FR3114191A1 - Remote Control UAV Waterproof Power Battery - Google Patents

Abstract

A sealed power supply battery (1) for a remotely controlled unmanned aircraft, the power supply battery (1) extending longitudinally along an alignment axis (X) and comprising: a plurality of energy cells aligned in series along the alignment axis (X) so as to form a single row of energy cells, the row of energy cells having an outer footprint,at least one power connector (3) connected to the row of energy cells and comprising a connection end intended to be connected to a control module (C) of the remote-controlled unmanned aircraft, anda heat dissipation casing (4), closely fitting the outer footprint of the row of energy cells, the casing (4) being sealed around the row of energy cells and the power connector, the connection end extending outside the casing (4). Abstract Figure: Figure 1

Description

Remote Control UAV Waterproof Power Battery

The present invention relates to the field of remote-controlled unmanned aircraft, which are known to those skilled in the art under the designation of "drone". The invention relates more specifically to the field of power supply batteries mounted on a remote-controlled unmanned aircraft.

For the sake of brevity, a remote-controlled unmanned aircraft will be referred to below as a “drone”.

In known manner, a drone comprises a rigid structure on which several electric motors are mounted to make the drone fly. The drone also comprises a control module, connected to the rigid structure of the drone and adapted to receive commands wirelessly and to control the motors according to the commands received. A user can thus direct the drone during its flight, for example, by means of a remote control or a telephone. The drone may also include recording equipment (video camera, etc.) which is fixed to the rigid structure of the drone and is functionally connected to the control module. In a known manner, the drone also comprises a power supply battery in order to electrically supply the motors, the control module and the equipment of the drone.

The supply battery, generally a lithium polymer battery, comprises in known manner an assembly of several rows of energy cells, commonly forming a block. Each cell generates electrical energy from an exchange of ions between two electrodes. Such a lithium polymer battery is advantageous because it has a high energy density, which allows greater autonomy and therefore a longer flight time of the drone. However, the greater the energy density of a power bank, the more it heats up, which can deteriorate it if it is not adequately cooled.

In addition, the electrolyte allowing the transfer of ions in the energy cells is a semi-rigid substance which requires the insertion of the supply battery in a protective box. The case protects the battery pack, while allowing it to be handled more easily. However, the addition of a case enveloping the power supply battery can affect its cooling in the event of significant heating. In addition, such a box has the disadvantage of significantly increasing the mass of the battery and therefore the payload of the drone, which can affect its speed or penalize its movements.

In addition, a drone generally evolves in an external environment, which can be humid, for example in the event of rain or the presence of spray at sea. It is also known to make the drone take off or land from the surface of the water. . Also, it is necessary to guarantee the tightness of the protective case, in order to limit any risk of the presence of water inside the case and therefore on the battery. Indeed, the heat released by the power supply battery can cause the appearance of water vapor increasing the humidity inside the case. High humidity can lead to the deterioration of the energy cells and electronic components present in the case, the lifespan of which can be affected.

Also in a known manner, the protective case is closed by a waterproof seal, which makes it possible to limit the risk of water infiltration into the case. However, the power battery being mounted on a drone, it has reduced dimensions and therefore a limited autonomy, which implies that it must be replaced regularly. When the operator opens the case to change the battery, the operator may have wet hands if the drone is used on water. The power supply battery or the inside of the box can then be wet when the operator handles them, which has a major drawback because it does not guarantee a dry environment inside the box in all circumstances.

In addition, the parallelepiped shape of the power bank resulting from the assembly of several superimposed rows of energy cells gives the power bank a compact shape, which does not allow good heat dissipation. The shape of such a battery does not allow the core of the supply battery to cool down when it is in operation.

The invention thus aims to eliminate at least some of these drawbacks by proposing a sealed power supply battery that is simple to install and has a small footprint. The supply battery according to the invention also aims to allow optimal dissipation of the heat emitted when the battery is in operation.

PRESENTATION OF THE INVENTION

• une pluralité de cellules énergétiques alignées en série suivant l’axe d’alignement de manière à former une unique rangée de cellules énergétiques, la rangée de cellules énergétiques présentant une empreinte extérieure,
• au moins un connecteur d’alimentation relié à la rangée de cellules énergétiques et comprenant une extrémité de connexion destinée à être reliée à un module de commande de l’aéronef sans pilote télécommandé, et
• une enveloppe de dissipation thermique, épousant de manière intime l’empreinte extérieure de la rangée de cellules énergétiques, l’enveloppe étant scellée de manière étanche autour de la rangée de cellules énergétiques et du connecteur d’alimentation, l’extrémité de connexion s’étendant en-dehors de l’enveloppe.

The invention relates to a sealed power supply battery for a remotely controlled unmanned aircraft, the power supply battery extending longitudinally along an alignment axis and comprising:

• a plurality of energy cells aligned in series along the axis of alignment so as to form a single row of energy cells, the row of energy cells having an outer footprint,
• at least one power supply connector connected to the row of energy cells and comprising a connection end intended to be connected to a control module of the remote-controlled unmanned aircraft, and
• a heat dissipation shroud, closely fitting the outer footprint of the row of power cells, the shroud being sealed around the row of power cells and the power connector, the connection end being extending outside the envelope.

By the expression "serial alignment", it is meant that the energy cells are arranged and aligned in a single row one behind the other.

Such a series alignment, different from the parallelepipedic shape of the prior art, in which the power supply battery comprised an assembly of a plurality of rows of energy cells, makes it possible to maximize the heat exchange surface, allowing better heat dissipation. The series alignment thus makes it possible to overcome the risk of overheating of a core of the power supply battery which would not be cooled in an optimal manner, which makes it possible to guarantee the power supply battery a duration of longer life.

An elongated shape also allows, when the power battery is mounted on a remotely controlled unmanned aircraft, to conveniently set the center of gravity of the aircraft during mounting, the center of gravity to be centered with respect to the aircraft to ensure its balance and allow optimal flight. In addition, a flat and elongated shape makes it possible to limit any risk of imbalance of the remotely controlled unmanned aircraft in flight.

The heat dissipation envelope, closely matching the shape of the outer footprint of the row of energy cells, makes it possible to increase even more significantly the heat transfer between the row of energy cells and the outside and allows to dissipate more heat.

A sealed envelope makes it possible to guarantee a tight environment for the energy cells, which makes it possible to limit any risk of the presence of humidity inside the envelope if a user handles the power supply battery for example while he has the wet hands or if the remotely controlled unmanned aerial vehicle is flying in the rain or at sea, for example. This extends the life of the battery pack.

Preferably, the envelope is rigid, so as to protect the energy cells from any risk of shock, for example.

Preferably, the envelope is made of a composite material. A composite material makes it possible to form a light envelope, which has very little impact on the payload of the remote-controlled unmanned aircraft, unlike the case of the prior art which had a large mass. In addition, a lightweight power battery allows for a lighter aircraft and therefore longer range.

In a preferred embodiment, the envelope comprises a stack of a plurality of layers comprising reinforcing fibers impregnated in a polymer resin.

Preferably, each layer of the envelope comprises Dyneema ® fibers, glass fibers or carbon fibers impregnated in an epoxy resin, giving both lightness and robustness to the envelope.

Preferably, the envelope has an envelope thickness of less than 2 mm, allowing greater dissipation of the thermal energy generated by the power supply battery. In addition, such a thickness allows a thin and light casing, which does not impact the total mass of the power supply battery, unlike the case of the prior art. Even in a sealed envelope, high heat dissipation qualities are obtained due to the thinness of the envelope. Preferably, the thickness of the envelope is less than 1 mm.

Preferably, each energy cell has a rigid shell. A rigid shell protects the energy cells and thus reduces the thickness of the envelope, the heat dissipation performance is thus greatly improved. In addition, the rigidity of the power bank is increased, which improves its resistance to shocks and therefore its lifespan. Preferably, the rigid shell of each energy cell is made of steel.

Preferably, each energy cell has a cylindrical shape, making it possible to limit the contact surfaces between two adjacent energy cells, making it possible to improve heat dissipation even more significantly.

Preferably, each energy cell having a cylindrical shape, the envelope has a corrugated outer surface, making it possible to increase the heat exchange surface between the energy cells and the outside.

In a preferred embodiment, the row of energy cells has an alignment thickness between 15 and 30 mm. Such a thickness reduces the bulk of the power battery on the remotely controlled UAV, which increases aerodynamics in flight. The autonomy of the aircraft is thus also increased. In addition, such a thickness allows a flatter and therefore more compact remote-controlled UAV for transport.

Preferably, the supply battery has a length along the alignment axis of between 15 and 500 mm.

Preferably, the power supply battery has a width along a lateral axis orthogonal to the alignment axis of between 50 and 150 mm.

Preferably, the power supply battery comprising an upper wall and a lower wall, intended to be connected to the remote-controlled unmanned aircraft, at least the lower wall present in a vertical section plane of the power supply battery, a concave profile. Such a profile makes it possible to maintain a space between the power battery and the rigid structure of the remotely controlled unmanned aircraft when the power battery is mounted on the aircraft, allowing the circulation of an air flow. The airflow allows better dissipation of the heat emitted by the row of energy cells, allowing better cooling.

Preferably again, the lower wall and the upper wall of the supply battery have, in a section plane transverse to the axis of the battery, a concave curved profile.

In one embodiment, the power supply battery comprises at least one spacing member, mechanically connected to an outer surface of the casing, so as to allow mounting and an even greater spacing of the power supply battery when this is mounted on the remotely controlled unmanned aircraft.

Such a spacer member makes it possible to move the power supply battery away from the rigid structure of the remote-controlled unmanned aircraft, in order to allow the circulation of a greater flow of air between the rigid structure and the battery. feed.

In one embodiment, the power supply battery comprises a plurality of spacing members, uniformly distributed around the periphery of the power supply battery.

In one embodiment, each spacer member is removable, allowing simple and quick attachment in the event of replacement of a supply battery.

Preferably, the power supply battery comprises at least one support member, mounted in the casing and configured to cooperate with the ends of each energy cell. Thus, the support member contributes to the rigidity of the supply battery, the casing can be thin to ensure sealing and optimal heat dissipation.

In a preferred embodiment, the power bank includes a thermally conductive chemical element mounted between the row of energy cells and the envelope, so as to increase the thermal conductivity of the energy cells with the envelope by filling the defects of alignment and surface condition that may appear between the energy cells and the envelope. The thermally conductive chemical element thus improves the dissipation of the heat generated by the energy cells in operation.

Preferably, the chemical element has a thermal conductivity of between 2 and 15 W/mK.

Preferably, the thermally conductive chemical element is a thermal paste.

Preferably, the envelope comprises a lower half-envelope and an upper half-envelope, mounted opposite the lower part, sealed to each other so as to form an envelope of a single holding. Two half-shells allow quick and easy assembly of the power bank, while ensuring a sealed environment inside the power bank once the two half-shells are sealed. In addition, such an arrangement in two half-envelopes makes it possible to guarantee the power supply battery significant rigidity in bending and in torsion. When sealed, the lower half-casing and the upper half-casing are irremovable.

The invention also relates to a remote-controlled unmanned aircraft comprising a rigid structure and a supply battery as described previously, mounted on the rigid structure.

Preferably, the remotely controlled unmanned aircraft comprising a plurality of motors, the power supply battery is positioned between the motors, so as to be placed in the air flow generated by each motor and thus allow optimal cooling by thermal convection .

• une étape de positionnement, dans la demi-enveloppe inférieure, de la rangée de cellules énergétiques, l’extrémité de connexion du connecteur d’alimentation étant positionnée en-dehors de la demi-enveloppe inférieure, et
• une étape de scellement de la demi-enveloppe supérieure sur la demi-enveloppe inférieure de manière à former une enveloppe étanche d’un seul tenant.

The invention finally relates to a method for mounting a power supply battery as described above, the casing comprising a lower half-casing and an outer half-casing, the method comprising:

• a step of positioning, in the lower half-envelope, the row of energy cells, the connection end of the power supply connector being positioned outside the lower half-envelope, and
• a step of sealing the upper half-envelope on the lower half-envelope so as to form a sealed envelope in one piece.

PRESENTATION OF FIGURES

The invention will be better understood on reading the following description, given by way of example, and referring to the following figures, given by way of non-limiting examples, in which identical references are given to similar objects. .

Figure 1 is a schematic representation of a remotely controlled unmanned aircraft including a battery pack according to one embodiment of the invention.

Figure 2 is a side view of the remotely operated unmanned aircraft including the battery pack of Figure 1.

Figure 3 is a schematic representation of the power-only battery according to one embodiment of the invention.

Figure 4 is a schematic representation of the energy cells positioned in the casing of the power battery of Figure 3.

Figure 5 is a view in a longitudinal sectional plane of the power battery of Figure 3.

Figure 6 is a side view of the battery pack of Figure 3.

Figure 7 is a rear view of the battery pack of Figure 3.

Figure 8 is a schematic representation of the lower and upper half-enclosures of the Figure 3 power battery enclosure.

FIG. 9 is a schematic representation of the steps of a method for mounting a power supply battery according to one mode of implementation of the invention.

It should be noted that the figures expose the invention in detail to implement the invention, said figures can of course be used to better define the invention if necessary.

DETAILED DESCRIPTION OF THE INVENTION

Disclosed is a power supply battery for a remotely controlled unmanned aircraft. Subsequently in this document, for the sake of brevity, a remotely controlled unmanned aircraft will be referred to as a “drone”.

As described above, with reference to Figures 1 and 2, a drone D comprises a rigid structure S on which are mounted several electric motors M to fly the drone D. The drone D also comprises a control module C electrically connected to each motor M and adapted to receive commands and to control the motors M according to the commands received.

Referring to Figure 1, the drone D extends longitudinally along an X axis, laterally along a Y axis and vertically along a Z axis, so as to form an orthogonal reference (X, Y, Z).

In order to allow the electrical supply of the motors M and of the control module C, the drone D comprises a supply battery 1.

The power supply battery 1 according to the invention is described in this document according to its position of use, that is to say mounted on the rigid structure S of the drone D. As such, the power supply battery 1 is described with reference to the orthogonal reference (X, Y, Z) and extends longitudinally along the X axis, which will be referred to below as the "alignment axis" X. In this document, the terms "lower" and "upper » refer to the vertical Z axis which runs from bottom to top. Similarly, in the remainder of this document, the "longitudinal plane" designates the plane formed by the X and Z axes, the "transverse plane" designates the plane formed by the Y and Z axes and the "horizontal plane" designates the plane formed by the X and Y axes.

As shown in Figures 3 and 4, the power bank 1 comprises a plurality of energy cells 2 (shown in Figure 4), a power connector 3 and a heat dissipation envelope 4.

In this example, the supply battery 1 is a lithium polymer battery, in which each energy cell 2 is configured to generate electrical energy from an exchange of ions between two electrodes. Such a lithium polymer battery is known to those skilled in the art and its operation will not be described in more detail in this document.

According to the invention, with reference to FIG. 4, the energy cells 2 are aligned in series along the alignment axis X so as to form a single row of energy cells 2. A single row of energy cells 2 makes it possible to maximize the heat exchange surface between the energy cells 2 and the outside, thus making it possible to maximize the dissipation of the heat generated by the energy cells 2 during the operation of the power supply battery 1. In addition, all the energy cells 2 are cooled in an equivalent and homogeneous manner, making it possible to limit the risk of overheating of an energy cell 2 which would be positioned at the heart of a battery which would have a parallelepiped shape. The supply battery 1 is thus better cooled, which limits the risk of deterioration and guarantees it a longer life.

The plurality of energy cells 2 aligned in a single row gives the power supply battery 1 an elongated shape (unlike the parallelepipedic shape of the prior art), which also makes it possible to configure the center of gravity of the drone D from practical way when mounting the power supply battery 1 on the rigid structure S of the drone D. An optimal setting of the center of gravity, that is to say centered with respect to the drone D, makes it possible to ensure the drone D's balance in flight and improves its maneuverability.

Thanks to a single row of energy cells 2, the thickness of the supply battery 1, that is to say in this example its dimension along the vertical axis Z, is reduced and similar to the thickness of the row of energy cells 2, that is to say the thickness of an energy cell 2. As such, as shown in Figure 5 representing a sectional view in the longitudinal plane (X, Z), the battery d Feed 1 preferably has a thickness, designated “alignment thickness” Ep2 of between 15 and 30 mm. The power supply battery 1 thus has a thin thickness, which makes it possible to reduce the size of the drone D and thus to increase its aerodynamics in flight and therefore its speed.

This document presents the example of a single row of energy cells 2 aligned along the alignment axis X, however the power supply battery 1 could alternatively comprise two rows of energy cells 2, arranged adjacently along the side axis Y, so as to form a more powerful power bank 1, while maintaining the alignment thickness Ep2 of a single row of energy cells 2, ensuring adequate heat dissipation and optimal cooling.

In one embodiment of the invention, with reference to Figures 4 and 5, each energy cell 2 has a cylindrical shape.

The row of energy cells 2 has an outer footprint P, shown in Figures 4 and 5. The cylindrical shape of the energy cells 2 gives the outer footprint P a wavy shape which increases the heat exchange surface of each energy cell 2, allowing them to be cooled individually more efficiently.

Preferably, with reference to FIG. 5, each energy cell 2 comprises a rigid shell 21, which makes it possible to reduce the thickness of the envelope 4 and thus to improve the heat dissipation performance, as will be described further below. details later in this document. Preferably again, the shell 21 of each energy cell 2 is made of steel, contributing to the rigidity and robustness of the power supply battery 1.

Preferably, the power supply battery 1 has a width, that is to say a dimension along the lateral axis Y, of between 50 and 150 mm and a length, that is to say a dimension along the longitudinal axis X, between 15 and 500 mm.

The row of energy cells 2 is mounted in a heat dissipation envelope 4, which will be described in more detail later in this document. In a preferred embodiment, as shown in Figure 4, the power supply battery 1 comprises two support members 6, mounted in the casing 4 and configured to cooperate respectively with the two ends of each energy cell 2. In this example, each support member 6 is in the form of a series of rings, into which is inserted one end of each energy cell 2. The latter are thus held fixedly in the envelope 4. It goes without saying that the support member 6 could just as well be in a different form, for example individual studs or even fixing clips. A support member 6 makes it possible, like the shells 21 of the energy cells 2, to participate in the overall rigidity of the sealed battery 1. This is advantageous given that the envelope 4 can be optimized for sealing and heat dissipation, the rigidity being ensured in part by other technical means.

As previously described, the power supply battery 1 comprises a power supply connector 3 connected to the row of energy cells 2 and configured to allow the exchange of electrical energy between the power supply battery 1 and one or more external equipment for power them. In this example, the power connector 3 includes a connection end 31 intended to be connected to the control module C of the drone D.

This document presents the example of a single power connector 3, however it goes without saying that the power supply battery 1 could just as well comprise a plurality of power connectors 3 to directly and individually power a plurality of electronic equipment. A single power supply connector 3 is nevertheless preferred to allow rapid replacement. Preferably, the power supply connector 3 is in itself sealed.

Referring to Figures 3 to 8, the heat dissipation envelope 4 makes it possible to hold the energy cells 2 together and to form a protection while evacuating the heat produced by the energy cells 2. For this, as shown in Figure 4, the envelope 4 comprises an inner surface SI in contact with the row of energy cells 2 (directly or via the support member 6) and an opposite outer surface SE. The envelope 4 is peripheral and defines an internal cavity in which the energy cells 2 are housed.

According to the invention, the envelope 4 is sealed around the row of energy cells 2 and around the power supply connector 3, the connection end 31 of the connector 3 extending outside the envelope 4, so as to limit any risk of introducing water inside the supply battery 1 while allowing the connection of the supply battery 1 for example to the control module C.

As shown in Figure 5, the envelope 4 intimately hugs the outer footprint P of the row of energy cells 2, making it possible to increase heat dissipation and thus to evacuate a greater quantity of heat. Such a profile also makes it possible to limit the size of the power supply battery 1, which improves the aerodynamics of the drone D.

Each energy cell 2 preferably having a cylindrical shape, the casing 4 preferably has a corrugated profile (shown in FIGS. 5 and 6), which increases the heat exchange surface between the interior of the casing 4 and the outside, as shown by the arrows F materialized in figure 5.

In a preferred embodiment, the envelope 4 is rigid, so as to protect the energy cells 2. More preferably, the envelope 4 is made of a composite material, making it possible to form an envelope 4 that is both robust and light. . The payload of the drone D is thus not impacted, allowing a more maneuverable, faster drone D and also makes it possible to increase the autonomy in flight.

Preferably, the envelope 4 comprises reinforcing fibers impregnated in a polymer resin. The reinforcing fibers can be glass fibers, carbon fibers or even high density polyethylene fibers, such as Dyneema® for example, providing a light, solid and impact-resistant envelope 4 .

In this example, the envelope 4 comprises a stack of four separate layers of reinforcing fibers impregnated in an epoxy resin. In this example, the envelope 4 comprises a stack of a layer of glass fibers, a first layer of carbon fibers, a second layer of carbon fibers and a layer of Dyneema ® fibers, the fibers of each layer being impregnated in epoxy resin. Such a stack of layers of composite material gives strength and lightness to the envelope 4.

Still with reference to FIG. 5, the envelope 4 has an envelope thickness Ep4 of between 0.1 and 2 mm. Preferably, the envelope thickness Ep4 is less than 1 mm. Such a thin envelope thickness Ep4 makes it possible to increase even more significantly the dissipation of the thermal energy generated by the supply battery 1 in operation. The power supply battery 1 thus comprises a thin and light envelope 4 while protecting it from the external environment. Thanks to the envelope 4 of the power supply battery 1 according to the invention, the latter is free from the addition of a heavy and bulky additional box as was the case in the prior art.

In a preferred embodiment, with reference to Figure 7, the casing 4 comprises a lower wall PI, intended to be at least partially in contact with the rigid structure S of the drone D and an opposite upper wall PS. In this example, the lower wall PI and the upper wall PS each extend in the horizontal plane (X, Y).

The lower wall PI comprises a central portion 44 and two end portions 45, on either side of the central portion 44. In the transverse plane (Y, Z), the lower wall PI has a concave profile, in which the central portion 44 forms a recess, allowing the passage of an air flow between the power supply battery 1 and the drone D when the power supply battery 1 is in use.

In this example, as shown in Figure 7, the central portion 44 and the end portions 45 have, in the transverse plane (Y, Z) a height difference h of between 0.5 and 30 mm. Such a height h allows the passage of a sufficiently large air flow to ensure optimal cooling of the energy cells 2. The energy cells 2 which generate heat when the power supply battery 1 is in operation are thus raised and moved away of the rigid structure S of the drone D.

In this example, each energy cell 2 is in intimate contact with the envelope 4 only at the level of the central portion 44. The support member 6 is thus configured to be positioned, in this example, inside the envelope 4 at the end portions 45 so as to support the energy cells 2 and to put them indirectly in contact with the envelope 4, thus making it possible to limit any risk of untimely displacement of the energy cells 2 in the envelope 4.

In one embodiment, the power supply battery 1 comprises a plurality of fixing members (not shown), making it possible to fix the power supply battery 1 to the drone D. In this example, each fixing member is connected to the envelope 4 at the lower wall PI and allows simple and quick fixing, for example by clipping.

Referring to Figure 8, the envelope 4 preferably comprises a lower half-envelope 41 and an upper half-envelope 42. Each half-envelope 41, 42 is preferably preformed so as to present a profile similar to the imprint exterior P of the row of energy cells 2. In other words, each half-envelope 41, 42 has been manufactured beforehand, for example by molding the exterior cavity P, so as to form a half-envelope 41, 42 whose profile intimately matches the profile of the outer footprint P of the row of energy cells 2.

Each half-envelope 41, 42 comprises an inner surface 46, intended to be in contact with the row of energy cells 2, an opposite outer surface 47 and a border 48. The inner surfaces 46 of the lower half-envelope 41 and of the upper half-envelope 42 make it possible to form the inner surface SI of the envelope 4, just as the outer surfaces 47 of the two half-envelopes 41, 42 make it possible to form the outer surface SE of the envelope 4.

The lower half-envelope 41 and the upper half-envelope 42 are configured to be mounted edge to edge facing each other and sealed at their edges 48, so as to form an envelope 4 in one piece. Preferably, once sealed, the two half-envelopes 41, 42 are inseparable, making it possible to guarantee sealing inside the power supply battery 1. In this example, the two half-envelopes 41, 42 are configured to be glued to each other at their edges 48. It goes without saying that the two half-envelopes 41, 42 can alternatively be connected to each other in a different way, for example by means of rivets.

In a preferred embodiment, with reference to Figure 5, the power supply battery 1 further comprises a thermally conductive chemical element 5, making it possible to improve heat dissipation. The chemical element 5 is preferably mounted between the row of energy cells 2 and the casing 4, so as to increase the thermal conductivity of the supply battery 1 and improve its cooling. Preferably, the chemical element 5 has a thermal conductivity of between 2 and 15 W/mK.

In this example, the chemical element 5 is in the form of a malleable or viscous material, making it possible to spread a conductive layer directly on the inner surface 46 of each half-envelope 41, 42 or on the row of energy cells 2. Preferably, the chemical element 5 is configured to be applied on either side of the row of energy cells 2, so as to improve the thermal conductivity by evacuating the heat through all the free surfaces of each cell energy 2, that is to say the entire surface of each energy cell 2 which is not in contact with an adjacent energy cell 2. The chemical element 5 also makes it possible to fill the alignment and surface state defects which may appear between the energy cells 2 and the casing 4 during the assembly of the supply battery 1. When the supply battery 1 is mounted, the chemical element 5 is then in contact both with the row of energy cells 2 and with the inner surface SI of the casing 4. In this example, the thermally conductive chemical element 5 is presented under the form of thermal paste.

In one embodiment, the power supply battery 1 comprises one or more spacing members (not shown), configured to allow both the mounting and the spacing of the power supply battery 1 from the rigid structure S of the drone D. In one example, the power supply battery 1 comprises four spacing members uniformly distributed around the power supply battery 1.

Each spacing member makes it possible, once mounted, to move the power supply battery 1 away from the rigid structure S of the drone D in order to allow the circulation of a greater flow of air between the drone D and the power supply battery 1.

Each spacer member is mechanically connected to the outer surface SE of the casing 4, for example by screwing, gluing, interlocking or by thermal sealing. In one embodiment, each spacer member is also configured to be mechanically connected to the rigid structure S of the drone D, for example by screwing, clipping or interlocking. Thanks to the spacer members, the power supply battery 1 has the shape of a bridge kept at a distance from the rigid structure S of the drone D, allowing more efficient cooling of the power supply battery 1.

Preferably, the power supply battery 1 further comprises an electrical management module, configured to electrically connect the power supply connector 3 to the row of energy cells 2 and to allow the operation of the power supply battery 1. Preferably, such a management module is mounted in a dedicated housing portion 43 of the envelope 4, shown in Figure 3.

As described above, with reference to Figures 1 and 2, the power supply battery 1 according to the invention is intended to be mounted on a drone D, such a drone D comprising a rigid structure S on which are mounted several electric motors M for fly the drone D and a control module C electrically connected to each motor M. In this example, the drone D comprises four motors M evenly distributed around the periphery of the drone D at equidistance from its center of gravity so as to ensure the stability of the drone D in flight.

The rigid structure S can be made of any material giving the drone D sufficient rigidity to allow its use. As such, the rigid structure S can be made of a composite, metallic or plastic material. The rigid structure S can alternatively be inflatable and thus be produced by a closed assembly of walls in a flexible material. Once inflated, thanks to the pressure exerted on the walls, the rigid structure S has a high rigidity.

The power supply battery 1 as described above is mounted on the rigid structure S of the drone D. Preferably, the power supply battery 1 is mechanically connected to the rigid structure S by means of the fastening members. The concave shape of the lower wall PI of the casing 4 makes it possible to maintain sufficient space between the power supply battery 1 and the drone D to allow the passage of an air flow, allowing optimal ventilation and therefore cooling. optimal power supply battery 1.

Thanks to the fixing elements, the power supply battery 1 according to the invention is preferably mounted on the rigid structure S of the drone D in a removable manner, so as to allow simple and rapid replacement, for example when the latter is discharged.

In a preferred embodiment, as shown in Figures 1 and 2, the power supply battery 1 is mounted on an upper face of the drone D, so as to position the power supply battery 1 close to the motors M driving the propellers. The power bank 1 is thus placed in the air flow generated by the propellers, which allows optimal cooling by thermal convection.

Even more preferably, the supply battery 1 is positioned on the rigid structure S equidistant from each motor M, themselves evenly distributed around the periphery of the drone D. In other words, the supply battery 1 is preferably positioned, in the horizontal plane (X, Y) at the level of the center of gravity of the drone D. Such positioning makes it possible to maintain the balance of the drone D, allowing optimal flight.

The power supply battery 1 according to the invention is advantageously sealed, which limits any risk of the presence of water vapor in contact with the energy cells 2, which makes it possible to increase their lifespan and therefore the lifespan of the power supply battery 1. Thanks to the sealed casing 4, an operator can easily touch and handle the power supply battery 1 even if his hands are wet or even in rainy weather, without risking damaging it. In addition, thanks to the elongated shape, its low thickness and the single row of energy cells 2, the power supply battery 1 according to the invention allows significant heat dissipation, which makes it possible to optimally and homogeneously cool the set of energy cells 2, making it possible to overcome a risk of overheating of the supply battery 1.

There will now be described a method of mounting a power supply battery 1 as previously described according to one mode of implementation of the invention, with reference to FIG. 9. In this example, the casing 4 comprises a lower half-envelope 41 and an upper half-envelope 42.

The method includes a preliminary step of preforming each half-envelope 41, 42 according to the profile of the outer cavity P of the row of energy cells 2. Such preforming is carried out for example by draping. It goes without saying that the preforming can be carried out in different ways.

In an application step E1, the operator then applies a layer of a thermally conductive chemical element 5 on the inner surface 46 of each half-casing 41, 42.

In this example, the operator then positions, in a positioning step E2, in the lower half-envelope 41 comprising the layer of chemical element 5, the row of energy cells 2 previously mounted in the support members 6. Each member support 6 is placed at the end portions 45 of the lower wall PI. Once positioned, the energy cells 2 rest on the central portion 44 of the lower wall PI and on each support member 6. The assembly formed by the energy cells 2 and the support members 6 partly ensures the rigidity of the battery supply 1.

Thanks to the preformed profile of the lower half-envelope 41, the latter comes into intimate contact with each energy cell 2 of the row of energy cells 2. The thermally conductive chemical element 5 is then in contact with both the row of energy cells 2 and the inner surface 46 of the lower half-casing 41. The power supply connector 3 is positioned in this step so as to pass through the casing 4. In other words, the connection end 31 of the connector power supply 3 is positioned outside the lower half-envelope 41. After this positioning step E2, the row of energy cells 2 has a face covered by the lower half-envelope 41 and a free face.

The operator then positions in a new positioning step E3, on the free face of the row of energy cells 2, the upper half-envelope 42 comprising the layer of chemical element 5, so that the upper half-envelope 42 matches the profile of each energy cell 2. The upper half-envelope 42 and the lower half-envelope 41 are positioned edge to edge, so that their respective edges 48 come into contact with one another.

The method then comprises a step E4 of sealing the upper half-envelope 42 on the lower half-envelope 41 so as to form a sealed envelope 4 in one piece. For this, the operator preferably applies glue to the edge 48 of each half-envelope 41, 42. The edges 48 are applied against each other, so as to glue the upper half-envelope 42 with the lower half-envelope 41.

Once sealed, the envelope 4 makes it possible to protect the row of energy cells 2 from bad weather and from any spraying of water, making it possible to increase the life of the energy cells 2. When the two half-envelopes 41, 42 are sealed, the connection end 31 of the connector 3 is located outside the sealed envelope 4, so as to be able to be connected to external equipment. The chemical element 5 plated on either side of the row of energy cells 2 between the energy cells 2 and the casing 4 as well as the low thickness and the material of the casing 4 make it possible to optimize the dissipation of the heat, making it possible to facilitate the cooling of the supply battery 1 when the latter is in operation.

Claims (10)

Sealed power supply battery (1) for remotely controlled unmanned aircraft, the power supply battery (1) extending longitudinally along an alignment axis (X) and comprising:

• a plurality of energy cells (2) aligned in series along the alignment axis (X) so as to form a single row of energy cells (2), the row of energy cells (2) having an outer footprint (P) ,
• at least one power supply connector (3) connected to the row of energy cells (2) and comprising a connection end (31) intended to be connected to a control module (C) of the remote-controlled unmanned aircraft, and
• a heat dissipation casing (4), intimately matching the outer cavity (P) of the row of energy cells (2), the casing (4) being sealed in a leaktight manner around the row of energy cells (2 ) and the power connector (3), the connection end (31) extending outside the casing (4).

Power battery (1) according to Claim 1, in which the casing (4) is made of a composite material. Supply battery (1) according to one of Claims 1 and 2, in which the casing (4) has a casing thickness (Ep4) of less than 2 mm. Supply battery (1) according to one of Claims 1 to 3, in which each energy cell (2) has a rigid shell (21). Supply battery (1) according to one of Claims 1 to 4, in which the row of energy cells (2) has an alignment thickness (Ep2) of between 15 and 30 mm. Supply battery (1) according to one of Claims 1 to 5, in which the casing (4) comprising an upper wall (PS) and a lower wall (PI), intended to be connected to the unmanned aircraft remote-controlled, at least the lower wall (PI) has in a vertical section plane of the power supply battery (1), a concave profile. Supply battery (1) according to one of Claims 1 to 6, comprising a thermally conductive chemical element (5) mounted between the row of energy cells (2) and the casing (4). Power supply battery (1) according to one of Claims 1 to 7, in which the casing (4) comprises a lower half-casing (41) and an upper half-casing (42), mounted opposite each other. screws of the lower part (41), sealed to each other so as to form a casing (4) in one piece. Remote-controlled unmanned aircraft comprising a rigid structure (S) and a supply battery (1) according to one of Claims 1 to 8, mounted on the rigid structure (S). A method of mounting a battery pack (1) according to claim 8, the method comprising:

• a positioning step (E3), in the lower half-casing (41), of the row of energy cells (2), the connection end (31) of the power supply connector (3) being positioned outside the lower half-envelope (41), and
• a sealing step (E4) of the upper half-casing (42) on the lower half-casing (41) so as to form a sealed casing (4) in one piece.