ELECTRICAL HOUSING FOR AN AIRCRAFT

Description

technical field

[0001] The present invention relates to the field of electrical energy storage, particularly in the field of aeronautics. It also relates, more generally, to electrical energy storage for applications where mass is a significant factor. Previous techniques

[0002] Traditionally, in the field of aeronautics, electrical energy storage is carried out using low voltage Lithium-Ion batteries, typically a voltage below 120V.

[0003] The term battery means a set of individual packs, each comprising modules made up of power elements and configured in combination in series and / or parallel to achieve the required electrical voltage and electrical capacity.

[0004] Modern aircraft have increasing electrical power requirements, which necessitates adjusting batteries accordingly. To provide the required electrical power while minimizing the weight of electrical equipment, it is advantageous to increase the battery voltage, for example to 800 V.

[0005] Typically, batteries are housed inside a casing consisting of a tray covered by a lid. The tray holds the installed batteries in place and also provides structural rigidity. Sufficient rigidity can be achieved by imposing a minimum wall thickness on the tray, but this significantly increases the casing's mass. In an improved design, the minimum casing thickness can be reduced through the use of localized reinforcements.

[0006] These solutions come with an increase in the mass of the case, either by increasing the minimum thickness of the tray, or by providing reinforcements.

[0007] Furthermore, the cover allows the tank to be sealed airtight and integrates electrical power and communication connections with electrical system management systems for diagnostic, control, and / or regulation purposes. The integration of power and communication connections may increase the risk of gas leaks in the event of thermal runaway, as well as weaken the structure's resistance. US 2021 / 167445 A1, US 2014 / 246259 A1, US 2014 / 072835 A1, US 2015 / 243956 A1, US 2018 / 111499 A1, CN 112 310 533 A, and EP 3 429 023 A1 represent prior art enclosures. Description of the invention

[0008] In view of the above, the aim of the invention is to overcome all or part of the aforementioned disadvantages and to provide an electrical housing for a battery, without a significant increase in mass.

[0009] Another aim of the invention is to provide such a housing, which avoids the risk of gas leakage and which, moreover, meets the safety requirements required in the field of aeronautics.

[0010] The invention therefore relates to an electrical energy storage box, characterized in that it comprises a platform on which the power elements of the battery are fixed and a bell covering the platform and mechanical fixing means for the bell on the platform, the platform comprising means for electrical connection of the battery, means for connecting means of communication, and means for thermal management of the power elements.

[0011] By integrating the battery power components, along with the power, communication, and thermal management connections, onto a single platform that supports all the battery's functional elements, the challenges of reinforcing the power component support are eliminated. Furthermore, the battery integration ratio, calculated as the ratio between the total equipment mass and the mass of the electrical power components, is improved. This improved integration ratio is accompanied by compliance with safety standards, particularly regarding the risks of thermal runaway and associated gas leaks.

[0012] Advantageously, the bell is made of a material with a lower bulk density than the tray and / or is heat-resistant.

[0013] The bell may include means for guiding gas emitted by the battery.

[0014] Preferably, the means of thermal management of the power elements include a cooling circuit.

[0015] In one embodiment, the tray is made of a metallic material.

[0016] The bell, meanwhile, can be made from a ceramic matrix composite material.

[0017] In one embodiment, the platform includes a base with notches into which the bell fits.

[0018] Alternatively, the platform includes a base comprising a peripheral edge delimiting a housing for receiving the bell and into which the mechanical fixing means for the bell are engaged.

[0019] According to another feature of the case according to the invention, a set of pre-stressed stiffening tie rods extend between the plate and the bell.

[0020] The invention also relates to an aircraft battery assembly, comprising a set of power elements and a housing as defined above, in which the battery power elements are mounted. Brief description of the drawings

[0021] 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: [ Fig 1 ] is a perspective view of the main constituent elements of a housing according to the invention; [ Fig 2 ] is a longitudinal cross-sectional view of a housing according to the invention; [ Fig 3 ] illustrates an exploded view of a housing according to the invention; [ Fig 4 ] shows the case of the figure 3 , in the closed position; [ Fig 5 ] illustrates an embodiment of a housing according to the invention; and [ Fig 6] illustrates a variant embodiment of a housing according to the invention. Detailed description of at least one embodiment

[0022] We have represented on the figures 1 to 4 an example of an embodiment of a battery case according to the invention, designated by the general numerical reference 1. This case is intended to receive a battery.

[0023] In the described embodiment, this unit is intended to be installed on board an aircraft. It should be noted, however, that the invention also applies, in general, to other fields where mass management and integration issues arise.

[0024] This housing is designed to provide mounting and connection for the battery's power cells and to protect the battery. It includes a tray 2 onto which the battery's power cells 3 are mounted and a bell 5.

[0025] Platform 2 has the necessary structural rigidity to be able to accommodate the desired power elements 3 by fixing.

[0026] The platform 2 can provide temperature control functionality and, for this purpose, include at least one cooling circuit 6 comprising pipes, such as 7, through which a coolant circulates. The platform 2 is advantageously made of a thermally conductive material, in this case a metallic material.

[0027] The cooling circuit 6 is installed in heat exchange relationship on the external face 8 of the platform 2, that is to say on the face opposite to the internal face 9 which houses the batteries 3. It can also be integrated into the platform 2.

[0028] The tray 2 is cooled by the cooling circuit and can consequently cool the batteries 3 to optimal operating temperatures.

[0029] For example, the cooling circuit includes metal tubes, such as 10, welded to plate 2.

[0030] The platform 2 is also equipped with several mounting elements 11 that allow its installation on board an aircraft. It should be noted, however, that the platform can alternatively consist of a structural aircraft support element designed for battery integration.

[0031] As for bell 5, it covers all the elements located inside housing 1 and represents a physical barrier that separates and protects the inside of housing 1 and its external environment.

[0032] It is specifically designed to reduce the risk of gas leaks.

[0033] Furthermore, in the event of a thermal runaway, the bell 5 protects the external environment of the housing 1 by limiting the impact of this event. It also guides the gases emitted by the battery during operation. To this end, the bell 5 includes a profiled opening 12 for gas management, designed to guide the emitted gases in a desired direction. For example, the profiled opening 12 is kept closed by a cover 13 that can rupture in the event of overpressure.

[0034] Bell 5 is made of a material that is both lightweight, strong and capable of providing protection functionality in case of thermal runaway, for example in a ceramic matrix composite material or in a composite material including an internal thermal protection layer.

[0035] With reference to the figure 3 , platform 2 includes means for electrical connection of the battery, comprising a power connector 14 necessary to supply electrical current to the aircraft systems, as well as means for connecting communication means, comprising a communication connector 15 with electrical system management systems for diagnostic, control and / or regulation purposes.

[0036] Finally, the housing is equipped with mechanical means of fixing the bell to the plate, made for example in the form of screws, bolts or any other suitable means of fixing for the intended use.

[0037] We will now describe, with reference to the figure 5 , on which elements identical to those described with reference to figures 1 to 4 are designated by the same numerical references, another embodiment of a housing according to the invention.

[0038] In this embodiment, which is otherwise identical to the embodiment of figures 1 to 4 , the plate 2 forms a base on which the bell 5 is fixed by means of a set of pre-stressed tie rods 16 which also ensure the rigidity of the case.

[0039] Each tie rod 16 includes at its end a passive anchorage 17 fixed in the plate 2 and, at the opposite end, an active anchorage 18 arranged in the bell 5. It should be noted that the fixing of the bell 5 to the plate 2 by the prestressed tie rods implements forces which balance themselves and which do not generate additional loads on the aircraft.

[0040] In this embodiment, the plate 2 has a peripheral rim with notches 19 into which the bell 5 engages.

[0041] Alternatively, illustrated by the figure 6 which is also identical to the figure 5, the platform 2 also constitutes a base having a raised peripheral edge delimiting a housing for receiving the bell 5 of the platform 2. In this embodiment, the bell 5 is fixed to the platform 2 by means of fixing elements 20 which engage in the bell 5 and the edge of the platform 2.

Claims

1. A housing (1) for an electrical energy storage battery, characterized in that it comprises a plate (2), onto which power elements (3) of the battery are attached, and a bell cover (5) covering the plate (2) and means for mechanically attaching the bell cover (5) onto the plate (2), the plate (2) comprising means (14) for the electrical connection of the battery, means (15) for the connection of communication means, and means for the thermal management of the power elements, said plate (2) forming a base provided with notches (19) into which the bell cover (5) is engaged.

2. The housing according to claim 1, wherein the bell cover (5) is made of a material with a lower specific weight than that of the plate (2) and / or is heat-resistant.

3. The housing (1) according to one of claims 1 and 2, wherein the bell cover (5) comprises means for guiding gases released by the battery.

4. The housing (1) according to any one of claims 1 to 3, wherein the means for the thermal management of the power elements comprise a cooling circuit (6).

5. The housing (1) according to any one of claims 1 to 4, wherein the plate (2) is made of a metal material.

6. The housing (1) according to any one of claims 1 to 5, wherein the bell cover (5) is made of a ceramic matrix composite material.

7. The housing (1) according to any one of claims 1 to 6, comprising a set of preloaded stiffening tie rods (16) extending between the plate (2) and the bell cover (5).

8. A battery assembly for an aircraft, comprising a set of power elements (3) and a housing (1) according to any one of claims 1 to 7, wherein the power elements (3) of the battery are mounted.