Shock absorption device for a handling system of an aircraft turbomachine module, preferably to protect operators from shocks against the handling system.
The shock-absorbing device with a clip-type fastening system addresses the limitations of existing solutions by ensuring reliable and long-lasting protection against FOD risks, enhancing operator safety during turbomachine module handling.
Patent Information
- Authority / Receiving Office
- FR · FR
- Patent Type
- Patents
- Current Assignee / Owner
- SAFRAN AIRCRAFT ENGINES SAS
- Filing Date
- 2024-05-27
- Publication Date
- 2026-04-10
AI Technical Summary
Existing shock-absorbing devices for aircraft turbomachine module handling systems have limited lifespan and pose Foreign Object Damage (FOD) risks due to adhesive bonding and foam disintegration, necessitating improved safety and longevity solutions.
A shock-absorbing device with a clip-type fastening system using elastic deformation for mounting on handling systems, featuring a shock-absorbing part and locking mechanisms to ensure reliable attachment and minimize FOD risks.
The device provides a simple, reliable, and long-lasting solution with reduced FOD risks, allowing easy installation even in complex geometries and ensuring operator safety by minimizing the risk of accidental disassembly.
Smart Images
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Abstract
Description
Title of the invention: Shock absorption device for a handling system of an aircraft turbomachine module, preferably to protect operators from shocks against the handling system. Technical field
[0001] The invention relates to the field of handling aircraft turbomachine modules, such as a low-pressure turbine module intended to be mounted on the turbomachine during its assembly.
[0002] The invention relates more preferentially to the field of protecting operators carrying out such handling operations against possible shocks to handling systems, and in particular shocks to the head. Prior art
[0003] Certain aircraft turbomachine module handling systems must be equipped with guards, preferably to ensure operator safety. This is particularly true for certain lifting gantries for low-pressure turbine modules, which present areas that pose a risk to operators carrying out handling operations. Due to the shape of these handling systems and the height to which these modules must be moved, head injuries are a particular concern.
[0004] Various technical solutions have been considered to address this problem. In particular, it has been recommended to glue protective foam elements onto the handling system to form a shock-absorbing device, preferably designed to ensure operator safety. However, this solution is not entirely satisfactory, firstly because the adhesive bonding has a limited lifespan. Furthermore, the disintegration of the foam poses a risk of foreign body ingestion into the turbomachine module, which could damage the turbomachine's operation. These risks are also known as FOD (Foreign Object Damage) risks.
[0005] There therefore remains a need to optimize prior art solutions, in particular to limit FOD risks, and to increase the lifespan of shock-absorbing devices. Description of the invention
[0006] To meet this need, the invention first relates to a shock-absorbing device intended to be mounted on a handling system for an aircraft turbomachine module, preferably to protect operators from shocks against the handling system, the shock-absorbing device comprising:
[0007] - a shock-absorbing part;
[0008] - at least one mounting system for the damping device on the system handling system, each mounting system defining, in a locked configuration of this mounting system, an opening intended to be traversed by a part of the handling system, the opening being at least partly defined by a first and a second retaining device, each integral with the damping part and comprising a free end, each mounting system also comprising a locking device for the two free ends of the two retaining devices in a locked position opposite each other, the locking device comprising a first locking element as well as a second locking element,
[0009] each mounting system being configured to be brought from an unlocked configuration to a temporary positioning configuration on the handling system, by elastic deformation of at least one of the two retaining members, so as to define, between the two free ends separated from each other, an insertion passage for the part of the handling system,
[0010] and the locking member being configured to be brought into a locking position, by introducing the first and second locking elements respectively into complementary first and second locking elements provided on the first and second retaining members, this introduction being permitted by elastic deformation of these retaining members.
[0011] Thanks to the invention, mounting the shock-absorbing device on the handling system is simple, reliable, involves a limited number of parts, and offers a long service life. This mounting relies largely on the flexibility of the component parts of the shock-absorbing device, and therefore on their elastic deformation capacity. This capacity is used both to temporarily separate the retaining elements from each other, allowing insertion onto the handling system, and then to lock these retaining elements using the locking mechanism provided for this purpose.
[0012] On this last point, the locking member is indeed mounted on the retaining members in the manner of a "clip" type fastening system, but thanks to the elastic deformation of these retaining members during the insertion of the locking elements. In addition to the speed of this type of assembly, the small number of parts involved significantly limits the risk of FOD, particularly compared to solutions using screws and nuts, or similar fasteners. These Moreover, the risks are further reduced by the fact that the locking mechanism remains extremely reliable, considerably reducing the possibility of accidental disassembly and loss of the locking mechanism.
[0013] Finally, it is observed that the design of the damping device according to the invention allows for simplified implementation, even in areas with complex geometries on handling systems. It also allows for easy interchangeability of these damping devices.
[0014] The invention preferably provides for at least one of the following optional technical features, taken individually or in combination.
[0015] Preferably, the shock-absorbing part includes a bottom, as well as a side wall extending from the bottom, so as to define a recess for housing a part of the handling system.
[0016] Preferably, each of the first and second locking elements comprises a pin provided with a shoulder, and each of the first and second complementary locking elements comprises a pin passage orifice opening onto a stop surface, preferably a counterbore, this stop surface being in contact with the shoulder of one of the pins in the locking position of the locking member.
[0017] Preferably, the locking member comprises a body carrying the first and second locking elements, the body being preferably intended to be housed in a first impression provided on the first retaining member and in a second impression provided on the second retaining member.
[0018] Preferably, each of the retaining members has a general shape of an arc of a circle, although other shapes could of course be envisaged, without going out of the scope of the invention.
[0019] Preferably, at least one of the elements among the shock-absorbing portion and the first and second retaining members of each mounting system, and preferably each of them, is made to have a Shore hardness between 40 and 60A, and preferably around 50A, preferably made of a polymer material, and more preferably of polyurethane. This hardness characteristic provides satisfactory shock-absorbing properties, while also offering the elastic deformation capacity required for mounting the shock-absorbing device on the handling system.
[0020] In addition, the locking member is preferably made of a metallic material or metallic alloy, and more preferably made of steel.
[0021] Preferably, the shock-absorbing part, and the first and second elements of each mounting system, are made together as a single unit, preferably by molding. Other manufacturing techniques, however, remain conceivable, such as 3D printing.
[0022] The invention also relates to an assembly comprising a handling system for an aircraft turbomachine module, as well as such a shock-absorbing device mounted on the handling system, preferably to protect operators from shocks against the handling system.
[0023] Preferably, the handling system comprises a first beam, one end of which is housed in the shock-absorbing part of the damping device, and a second beam projecting on either side of the first beam, so as to form two projecting beam portions passing through respectively a first and a second mounting system of the damping device.
[0024] Finally, the invention relates to a method for mounting such a shock-absorbing device on a handling system for an aircraft turbomachine module, the method comprising the following steps:
[0025] - bringing each mounting system from its unlocked configuration, to its provisional configuration for installation on the handling system, by elastic deformation of at least one of the two retaining devices;
[0026] - insertion of the handling system part into the defined insertion passage between the two free ends separated from each other of the two retaining devices of each mounting system;
[0027] - for each mounting system, bringing the locking member into its locking position, by introducing the first and second locking elements respectively into the first and second complementary locking elements provided on the first and second retaining devices, this introduction being authorized by elastic deformation of these retaining devices.
[0028] Other advantages and features of the invention will appear in the detailed, non-limiting description below. Brief description of the drawings
[0029] The detailed description that follows refers to the attached drawings on which:
[0030] [Fig.1] is a schematic half view in longitudinal section of a conventional aircraft turbomachine;
[0031] [Fig.2] is a perspective view of part of a handling system carrying the low-pressure turbine module of the turbomachine shown in the previous figure;
[0032] [Fig.3] is a side view of the handling system shown in the figure previous;
[0033] [Fig.4] is a perspective view of an assembly comprising the handling system shown in Figures 2 and 3, equipped with a shock-absorbing device according to a preferred embodiment of the invention;
[0034] [Fig.5] is a perspective view similar to the previous one, from a different angle of view;
[0035] [Fig.6] is a cross-sectional view of the assembly shown in the previous figure;
[0036] [Fig.7] is a perspective view of the shock-absorbing device shown on figures 4 to 6;
[0037] [Fig.8] is an enlarged perspective view of part of the shock-absorbing device shown in the previous figure;
[0038] [Fig.9] is a perspective view of a locking member belonging to the shock-absorbing device;
[0039] [Fig. 10] is a perspective view of another locking member belonging to the shock-absorbing device;
[0040] [Fig. 11] is a cross-sectional view of the locking member shown in [Fig.9], in its locked position within the shock-absorbing device;
[0041] [Fig. 12] is a cross-sectional view of the locking member shown in [Fig. 10], in its locked position within the shock-absorbing device;
[0042] [Fig. 13]
[0043] [Fig. 14]
[0044] [Fig. 15]
[0045] [Fig. 16]
[0046] [Fig. 17] are schematic views illustrating different stages of a process according to the invention, for mounting the shock-absorbing device on the handling system. Detailed description of implementation methods
[0047] Figure 1 comprises a reference frame L, R, and C defining, respectively, mutually orthogonal longitudinal, radial, and circumferential directions, these directions corresponding to those of a conventionally designed aircraft turbomachine 1. This is a twin-spool, turbofan engine, but the invention may relate to other types of aircraft turbomachines, such as turboprops.
[0048] Hereafter, the terms "upstream" and "downstream" are defined with respect to a principal direction DI of gas flow through the turbojet 1 when it is operating in direct thrust mode. The direction DI is parallel to the longitudinal direction L, and also parallel to a longitudinal axis Al of the turbojet, around which its various components extend. In this case, from upstream to downstream of the turbojet 1, these components are a fan 4 and a low-pressure compressor. 5, a high-pressure compressor 6, a combustion chamber 7, a high-pressure turbine 8 and a low-pressure turbine 9.
[0049] During the operation of the turbojet 1, an airflow 10 enters the turbojet 1 through an air inlet 3, passes through the fan 4, and then splits into a central primary flow 10A and a secondary flow 10B. The primary flow 10A flows in a main gas circulation channel 11A passing through the compressors 5 and 6, the combustion chamber 7, and the turbines 8 and 9. The secondary flow 10B, on the other hand, flows in a secondary channel 11B surrounding the main channel 11A, also called the primary channel, or aerodynamic flow channel.
[0050] During the assembly of the turbojet engine, its modules are assembled one after the other using handling systems. The present invention preferably relates to the handling of the module formed by the low-pressure turbine 9, also called the low-pressure turbine module. However, the invention could also relate to the handling of other turbojet engine modules, such as the high-pressure turbine module.
[0051] With reference now to Figures 2 and 3, a portion of a handling system 20, intended for handling the low-pressure turbine module 9, is shown. In these figures, the module 9 is shown mounted on the handling system 20, using a support 22 arranged at the interface between this module 9 and the handling system. The support 22, generally annular in shape, comprises several handling trunnions 24, one of which is visible in [Fig. 2].
[0052] The handling system 20 here comprises a lifting jib, including in particular a first beam 26 oriented vertically, or substantially vertically. The first beam 26 may, for example, have a square or rectangular cross-section. At its lower end, the lifting jib includes a second beam 28 oriented horizontally, or substantially horizontally. The second beam 28 may, for example, have a circular cross-section, and it passes through the first beam 26. Thus, the second beam 28 projects on either side of the first beam 26, so as to form two projecting beam sections 28a, 28b, both intended for mounting a shock-absorbing device, as will be detailed later.In this regard, it is noted that it is the lower end 26a of the first beam 26, located under the second beam 28 and between its two projecting portions 28a, 28b, which is planned to be equipped with the shock-absorbing device, preferably in order to preserve the safety of the operators.
[0053] The projecting beam portion 28b, located on the side of module 9, serves as a fitting for a retaining tube 30 belonging to the support 22. This tube 30 has at its end a collar 32, retained in the direction the fitting is by means of a retaining system 34 fixed on the first beam 26. Spacers 35 are arranged between the collar 32 and the first beam 26, bearing against these two elements 26, 32.
[0054] Finally, the upper end of the first beam 26 is fixed to a third beam 36 of the lifting jib, also horizontally or substantially horizontally oriented. The third beam 36 cooperates with a support mechanism 38, also designed to slide this beam 36 along its length.
[0055] With reference now to Figures 4 to 6, an assembly 40 is shown comprising the handling system 20, as well as a shock-absorbing device 42 mounted on this system 20. The area of this system to be primarily protected concerns the lower end 26a of the first beam 26, located under the second beam 28 and between its two projecting portions 28a, 28b. Indeed, there is a particular need to protect operators against potential impacts on this lower and projecting area of the lifting jib, and in particular impacts to the head.
[0056] Overall, the damping device 42 comprises a shock-absorbing part 44, as well as two mounting systems 46, 46' for the device 42 on the handling system 20. The device 42 adopts a general basket shape, with two handles for mounting on the handling system 20. A similar design with a single handle is also conceivable, without departing from the scope of the invention.
[0057] The damping portion 44 is that which houses and surrounds the end 26a of the first beam 26. To this end, the damping portion 44 comprises a base 45, as well as a side wall 48 extending from the base, so as to define a recess 50 for housing the end 26a. The shape of the side wall 48 is complementary to that of the end 26a of the first beam 26. It therefore has a generally square or rectangular cross-section. The damping portion 44 thus forms the core of the basket, defining the recess 50, which is completely closed laterally and at one of its ends, while remaining open at its opposite end to allow the insertion of the beam 26 to be protected.
[0058] The two mounting systems 46, 46' of the damping device 42 are partly integrated into the damping part 44, as will be described later.
[0059] Each mounting system 46, 46' defines, in a locked configuration as shown in Figures 4 to 6, an opening 52, 52' through which a part of the lifting jib passes, and more specifically through the two projecting beam sections 28a, 28b, respectively. These mounting systems 46, 46' thus form the two handles of the aforementioned basket, facing each other and originating respectively from two parallel sections of the side wall 48 of the damping part 44.
[0060] The two mounting systems 46, 46' are of identical or similar design. Therefore, in the figures, the same numerical references are used for identical or similar components of the first mounting system 46 and the second mounting system 46', the extension "'" being added to each numerical reference for the components of this second system.
[0061] Subsequently, only the first mounting system 46 will be described in detail, but it should be understood that the design of the second mounting system 46' is identical or similar to that of the first mounting system.
[0062] With reference now to Figures 7 and 8, the damping device 42 is shown with its mounting systems 46, 46' in an unlocked configuration, in which a locking member, which will be described below, is not yet installed. The first mounting system 46 comprises a first retaining member 54a and a second retaining member 54b, which together define the upper area of the opening 52. Each of these two retaining members 54a, 54b has a general arc shape, for example, on the order of 60 to 120°, and preferably on the order of 90°. Consequently, these two members 54a, 54b together define the upper area of the opening 52, over approximately 180°, to form a basket handle. The lower area of this opening 52 is delimited over approximately 180° by a notch in the side wall 48 of the damping part 44 of the device 42.
[0063] Each of the two retaining members 54a, 54b is integral with the side wall 48 of the damping part 44, preferably being made in one piece with this part 44. In the unlocked configuration of the first mounting system 46, the two retaining members 54a, 54b respectively have two free ends 56a, 56b, facing each other, and possibly in contact. Still in this same configuration, the two retaining members 54a, 54b are preferably in the same plane, corresponding preferably to a plane of one of the portions of the side wall 48 of the damping part 44. It is noted that the two retaining members 54a', 54b' of the second mounting system 46' may have notches 59, in order to allow the spacers of the support 22 of the module 9 to pass through, when the device 42 is mounted on the lifting jib.
[0064] With the exception of the locking elements, which will be described below, the entire damping device 42 shown in [Fig. 7] can be made from a single piece, preferably by molding. The material recommended for making this single piece has shock-absorbing characteristics, as well as elastic properties to allow for the temporary elastic deformations of certain components required for mounting the damping device 42 on the lifting jib.
[0065] Preferably, it is a polymer material, and even more preferably a polyurethane, having a Shore hardness of the order of 50A.
[0066] With reference to figures 9 and 10, a locking member 60 forming an integral part of the first mounting system 46, and a locking member 60' forming an integral part of the second mounting system 46', are respectively shown.
[0067] The locking member 60 is designed to cooperate with the retaining members 54a, 54b, in order to hold the two free ends 56a, 56b in a locked position, facing each other. To this end, the locking member comprises a body 62 in the form of a plate, preferably domed or arched, carrying at its opposite ends first and second locking elements 64a, 64b, respectively.
[0068] Each of the first and second locking elements 64a, 64b takes the form of a pin, preferably extending orthogonally or substantially orthogonally to the body 62. Each pin 64a, 64b is provided with an enlarged head, preferably conical or frustoconical in shape, and defining a shoulder 66 at the level of the transition with a pin shank 68, of smaller diameter.
[0069] The locking members 60, 60' are preferably made of steel, or any other material capable of elastically deforming the retaining members 54a, 54b, 54a', 54b', during the assembly of these members 60, 60'.
[0070] To achieve such an assembly of the locking member 60, the first and second retaining members 54a, 54b are respectively equipped with first and second complementary locking elements 70a, 70b (visible in Figures 11 and 12). Each of these latter has an orifice 72 for the passage of a pin through its associated free end 56a, 56b, this orifice 72 opening onto a counterbore 74, itself opening onto an external surface of the associated retaining member 54a, 54b.
[0071] In the locking position of the locking members 60, 60' shown in figures 11 and 12, the shoulder 66, 66' of each pin is in contact / against its associated counterbore 74, 74', preventing the dismantling of these members 60, 60'.
[0072] Furthermore, with reference to figures 7, 8, 11 and 12, the body 62, 62' of each locking member 60, 60' is housed partly in a first recess 76a, 76a' provided on the first retaining member 54a, 54a', and partly in a second recess 76b, 76b' provided on the second retaining member 54b, 54b'.
[0073] The indentations are preferably complementary in shape to that of the body of their associated locking members, so as to prevent the latter from rotating when they occupy their locked position within the mounting systems 46, 46'. Furthermore, in order to further reduce the risk of circumferential opening of the mounting systems 46, 46', due to separation of the ends free 56a, 56b, 56a', 56b', the ends of bodies 62, 62', as well as their corresponding portions of imprint, are preferentially enlarged with respect to a central part of these bodies.
[0074] With reference now to figures 13 to 17, a preferred embodiment of a method for mounting the shock-absorbing device 42 on the handling system 20 of the low-pressure turbine module 9 will now be described.
[0075] First, with reference to [Fig. 13], the first step consists of bringing the shock-absorbing device 42 towards the end 26a of the first beam 26 to be protected. During this step, or before its implementation, each mounting system 46, 46' is brought from its unlocked configuration in [Fig. 7] to a temporary mounting configuration on the lifting jib. This step is shown schematically in figures 14 and 15, and it consists of elastically deforming the two retaining members 54a, 54a', 54b, 54b' of the two mounting systems 46, 46', so as to define between the two free ends 56a, 56a', 56b, 56b' separated from each other of each system 46, 46', an insertion passage 78, 78' for the protruding beam portions 28a, 28b.
[0076] The provisional configuration is maintained until the end 26a of the first beam of the lifting jib is completely inserted into the damping part 44 of the device 42. During this movement, the protruding beam portions 28a, 28b are inserted in parallel into the respective insertion passages 78, 78', defined between the free ends held apart from each other.
[0077] Next, the constraint on the two retaining members 54a, 54a', 54b, 54b' of each mounting system 46, 46' is released, so that these systems 46, 46' return to their unlocked configuration, but with the protruding beam portions 28a, 28b passing through the openings 52, 52', again closed circumferentially.
[0078] The final assembly step, shown schematically in [Fig. 16], consists, for each mounting system 46, 46', of bringing the locking member 60, 60' into its locking position. To do this, the first and second pins 64a, 64a', 64b, 64b' are inserted respectively into the first and second complementary locking elements 70a, 70a', 70b, 70b'. This insertion is made possible by the elastic deformation of the openings 72, 72' as the enlarged pin heads pass through, as shown schematically in [Fig. 17]. At the end of this insertion, when the pin heads pass through the openings 72, 72', the shoulders 66, 66' of the pins come into contact with the counterbores 74, 74'. The stress applied to the orifices 72, 72' is at least partially released, so that they return to their original shape, or a shape close to it when the diameter of the stem 68, 68' of the pins is greater than that of these orifices.The locking mechanisms 60, 60' then adopt their . locking position, placing the free ends of the retaining members in their locked position opposite each other in pairs, and more generally placing the mounting systems 46, 46' to which they belong, in their locked configuration.
[0079] Such a locking mechanism is similar to a clipping mechanism, and it proves to be particularly simple to implement and reliable.
[0080] After mounting the shock-absorbing device 42 on the handling system 20, the low-pressure turbine module 9 can be mounted on this handling system, via its support 22.
[0081] Various modifications can be made by a person skilled in the art to the invention just described, solely by way of non-limiting examples, and whose scope is defined by the attached claims.
Claims
1.
2. Demands Shock damping device (42) intended to be mounted on a handling system (20) of an aircraft turbomachine module (9), the damping device being characterized in that it comprises: - a shock damping part (44); - at least one mounting system (46, 46') of the damping device on the handling system (20), each mounting system defining, in a locked configuration of this mounting system, an opening (52, 52') intended to be traversed by a part (28a, 28b) of the handling system (20), the opening being at least partially delimited by a first and a second retaining member (54a, 54b, 54a', 54b'), each integral with the damping part (44) and comprising a free end (56a, 56b, 56a', 56b'), each mounting system (46, 46') also comprising a locking member (60, 60') of the two free ends (56a, 56b, 56a', 56b') of the two retaining members (54a, 54b, 54a', 54b'), in a locked position facing each other, the locking member (60, 60') comprising a first locking element (64a, 64a') and a second locking element (64b, 64b'), Each mounting system (46, 46') is configured to be brought from an unlocked configuration to a temporary positioning configuration on the handling system (20) by elastic deformation of at least one of the two retaining members (54a, 54b, 54a', 54b'), so as to define, between the two free ends (56a, 56b, 56a', 56b') separated from each other, an insertion passage (78, 78') for the part of the handling system, and the locking member (60, 60') is configured to be brought into a locked position by inserting the first and second locking elements (64a, 64a', 64b, 64b') respectively into complementary first and second locking elements (70a, 70a', 70b, 70b') provided on the first and second retaining members. (54a, 54b, 54a', 54b'), this introduction being authorized by elastic deformation of these retaining devices.Damping device according to claim 1, characterized in that the shock-damping part (44) comprises a base (45). as well as a side wall (48) extending from the bottom (45), so as to define a hollow (50) for housing a part (26a) of the handling system (20).
3. Damping device according to claim 1 or 2, characterized in that each of the first and second locking elements (64a, 64a', 64b, 64b') comprises a pin provided with a shoulder (66, 66'), and in that each of the first and second complementary locking elements (70a, 70a', 70b, 70b') comprises a pin passage orifice (72, 72') opening onto a stop surface (74, 74'), preferably a counterbore, this stop surface (74, 74') bearing against the shoulder (66, 66') of one of the pins in the locking position of the locking member (60, 60').
4. Damping device according to any one of the preceding claims, characterized in that the locking member (60, 60') comprises a body (62, 62') carrying the first and second locking elements (64a, 64a', 64b, 64b'), the body being preferably intended to be housed in a first recess (76a, 76a') provided on the first retaining member (54a, 54a'), and in a second recess (76b, 76b') provided on the second retaining member (54b, 54b').
5. Damping device according to any one of the preceding claims, characterized in that at least one of the elements among the shock-damping part (44) and the first and second retaining members (54a, 54a', 54b, 54b') of each mounting system (46, 46'), is made so as to have a Shore hardness of between 40 and 60A, and preferably of the order of 50A, preferably made of polymer material, and more preferably of polyurethane.
6. Damping device according to any one of the preceding claims, characterized in that the locking member (60, 60') is made of a metallic material or metallic alloy, and more preferably made of steel.
7. Damping device according to any one of the preceding claims, characterized in that the shock-damping part (44), and the first and second members of each mounting system (54a, 54a', 54b, 54b'), are made together as a single unit, preferably by molding.
8. Assembly (40) comprising a handling system (20) for an aircraft turbomachine module (9), and a shock-absorbing device (42) mounted on the handling system (20), preferably to protect operators from shocks against the handling system, the shock-absorbing device (42) being in accordance with any one of the preceding claims.
9. Assembly according to claim 8, characterized in that the handling system (20) comprises a first beam (26), one end of which (26a) is housed in the shock-absorbing part (44) of the damping device (42), and a second beam (28) projecting on either side of the first beam (26), so as to form two projecting beam portions (28a, 28b) passing respectively through a first and a second mounting system (46, 46') of the damping device (42).
10. Method of mounting a shock-absorbing device (42) according to any one of claims 1 to 7, on a handling system (20) of an aircraft turbomachine module (9), the method comprising the following steps: - bringing each mounting system (46, 46') from its unlocked configuration, to its provisional configuration for placement on the handling system, by elastic deformation of at least one of the two retaining members (54a, 54a', 54b, 54b'); - insertion of the part (28a, 28b) of the handling system (20), into the insertion passage (78, 78') defined between the two free ends (56a, 56a', 56b, 56b') separated from each other of the two retaining members (54a, 54a', 54b, 54b') of each mounting system (46, 46');- for each mounting system, bringing the locking member (60, 60') into its locking position, by inserting the first and second locking elements (64a, 64a', 64b, 64b') respectively into the first and second complementary locking elements (70a, 70a', 70b, 70b') provided on the first and second retaining members (54a, 54a', 54b, 54b'), this introduction being permitted by elastic deformation of these retaining members.;