Method and device for machining an aeronautical workpiece

Abstract

The invention relates to a method (300) and a machining tool for machining a workpiece (1) having a surface (S1, S2) intended to be machined and connected to an edge (B1) of the workpiece (1), the surface (S1, S2) and the edge (B1) extending along a length L1 of the workpiece (1), the method comprising the steps of: a) applying a machining tool (100) to the workpiece (1), the tool (100) comprising at least one reference guide (104, 106a, 106b, 106c) which is brought to bear against the surface (S1, S2) and / or the edge (B1) of the workpiece (1); b) moving the tool (100) along the length L1 so that the rotary member (102) machines the part of the surface according to a predetermined shape profile (PF1, PF2, PF3, PF4), the tool (100) being maintained in bearing contact with the workpiece (1) during this movement.

Description

Description TITLE: METHOD AND DEVICE FOR MACHINING AN AERONAUTICAL PART Technical field of the invention

[0001] The present invention relates to the field of manufacturing aircraft parts or aeronautical parts, in particular that of machining one or more aeronautical parts. More specifically, the invention relates to a method of machining at least one part and a tool for implementing this method. Technological background

[0002] Generally speaking, aircraft design involves assembling several aircraft parts of different shapes that are joined end to end. The parts may, for example, have an axis of revolution or an elongated shape. This assembly phase can be tricky in that the edges, for example annular or linear, of two adjacent parts must be perfectly aligned.

[0003] During the assembly phase, it may happen that the edge of one of the adjacent parts is deformed or has defects so that assembly or alignment is not possible. It may then be necessary to machine this edge to make it conform to the edge of the other adjacent part.

[0004] Furthermore, after manufacturing or using an assembled aeronautical part, non-conformity defects may appear at the junction of two adjacent parts. In this case, too, an intervention to bring them into conformity must be possible.

[0005] Documents W0-A1-2022117196, IT-A1-202000016420 and DE-U1-202017000082 are known in the prior art.

[0006] Document EP-A2-0 763 395, for example, describes a device for machining aeronautical parts comprising a guide assembly and a cutting or machining tool, the guide assembly comprising a rigid plate and a T-shaped rail defining a path and mounted on one side of the plate to act as a support and guide for the machining tool. The machining tool comprises a base assembly and an air supply assembly which is supported by the base assembly.

[0007] In operation, the machining tool is pneumatically lifted by the air supply assembly a slight distance from the path so that a mechanic can translate the machining tool along the path to machine an edge of an aircraft part to a predetermined profile.

[0008] However, this solution has drawbacks. For example, the assembly is complex and due to the large size of the machining system (formed by the machining tool and the guiding device), it is not suitable for small parts or parts already assembled. This lack of adaptability can therefore lead to limited use and a decrease in accuracy.

[0009] Document WO-A1-2015 / 063750, for its part, describes a method and a guiding device for reproducing a contour of a second aeronautical part on a first part. According to the method, a guiding device is first engaged by gripping on the first part. A guiding unit of the guiding device is then abutted against an edge of the second part, the edge defining the contour to be reproduced. The guiding device is then moved, with a machining tool thereon, along the edge of the first aeronautical part while the guiding unit traces the edge of the second part to impart movement to the guiding device in an axial direction of the first part.

[0010] Like the previous document, document W0-A1 -2015 / 063750 has drawbacks. For example, the gripping engagement phase involves sandwiching a wall of the first part between rollers for rolling engagement, and abutting a pulley roller against an edge of the first part for rolling engagement. For fragile materials, this phase can therefore be tricky because it can lead to damage to the part. Furthermore, the number of shape profiles that can be achieved with such a process seems limited.

[0011] It may therefore be desirable to provide a machining process and tool which make it possible to overcome at least some of the aforementioned problems and constraints. Summary of the invention

[0012] There is therefore proposed a method of machining a first part, this part comprising a surface connected to an edge of the part, the surface and the edge extending along a length of the first part, a part of this surface which adjoins said edge being intended to be machined, the method comprising the steps of: a) applying a machining tool to the part, this tool comprising at least one reference guide which is placed in abutment on the surface and / or the edge of the part, this tool further comprising a rotary machining member; b) moving the tool along the length so that the rotary member machines the part of the surface according to a predetermined shape profile, the reference guide of the tool being kept in abutment on the part during this movement.

[0013] Thus, thanks to the invention it is possible to quickly and accurately remove defects or imperfections resulting from the manufacture of parts or from the use of these parts without the risk of damaging them or machining the parts beyond the maximum permitted dimension for the parts. The invention also allows for a time saving in the process of manufacturing the parts or their maintenance, these operations being able to be carried out without requiring disassembly of the parts.

[0014] A machining method according to the invention may further comprise one or more of the following optional features, in any technically possible combination: the machining is carried out by grinding or milling; in step a), the tool comprises a first reference guide resting on the edge and a second reference guide resting on the surface; a second part having an axis of revolution is mounted coaxially with the first part and extends in the extension of this first part on the side of said edge, and in which, in step a), the tool comprises a first reference guide resting on the edge and a second reference guide on the surface of the second part; the machining comprises the production of a profile from a set of profiles comprising at least one chamfer or bevel; The first part has an axis of revolution; The first part has an annular surface connected to an annular edge; The surface and the edge extend around the axis of revolution of the first part; The tool is moved around said axis of revolution; The second part has an axis of revolution; The second part is mounted coaxially to the first part The first and second parts are aeronautical parts.

[0015] The present invention also relates to a tool for machining parts.

[0016] The tool for machining parts, in particular aeronautical parts, comprising: a rotating member; a body comprising at least: • a housing configured to receive the rotating member; • a face intended to be positioned opposite the part to be machined, said face comprising: o an opening opening onto the housing and configured so as to allow the rotary member to come into contact with a surface of the part to be machined; and o at least one reference guide configured to bear on the surface and / or the edge of the part so as to guide the machining tool; and a motorization system connected to the body and configured to drive the member in rotation; said rotary member being configured to machine the part of the surface according to a predetermined shape profile.

[0017] The machining tool according to the invention may further comprise one or more of the following optional features, in any technically possible combination: The opening into the housing is configured to allow the rotating member to contact an annular surface of the workpiece; the rotating member is a grinding wheel or a milling cutter; the rotating member comprises: • a hollow head having a revolution profile and comprising an external machining surface intended to come into contact with the surface of the part for the purpose of its machining; and • a rod comprising an end secured to the head and a free end, opposite the end secured to the head and configured to couple to the motorization system. the hollow head is cylindrical; the hollow head comprises an external cylindrical surface; the machining tool comprises at least a first reference guide configured to bear on the edge of the part to be machined and a second reference guide configured to bear on the surface of the part to be machined, this first reference guide being located on a front face of the body intended to be positioned opposite the surface of the part to be machined and above the head of the rotary member, said first reference guide forming at least one flat or curved strip;the machining tool further comprises another second reference guide configured to bear on the surface of the workpiece, this second reference guide being located below the first reference guide, either arranged on either side of the head of the rotary member, or arranged so that the head of the rotary member is located between said second reference guide and the first reference guide, or both, the second reference guide having the shape of at least one tenon or at least one tab with rounded edges matching the internal surface of the workpiece; the rotary member comprises a third reference guide configured to bear on the surface of the workpiece, this third reference guide being located on the front face of the body, above the first reference guide, the third reference guide having a projecting shape with a rounded edge matching the internal surface of the workpiece;the machining tool comprises at least:; • a square on which rests a lower portion of the tool body; and. • at least one adjustment shim inserted between the square and the lower portion of the body of the tool, this shim having a thickness which is determined according to a desired machining depth of the rotating member. the motorization system comprises at least: • an axis-motor coupler configured to receive the free end of the machining tool rod; • a motor to rotate the coupler; and • a motor activation device. The motorization system is electric, pneumatic or hydraulic. The machining tool includes a system for extracting dust emitted during the machining of the part(s), this extraction system being carried by the body. Brief description of the figures

[0018] The invention will be better understood with the aid of the following description, given solely by way of example and with reference to the appended drawings in which: Figure 1 is a schematic representation of a perspective view of an aeronautical part; Figure 2A is a schematic representation of a perspective view of an assembled aeronautical part; Figure 2B is a schematic representation of an example of non-conformity of the edges of two aeronautical parts; Figure 4 is a schematic representation of the steps of the machining method according to the invention; Figure 5A is a schematic representation of a perspective view of carrying out step a) of the method of machining an aeronautical part according to one embodiment; Figure 5B is a schematic representation of a partial radial sectional view of Figure 5A; Figure 6A is a schematic representation of a perspective view of carrying out step a) of the method for machining an aeronautical part according to another embodiment; Figure 6B is a schematic representation of a partial radial sectional view of Figure 6A; Figure 7A is a schematic representation of a radial sectional view of the rotary member, according to one embodiment; Figure 7B is a schematic representation of a radial sectional view of the machining tool according to the invention; Figure 7C is a schematic representation of a perspective view of the machining tool. Detailed description of the invention

[0019] Although in the examples which will be described below, for illustrative purposes, the parts are aeronautical parts which have an axis of revolution and comprise annular surfaces, those skilled in the art will understand that these examples are in no way limiting. The invention can be applied to parts, aeronautical or not, of different shapes having or not an axis of revolution, an annular or linear edge, a flat or annular or curved, or complex surface.

[0020] By convention, in the description below, the terms "longitudinal" and "axial" describe the orientation of structural elements extending in the direction of a longitudinal axis. This longitudinal axis corresponds substantially to an axis of rotation or revolution. The terms "radial" or "vertical" describe an orientation of structural elements extending in a direction perpendicular to the longitudinal axis. The terms "inner" and "outer", and "internal" and "external" are used in reference to a positioning relative to the longitudinal axis. Thus, a structural element extending along the longitudinal axis has an inner face facing the longitudinal axis and an outer surface, opposite its inner surface.

[0021] Figure 1 shows an example of an aeronautical part 1 to which the machining method of the present invention is applied. The part may be, for example, made of composite material, metal, wood or any other type. Preferably, the part is made of composite material.

[0022] The aeronautical part 1 comprises an internal surface Si and an external surface S'i opposite the internal surface Si. The surfaces Si, S'i are connected to an edge B1 of the part 1, the surfaces Si, S'i and the edge B1 extending along a length L1 of the part. In this non-limiting example, the part 1 has a longitudinal axis of revolution A. The edge B1 and the surfaces Si, S'i are annular and extend around the axis of revolution A.

[0023] Part 1 is for example an annular casing or an annular cover, such as a nacelle casing or cover for an aircraft turbomachine.

[0024] The part of this surface Si, S'i which adjoins the edge B1 of the aeronautical part 1 may be required to be machined, for example and in a non-limiting manner, due to the presence of defects during the manufacture of the part 1 or deformation of the latter after its manufacture and during its use.

[0025] With reference to Figure 2A, another example of an aeronautical part is described. The part may be, for example, made of composite material, metal, wood or any other type. Preferably, the part is made of composite material. The part is an assembly formed by a first aeronautical part 1 and by a second aeronautical part 2. For example, and in a non-limiting manner, the first part 1 may be similar to the example of Figure 1 and the second part may also have an axis of revolution A' (not shown).

[0026] Generally, the second part 2 is mounted on the first part 1. The second part, which extends in the extension of the first part 1 on the side of the edge B1 of the first part 1, also comprises an edge B2. The assembled aeronautical parts can be separated by a clearance 12, for example of the order of 0.4 mm in width, at the junction of the first and second aeronautical parts. The clearance 12 is measured between the edges B1 and B2 respectively of the first and second parts. In the example of FIG. 2A, the second part 2, having an axis of revolution A' (not shown), is mounted coaxially with the first part 1 which also comprises an axis of revolution.

[0027] Part 2 is for example an air inlet in a nacelle for an aircraft turbomachine.

[0028] Just like the first part 1, the second aeronautical part comprises an internal surface S2 and an external surface S'2 opposite the internal surface S2. The surfaces can be planar or annular as in the example in Figure 2A.

[0029] Still with reference to FIG. 2A, defects or deformations may appear at the junction of the first and second aeronautical parts 1, 2, for example during the manufacture of the part 1 or the deformation of the latter after its manufacture and during its use. For example, and in a non-limiting manner, there may be a difference in level or alignment, in the radial direction, between the first part 1 and the second part 2 at the junction.

[0030] Figure 2B illustrates an example of a defect relating to a level or alignment difference between the first part 1 and the second part 2.

[0031] In example i) parts 1 and 2 are aligned, an axis of symmetry XX', parallel to the axis of revolution or longitudinal A, passing through the center of the two parts. Examples ii) and iii), for their part, illustrate an offset or deviation, respectively internal ii) (in the direction of the longitudinal axis A) and external iii), of part 2 relative to part 1. The axis of symmetry XX' only passing through the center of one of the parts here, the second part 1.

[0032] The mismatch can be located at the internal or external surfaces or both. A mismatch between the first and second part, in the above-mentioned example where the second part is an air inlet duct, can cause for example turbulence in the air flow entering the turbomachine. This can affect the performance of the turbomachine. Thus, as mentioned above, it is important that the surfaces, especially internal ones, are aligned to avoid such a disturbance.

[0033] The machining method (300), illustrated in Figure 3, aims in part to correct or eliminate the defects or deformations described above. More generally, the method concerns the machining of the internal or external surface of an aeronautical part or both successively.

[0034] In the following, the illustrative examples will relate to the machining of the internal surface of an aeronautical part without this being limiting. Furthermore, although the examples describe parts having an axis of revolution, the person skilled in the art will understand that these examples are not limiting as mentioned above.

[0035] Generally speaking, the term "surface" can refer, for example, to a flat or annular or curved or complex surface.

[0036] Still with reference to figure 3, the method 300 for machining an aeronautical part 1 comprises at least two steps a) and b).

[0037] In the first step a), a machining tool 100 is arranged on the part to be machined, for example, and in a non-limiting manner, the part 1 illustrated in FIG. 1 or 2.

[0038] This tool (100) may comprise at least one reference guide which is placed in abutment on the internal surface Si or external S'i and / or the edge B1 of the part 1. The tool 100 may further comprise a rotary machining member.

[0039] In the second step b), the tool 100 is moved along the length L1 so that the rotary member machines the part of the surface according to a predetermined shape profile, the reference guide of the tool 100 being kept in contact with the part 1 during this movement.

[0040] Machining can be carried out, for example, by grinding or milling, for example on the entire surface to be machined. Preferably, machining is carried out by grinding. Machining can also be carried out on any type of material (composite, metal, etc.).

[0041] Figure 4 illustrates examples of predetermined shape profiles that can be produced using the method described above. Thus, the predetermined profile can be flat PFi, convex PF2, concave PF3 or complex PF4.

[0042] Thus, the machining may comprise the production of a profile from a set of profiles. The set of shaped profiles may comprise at least, for example, a chamfer or a bevel.

[0043] Figure 5a illustrates an embodiment of step (a) of the machining method applied to an aeronautical part 1 similar, for example, and in a non-limiting manner, to that of the example of Figure 1. The machining tool 100 is positioned on the edge B1 of the part 1, a first reference guide 104 being supported on the edge. In this example, it is a part of the internal surface Si which is machined.

[0044] With reference to figure 5b, illustrating a radial sectional view of the machining of the aeronautical part 1, which may be for example, and in a non-limiting manner, similar to the aeronautical part of figure 5a, the machining tool is also supported on the internal surface Si via a second reference guide 106b (in dotted lines) located axially below the first reference guide 104. The internal surface Si of the aeronautical part is machined according to a predetermined profile PF1 which is flat.

[0045] In this case, the machining process proceeds as follows: the tool is translated in a back and forth movement along the edge B1 and over the entire length of the part of the internal surface Si having an offset relative to a normal part of the internal surface S1 of the part 1. By normal, it is meant that the part of the surface does not have deformations or an elevation. During this movement, the first reference guide 104 and the second reference guide 106b are kept in continuous support respectively on the edge B1 of the part 1 and the internal surface Si of the part 1. The tool may comprise a rotary member 102 which is brought into contact with the internal surface S1 at the level of the zone having an offset, that is to say in the vicinity of the edge B1 in this example, to machine it in order to eliminate the offset.The translational movement associated, simultaneously, with the rotational movement of the member 102 makes it possible to machine the part of the internal surface of the part 1 in a homogeneous manner.

[0046] In another embodiment illustrated in Figure 6a, step a) of the machining method 300 is applied to an assembled aeronautical part. For example, and in a non-limiting manner, the assembled aeronautical part may be similar to the aeronautical part of Figure 2.

[0047] The machining tool 100 is positioned on the edge B1 of the part 1. A first reference guide 104 is inserted into the clearance 12 between the first aeronautical part 1 and the second aeronautical part 2, the first guide 104 bearing on the edge B1. In this example, it is a part of the internal surface Si which is machined.

[0048] With reference to figure 6b, illustrating a radial sectional view of the machining of the aeronautical part 1 of figure 6a, the machining tool is also supported on the internal surface S2 via a third reference guide 106 a located axially above the first reference guide 104.

[0049] In this case, the inner surface Si of the part 1 must be machined so as to be aligned with the inner surface S2 of the second part 2 at the junction. During machining, similarly to the case described in Figures 1, 5A and 5B, the tool is translated in a back and forth movement. The movement is carried out along the clearance 12 and over the entire length of the part of the inner surface Si having an offset relative to the inner surface S2 of the second part 2. During this movement, the first reference guide 104 and the third reference guide 106 a are kept in continuous support respectively on the edge B1 of the part 1 and the internal surface S2 of the part 2. The rotary member 102 is brought into contact with the internal surface Si of the first part 1 at the level of the zone having an offset to machine it in order to eliminate the offset with the internal surface S2 of the second part 2. The translational movement associated with the rotational movement of the member 102 makes it possible to machine in a homogeneous manner the part of the internal surface of the part 1 having an offset.

[0050] The invention also relates to a machining tool for implementing the machining method described above.

[0051] The machining tool 100 comprises at least one rotary member 102, a body 110 and a motorization system 120 as illustrated, for example, in FIGS. 7B and 7C.

[0052] With reference to Figure 7A, an example of a rotary member 102 will be described.

[0053] The rotary member 102 is configured to machine the portion of the surface Si, S2, S'i, S'2 according to a predetermined shape profile. It may comprise at least one head 202, having a revolution profile and configured to machine the parts and a rod 200 comprising a free end configured to couple the rotary member 102 to another element of the machining tool 100, for example the motorization system 120. The rod 200 also comprises an end opposite the free end and secured to the head 202. In this example, the head 202 is cylindrical.

[0054] Still with reference to figure 7A, the head comprises an external surface 204 intended to come into contact, for example, with the internal surface Si or external surface S'i, of the aeronautical part 1 with a view to its machining.

[0055] Preferably, the head 202 is hollow. This makes it possible to lighten the rotating member 102 and to limit, for example, the centrifugal effect during high-speed rotation of the rotating member 102. This limitation has the effect of ensuring greater machining precision. In particular, fragile parts can be machined without being damaged.

[0056] It will be understood that the revolution profile of the head 202 is not limited to a cylindrical profile having a cylindrical outer surface and can be configured to achieve at least one of the profiles illustrated in FIG. 4.

[0057] Figure 7B, for its part, illustrates a radial sectional view of a machining tool 100 according to the invention.

[0058] The body 110 of the machining tool 100 comprises at least one housing 112 designed to receive the rotary member 102.

[0059] In the example of Figure 7B, the body 110 has a general parallelepiped shape with: a) a front face intended to be positioned opposite the internal surface Si of the part 1 to be machined; b) a rear face opposite the front face; c) an upper portion located at the head of the rotary member 102; d) and a lower portion connected to a motorization system 120 in the example shown.

[0060] The front face comprises an opening 114 which opens onto the housing 112. The opening is configured so as to allow the rotating member 102 to come into contact with the internal surface Si of the part 1.

[0061] The machining tool 100 further comprises a first reference guide 104 located on the front face of the body 110, at its upper portion and in particular slightly above the head 202 of the rotary member. This first reference guide 104 is configured to bear on the edge B1 of the aeronautical part 1 to be machined. The first reference guide 104 is also configured to be inserted into the clearance 12 between the junction of a first and a second aeronautical part 1, 2 as illustrated in FIG. 6b. Preferably, the first guide is a flat strip with an adaptable thickness for insertion into the clearance 12. For example, and in a non-limiting manner, for a clearance 12 of the order of 0.4 mm, the thickness of the first guide may be of the order of 0.3 mm.

[0062] Alternatively, the first guide can be a curved ruler.

[0063] Thus, we understand that the shape of the first guide can be configured according to the contour of the part to be machined.

[0064] The machining tool 100 further comprises at least one second reference guide 106b, 106 c , located on the front face of the body 110 and below the first reference guide 104. The second reference guide 106b is either arranged on either side of the head of the rotary member 102, or arranged so that the head of the rotary member 102 is located between the second reference guide 106 c and the first reference guide, or both. The second reference guide is further configured to rest on the surface Si of the first part 1 to be machined. The second reference guide 106b, 106 c has, for example, the shape of a tenon 106b or a tongue 106 c with rounded edges matching the internal surface Si of the part 1 to be machined.

[0065] The machining tool 100 may further comprise a third reference guide 106 a , located on the front face of the body 110, slightly above the first reference guide 104. The third reference guide 106 a is configured to bear on the internal surface Si of the part 1 to be machined or on the internal surface S2 of a second aeronautical part, in the case of an assembly of a first 1 and a second 2 aeronautical part as illustrated in figures 2A, 6A and 6B. The third reference guide 106 a has a projecting shape with a slightly rounded edge, preferably rounded, to fit the internal surface Si of part 1 or on the internal surface S2 of the second part 2.

[0066] In a first variant (not shown), the machining tool comprises the first reference guide 104 and the second reference guide 106b, 106 c for machining an aeronautical part similar to that of figure 1.

[0067] In a second variant (not shown), the machining tool comprises the first reference guide 104 and the third reference guide for machining an assembled aeronautical part, similar to that of FIG. 2.

[0068] We therefore understand that the machining tool can be adapted according to the application and the shape of the aeronautical revolution part to be machined.

[0069] In some embodiments, a machining tool 100 may be provided comprising at least one body 110 whose front face comprises at least the first reference guide 104 and housings configured for fixing the second 106b, 106c, and third 106 areference guide. In this case, the second and third reference guides can also be configured to snap into the recesses provided on the front face of the machining tool body. Thus, depending on the application, i.e. the type of workpiece to be machined, the appropriate reference guide can be selected and attached.

[0070] It is thus understood that the machining tool can be in the form of a kit comprising at least the characteristics mentioned above.

[0071] Furthermore, advantageously, those skilled in the art will understand that the rotary member 102 and the first, second and third reference guides are arranged so that the machining of the predetermined shape profile PF1, PF2, PF3, PF4, such as illustrated in Figure 4, by the rotary member 102 is produced as a function of the first 104 and second 106b, 106 c and / or third 106 arequested reference guides. The machining tool is therefore suitable for producing several types of profiles.

[0072] The machining tool 100 further comprises a bracket 118 located partly on the rear face of the body of the tool and on which the lower portion of the body 110 of the tool rests, as illustrated in FIGS. 7B and 7C.

[0073] The machining tool 100 also comprises at least one shim 116 a , 116b adjustment configured to define the machining depth of the rotary member 102.

[0074] So, at least one 116 wedge a can be inserted between the bracket 118 and the lower portion of the body 110 of the tool 100, this shim having a thickness which is determined as a function of a desired machining depth of the rotary member.

[0075] For example, and in a non-limiting manner, in the case of a part similar to that of figure 1, the thickness of the shim can be determined by measuring the offset between the part of the internal surface Si of the first part 1 exhibiting a deformation and another part of the internal surface in a normal state, that is to say not exhibiting any deformation for example.

[0076] Similarly, in the example of Figure 2A, the thickness of the shim can, for example, be determined by measuring the offset between the inner surfaces S1 and S2 of the first and second parts.

[0077] Another shim 116b may also be arranged at an upper end of the body 110 so as to control whether or not the third reference guide 106 is supported. a , located above the first reference guide 104, on the internal surface S2 OR external surface S'2 of a second aeronautical part 2.

[0078] Those skilled in the art will then understand that an advantage which arises from controlling the positioning of the rotary member 102 opposite the surface Si, S2 to be machined and also the supports 104, 106 a , 106b, 106 c requested is the improvement of the machining precision of the parts. This precision allows, for example and in a non-limiting manner, to machine the parts while respecting the maximum dimension authorized for the parts. The parts are generally sized to respect certain operating conditions. During the manufacture of the parts, dimensions or dimensions (nominal, minimum and maximum) are therefore defined for optimal operation of the parts. Thus, failure to respect the defined dimensions due to poor precision in the machining of the parts can lead to poor operation of the structure integrating the machined parts. Furthermore, the reference guides can be supported on the edge or surfaces without exerting constraints which could induce deformation of the surfaces to be machined.

[0079] Supports 104, 106 a , 106b, 106 c can be made of plastic, metal, or aluminum alloy. Thus, the material used for the manufacture of each support can be determined according to the complexity of the support shape or the level of wear of the workpiece.

[0080] Still with reference to FIG. 7B, the motorization system 120 or motor connected to the body 110 is configured to drive the rotary member 102 in rotation. The terms motorization system and motor designate the same thing.

[0081] The motorization system 120 comprises at least: an axis-motor coupler 124 configured to receive the free end of the rod 200; an axis-motor 122 to drive the coupler 124 in rotation.

[0082] With reference to Figure 7C, illustrating a perspective view of the machining tool, the motorization system may further comprise an activation device 126 of the motorization system 120 or motor. The motorization system 120 may be, for example, of the electric, pneumatic or hydraulic type.

[0083] The machining tool may further comprise a gripping means 132, fixed to the motorization system and on which the activation device is arranged.

[0084] The body 110 of the tool and the motorization system can be connected to the bracket 118 via screws 134 respectively b and 134 a .

[0085] The machining tool may further comprise a suction system 128 for the dust emitted during the machining of a part, the suction system 128 being carried by the body 110.

[0086] The machining tool may further comprise a connecting nozzle 130, disposed proximate the head 202 of the rotating member 102 and configured to connect to one end of the suction system 128.

[0087] In a first variant (not shown), the machining tool comprises the first reference guide 104 and the second reference guide 106b, 106 c for machining an aeronautical part similar to that of figure 1.

[0088] The skilled person will further understand that assembled parts such as those in Figure 2, for example, can be machined during or after manufacture, without being disassembled. This saves time. This time saving is linked, in part, to the portability and adaptability of the machining tool described above to parts of different sizes. In particular, no complex assembly is required for machining an aeronautical part. For example, mounting a rail on the part to be machined to use it as a reference guide is not necessary. An intervention for maintenance is therefore faster.

[0089] In the detailed presentation of the invention given above, the terms used should not be interpreted as limiting the invention to the embodiments set forth in this description, but should be interpreted to include all equivalents within the reach of those skilled in the art by applying their general knowledge to the implementation of the teaching just disclosed to them.

Claims

Claims [1] Method (300) for machining a first part (1), this part comprising a surface (S1, S1') connected to an edge (B1) of the part (1), the surface (S1, S1') and the edge (B1) extending along a length (L1) of the first part, a part of this surface which adjoins said edge being intended to be machined, the method comprising the steps of: a) applying a machining tool (100) to the part (1), this tool (100) comprising at least one reference guide (104, 106) a , 106b, 106 c ) which is pressed against the surface (S1, S1') and / or the edge (B1) of the part (1), this tool (100) further comprising a rotary machining member (102); b) moving the tool (100) along the length (L1) so that the rotary member (102) machines the part of the surface according to a predetermined shape profile (PF1, PF2, PF3, PF4), the reference guide (104, 106 a , 106b, 106 c) of the tool (100) being held in support on the part (1) during this movement. [2] The method (300) of claim 1, wherein the machining is performed by grinding or milling. [3] Method (300) according to claim 1 or 2, wherein, in step a), the tool (100) comprises a first reference guide (104) resting on the edge and a second reference guide (106b, 106 c ) resting on the surface (S1). [4] Method (300) according to one of claims 1 to 3, in which a second part (2) is mounted on the first part (1) and extends in the extension of this first part (1) on the side of said edge (B1), the first (1) and second (2) parts being separated by a clearance (12), and in which, in step a), the tool (100) comprises a first reference guide (104) resting on the edge (B1) of the first part and another reference guide (106 a ) resting on the surface (S2) of the second part. [5] Method (300) according to any one of claims 1 to 4 wherein the machining comprises producing a profile from a set of profiles comprising at least one chamfer or bevel. [6] Machining tool (100) for implementing a method (300) according to one of the preceding claims, in which it comprises: a rotary member (102); a body (110) comprising at least: • a housing (112) configured to receive the rotary member (102); • a face intended to be positioned opposite the part to be machined, said face comprising: o an opening (114) opening onto the housing (112) and configured so as to allow the rotary member to come into contact with a surface (S1, S1') of the part (1) to be machined; and o at least one reference guide (104, 106 a , 106b, 106 c) configured to bear on the surface (S1, S1') and / or the edge (B1) of the part (1) so as to guide the machining tool; and b) a motorization system (120) connected to the body (110) and configured to drive the member (102) in rotation; said rotary member (102) being configured to machine the part of the surface (S1, S1') according to a predetermined shape profile (PF1, PF2, PF3, PF4). [7] Machining tool (100) according to the preceding claim, in which the rotating member (102) is a grinding wheel or a milling cutter. [8] Machining tool (100) according to any one of claims 6 to 7, wherein the rotary member (102) comprises: a hollow head (202) having a revolution profile and comprising an external machining surface (204) intended to come into contact with the surface (S1, S1 ') of the part (1) for the purpose of machining it; and a rod (200) comprising an end secured to the head (202) and a free end, opposite the end secured to the head (202) and configured to couple to the motorization system (120). [9] Machining tool (100) according to any one of claims 6 to 8, comprising at least one first reference guide (104) configured to bear on the edge (B1) of the part (1) to be machined, this first reference guide (104) being located on a front face of the body (110) intended to be positioned opposite the surface (Si, S'i) of the part 1 to be machined and above the head (202) of the rotary member (102), said first reference guide (104) forming at least one flat or curved strip. [10] Machining tool (100) according to claim 9, comprising at least one second reference guide (106b, 106 c) configured to bear on the surface (S1, S1') of the workpiece, this second reference guide being located below the first reference guide (104), either arranged on either side of the head of the rotary member (102), or arranged so that the head of the rotary member (102) is located between said second reference guide (106 c ) and the first reference guide, or both, the second reference guide (106b, 106 c ) having the shape of at least one tenon (106b) or at least one tab (106 c ) with rounded edges matching the internal surface (Si) of the part to be machined. [11] Machining tool (100) according to claim 9 or 10, comprising at least one other reference guide (106 a) configured to be supported on the surface (S1, S1') of the part to be machined, this other reference guide being located on the front face of the body (110), above the first reference guide (104), this other reference guide (106 a ) having a projecting shape with a rounded edge matching the internal surface (Si) of the part to be machined. [12] Machining tool (100) according to any one of claims 6 to 11, comprising: a bracket (118) on which a lower portion of the body (110) of the tool rests; and at least one shim (116 a , 116b) adjustment wedge interposed between the square (118) and the lower portion of the body (110) of the tool, this wedge having a thickness which is determined as a function of a desired machining depth of the rotary member (102). [13] Machining tool (100) according to any one of the preceding claims, wherein the motorization system (120) comprises at least: a) an axis-motor coupler (124) configured to receive the free end of the rod (200); b) an axis-motor (122) for rotating the coupler; and c) a motor activation device (126). [14] Machining tool (100) according to the preceding claim, in which the motorization system (120) is of the electric, pneumatic or hydraulic type. [15] Machining tool (100) according to any one of the preceding claims, comprising a suction system (128) for dust emitted during machining, this suction system being carried by the body (110).

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