Pneumatic de-icing system for an aircraft

Abstract

The invention relates to a pneumatic de-icing system (10) for an aircraft, this system (10) having a stack of layers which comprises: - a support layer (12) suitable for covering a component of the aircraft, - an outer layer (14) situated opposite the support layer (12) and capable of being elastically deformed to detach the ice on this outer layer (14), - a first layer (16) of first inflatable cells (18) which is interposed between the support layer (12) and the outer layer (14), and - a second layer (20) of second inflatable cells (22) which is interposed between the first layer (16) and the support layer (12).

Description

[0001] DESCRIPTION

[0002] TITLE: PNEUMATIC DE-ICING SYSTEM FOR AN AIRCRAFT

[0003] 5. Technical field of the invention

[0004] The present invention relates to a pneumatic de-icing system for an aircraft, as well as a method for manufacturing such a system.

[0005] Technical background

[0006] The technical background includes, in particular, documents US-A1-2,504,684, EP-A1-3415435, FR-A-950094 and US-A-2,937,826.

[0007] A de-icing system is intended to equip the wings, tail assemblies, engine air intakes or other similar parts belonging to aircraft such as airplanes or helicopters.

[0008] It is known that when these aircraft cross areas where weather conditions are harsh and unfavorable, frost can form in the short or long term on these aerodynamic surfaces.

[0009] This ice buildup can subsequently lead to increased weight and a change in the wing's aerodynamic profile, potentially altering the aircraft's lift and drag, and therefore its flight characteristics. Consequently, these surfaces can be equipped with electric or pneumatic de-icing systems.

[0010] An electric defrosting system generally comprises electric heating elements. A pneumatic defrosting system generally comprises an inflatable bladder, and the invention relates to this latter case.

[0011] A pneumatic de-icing system generally includes a flexible envelope that at least partially covers the aerodynamic surface to be protected from frost and that can be inflated to change its shape or profile.

[0012] Thus, when frost forms on the aerodynamic surface, pressurized gas is sent into the envelope. The envelope then undergoes a sudden expansion which causes the frost layer to break into a multitude of pieces, and these are then ejected from the surface.

[0013] In current technology, a de-icing system comprises a stack of layers including:

[0014] - a support layer suitable for covering the aircraft part to be protected from frost,

[0015] - an outer layer opposite the support layer and capable of defining the aerodynamic surface on which frost is likely to form, and - a layer of inflatable cells interposed between the support layer and the outer layer.

[0016] This cell layer is connected to a gas passage port for supplying gas to the cells, as well as for venting gas from the cells.

[0017] The cells are arranged next to each other in the cell layer.

[0018] However, when the cell layer malfunctions, the entire de-icing system malfunctions. One solution to this problem is to divide the cell layer into several independent arrays, each containing its own cells and connected to its own gas flow port. The cell arrays are distributed throughout the cell layer, and when one cell array malfunctions, the other cell array(s) can continue to operate because they function autonomously.

[0019] However, this degraded mode of operation is not optimal because, since the cells of the different networks are distributed within the same layer, it is understood that the areas of the aerodynamic surface corresponding to the non-functional cells will not be inflated and therefore cannot be separated from the frost.

[0020] The present invention offers a simple, effective and economical solution to this problem.

[0021] Summary of the invention

[0022] The invention relates to a pneumatic de-icing system for an aircraft, this system comprising a stack of layers including: - a support layer suitable for covering a part of the aircraft,

[0023] - an outer layer opposite the supporting layer and capable of being elastically deformed to detach frost from this outer layer,

[0024] - a first layer of inflatable cells sandwiched between the support layer and the outer layer, this first layer being connected to at least one first gas passage port at the level of the support layer, the inflatable cells being arranged side by side in the first layer,

[0025] characterized in that it further comprises:

[0026] - at least one second layer of inflatable second cells intercalated between the first layer and the support layer, this second layer being connected to at least one second gas passage port at the level of the support layer, the second cells being arranged next to each other in the second layer and being able to be supplied with gas by said at least one second port independently of the gas supply of the first cells by said at least one first port.

[0027] The invention thus proposes a redundant cell layer, meaning that the de-icing system comprises two or more superimposed and independent cell layers. The cell layers are therefore arranged in a sandwich configuration. The first layer of cells operates autonomously and can include one or more independent cell arrays. Similarly, the second layer of cells also operates autonomously and can include one or more independent cell arrays. The first cells can be inflated independently of the second cells, or simultaneously with them. The superposition of the cells and their autonomous operation are advantageous for several reasons. The second cell layer can serve as a backup, activated only when the first cell layer malfunctions.The second layer of cells can be used alternately with the first layer to avoid excessive stress on the first layer and thus increase its lifespan. The second layer of cells can be used simultaneously with the first layer, as the cell layers can be smaller than those of the previous technique because they are distributed across two separate layers. Furthermore, since the layers are superimposed, even if the first layer fails, the second layer can inflate the entire aerodynamic surface to be protected without the risk of leaving uninflated areas, as was the case with the previous technique.

[0028] The system according to the invention may comprise one or more of the following features or steps, considered independently of each other or in combination with each other:

[0029] - The first layer includes:

[0030] - a single first gas passage port, the first cells all being interconnected to form a single first network of cells linked to the single first port, or

[0031] - two or more first gas transit ports, the first cells being distributed in two or more first cell networks, the first cells of each network being connected to each other and to one of the first ports, the first networks being capable of being supplied with gas by said first ports independently of each other;

[0032] - the second layer includes:

[0033] - a single second gas passage port, the second cells all being interconnected to form a single second cell network connected to the single second port, or

[0034] - two or more secondary gas transit ports, the secondary cells being distributed in two or more secondary cell networks, the secondary cells of each network being connected to each other and to one of the secondary ports, the secondary networks being capable of being supplied with gas by said secondary ports independently of each other;

[0035] - the first cells each have a general elongated shape and extend parallel to each other, and in which the second cells each have a general elongated shape and extend parallel to each other;

[0036] - the first cells extend parallel to the second cells; - the first cells extend perpendicularly to the second cells or at an angle to the second cells; - the number and / or dimensions of the first cells is / are identical to the number and / or dimensions of the second cells; alternatively, the number and / or dimensions of the first cells is / are different from the number and / or dimensions of the second cells;

[0037] - at least some of the first and second cells are directly positioned one above the other;

[0038] - at least some of the first and second cells are offset from each other;

[0039] - the first cells are formed between two sub-layers or sub-superpositions of layers which are connected to each other along first lines of connection so as to delimit the contours of the first cells, and in which the second cells are formed between two sub-layers or superpositions of sub-layers which are connected to each other along second lines of connection so as to delimit the contours of the second cells;

[0040] - the first and second connecting lines are formed by sewing or welding;

[0041] -- the layers or superpositions of layers that form the first and second cells are made of elastomer or thermoplastic elastomer;

[0042] - at least one of the sublayers or superpositions of sublayers that form the first cells includes a first drainage layer with interconnected voids, and at least one of the sublayers or superpositions of sublayers that form the second cells includes a second drainage layer with interconnected voids; - the first port extends from the support layer to the first layer of first cells and passes through a filler element that is located next to the second layer of second cells;

[0043] - the first and second ports are at least partly perpendicular to the support layer.

[0044] The invention also relates to a method for manufacturing a defrosting system according to one of the preceding claims, in which it comprises the following steps:

[0045] a) deposition or formation of the outer layer on a mold, b) deposition or formation of the first and second layers of inflatable cells on the outer layer,

[0046] c) deposition or formation of the support layer on the first and second layers of inflatable cells, and

[0047] before or after step c), a step of attaching the first and second ports to the first and second layers of inflatable cells, respectively. The method according to the invention may comprise one or more of the following features or steps, considered independently or in combination:

[0048] - after step c), the system is subjected to vulcanization, cold bonding or hot welding to solidify the stack of layers;

[0049] - the first and second layers of inflatable cells are delimited by: - ​​seams which are made before step b), or

[0050] - welds which are carried out before, during or after step b).

[0051] Brief description of the figures

[0052] Other features and advantages of the invention will become apparent upon reading the detailed description that follows, for an understanding of which reference should be made to the accompanying drawings in which:

[0053] Figure 1 is a very schematic cross-sectional view of a defrosting system according to the invention.

[0054] Figure 2 is a very schematic view, for example from above, of a defrosting system according to the invention.

[0055] Figure 3a is a very schematic view, for example from above, of a variant of the defrosting system according to the invention.

[0056] Figure 3b is a very schematic view, for example from above, of another variant of the defrosting system according to the invention.

[0057] Figure 3c is a very schematic view, for example from above, of another variant of the defrosting system according to the invention.

[0058] Figure 3d is a very schematic view, for example from above, of another variant of the defrosting system according to the invention.

[0059] Figure 3e is a very schematic view, for example from above, of another variant of the defrosting system according to the invention; Figure 3f is a very schematic view, for example from above, of another variant of the defrosting system according to the invention.

[0060] Figure 4 is a schematic cross-sectional view of an embodiment of a defrosting system according to the invention.

[0061] Figure 5 is a schematic cross-sectional view of an alternative embodiment of a defrosting system according to the invention.

[0062] Figures 6a-6b show the first steps of a process according to the invention for manufacturing the de-icing system of Figure 5,

[0063] Figure 7 shows another step in the process according to the invention for manufacturing the defrosting system of Figure 5,

[0064] Figure 8 shows another step in the process according to the invention for manufacturing the defrosting system of Figure 5,

[0065] Figure 9 shows another step in the process according to the invention for manufacturing the defrosting system of Figure 5,

[0066] Figure 10 shows another step in the process according to the invention for manufacturing the defrosting system of Figure 5,

[0067] Figure 11 is a schematic cross-sectional view of another embodiment of a defrosting system according to the invention.

[0068] Figures 12a-12b show the first steps of a process according to the invention for manufacturing the de-icing system of Figure 11,

[0069] Figure 13 shows another step in the process according to the invention for manufacturing the defrosting system of Figure 11.

[0070] Figure 14 shows another step in the process according to the invention for manufacturing the defrosting system of Figure 11.

[0071] Figure 15 shows another step in the process according to the invention for manufacturing the defrosting system of Figure 11.

[0072] Figure 16 shows several operating stages of the defrosting system according to the invention, according to a first mode, and

[0073] Figure 17 shows several operating steps of the defrosting system according to the invention, according to a second mode.

[0074] Detailed description of the invention Figure 1 represents the general principle of the invention which is the superposition of two layers of inflatable cells within the same de-icing system 10.

[0075] The defrosting system 10 is pneumatic and comprises a stack of layers including:

[0076] - a support layer 12 suitable for covering a part of the aircraft,

[0077] - an outer layer 14 opposite the support layer 12 and capable of being elastically deformed to detach the frost on this layer 14,

[0078] - a first layer 16 of first inflatable cells 18 sandwiched between the support layer 12 and the outer layer 14, and

[0079] - at least one second layer 20 of inflatable second cells 22 intercalated between the first layer 16 and the support layer 12.

[0080] The first layer 16 is connected to at least one first gas passage port 24, this or these first port(s) 24 being located at the level of the support layer 12.

[0081] The second layer 20 is connected to at least one second gas passage port 26, this or these second port(s) 26 being located at the level of the support layer 12.

[0082] In the example shown, ports 24 and 26 are next to each other.

[0083] Ports 24, 26 for example are made of metal (such as aluminum alloy) or thermoplastic.

[0084] The first 18 cells are arranged next to each other in the first layer 16, and the second 22 cells are arranged next to each other in the second layer 20.

[0085] It is understood that the first cells 18 are supplied with gas by port(s) 24, independently of the supply of gas to the second cells 22 by port(s) 26.

[0086] It is important to note that the surface of the part intended to be covered by the de-icing system 10 is not necessarily flat, and therefore the de-icing system 10 is not necessarily flat in its final operating position. For example, when the surface to be protected from frost is the leading edge of a wing or an air intake, the de-icing system 10 conforms to the shape of this surface and therefore has a generally curved shape. Although the examples illustrated in the drawings show flat layers, it is understood that these layers can have other shapes, and in particular, any shape whatsoever.

[0087] Figure 2, for example, is a top, bottom, or front view of a complete defrosting system 10. It takes the form of a flexible inflatable envelope that can be attached and glued to the surface of the part to be protected, for example.

[0088] In this figure 2, the first layer 16 comprises a single first gas passage port 24, and the first cells 18 are all connected to each other to form a single first network R1 of cells 18 connected to the single first port 24.

[0089] In this same figure 2, the second layer 20 comprises a single second gas passage port 26, and the second cells 22 are all connected to each other to form a single second network R1' of cells 22 connected to the single second port 26.

[0090] We also see that the first cells 18 each have a generally elongated shape and extend parallel to each other, and that the second cells 22 each have a generally elongated shape and extend parallel to each other. Each of the first cells 18 communicates with at least one adjacent first cell 18 via its longitudinal ends, and each of the second cells 22 communicates with at least one adjacent second cell 22 via its longitudinal ends.

[0091] We also see that the first cells 18 extend parallel to the second cells 22.

[0092] As illustrated, the number and dimensions of the first 18 cells can be identical to the number and dimensions of the second 22 cells. Furthermore, the first and second 18 and 22 cells can be directly positioned one above the other.

[0093] Figure 3a is a similar view to that of Figure 2 of another de-icing system 10. In this Figure 3a, the first layer 16 comprises two or more first gas passage ports 24, and the first cells 18 are distributed in two or more first cell arrays R1, R2, R3.

[0094] The first cells 18 of each of the networks R1, R2, R3 are connected to each other and to one of the first ports 24. The first networks R1, R2, R3 are capable of being supplied with gas by the first ports 24 independently of each other.

[0095] The second layer 20 comprises two or more second gas passage ports 26, and the second cells 22 are distributed in two or more second cell networks R1', R2', R3'.

[0096] The second cells 22 of each of the networks R1', R2', R3' are connected to each other and to one of the second ports 26. The second networks R1', R2', R3' are capable of being supplied with gas by the second ports 26 independently of each other.

[0097] It is also observed that the first cells 18 each have a generally elongated shape and extend parallel to one another, and that the second cells 22 each have a generally elongated shape and extend parallel to one another. Each of the first cells 18 communicates with at least one adjacent first cell 18 via one of its longitudinal ends, and each of the second cells 22 communicates with at least one adjacent second cell 22 via one of its longitudinal ends. The diagram shows that the connection between the cells 18 of the same network R1, R2, R3 is such that this network has a comb-like shape, and that the connection between the cells 22 of the same network R1', R2', R3' is such that this network has a serpentine shape.

[0098] We also see that the first cells 18 extend parallel to the second cells 22.

[0099] As illustrated, the number and dimensions of the first 18 cells can be identical to the number and dimensions of the second 22 cells. Furthermore, the first and second 18 and 22 cells can be directly positioned one above the other.

[0100] The embodiment shown in Figure 3b differs from that shown in Figure 3a in that the number of first cells 18 is greater than the number of second cells 22. Although the second cells 22 are positioned directly below the first cells 18, layer 20 and the second network R1' are less extensive than layer 16 and the first network R1; therefore, layer 20 and the first network R1 extend well beyond the second network R1'. For example, layer 20 and the second network R1' are located approximately in the middle and below layer 16 and the first network R1.

[0101] We can also see that the second port 26 can be at a distance from the first port 24.

[0102] The variant embodiment of Figure 3c differs from the embodiment of Figure 3a in that the first cells 18 are perpendicular to the second cells 22.

[0103] Furthermore, the number and dimensions of the first 18 cells can be identical to the number and dimensions of the second 22 cells.

[0104] The variant embodiment of figure 3d differs from the embodiment of figure 3a in that the second port 26 is at a distance from the first port 24.

[0105] The embodiment variant in Figure 3e represents a combination of the solutions in Figures 3b and 3c.

[0106] The variant embodiment of Figure 3f differs from the embodiment of Figure 3a in that the first cells 18 are inclined relative to the second cells 22.

[0107] We now refer to figure 4 which illustrates a more concrete embodiment of a defrosting system 10.

[0108] The outer layer 14 comprises one layer or two or more superimposed sublayers 14a, 14b. In the example shown, it comprises two sublayers 14a, 14b. These sublayers 14a, 14b are, for example, made of elastomer.

[0109] The support layer 12 comprises a single layer or two or more superimposed sublayers. In the example shown, it comprises a single layer, for example made of elastomer, but may include at least one fabric or braid.

[0110] The support layer 12 is traversed here by ports 24, 26. Each of the ports 24, 26 can have a general tubular shape, one section 28 of which protrudes from the support layer 12, on the side opposite the outer layer 14, and another section 30 of which is engaged in the stack of layers for the fluidic connection of its end to the corresponding cells 18, 22. In the example shown, the first port 24 extends from the support layer 12 to the first layer 16 of the first cells 18 and passes through a filler element 32 which is located next to the second layer 20 of the second cells 22.

[0111] The second port 26 extends from the support layer 12 to the second layer 20 of second cells 22.

[0112] We can also see that ports 24, 26 can be at least partly perpendicular to support layer 12.

[0113] The first cells 18 are preferably formed between two sublayers 34, 36 or superpositions of sublayers 34a, 34b, 36a, 36b which are connected together along first bond lines L1, L2, ..., Ln so as to delimit contours of the first cells 18, as can be seen in figures 1 to 4.

[0114] The second cells 22 are formed between two sublayers 38, 40 or superpositions of sublayers 38a, 38b, 40a, 40b which are connected together along second bond lines L1', L2', ..., Ln' so as to delimit contours of the second cells 22, as can also be seen in figures 1 to 4.

[0115] The connecting lines L1, L2, ..., Ln can be distinct from the connecting lines L1', L2', ..., Ln', in particular in the embodiment of Figure 3c, 3e, and 3f for example.

[0116] The connecting lines L1, L2, ..., Ln can be superimposed with the connecting lines L1', L2', ..., Ln', in particular in the embodiments of figures 2, 3a, 3b and 3d for example.

[0117] Among the layers 34, 36, 34a, 34b, 36a, 36b, at least one of these layers is preferably a C1 drainage layer, and among the layers 38, 40, 38a, 38b, 40a, 40b, at least one of the layers is a C2 drainage layer.

[0118] A C1, C2 drainage layer is a layer which has interconnected voids which allow fluidic communication between the different cells of the same network.

[0119] The de-icing system 10 of Figure 5 differs from that of Figure 4 in that an additional layer 42 of the waterproof membrane type is interposed between the layers 16, 20. Reference is now made to Figures 6a to 10 which illustrate a manufacturing process for the de-icing system 10 of Figure 4 or 5. In this manufacturing process, the different layers of the stack are considered to be made of elastomer or elastomer-based material, or fabric.

[0120] The process includes a first step a) illustrated in figures 6a-6b of depositing or forming the outer layer 14 on a mold 44, and in particular the sub-layers 14a, 14b one after the other on the mold 44.

[0121] The process includes a step b) illustrated in figures 7 and 8 of preparation of the first and second layers 16, 20 of inflatable cells 18, 22 and of deposition of these layers 16, 20 on the outer layer 14.

[0122] The connecting lines L1, L2, ..., Ln, L1', L2', ..., Ln' are formed to delimit cells 18, 22. These connecting lines are advantageously made by seams which cross the corresponding layers.

[0123] The different layers or sub-layers of the first and second layers 16, 20 are stacked as illustrated in figure 7.

[0124] The assembly is then deposited on the outer layer 14 as illustrated in figure 8.

[0125] The process then includes a step c) illustrated in figure 9 comprising the deposition or formation of the support layer 12 on the first and second layers 16, 20.

[0126] Before or after step c), the ports 24, 26 are connected to the first and second layers 16, 20 respectively, as illustrated in figures 9 and 10. After step c), the system is preferably subjected to vulcanization to solidify the stack of layers.

[0127] Reference is now made to Figures 11 to 15, which illustrate a manufacturing process for the de-icing system 10, in which at least some of the layers are made of thermoplastic (TP) and / or thermoplastic elastomer (TPE). A distinctive feature of this system is that the connecting lines can be made by welding. The de-icing system 10 may include at least one fabric or braid.

[0128] The process includes steps a) and b) illustrated in figures 12a, 12b and 13 of deposition or formation of the outer layer 14, and of deposition or formation of the first and second layers 16, 20 of inflatable cells 18, 22 on the outer layer 14. Figure 13 also shows a step c) of deposition or formation of the support layer 12 on the first and second layers 16, 20.

[0129] The bond lines L1, L2, Ln, L1 L2', Ln' can then be formed to delimit cells 18, 22 (Figure 14). These bond lines are advantageously made by welds that cross the corresponding layers.

[0130] Before or after step c), the connection of ports 24, 26 to the first and second layers 16, 20 respectively is made, as illustrated in figure 15.

[0131] After step c), the system is preferably subjected to hot welding or cold bonding to solidify the stack of layers.

[0132] Figures 16 and 17 show two modes of operation of a defrosting system 10 according to the invention, these defrosting modes being applicable to all the variants described above.

[0133] In Figure 16, arrows F1 and F2 show the nominal operation of the system 10 during which only the first layer 16 of cells 18 is inflated and used for de-icing. There is an alternation of supplying the cells 18 with pressurized gas and of extracting the pressurized gas and evacuating the cells, so that the cells 18 inflate and deflate at a predetermined rate.

[0134] Arrow F3 shows a failure of the first layer 16 such as for example a sealing defect or a leak from one of the cells 18.

[0135] In this case, arrows F4 and F5 show a backup operation of system 10 during which only the second layer 20 of cells 22 is inflated and used for de-icing. There is an alternation of supplying the cells 22 with pressurized gas and extracting the pressurized gas and evacuating the cells, so that the cells 22 inflate and deflate at a predetermined rate, replacing the first cells 18 which are no longer in use.

[0136] In Figure 17, the arrows illustrate the alternating operation of the first and second layers 16 and 20. The system thus transitions from a deflated state to a swollen state in which only cells 18 are inflated, then back to a deflated state, then to a swollen state in which only cells 20 are inflated, and finally back to a deflated state. This cycle is repeated as many times as necessary at a predetermined rate. Dimensionally, cells 18 and 22 can be up to one meter long or more, and several centimeters wide. The cells are separated from each other by a distance of 1 cm or less, for example, which corresponds to the width of the connecting lines between the cells.

Claims

DEMANDS 1. A pneumatic de-icing system (10) for an aircraft, this system (10) comprising a stack of layers including: - a support layer (12) suitable for covering a part of the aircraft, - an outer layer (14) opposite the support layer (12) and capable of being elastically deformed to detach frost from this outer layer (14), - a first layer (16) of first inflatable cells (18) interposed between the support layer (12) and the outer layer (14), this first layer (16) being connected to at least one first gas passage port (24) at the level of the support layer (12), the first inflatable cells (18) being arranged side by side in the first layer (16), characterized in that it further comprises: - at least one second layer (20) of inflatable second cells (22) interposed between the first layer (16) and the support layer (12), this second layer (20) being connected to at least one second gas passage port (26) at the level of the support layer (12), the second cells (22) being arranged side by side in the second layer (20) and being capable of being supplied with gas by said at least one second port (26) independently of the supply of gas to the first cells (18) by said at least one first port (24).

2. De-icing system according to claim 1, wherein the first layer (16) comprises: - a single first gas passage port (24), the first cells (18) all being connected to each other to form a single first network (R1) of cells connected to the single first port (24), or - two or more first gas passage ports (24), the first cells (18) being distributed in two or more first cell networks (R1, R2, R3), the first cells (18) of each of the networks (R1, R2, R3) being connected to each other and to one of the first ports (24), the first networks (R1, R2, R3) being able to be supplied with gas by said first ports (24) independently of each other.

3. De-icing system according to claim 1 or 2, wherein the second layer (20) comprises: - a single second gas passage port (26), the second cells (22) all being connected to each other to form a single second network (R1') of cells connected to the single second port (26), or - two or more second gas passage ports (26), the second cells (22) being distributed in two or more second cell networks (R1', R2', R3'), the second cells (22) of each of the networks (R1', R2', R3') being connected to each other and to one of the second ports (26), the second networks (R1', R2', R3') being able to be supplied with gas by said second ports (26) independently of each other.

4. Defrosting system (10) according to any one of the preceding claims, wherein the first cells (18) each have a generally elongated shape and extend parallel to each other, and wherein the second cells (22) each have a generally elongated shape and extend parallel to each other.

5. Defrosting system (10) according to any one of the preceding claims, wherein the number and / or dimensions of the first cells (18) is / are identical to the number and / or dimensions of the second cells.

6. Defrosting system (10) according to any one of claims 1 to 5, wherein at least some of the first and second cells (18, 22) are directly positioned one above the other.

7. De-icing system (10) according to any one of claims 1 to 5, wherein at least some of the first and second cells (18, 22) are offset from each other.

8. De-icing system (10) according to any one of the preceding claims, wherein the first cells (18) are formed between two layers (34, 36) or superpositions of layers (34a, 34b, 36a, 36b) which are connected to each other along first connecting lines (L1, L2, ..., Ln) so as to delimit contours of the first cells (18), and wherein the second cells (22) are formed between two sub-layers (38, 40) or superpositions of sub-layers (38a, 38b, 40a, 40b) which are connected to each other along second connecting lines (L1', L2', ..., Ln') so as to delimit contours of the second cells (22).

9. De-icing system (10) according to claim 8, wherein the first and second connecting lines (L1, L2, Ln, L1 L2', Ln') are formed by stitching or welding.

10. De-icing system (10) according to claim 8 or 9, wherein at least one of the sub-layers (34, 36) or superpositions of sub-layers (34a, 34b, 36a, 36b) which form the first cells (18) comprises a first drainage layer (C1) having interconnected voids, and at least one of the sub-layers (38, 40) or superpositions of sub-layers (38a, 38b, 40a, 40b) which form the second cells (22) comprises a second drainage layer (C2) having interconnected voids.

11. De-icing system (10) according to any one of the preceding claims, wherein the first port (24) extends from the support layer (12) to the first layer (16) of first cells (18) and passes through a filling element (32) which is located next to the second layer (20) of second cells (22).

12. De-icing system (10) according to any one of the preceding claims, wherein the first and second ports (24, 26) are at least partly perpendicular to the support layer (12).

13. Method of manufacturing a de-icing system (10) according to any one of the preceding claims, wherein it comprises the following steps: a) deposition or formation of the outer layer (14) on a mold (44), b) deposition or formation of the first and second layers (16, 20) of inflatable cells (18, 22) on the outer layer (14), c) deposition or formation of the support layer (12) on the first and second layers (16, 20) of inflatable cells (18, 22), and before or after step c), a step of linking the first and second ports (24, 26) respectively to the first and second layers (16, 20) of inflatable cells (18, 22).

14. Method according to claim 13, wherein, after step c), the system is subjected to vulcanization, cold bonding or hot welding to solidify the layer stack.

15. A method according to claim 13 or 14, wherein the first and second layers of inflatable cells are delimited by: - seams that are made before step b), or - welds which are carried out before, during or after step b).

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