Method for assembling a first metal part and a second part made of an organic matrix composite material, and part produced by said assembly

Abstract

The present invention relates to a method for assembling a first metal part (12) and a second part (14) made of an organic matrix composite material, the first part (12) having a first connection part (12A) and the second part (14) having a second connection part (14A), the method comprising the steps of: overlapping the first connection part and the second connection part such that a through hole (14B) of the second connection part opens into the first connection part; forming a protective layer (18) on at least a side wall (14B3) of the through hole; forming a seal between the protective layer and the first connection part; and forming a fastening element (20) fastened to the first connection part (12) and extending into the through hole (14B) to surround the second connection part by additive manufacturing using cold gas spray deposition of metal powder.

Description

[Technical Field]

[0001] The present disclosure relates to a method of assembling two pieces of a component, one made of metal and the other made of an organic matrix composite. For example, but not by way of limitation, such a component may be a combustion chamber jacket for a rocket engine. [Background technology]

[0002] Methods for assembling metal components and components made of organic matrix composites are known. However, these assembly methods can very often be improved. Therefore, a need exists in this regard. Summary of the Invention

[0003] One embodiment is a method of assembling a first metal component with a second component made of an organic matrix composite, the first metal component having a first connection and the second component having a second connection, the method comprising: overlapping the first and second connection portions such that a through hole of the second connection portion opens into the first connection portion and the through hole has a sidewall; forming a protective layer on at least a sidewall of the through hole; forming a seal between the protective layer and the first connection; forming a fastening element fastened to the first connection portion, extending into the through hole, and surrounding the second connection portion by additive manufacturing using cold gas spray deposition of metal powder, also known by the abbreviation CGS as "Cold Gas Spraying."

[0004] A connection portion of a part is understood to be a portion that is configured to be in direct contact with and cooperate with another part, and therefore a portion that does not cooperate with the other part, e.g., a non-overlapping or non-interlocking portion, is not part of the connection portion of the other part.

[0005] It is also understood that the second connecting part has one or more through holes. In the following, unless otherwise specified, the term "through hole" shall mean "at least one through hole." According to a first alternative, the through hole is formed before the method is performed, and the second connecting part exhibits a through hole before the two connecting parts are superimposed. According to a second alternative, the second connecting part does not have a through hole before the method is performed, and the through hole is formed during an intermediate step after the two connecting parts are superimposed. In this case, a blind hole may or may not be formed in the first connecting part during this intermediate step. A blind hole is understood to be a hole that has only a single orifice and forms a concave surface. Such a blind hole can improve the attachment of a fastening element to the first connecting part. In the case of a blind hole, the protective layer can, for example, extend over the side wall of the blind hole, forming a seal between the protective layer and the bottom of the blind hole.

[0006] Additive manufacturing using cold gas spray deposition of metal powder is understood to be a manufacturing method in which metal is deposited at a temperature below its melting temperature. Such a deposition method is particularly suitable for assembling a second part, as it ensures that the temperature of the metal during deposition remains below the degradation temperature of the organic matrix composite of the second part. Subsequently, unless otherwise specified, "CGS deposition" shall mean "additive manufacturing using cold gas spray deposition of metal powder."

[0007] For example, the fastening element may, but need not necessarily, be made of the same grade of metal as the first component. The fastening element surrounds all or a portion of the second connecting portion. In other words, the second connecting portion is sandwiched, in whole or in part, between the fastening element and the first connecting portion. The fastening element may have various forms. For example, the fastening element may be in the form of a pin, a bridging piece, an annular flange, etc.

[0008] The protective layer is understood to be a layer capable of protecting the second part during the formation by CGS deposition of the fastening element. The seal is understood to hermetically connect the protective layer and the first connection part. It should be understood that at least one surface portion of the first connection part remains without through-holes (i.e., is not covered by a seal or protective layer) so that the fastening element can be formed directly on that surface portion to fix the fastening element on the first connection part. In the following, unless otherwise specified, "joint" means "seal".

[0009] The present inventors have found that during the formation of fastening elements by CGS deposition in prior art methods, some of the sprayed material can escape between the first and second connection parts. This leads to both wear of the second connection part (the escaped metal particles attack the composite material of the second part) and failure of the fastening element, especially at the interface between the fastening element and the first connection part. The present inventors have observed that this weakens the mechanical strength of the assembly.

[0010] By forming a seal between the protective layer and the first connection, the material sprayed during CGS deposition can no longer escape, allowing the fastening element to be formed without defects at the joint with the first connection and without damaging the second connection. The mechanical strength of the assembly is significantly improved over assemblies obtained using prior art methods.

[0011] For example, the parts may be flat or curved plates and the fasteners may form flat or curved flanges.

[0012] For example, the first connecting portion and the second connecting portion form a plate extending in a first direction and a second direction, respectively, and having a thickness in a third direction orthogonal to the first and second directions, the first part and the second part are arranged side by side in the first direction, at least one through hole extends in the third direction, and the first connecting portion and the second connecting portion overlap each other in the first and second directions. The first direction and / or the second direction can be linear or curved in a manner similar to directions defined in a Cartesian, cylindrical, or spherical coordinate system.

[0013] In certain embodiments, the protective layer extends across the entire interface between the second connection portion and the fastening element.

[0014] For example, the fastening element may cooperate with the second part on a surface other than the side of the hole, in which case the protective layer formed as described above may fully protect the second part over all surfaces configured to cooperate with the fastening element during formation of the fastening element.

[0015] In certain embodiments, the protective layer is formed using a metal sheet.

[0016] For example, the metal sheet may initially have a planar shape and be applied onto the second connecting portion, and then be deformed to fit the shape of all or part of the second connecting portion, particularly the shape of the sidewall of the hole. For example, the metal sheet may then be machined, for example by milling, to leave free access to the bottom of the hole, i.e., the first connecting portion. For example, the metal sheet may be made of a metal that is more susceptible to plastic deformation than the material of the first connecting portion and / or the second connecting portion. For example, the metal sheet may be a sheet of gold, silver, aluminum, copper, etc.

[0017] In certain embodiments, the seal is formed between the metal sheet and the first connection by metal deposition by metal arc wire additive manufacturing.

[0018] Subsequently, and unless otherwise specified, "arc wire deposition" shall mean "metal arc wire additive manufacturing." Such a deposition is very unobtrusive to the substrate to which it is applied, both from a thermal and abrasive standpoint, and is particularly well suited for the second component and the metal layer. This ensures the integrity of the metal layer and the second component, and therefore ultimately the solidity of the assembly.

[0019] Arc wire deposition allows for the direct application of a soft metal that can fill gaps or gaps and form a robust and reliable seal.

[0020] For example, the arc wire deposit can cover the entire wall of the hole, including the bottom, and then a portion of the bottom of the hole can be machined, for example, by milling, to leave free access to the bottom of the hole, i.e., the first connection, while preserving a portion of the arc wire deposit extending from the metal sheet to the first connection, which forms a seal. For example, the metal of the arc wire deposit can be the same as the metal of the metal sheet, but this is not necessarily required. This allows for satisfactory adhesion between the metal sheet and the arc wire deposit.

[0021] In certain embodiments, the protective layer and the seal are formed simultaneously by at least one metal deposition by metal arc wire additive manufacturing.

[0022] Forming the protective layer and the seal in the same step saves time. Furthermore, by reducing the number of steps, the number of interventions is also reduced, thus reducing the risk of degrading the first and / or second connections.

[0023] In certain embodiments, the protective layer and the seal are formed simultaneously by at least two metal depositions, a first deposition being a metal arc wire additive manufacturing metal deposition and a second deposition being a cold gas spray deposition of metal powder carried out on the first deposition, the second deposition being distinct from the additive manufacturing step using cold gas spray deposition of metal powder to form the fastening element.

[0024] In other words, the protective layer and the seal are formed in at least two passes: at least a first pass by arc wire deposition and at least a second pass by CGS deposition. For example, the metal of the first and second deposits at the bottom of the hole is removed (leaving behind the portion that forms the seal between the first and second connections) before forming the fastening element. In other words, the seal and the protective layer can form a single, identical, continuous element in this example. For example, the same material, such as copper, can be used for the first and second deposits, but this is not necessarily required. For example, in the case of a rotationally symmetric part, the first and / or second layer can be a continuous circumferential layer deposition.

[0025] One embodiment relates to a method of manufacturing a combustion chamber jacket of a rocket engine, comprising an assembly method according to any one of the embodiments described in this disclosure.

[0026] The assembly method according to the present disclosure is particularly well suited to rocket engine combustion chamber jackets.

[0027] One embodiment relates to a component comprising a first metal component and a second component made of an organic matrix composite material assembled together by an assembly method according to any one of the embodiments described in the present disclosure.

[0028] The objects and advantages of the present disclosure will be better understood upon reading the following detailed description of various embodiments, given by way of non-limiting examples, which description makes reference to the accompanying drawings in which: [Brief explanation of the drawings]

[0029] [Figure 1] FIG. 1 shows the first stage of the assembly method. [Figure 2A] FIG. 2A shows one of two alternative assembly methods. [Figure 2B] FIG. 2B shows one of two alternative assembly methods. [Figure 3A] FIG. 3A shows a second stage of the assembly method for one of the two alternatives of FIG. 2A according to the first embodiment. [Figure 3B] FIG. 3B shows a second stage of the assembly method for one of the two alternatives of FIG. 2B according to the first embodiment. [Figure 4A] FIG. 4A shows a third stage of the method of assembly of one of the two alternatives of FIG. 2A according to the first embodiment. [Figure 4B] FIG. 4B shows a third stage of the method of assembly of one of the two alternatives of FIG. 2B according to the first embodiment. [Figure 5A] FIG. 5A shows a fourth stage of the assembly method for one of the two alternatives of FIG. 2A according to the first embodiment. [Figure 5B] FIG. 5B shows a fourth stage of the assembly method for one of the two alternatives of FIG. 2B according to the first embodiment. [Figure 6A] FIG. 6A shows one of three intermediate stages for simultaneously producing a protective layer and a seal for the two alternatives of FIGS. 2A and 2B, respectively, according to a second embodiment. [Figure 6B] FIG. 6B shows one of three intermediate stages for simultaneously producing a protective layer and a seal for the two alternatives of FIGS. 2A and 2B, respectively, according to a second embodiment. [Figure 6C] FIG. 6C shows one of three intermediate stages for simultaneously producing a protective layer and a seal for the two alternatives of FIGS. 2A and 2B, respectively, according to a second embodiment. [Figure 6D] FIG. 6D shows one of three intermediate stages for simultaneously producing a protective layer and a seal for the two alternatives of FIGS. 2A and 2B, respectively, according to a second embodiment. [Figure 7A] FIG. 7A shows the fifth stage of the assembly method for the two alternatives of FIGS. 2A and 2B. [Figure 7B] FIG. 7B shows the fifth stage of the assembly method for the two alternatives of FIGS. 2A and 2B. [Figure 8] FIG. 8 shows an outer jacket of a combustion chamber of a rocket engine obtained using the assembly method according to the first or second embodiment. [Figure 9] FIG. 9 shows a rocket engine equipped with the outer jacket of the rocket engine combustion chamber of FIG. DETAILED DESCRIPTION OF THE INVENTION

[0030] It should be noted that the figures are highly schematic for clarity of the present disclosure. A method for assembling a first metal component 12 and a second component 14 made of an organic matrix composite material will be described with reference to FIGS. 1 to 7. For example, the first component 12 is made of a metal alloy, such as a nickel-based alloy, and the second component 14 is made of a thermoplastic or thermosetting organic matrix composite material. FIGS. 2A, 2B, 3A, 3B, 4A, 4B, 5A, 5B, 6C, and 6D are cross-sectional views along plane II in FIG. 1. It should be noted that the first and second stages in FIGS. 1, 2A, and 2B and the fifth stage in FIGS. 7A and 7B are common to the first and second embodiments, and FIGS. 3A, 3B, 4A, 4B, 5A, and 5B belong to the first embodiment, while FIGS. 6A, 6B, 6C, and 6D belong to the second embodiment.

[0031] In this example, the first part 12 and the second part 14 are rotationally symmetric parts. More specifically, the first part 12 and the second part 14 each have a generally annular plate shape extending in an axial direction X (axis of rotational symmetry), a radial direction R, and a circumferential direction C. The radial direction R is a direction perpendicular to the axial direction X. The azimuthal or circumferential direction C corresponds to a direction describing a ring around the axial direction X. The three directions, axial, radial, and azimuthal, correspond to directions defined by height, radius, and angle, respectively, in a cylindrical coordinate system.

[0032] The first part has a first connecting portion 12A with a shoulder 12C that extends transversely to the axial direction X. That is, in this example, the shoulder 12C extends in the radial direction R and the circumferential direction C. The first connecting portion 12A thus forms a step that receives the second connecting portion 14A of the second part 14.

[0033] During the first stage shown in FIG. 1, the first part 12 and the second part 14 move toward each other along the axis X, as indicated by arrow I, such that the first connecting portion 12A and the second connecting portion 14A overlap, until the second part 14 abuts the shoulder 12C.

[0034] According to a first alternative shown in FIG. 2A, the second connecting portion 14A is provided with at least one through hole 14B before the first stage. The through hole 14B extends in the radial direction R and opens into the first connecting portion 12A. In this example, the through hole 14B is frustoconical, with a side wall 14B3 uniformly inclined relative to the axis Att and converging radially toward the first connecting portion 12A. Any other shape of through hole is also possible. In this example, the first connecting portion 12A does not have a blind hole, but it can be provided with a blind hole formed before the first stage or even after the first stage, as will be described below with reference to the second alternative shown in FIG. 2B.

[0035] According to a second alternative example shown in FIG. 2B, no through holes are provided in the second connecting portion 14A prior to the first stage. After the first stage, at least one through hole 14B is formed, for example, using a drill bit F. In this example, when drilling the through hole 14B in the second connecting portion 14A, a blind hole 12B is also drilled in the first connecting portion 12A in an extension of the through hole 14B. The through hole 14B and the blind hole 12B extend in the radial direction R. The through hole 14B is similar to that described with reference to FIG. 2A. The blind hole 12B has a geometric axis Atb extending radially between the inlet 12B1 and the bottom 12B2 and a side wall 12B3 extending between the inlet 12B1 and the bottom 12B2. In this example, the blind hole 12B has a frustoconical shape, with the side wall 12B3 uniformly inclined relative to the axis Atb and converging from the inlet 12B1 to the bottom 12B2. Any other shape of blind hole is possible. According to an alternative example, the blind hole 12B is present before the first stage, but the through hole 14B is not.

[0036] Next, a protective layer 18 is formed on at least the sidewall 14B3 of the through-hole 14B. The protective layer 18 can be formed, for example, according to the first embodiment or the second embodiment described below.

[0037] According to a first embodiment, during the second stage, as shown in Figures 3A and 3B, a metal sheet 18A can be placed, for example, on the second connection portion 14A opposite the first connection portion 12A, and then the metal sheet 18A is stamped to fit the walls of the hole 14B (Figure 3A, first alternative) or the walls of the hole 14B and the hole 12B (Figure 3B, second alternative). In Figures 2A and 2B, the stamped metal sheet 18A is shown with dashed lines. In this example, the metal sheet 18A is made of copper.

[0038] Subsequently, during a third step, the portion of the metal sheet 18B extending over the bottom of the hole is machined, in this example milled, to expose the first connecting portion 12A at the bottom of the hole, as shown in Figures 4A and 4B, i.e., after machining, the first connecting portion 12A forms the bottoms 14B2, 12B2 of the hole.

[0039] In Figures 4A and 4B, the machined and removed parts of the metal sheet 18A are shown by dashed lines. In Figure 4A, the first connecting portion 12A does not have a blind hole (first alternative), and the protective layer 18 extends to the first connecting portion 12A over the entire radial height of the through hole 14B. In Figure 4B, the first connecting portion 12A has a blind hole 12B (second alternative), and the protective layer 18 extends over the entire radial height of the through hole 14B and the blind hole 12B to the bottom 12B2 of the blind hole 12B.

[0040] Then, during a fourth step, a seal 19 is formed between the protective layer 18 and the first connection portion 12A, as shown in Figure 5A (first alternative) and Figure 5B (second alternative). In this example, the seal 19A is formed by arc wire deposition of the seal 19A between the metal sheet 18A and the first connection portion 12A. In this example, the metal used to form the seal is copper or a copper-based alloy.

[0041] The arc wire deposit covers the bottoms 14B2, 12B2 of the holes, and then, similar to the third step described above, the arc wire deposit is machined to expose the first connection portion 12A at the bottom of the holes, taking care not to alter the seal 19A extending between the metal sheet 18A and the first connection portion 12A. For example, the diameter of the mill used in this step is smaller than the diameter of the mill used in the third step. In Figures 5A and 5B, the machined and removed parts of the arc wire deposit are shown in dashed lines.

[0042] According to the second embodiment, as shown in FIGS. 6A, 6B, 6C, and 6D, the protective layer 18 and the seal 19B are simultaneously formed by arc wire deposition. More precisely, in this example, a first arc wire deposition is generated in the circumferential direction C by forming one or more annular elongated pieces 18B1 along the desired axial width, as shown in FIG. 6A. In this example, this first deposition 18B1 is copper. The sidewall 14B3 of the through-hole 14B is covered over its entire radial height. In this example, the surface of the first connection portion 12A exposed through the through-hole 14B is also covered. A second CGS deposition is then performed in the circumferential direction C to form one or more annular elongated pieces 18B2 so as to partially cover the circumferential elongated piece 18B1 by the desired axial width, in this example. As shown in FIG. 6B , this annular elongated part 18B2 extends over the entire circumference of the second connecting portion 14A in the circumferential direction C and covers the side wall 14B3 of the through hole 14B over its entire radial height. In this example, the surface of the first connecting portion 12A exposed through the through hole 14B, which is covered by the elongated part 18B1, is also covered by the elongated part 18B2. In this example, the second deposition part 18B2 is copper. Alternatively, the annular elongated part 18B2 entirely covers the axial elongated part 18B1. In this second embodiment, the protective layer 18 is thus formed by the deposition layer 18B arising from the elongated parts 18B1 and 18B2. By forming such elongated parts, the protective layer 18 further extends toward the vicinity of the through hole 14B, facing the first connecting portion 12A. During the two arc wire and CGS depositions to form the annular elongated part, a seal 19B is simultaneously created between the layer 18B and the first connecting portion 12A, as shown in FIG. 6C (first alternative) and FIG. 6D (second alternative). In fact, the protective layer 18B is formed in contact with the first connecting portion 12A. As in the first embodiment, the portion of the layer 18B extending over the bottom of the hole is then machined away, in this example by milling, as shown in FIGS. 6C and 6D, to expose the first connecting portion 12A at the bottom of the hole. That is, the bottoms 14B2, 12B2 of the hole are formed by the first connecting portion 12A.During this operation, care is taken not to alter the part 19B that forms the seal. In Figures 6C and 6D, the machined and removed parts are shown in dashed lines.

[0043] Finally, during the fifth step common to the first and second embodiments, as shown in FIG. 7A (first alternative) and FIG. 7B (second alternative), the fastening element 20 is formed by CGS deposition. For example, the fastening element 20 is made of a metal alloy, for example a nickel-based alloy. This fastening element 20 extends through the through-hole 14B, is fastened to the first connecting portion 12A (i.e., at the bottom 14B2, 12B2), and together with the second connecting portion 14A, surrounds the first connecting portion 12A. It should be noted in particular that the fastening element 20 surrounds the second connecting portion 14A, particularly via the sidewall 14B3 of the through-hole 14B, which is inclined relative to the axis Att of the through-hole 14B. In other words, the sidewall 14B3 forms a seat for the fastening element 20, which allows the first part 12 to be fastened to the second part 14. In this example, the interface between the fastening element 20 and the second connecting portion 14A extends up to the vicinity of the through-hole 14B, forming part of a seat cooperating with the fastening element 20. The fastening element 20 also surrounds the second connecting portion 14A in this vicinity. According to an alternative, there are as many point-like attachment elements as there are through-holes 14B. According to another alternative (not shown), a single fastening element forming an annular flange extends in all through-holes 14B around the entire circumference of the second connecting portion 14A in the circumferential direction C. According to yet another alternative (not shown), the fastening element forms a bridging part fastened to the first part 12 both on the first connecting portion 12A through the through-hole of the second connecting portion (14A) and on a part of the first part other than the first connecting portion 12A (for example, on the part of the first part 12 on the left in Figures 7A and 7B).

[0044] 8 shows the part 10 obtained by the above-described assembly. In this example, there are as many fastening elements 20 as there are through-holes. In this example, the part 10 is a combustion chamber jacket of a rocket engine. In this example, the above-described assembly method is part of a method for manufacturing a combustion chamber jacket of a rocket engine.

[0045] FIG. 9 shows a rocket engine 100 with a combustion chamber jacket 10 opening into an outlet 30 .

[0046] While the present invention has been described above with reference to specific examples, it is clear that variations and modifications can be made to these examples without departing from the general scope of the invention as defined in the claims. In particular, individual features of different embodiments shown or mentioned can be combined in further embodiments. The specification and drawings are therefore to be regarded as illustrative rather than restrictive.

[0047] It is also clear that all features described in relation to the method, either alone or in combination, can be substituted for the apparatus, and conversely, all features described in relation to the apparatus, either alone or in combination, can be substituted for the method. The present disclosure also includes the following inventions. The first aspect is A method for assembling a first metal component (12) with a second component (14) made of an organic matrix composite material, the first metal component (12) having a first connection portion (12A) and the second component (14) having a second connection portion (14B), comprising: The method comprises: overlapping the first connection portion (12A) and the second connection portion (14A) so that a through hole (14B) of the second connection portion (14A) opens into the first connection portion (12A) and the through hole (14B) has a side wall (14B3); forming a protective layer (18) on at least the sidewall (14B3) of the through hole (14B); forming a seal (19A, 19B) between the protective layer (18) and the first connection portion (12A); and forming a fastening element (20) fastened to the first connecting portion (12A), extending into the through hole (14B), and surrounding the second connecting portion (12B) by additive manufacturing using cold gas spray deposition of metal powder. The second aspect is The assembly method according to the first embodiment, wherein the protective layer (18) extends over the entire interface between the second connecting portion (14A) and the fastening element (20). The third aspect is In the assembly method of the first or second embodiment, the protective layer (18) is formed using a metal sheet (18A). The fourth aspect is A method of assembly in a third aspect, wherein the seal (19A) is formed by metal deposition by additive manufacturing of metal arc wire between the metal sheet and the first connection. The fifth aspect is The method of assembly according to the first or second embodiment, wherein the protective layer (18) and the seal (19B) are simultaneously formed by at least one metal deposition by metal arc wire additive manufacturing. The sixth aspect is An assembly method in a fifth aspect, wherein the protective layer (18) and the seal (19B) are formed simultaneously by at least two metal depositions, a first deposition portion (18B1) being a metal deposition portion by metal arc wire additive manufacturing, and a second deposition portion (18B2) being a cold gas spray deposition of metal powder carried out on the first deposition portion (18B1), the second deposition portion being different from the additive manufacturing stage using cold gas spray deposition of metal powder to form the fastening element (20). A seventh aspect is A method for manufacturing a combustion chamber jacket (10) of a rocket engine, comprising the assembly method according to any one of the first to sixth aspects. The eighth aspect is A component comprising a first metal component (12) and a second component (14) made of an organic matrix composite material, assembled together by the assembly method according to any one of the first to sixth aspects.

Claims

1. A method for assembling a first metal component (12) with a second component (14) made of an organic matrix composite material, the first metal component (12) having a first connection portion (12A) and the second component (14) having a second connection portion (14A), comprising: The method comprises: a step of overlapping the first connecting portion (12A) and the second connecting portion (14A) so that a through hole (14B) of the second connecting portion (14A) opens into the first connecting portion (12A) and the through hole (14B) has a side wall (14B3); forming a protective layer (18) on at least the sidewall (14B3) of the through hole (14B); forming a seal (19A, 19B) between said protective layer (18) and said first connection portion (12A); and forming a fastening element (20) fastened to the first connecting portion (12A), extending into the through hole (14B), and surrounding the second connecting portion (14A) by additive manufacturing using cold gas spray deposition of metal powder.

2. 2. The assembly method of claim 1, wherein the protective layer (18) extends over the entire interface between the second connection portion (14A) and the fastening element (20).

3. 3. The assembly method according to claim 1 or 2, wherein the protective layer (18) is formed using a metal sheet (18A).

4. 4. The method of claim 3, wherein the seal (19A) is formed by metal arc wire additive manufacturing metal deposition between the metal sheet and the first connection.

5. 3. The method of assembly according to claim 1 or 2, wherein the protective layer (18) and the seal (19B) are formed simultaneously by at least one metal deposition by metal arc wire additive manufacturing.

6. 6. The assembly method according to claim 5, wherein the protective layer (18) and the seal (19B) are simultaneously formed by at least two metal depositions, a first deposition (18B1) being a metal deposition by metal arc wire additive manufacturing and a second deposition (18B2) being a cold gas spray deposition of metal powder carried out on the first deposition (18B1), the second deposition being distinct from an additive manufacturing stage using cold gas spray deposition of metal powder to form the fastening element (20).

7. A method for manufacturing a jacket (10) for a combustion chamber of a rocket engine, comprising the assembly method according to any one of claims 1 to 6.

8. A component comprising a first metal component (12) and a second component (14) made of an organic matrix composite material, assembled together by the assembly method of any one of claims 1 to 6.

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