DEVICE FOR COUPLING A PROPULSION SYSTEM TO A ENGINE PISTON OF AN AIRCRAFT AND CORRESPONDING AIRCRAFT

Abstract

DEVICE FOR COUPLING A PROPULSION SYSTEM TO A REACTOR PISTON OF AN AIRCRAFT AND CORRESPONDING AIRCRAFT The invention relates to a device for coupling a propulsion system (102) to a reactor piston (106) of an aircraft (10), said device comprising a base (20) which comprises a first (21) and a second (23) base part joined to each other, so as to form a base (200) intended to be fixed to said propulsion system and a first wall (201) extending substantially perpendicular to said base (200). Said first wall of said base cooperating with a sleeve (50), a pair of flanges (282a, 282b) and means (22) for fixing to said reactor piston. With such a device, it is possible to provide a more secure solution for fixing a propulsion system in the event of a failure of the fastener. Fig. 3

Description

Title of the invention: DEVICE FOR COUPLING A PROPULSION SYSTEM TO A ENGINE PISTON OF AN AIRCRAFT AND CORRESPONDING AIRCRAFT Technical field

[0001] The present invention relates to a device for coupling a propulsion system to the wing of an aircraft. More specifically, the invention relates to a device for coupling a propulsion system to the engine pylon of the aircraft, as well as to an aircraft comprising a propulsion system and at least one such device for coupling the propulsion system to the engine pylon. STATE OF THE PRIOR ART

[0002] Typically, for an aircraft, a propulsion assembly comprises, for example, a turbojet engine which is attached to a wing of the aircraft using a reactor mast. The reactor mast generally consists of a structure comprising a plurality of tubes attached to ribs.

[0003] The turbojet engine is attached to the ribs of the engine pylon by means of engine mounts which conventionally comprise, at the front, a plurality of front engine mounts, and at the rear, a plurality of rear engine mounts. Generally, the turbojet engine is attached, at the front, at its gearbox and, at the rear, at the body of the turbojet engine.

[0004] [Fig. 2] illustrates an example of a prior art attachment 9 for coupling a turbojet engine T to the engine pylon M of an aircraft. The attachment 9 comprises a base 90 in the shape of an inverted T comprising a base 900 from which a wall 902 extends substantially perpendicularly. The base 900 has a generally quadrilateral shape and is intended to be in contact with the turbojet engine T and to be fixed to the turbojet engine T for example using screw elements (at the gearbox for the front attachment and at the body of the turbojet engine for the rear attachment, for example).

[0005] The wall 902 comprises a bore in which is housed a sleeve (not visible) itself having a bore in which is threaded a fixing pin 91 which is fixed to the engine pylon M, for example by screwing. The attachment 9 further comprises damping pads 92 implemented on either side of the wall 902 of the base 90 and held by a set of flanges 93 to partially absorb the forces generated by the turbojet. A attachment 9 implementing pads 92 is also called a flexible attachment. A spacer 94 can also be implemented, around a part of the sleeve, between the base 9 and the engine pylon M.

[0006] Although current installations are satisfactory in terms of fixing the turbojet engine to the engine pylon, the implementation of these installations requires a multiplication of these installations to prevent a possible failure of the attachment, in particular, in the event of breakage or cracking of the base 900. The multiplication of these installations results in an overload and therefore increased fuel consumption, which is not satisfactory.

[0007] It is therefore necessary to provide a solution ensuring optimal and more secure attachment of a turbojet to the wing of an aircraft. Statement of the invention

[0008] An object of the present invention is to provide a device for coupling a propulsion system to the engine pylon of an aircraft, this device providing a more secure solution for fixing a propulsion system in the event of failure of the attachment.

[0009] For this purpose, a device is proposed for coupling a propulsion system to a reactor mast of an aircraft, said device comprising:

[0010] - a base having a substantially inverted T shape, said base comprising a base intended to be fixed to said propulsion system and a first wall extending substantially perpendicular to said base, said first wall comprising a first bore extending along a longitudinal axis;

[0011] - a substantially tubular sleeve comprising a first portion received at less partly in said first bore of said base and a second portion of which a first end extends in the extension of said first portion in the direction of said reactor mast, a second end of said second portion being intended to cooperate with said reactor mast, said sleeve comprising a central bore coaxial with said longitudinal axis;

[0012] - fixing means comprising a first nut intended to be secured to said reactor mast and a first fixing screw, said first fixing screw comprising a first fixing head from which a first threaded rod extends perpendicularly, said first threaded rod being threaded into said central bore of said sleeve;

[0013] - a second front flange and a second rear flange, said second flanges being arranged respectively on either side of said first wall of said base, said second flanges each comprising a fourth bore coaxial with said longitudinal axis;

[0014] - a spacer intended to be arranged between said second rear flange and said reactor mast, said spacer comprising a fifth bore coaxial with said longitudinal axis so that said spacer is threaded onto said second portion of said sleeve.

[0015] Said first portion of said sleeve is threaded into said fourth bores of said second flanges. Said first fixing head bears against said second front flange and said first threaded rod is threaded through said central bore of said sleeve, said first threaded rod being screwed to said first nut secured to said reactor mast.

[0016] According to the invention, said base comprises a first and a second base part, each of said first and second parts being in the form of an L, where said first part comprises a first base wall from which a second wall comprising a sixth bore extends perpendicularly, and where said second part comprises a second base wall from which a third wall comprising a seventh bore extends perpendicularly.

[0017] Said first and second base parts are joined against each other so that said second wall and said third wall together form said first wall of said base, that said first and second base walls together form said base of said base, and that said sixth and seventh bores together form said first bore.

[0018] In this way, if one of the first or second base parts fails, the other base part ensures that the coupling of the propulsion system to the engine pylon is maintained. The risk of complete loss of the device for coupling the propulsion system to the engine pylon is therefore reduced.

[0019] Advantageously, the device comprises means for centering along said longitudinal axis said first and second base parts relative to each other.

[0020] According to a particular aspect, said centering means comprise at least one male cylinder coaxial with the longitudinal axis, projecting from a first contact face of said second wall, or respectively of said third wall, and at least one cylindrical housing coaxial with the longitudinal axis, for receiving said at least one male cylinder, said at least one cylindrical housing being provided at a second contact face of said third wall, or respectively of said second wall, said first and second contact faces being arranged opposite each other when said first and second parts of the base are assembled.

[0021] According to another particular aspect, the fixing means comprise a second nut arranged to bear against a free end of said first threaded rod opposite said first fixing head, the second fixing means also comprising a second fixing screw comprising a second fixing head from which a second threaded rod extends perpendicularly. Said second fixing head bears against said first fixing head and said second threaded rod is threaded into an eighth bore extending coaxially with said longitudinal axis, passing through said first fixing screw, and wherein said second threaded rod is screwed into said second nut.

[0022] According to another particular aspect, the device also comprises: - a pair of first flanges, said first flanges being fixed respectively on either side of said first wall of said base, said first flanges each comprising a second bore coaxial with said longitudinal axis; and - a pair of bearings, said bearings being arranged respectively against one of said first flanges, said bearings each comprising a third bore coaxial with said longitudinal axis;

[0023] wherein said pads are each sandwiched between a second flange and a first flange;

[0024] and wherein said first portion of said sleeve is threaded into said second bores of said first flanges and into said third bores of said bearings.

[0025] The invention also proposes an aircraft comprising a propulsion system, a reactor mast and at least one device as described previously, said propulsion system being coupled to the reactor mast by said at least one device, where said base is fixed to said propulsion system, and where said first nut is fixed to said reactor mast. Brief description of the drawings

[0026] The above-mentioned features of the invention, as well as others, will appear more clearly on reading the following description of an exemplary embodiment and of these variants, said description being made in relation to the attached drawings, among which:

[0027] [Fig-1] is a side view of an aircraft according to the invention;

[0028] [Fig.2] is a perspective view of a fastener according to a prior art solution;

[0029] [Fig.3] is a perspective view of a coupling device according to an example of realization of the invention;

[0030] [Fig.4] is a side and sectional view along plane A of the device of [Fig.3];

[0031] [Fig.5] is a side view and section along plane A of a first variant of the device of [Fig.3];

[0032] [Fig.6] is a side view and section along plane A of a second variant of the device of [Fig.3]; and

[0033] [Fig.7] is a side view and section along plane A of a third variant of the device of [Fig.3].

[0034] DETAILED DESCRIPTION OF AN EXAMPLE OF EMBODIMENT

[0035] [Fig.l] shows an aircraft 10 which comprises a propulsion system 102 for example of the turbojet or turboprop type. The propulsion system 102 is linked to a wing 104 of the aircraft 10 via a reactor mast 106.

[0036] In the following description, the terms relating to a position are taken with reference to an aircraft in normal flight position, that is to say as it is shown in [Fig.l] and the "front" and "rear" positions are taken with respect to the front and rear of the propulsion system 102 and with respect to the direction of advance F of the aircraft 10 when the propulsion system 102 is operating.

[0037] In the following description, and by convention, X is the longitudinal direction of the propulsion system which is horizontal when the aircraft is on the ground, Y is the transverse direction which is horizontal when the aircraft is on the ground, and Z is the vertical direction which is vertical when the aircraft is on the ground, these three directions X, Y and Z being orthogonal to each other.

[0038] The reactor mast 106 and the propulsion system 102 have a vertical median plane XZ and the propulsion system 102 is here a turboprop with a propeller 102a, but it could be of the double-flow turbojet type with a nacelle.

[0039] Figs. 3 and 4 show a device 2 for coupling a propulsion system 102 to the engine pylon 106 of the aircraft 10 according to a main embodiment of the invention. The device 2 is here illustrated horizontally so that the elements can be described in relation to the orthonormal reference frame X, Y and Z described above. It is obviously understood that the device 2 can be arranged and oriented differently in order to adapt to the propulsion system 102 and the engine pylon 106 to which the device is attached. [Fig. 4] illustrates a side view in section along the section plane A. The section plane A is a plane parallel to the vertical plane XZ passing through the axis of the first fixing screw described in more detail in the remainder of this description. The section plane A is the same for Figs. 5 to 7.

[0040] In this example, the device 2 comprises a base 20 having a substantially inverted T shape. This base 20 comprises a substantially planar base 200, which in this illustration extends in a plane parallel to the XY plane. The base 200 is intended to be fixed to the propulsion system 102 by fixing means such as screw elements. To do this, the base 200 has, in this example, holes 205 provided at least at each corner of the base 200. The holes 205 are each intended to receive a fixing screw to allow fixing by screwing. Other techniques for fixing the base to the propulsion system are conceivable, such as riveting or welding in particular.

[0041] The base 20 comprises a first wall 201 which extends substantially perpendicular to the base 200, that is to say in a plane parallel to the plane YZ. The first wall 201 further comprises a first bore 202 located substantially in the center of the first wall 201 and which extends along a longitudinal axis 5 which is here shown substantially parallel to the horizontal axis X.

[0042] The base 20 may also comprise reinforcing side walls 203 extending between the base 200 and the first wall 201, at the lateral edges of the base 20, so as to absorb mechanical forces. In this example, the side walls 203 have a triangular shape.

[0043] The device 2 also comprises a sleeve 50 which is generally tubular and extends coaxially to the longitudinal axis 5. The sleeve 50 comprises a first portion 502 of which at least a part is received in the first bore 202 of the base 20 and a second portion 504 of which a first end extends from and in the extension of the first portion 502 in the direction of the reactor mast 106.

[0044] As illustrated in [Fig.4], the free end of the second portion 504 is intended to cooperate with the reactor mast 106. More precisely, the free end of the second portion 504 is fitted into a housing 107 provided in the reactor mast 106.

[0045] In this example, the first 502 and second 504 portions are separated by a shoulder 508 making it possible to optimize the positioning of the sleeve 50, as described in more detail below.

[0046] The sleeve 50 further comprises a central bore 506 extending coaxially with the first bore 202 of the base 20. This central bore 506 is intended to receive a first fixing screw 221 described below.

[0047] The device 2 comprises fixing means 22 which make it possible to fix the device 2 to the reactor mast 106. To do this, the fixing means 22 comprise a first nut 220 secured to the reactor mast 106 and a first fixing screw 221. In this example, the first nut 220 secured to the reactor mast 106 is of the captive type, but any other type of nut which can be secured to the reactor mast can be used. An axial mounting clearance J1 (visible in [Fig.4]) may be provided between the free end of the second portion 504 of the sleeve 50 and the first nut 220 so as to allow the deformation of the bearings described below when tightening the first fixing screw 221. The axial clearance J1 also allows the compression of the spacer 30 between the engine mast 106 and a second rear flange 282b described below.

[0048] The first fixing screw 221 comprises a first fixing head 222 arranged opposite the engine mast 106 and which bears against a second front flange 282a (described below). A first threaded rod 223 extends perpendicularly from the first fixing head 222, along the longitudinal axis 5, and is threaded into the central bore 506 of the sleeve 50. The first threaded rod 223 has a length greater than the length of the sleeve 50 so that it can be screwed into the nut 220 secured to the reactor mast 106. The sleeve 50, via the fixing means 22, makes it possible to transfer the shear forces generated by the propulsion system 102 to the reactor mast 106.

[0049] The device 2 further comprises a pair of first flanges comprising a first front flange 242a and a first rear flange 242b. The first front flange 242a and rear flange 242b are fixed respectively on either side of the first wall 201 of the base 20. In this example, the fixing of the first front flange 242a and rear flange 242b to the first wall 201 is carried out by fixing screws located near the lateral edges of the first wall 201. It is understood, however, that other fixing means can be envisaged without departing from the principle of the invention.

[0050] The first front flange 242a and rear flange 242b each comprise a second bore, respectively 244a, 244b, extending coaxially with the longitudinal axis 5. The dimensions of the second bores 244a, 244b are configured to allow the reception of the first portion 502 of the sleeve 50. In this example, a radial mounting clearance is provided between the second bores 244a, 244b and the first portion 502 of the sleeve 50 to allow deformation of the bearings (described below) up to a predetermined load level.

[0051] The device 2 comprises at least one pair of pads which allows a predetermined deformation of the device 2 in order to absorb at least part of the forces generated by the propulsion system 102. The implementation of these pads makes it possible to obtain a “flexible attachment”.

[0052] In this example, the device 2 comprises two pads, namely a front pad 262a and a rear pad 262b. The front pads 262a and rear pads 262b are arranged respectively to bear against the first front flange 242a and the first rear flange 242b.

[0053] The front 262a and rear 262b bearings each comprise a third bore, respectively 264a, 264b, extending coaxially with the longitudinal axis 5. The dimensions of the third bores 264a, 264b are configured to allow the reception of the first portion 502 of the sleeve 50. In this example, a radial mounting clearance is provided between the third bores 264a, 264b and the first portion 502 of the sleeve 50 to allow deformation of the bearings 262a, 262b up to the predetermined load level. In this example, the bearings 262a, 262b are made of elastomer whose elasticity can be selected according to the desired maximum deformation for example.

[0054] The device 2 further comprises a pair of second flanges comprising a second front flange 282a and a second rear flange 282b. The second flanges front 282a and rear 282b are arranged respectively on either side of the first wall 201 of the base 20. More precisely, the second front 282a and rear 282b flanges respectively bear against the front 262a and rear 262b pads so that the front pad 262a is sandwiched between the first front flange 242a and the second front flange 282a and the rear pad 262b is sandwiched between the first rear flange 242b and the second rear flange 282b.

[0055] The second front 282a and rear 282b flanges each comprise a fourth bore, respectively 284a, 284b, extending coaxially with the longitudinal axis 5. In this example, no radial mounting clearance is provided between the fourth bores 284a, 284b and the first portion 502 of the sleeve 50 in order to allow joint radial movement between the sleeve 50 and the second front 282a and rear 282b flanges. In particular, the first and second base parts 21, 22 move relative to the sleeve 50 and to the second front 282a and rear 282b flanges thanks to the deformation of the bearings 262a, 262b.

[0056] The sleeve 50 will drive the second front flange 282a and rear flange 282b, which in turn cause the deformation of the bearings 262a, 262b.

[0057] The second front 282a and rear 282b flanges each comprise, on their face 287a, 287b facing each other when the device 2 is assembled, that is to say on the face in contact with the bearing, a first 288a and a second 288b recess. More specifically, the first recess 288a provided on the face 287a of the second front flange 282a makes it possible to receive the free end of the first portion 502 of the sleeve 50. In this example, an axial mounting clearance J2 (visible in [Fig.4]) is provided between the recess 288a and the first portion 502 of the sleeve 50 to allow deformation of the bearings 262a, 262b when screwing in the first fixing screw 221. The second recess 288b provided on the face 287b of the second rear flange 282b makes it possible to receive the shoulder 508 separating the first 502 and second 504 portions of the sleeve 50.

[0058] The device 2 also comprises a spacer 30 intended to be arranged between the second rear flange 282b and the reactor mast 106 and to bear against the second rear flange 282b and the reactor mast 106 when the device 2 is assembled. When the first fixing screw 221 is tightened, the spacer 30 is therefore compressed between the second rear flange 282b and the reactor mast 106.

[0059] The spacer 30 comprises a fifth bore 32 extending coaxially to the longitudinal axis 5. The dimensions of the fifth bore 32 are configured to allow the reception of the second portion 504 of the sleeve 50. More precisely, the spacer 30 is threaded onto the second portion 504 of the sleeve 50 and therefore extends around the second portion 504 of said sleeve 50.

[0060] The first portion 502 of the sleeve 50 is therefore threaded into the second bores. 244a, 244b of the first flanges 242a, 242b, in the third bores 264a, 264b of the bearings 262a, 262b and in the fourth bores 284a, 284b of the second flanges 282a, 282b, while the spacer 30 is threaded onto the second portion 504 of the sleeve 50. In addition, the first fixing head 222 bears against the second front flange 282a and the first threaded rod 223 is threaded through the central bore 506 of the sleeve 50 to be screwed to the first nut 220 secured to the engine mast 106. Thus, the implementation of the spacer 30 and the second flanges 282a, 282b therefore allows, during screwing of the first fixing screw 221, to tighten the elements of the device 2 together.

[0061] The device 2 can optionally implement a protective cylinder 60 which is fitted onto at least a portion of the first portion 502 of the sleeve 50. The cylinder 60 makes it possible to protect the sleeve 50 from possible contact and friction of the latter with the base 20 during deformation of the pads 262a, 262b.

[0062] According to the invention, and in order to provide a solution in the event of failure of the base 20 (such as a crack at the base 200, for example), the base 20 is divided so as to comprise a first 21 and a second 23 base parts 20. In this way, if one of the first 21 or second 22 base parts 20 fails, the other base part makes it possible to ensure that the coupling of the propulsion system 102 to the engine pylon 106 is maintained. The risk of complete loss of the device 2 for coupling the propulsion system 102 to the engine pylon 106 is therefore reduced. In addition, this solution makes it possible to provide a multiple path (via the first and second base parts) for transferring the forces generated by the propulsion system 1002 to the engine pylon 106.

[0063] More precisely, each of the first 21 and second 23 parts is in the form of an L whose vertical portions are joined to each other during assembly of the device 2. The first part 21 comprises a first base wall 210 extending in a plane parallel to the horizontal plane XY from which a second wall 212 extends perpendicularly, which therefore extends in a plane parallel to the vertical plane YZ. The second wall 212 comprises a sixth bore 214 extending coaxially to the longitudinal axis 5.

[0064] The second part 23 of base 20 comprises a second base wall 230 extending in a plane parallel to the horizontal plane XY and from which a third wall 232 extends perpendicularly, which therefore extends in a plane parallel to the vertical plane YZ. The third wall 232 comprises a seventh bore 234 extending coaxially to the longitudinal axis 5. In this example, each of the first 21 and second 23 parts of base 20 comprises reinforcing side walls 203.

[0065] The first 21 and second 23 base parts 20 are arranged to bear against each other so that: the second wall 212 and the third wall 232 are placed against each other and together form the first wall 201 of the base 20, the first base wall 210 and the second base wall 230 together form the base 200 of the base 20 and the sixth 214 and seventh 234 bores together form the first bore 202 of the base 20.

[0066] In the example illustrated in Figs. 3 and 4, each of the first 210 and second 230 base walls comprises four holes 205 arranged substantially at each corner of the first 210 and second 230 base walls. The holes 205 are each intended to receive a fixing screw which makes it possible to fix the first 21 and second 23 base parts 20 to the propulsion system 102.

[0067] In a first variant of the main embodiment, and as illustrated in [Fig. 5], the device 2 further comprises centering means 40 relative to the direction X, and more precisely relative to the longitudinal axis 5 of the first fixing screw 221, of the first 21 and second 23 base parts 20 relative to each other. These centering means 40 make it easier to position the first 21 and second 23 base parts 20 relative to each other and to assemble the various elements of the device 2. The centering means 40 also make it possible to improve the holding of the first 21 and second 23 base parts 20 relative to each other, for example in the event of a failure of one of the first 21 and second 23 base parts 20.

[0068] In this example, the centering means 40 comprise at least one male cylinder 402, coaxial with the longitudinal axis 5, carried and projecting from a first contact face 211, 231 of the part 21 or of the part 22 of the base 20. The at least one male cylinder 402 cooperates with a corresponding female cylindrical housing 404 for receiving the male cylinder 402. The cylindrical housing 404 extends coaxially with the longitudinal axis 5 and is formed in a second contact face 211, 231 of the other of the parts 21, 23. The first and second contact faces are arranged opposite each other when the first 21 and second 23 parts of the base 20 are assembled.

[0069] More particularly, in the example illustrated in [Fig. 5], the first wall 201 of the first part 21 of the base 20 comprises a cylindrical housing 404 on its second contact face 211, oriented towards the second part 23 of the base 20. The second wall 230 of the second part 23 of the base 20 comprises a male cylinder 402 projecting from the first contact face 231 oriented towards the first part 21 of the base 20. The male cylinder 402 and the cylindrical housing 404 have dimensions and a corresponding positioning so that the male cylinder 402 of the second part 23 of the base 20 is received in the cylindrical housing 404 of the first part 21 of base 20.

[0070] It is easily understood that the male cylinder could be carried by the first base part and that the cylindrical housing could be provided in the second base part without departing from the principle of the invention.

[0071] In a second variant of the main embodiment, and as illustrated in [Fig. 6], the device 2 comprises a solution in the event of failure of the first fixing screw 221. In this second variant, the fixing means 22 of the device 2 comprise a second nut 224, called a locknut, and a second fixing screw 225. The second nut 224 is arranged within the reactor mast 106 and bears against the free end of the first threaded rod 223 of the first fixing screw 221, that is to say the end opposite the first fixing head 222 of the first fixing screw 221. More precisely, the second nut 224 is housed in the mast 106 and is of the through-nut type. The second fixing screw 225 comprises a second fixing head 226 bearing against the first fixing head 221 from which a second threaded rod 227 extends perpendicularly, along the longitudinal axis 5.The second threaded rod 227 is threaded into an eighth bore 228 passing through the first fixing screw 221 and extending along the longitudinal axis 5. The length of the second threaded rod 227 is selected so that the second threaded rod 227 protrudes from the free end of the first threaded rod 223 and the second threaded rod 227 can be screwed into the second nut 224.

[0072] In this way, in the event of failure of the first fixing screw 221 (a breakage of the threaded rod, for example), the second fixing screw 225 will take over so as to ensure that the coupling of the propulsion system 102 to the reactor mast 106 is maintained. In other words, the second fixing screw 225 is “on standby”, in the sense that it is not directly engaged with the elements of the device 2, unlike the first fixing screw 221. The second fixing screw 225 is only engaged in the event of failure of the first fixing screw 221.

[0073] In a third variant illustrated in [Fig. 7], the device 2 comprises both the centering means 40 described in relation to [Fig. 5] and the second fixing screw 225 described in relation to [Fig. 6]. Since the implementation of the centering means 40 and the second fixing screw is identical, it is not described again. Such a device 2 therefore provides a solution in the event of failure of the base 20 and / or the first fixing screw 221.

Claims

1. Claims Device (2) for coupling a propulsion system (102) to a reactor mast (106) of an aircraft (10), said device (2) comprising: - a base (20) having a substantially inverted T shape, said base comprising a base (200) intended to be fixed to said propulsion system (102) and a first wall (201) extending substantially perpendicular to said base (200), said first wall (201) comprising a first bore (202) extending along a longitudinal axis (5); - a substantially tubular sleeve (50) comprising a first portion (502) received at least in part in said first bore (202) of said base (20) and a second portion (504) of which a first end extends in the extension of said first portion (502) in the direction of said reactor mast (106), a second end of said second portion (504) being intended to cooperate with said reactor mast (106), said sleeve (50) comprising a central bore (506) coaxial with said longitudinal axis (5); - fixing means (22) comprising a first nut (220) intended to be secured to said reactor mast (106) and a first fixing screw (221), said first fixing screw (221) comprising a first fixing head (222) from which a first threaded rod (223) extends perpendicularly, said first threaded rod (223) being threaded into said central bore (506) of said sleeve (50); - a second front flange (282a) and a second rear flange (282b), said second flanges (282a, 282b) being arranged respectively on either side of said first wall (201) of said base (20), said second flanges (262a, 262b) each comprising a fourth bore (284a, 284b) coaxial with said longitudinal axis (5); - a spacer (30) intended to be arranged between said second rear flange (282b) and said reactor mast (106), said spacer (30) comprising a fifth bore (32) coaxial with said longitudinal axis (5) so that said spacer (30) is threaded onto said second portion (504) of said sleeve (50); wherein said first portion (502) of said sleeve (50) is threaded into said fourth bores (284a, 284b) of said second flanges (262a, 262b); wherein said first fixing head (222) bears against said second front flange (282a), and wherein said first threaded rod (223) is threaded through said central bore (506) of said sleeve (50), said first threaded rod (223) being screwed to said first nut (220) secured to said engine mast (106); characterized in that said base (20) comprises a first (21) and a second (23) base (20) part, each of said first (21) and second (23) parts being in the form of an L, wherein said first part (21) comprises a first base wall (210) from which extends perpendicularly a second wall (212) comprising a sixth bore (214),and wherein said second portion (23) comprises a second base wall (230) from which extends perpendicularly a third wall (232) comprising a seventh bore (234), said first (21) and second (23) base portions (20) being placed against each other so that said second wall (212) and said third wall (232) together form said first wall (201) of said base (20), that said first base wall (210) and second base wall (230) together form said base (200) of said base (20), and that said sixth (214) and seventh (234) bores together form said first bore (202).,

2. Device (2) according to claim 1, characterized in that it comprises centering means (40) along said longitudinal axis (5) of said first (21) and second (23) base parts (20) relative to each other.

3. Device (2) according to claim 2, characterized in that said centering means (40) comprise at least one male cylinder (402) coaxial with the longitudinal axis (5), projecting from a first contact face (211, 231) of said second wall (212), or respectively of said third wall (232), and at least one cylindrical housing (404) coaxial with the longitudinal axis (5) for receiving said at least one male cylinder (402), said at least one cy- lindrique (404) being arranged at a second contact face (211, 231) of said third wall (232), or respectively of said second wall (212), said first and second contact faces (211, 231) being arranged opposite each other when said first (21) and second (23) parts of the base (20) are assembled.

4. Device (2) according to any one of claims 1 to 3, characterized in that said fixing means (22) comprise a second nut (224) arranged to bear against a free end of said first threaded rod (223) opposite said first fixing head (222), the second fixing means (22) also comprising a second fixing screw (225) comprising a second fixing head (226) from which a second threaded rod (227) extends perpendicularly, where said second fixing head (226) bears against said first fixing head (222), and where said second threaded rod (227) is threaded into an eighth bore (228) extending coaxially with said longitudinal axis (5), passing through said first fixing screw (221), and where said second threaded rod (227) is screwed into said second nut (224).

5. Device (2) according to any one of claims 1 to 4, characterized in that said device (2) also comprises: - a pair of first flanges (242a, 242b), said first flanges (242a, 242b) being fixed respectively on either side of said first wall (201) of said base (20), said first flanges (242a, 242b) each comprising a second bore (244a, 244b) coaxial with said longitudinal axis (5); and - a pair of bearings (262a, 262b), said bearings (262a, 262b) being arranged respectively against one of said first flanges (242a, 242b), said bearings (262a, 262b) each comprising a third bore (264a, 264b) coaxial with said longitudinal axis (5); in that said bearings (262a, 262b) are each sandwiched between a second flange (264a, 264b) and a first flange (242a, 242b); and in that said first portion (502) of said sleeve (50) is threaded into said second bores (244a, 244b) of said first flanges (242a, 242b) and in said third bores (264a, 264b) of said bearings (262a, 262b).

6. An aircraft (10) comprising a propulsion system (102), a powerplant (106) and at least one device (2) according to any one of claims 1 to 5, said propulsion system (102) being coupled to the powerplant (106) by said at least one device (2), wherein said base (20) is fixed to said propulsion system (102) and wherein said first nut (220) is fixed to said powerplant (106).

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