14) having a first end fixed to the part to be clamped (8) associated 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 synchronized connection means (5) in a locked position.

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

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

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