• 专利附录
  • 专利说明
  • 权利要求
  • 类似技术
  • 同族专利
  • 引用文献
  • 法律状态
  • 优先权
    • 专利摘要:
    The present invention relates to a method for directly manufacturing at least one part at a predetermined position (Z1, ..., Zn) of a structure (T), said method comprising the following successive steps: a) scanning, via a scanner three-dimensional (30) of the structure at the predetermined position (Z1); b) comparing, by a central unit, a virtual surface mesh of the predetermined position with a real surface mesh of said predetermined position, said actual surface mesh being calculated by the central unit from data obtained following the scan carried out at step a); c) determining, by the central unit, the gaps between said two meshes; d) calculating, by the central unit, the piece modeling data, called insert, the dimensions of which fill said gaps calculated in the step to obtain a model of a spacer; e) merging, by the central unit, of a virtual model of a part associated with said predetermined position with the model of the intermediate part calculated in step d) in order to obtain a model of an adjusted part, said model adjusted to the geometry of the structure at the predetermined position; f) manufacturing by deposition of material, by deposition means, the piece adjusted to the position from the adjusted model (AJST) calculated in step e).
    公开号:FR3022527A1
    申请号:FR1455753
    申请日:2014-06-23
    公开日:2015-12-25
    发明作者:Yann-Henri Laudrain
    申请人:Airbus Operations SAS；
    IPC主号:
    专利说明:

    [0001] The present invention relates to a method for the direct manufacture of at least one part on a structure, in particular an aircraft fuselage, and a device for implementing this method. process. A fuselage comprises a primary structure, formed in particular of transverse frames and longitudinal rails, an outer skin supported by the primary structure, as well as a floor fixed to the primary structure. During the manufacture of the fuselage on a production site, many pieces of different types are attached to the primary structure to reinforce it, such as a splint and a splint fixed to one another at the joint between two coplanar frames and enclosing said two frames in order to couple them to one another. Currently, the parts to be fixed are manufactured by different entities outside the production site and then brought to the latter where they are stored in the store of the production site. Operators must, prior to fastening the part to the fuselage by screwing or riveting - get the parts to the store to transport them in the fuselage to a position where they must be fixed, - stall these parts, by means of liquid wedging or pasty, requiring a long drying time, to take into account the contact defects between the primary structure and the workpiece, said defects being due to the clearances (less than the millimeter) inherent in the assembly of large elements. These provisions slow down the rate of production of fuselages. One solution to this problem would be to manufacture the parts directly on the fuselage where they need to be fixed. Document EP2537642 discloses a device for printing 3D parts, but this device is arranged in a closed chamber specifically dedicated to printing and only makes it possible to manufacture a part according to a predetermined size, the part thus manufactured (requiring a phase of machining to extract it from its support plate) must always be brought to the production site then wedged.
    [0002] One of the objects of the present invention is to remedy all or part of the disadvantage mentioned above. For this purpose, the present invention relates to a method of directly manufacturing at least one part at a predetermined position of a structure, said method comprising the following successive steps: a) scanning, via a three-dimensional scanner, of the structure at level of the predetermined position; b) comparison, by a central unit, of a virtual surface mesh of the predetermined position with a real surface mesh of said predetermined position, said actual surface mesh being calculated by the central unit from data obtained following the scan carried out in step a); c) determining, by the central unit, the gaps between said two meshes; d) calculating, by the central unit, the data of modeling of a part, called insert, the dimensions of which fill said gaps calculated in step to obtain a model of an intermediate part; e) merging, by the central unit, of a virtual model of a part associated with said predetermined position with the model of the intermediate part calculated in step d) in order to obtain a model of an adjusted part, said model adjusted to the geometry of the structure at the predetermined position; F) manufacturing by deposition of material, by deposition means, of the workpiece adjusted to the position from the adjusted model calculated in step e). The characteristics of the invention mentioned below, as well as others, will emerge more clearly on reading the following description of exemplary embodiments, said description being given in relation to the attached drawings, among which: Figure 1 is a block diagram of the device for the direct deposition of a workpiece to a predetermined position of a material deposition structure according to one embodiment of the invention; FIG. 2 is a schematic view of an exemplary embodiment of the device of FIG. 1, disposed inside a fuselage; FIG. 3 is a schematic view of a predetermined position of the fuselage on which a splint is to be made by means of the device illustrated in FIG. 2; FIG. 4 is a view similar to FIG. 3 showing a virtual model of a splice to be manufactured on said predetermined position; Figure 5 is an enlargement of the device of Figure 2 showing the details of an articulated arm; FIG. 6 is a diagram illustrating an implementation of the device according to the invention for the manufacture of a splice on the predetermined position of FIG. 3; and FIG. 7 is a view similar to FIG. 3 showing a splint manufactured by means of the device of the invention according to FIG. 2.
    [0003] With reference to FIG. 1, the device 1 according to the invention comprises a central unit 2 controlling displacement means 3 designed to move the device 1, measurement means 4, material deposition means 6 associated with an arm 5 as well as a positioning unit 7 supplying the central unit 2 with data on the position of the device 1. As shown in FIG. 2, the device 1 is in the form of an autonomous mobile robot 100 comprising a chassis 11 of parallelepipedal shape mounted on wheels 14 and on which is fixed the articulated arm 5. According to the invention, the robot 100 is designed to move in a fuselage T and deposit layers of metallic or plastic material to predetermined positions Z1, Z2,... Zn (integer n, the predetermined positions are represented by hatched areas in FIG. 2) of the fuselage T via the material deposition means 6 and the art arm icule 5 to form parts directly on said fuselage T. According to the invention, the dimensions of each of the parts manufactured by the device 1 are adjusted to the geometry of the fuselage T as a function of measurements made by the measuring means 4 to 1. the location of the deposit in order to take into account the geometrical specificities (sets of assemblies, surface irregularities, etc.) of said fuselage T. With reference to FIG. 1, the measuring means 4 comprise at least one configured three-dimensional scanner 30 for scanning areas of the fuselage T, as well as two databases DB1, DB2 each containing data, in the form of point coordinates, obtained by three-dimensional assisted modeling of a virtual fuselage Tg which is a generic model of the fuselage T. Unlike the real T fuselage, the virtual fuselage Tg is a perfect model whose assemblies between the constituent elements have no play.
    [0004] The data of the first DB1 database comprises the modeling of all the elements forming the virtual fuselage Tg, in particular its primary structure (frames, smooth, skin, sleepers, ...) and its secondary structure (floor, supports, uprights ...). In addition, sets of adjacent points representing the predetermined positions Z1 ..., Zn on the virtual fuselage Tg are recorded in the first database DB1. With reference to FIG. 3, a predetermined position Z1 (hatched in FIG. 3) recorded in the first database DB1 comprises, for example, the three-dimensional modeling data of two longitudinal rails 10 and two frames 12.
    [0005] Each of the two frames 12 rests perpendicularly on the rails 10 at the sole 12a of the frame and the two frames 12, although located in the same plane, are non-contiguous. The skin 13 is attached to the sole 10a of the rails 10. The data of the second database DB2 comprises the virtual modeling of the part, including its mechanical strength specifications, called the virtual model of the part, to be manufactured on each part. predetermined zone Z1, .., Zn. With reference to FIG. 4 and taking again the preceding example, the virtual model of the part to be manufactured on the predetermined zone Z1 corresponds to a splint 14 resting on each of the two frames 12, so that the splice 14 forms a join between the two frames to couple them to each other. A three-dimensional scanner 30 is provided, in use, to scan areas of the fuselage T and thus collect real coordinates of a plurality of points of the scanned areas. The points collected are then transmitted to the central unit 2 which, in use, calculates a surface mesh, called the real mesh MR, of the scanned area. Preferably, a three-dimensional scanner 30 is optical non-contact technology, such as laser, photogrammetry, or videogrammetry and analyzes an area located at a distance of between 5 cm and 1 m from said scanner and can scan an area with a diameter of 1 m at a distance of 1 m. It will be noted in FIG. 2 that the device 1 comprises a single three-dimensional scanner 25 mounted at the free end 20 of the articulated arm 5. According to the invention, and as will be detailed below with an example of manufacturing a splits, the dimensions of the virtual model of the part recorded in the second database DB2, said template forming a template, is adjusted by the central unit 2 according to the actual data provided by the three-dimensional scanner 30 in order to manufacture a suitable part the geometrical specificities of the fuselage T. The displacement means 3 comprise electric motors and servocontrols associated with the wheels 14 and for moving the latter.
    [0006] The positioning unit 7 is of any known type, and is for example an optical positioning unit by image analysis, potentially combined with a wave positioning unit (radiofrequency type when radiofrequency labels are arranged on the screen). fuselage floor, or triangulation type via a mesh network of 5 wireless communication ...). In use, the positioning unit 7 provides positioning data to the central unit 2 which determines the position of the device 1 in the virtual fuselage Tg from the data recorded in the first database DB 1.
    [0007] The material deposition means 6 allow the direct deposition of plastic or metal material layer after layer on a predetermined position Z1, ..., Zn and are associated with the articulated arm 5. The latter, illustrated in FIG. pivoting head 21 fixed to the free end 20 of the arm and a plurality of joints providing at least six degrees of freedom to the pivoting head 21, allowing the latter to be oriented and displaced in all directions relative to 11. The movement of the articulated arm 5 is ensured by servocontrols and motors controlled by the central unit 2. The material deposition means 6 are for example provided for the implementation of an additive laser construction method direct by deposition of molten metal powder and 20 then comprise a coaxial nozzle 41 mounted at the free end of the swivel head 21, a metal powder distribution system 42, a neutral gas distribution system 43 and a laser 44 arranged in the nozzle 41 so as to emit a radius through the free opening 41a of the nozzle.
    [0008] The metal powder distribution system 42 as well as the neutral gas distribution system 43 each comprise a pump (not shown in the figures) arranged in the frame, an upstream umbilicus and a downstream umbilicus (not shown in the figures). The upstream umbilicus connects the pump to a tank external to the device 1, respectively metal powder or neutral gas. The downstream umbilicus is attached to the articulated arm 5 and 30 connects the pump to the nozzle 41 so that, respectively grains of the metal powder or the neutral gas, can be ejected via the free opening 41a of the nozzle under the effect of the pump. For example, the neutral gas used is argon, the grains constituting the metal powder are spherical with a particle size of between 45 and 150 μm where the metal is for example a shade of titanium or aluminum. . The laser 44 has an average power of between 500 Watts and 6000 Watts.
    [0009] The manufacture, by means of the device 1, of a metal splice at the joint between two frames 12 at a predetermined position Z1 in order to couple the two frames 12 to one another will now be described in connection with FIG. 6. It will be considered that the device 1 according to the invention is disposed on the floor 50 of a fuselage T.
    [0010] In a first step El which corresponds to the start-up of the device 1, the central unit 2 implements a dedicated program for manufacturing a metal splint directly on a predetermined position Z1 of a fuselage T, said position being modeled in FIG. the first DB1 database. According to the program implemented by the central unit 2, the latter uses the modeling data of the first DB1 database to calculate the displacements and the position of the device 1 in the fuselage T on the basis of the data provided by the Positioning unit 7. In a second step E2, the central unit 2 calculates, by consulting the first database DB1, a path to be taken by the device 1 so that its articulated arm 5 has a range sufficient to reach the desired position. predetermined area Z1. The central unit 2 sends, once this calculation is made, instructions to the moving means 3 so that the device 1 moves at the end point of the path. It should be noted that the range of the articulated arm 5 is determined according to the dimensions of said arm and the movement of its joints and is a data recorded in the memories of the central unit 2.
    [0011] In a third step E3, the central unit 2 sends instructions to the motors and servocontrols of the articulated arm 5 so as to place the nozzle 41 in the vicinity (<8 mm depending on the width of the layer to be deposited) of the predetermined zone Z1 the free end 41a of the nozzle facing the area on which the metal material is to be deposited. In a fourth step E4, the central unit 2 uses the three-dimensional scanner 30 for measuring means 4. The latter scans an area comprising the predetermined position Z1 and supplies the central unit 2 with the real coordinates of the points of the elements. (frames 12, skin 13, smooth 10) forming the fuselage T at the predetermined position Zl. From these data, the central unit 2 calculates a real surface mesh, called the real mesh MR, of the predetermined position Z1. In a fifth step E5, the central unit 2 calculates a virtual surface mesh, called MV virtual mesh, of the predetermined position ZI from the data of the first DB1 database and implements a 3D registration algorithm in order to set in 5 optimal correspondence the two surface meshes, respectively the real mesh and the virtual mesh. The 3D registration algorithm uses for example the least squares method by considering the elements in play infinitely rigid and this to find the best superposition of the two meshes, under constraints that the functional sides, for example the sole 12a of the two frames 12, elements of the primary structure to be coupled are aligned on the two meshes. At the end of the step ES, the central unit 2 associates, as a pair of curves, each curve of the virtual mesh with a curve of the real mesh. In a sixth step E6, once the two meshes are superimposed, the central unit 2 compares, for all the pairs of curves, the positions of the two curves of the same pair with respect to each other and calculates the d differences between these two positions. The presence of a deviation d is indicative of an assembly clearance between the fuselage T and the virtual fuselage Tg at the predetermined position Z1. The central unit 2 determines, in a seventh step E7, and from deviations calculated in step E6, the three-dimensional modeling data of a part, called interleaving piece INT, which would be interposed in the gaps d between the two meshes. At the end of this step, the model of the intercalary part INT is obtained. In an eighth step E8, the central unit 2 merges, by a Boolean operation, the virtual model of the splice 14 recorded in the second database DB2 with the model of the intercalated piece INT and determines a model of a part adjusted, AJST adjusted model 25, to the fuselage geometry (T at the predetermined position Z1; In a ninth step E9, the central unit 2 controls the material deposition means 6 to form the AJST adjusted splint by deposition of material on the predetermined position Z1 according to an optimized strategy of predetermined trajectory by simulation ensuring on the one hand the specified mechanical characteristics from the second DB2 database, and on the other hand the accessibility of the device avoiding any collision possible with the environment (structure) The laser 44 is then operational and produces on demand a laser beam. The nozzle 41 of the pump of the metal powder distribution system 42 is subjected, in the nozzle 41, to a saturated atmosphere of neutral gas ejected by the pump 43 of the neutral gas distribution system 43 in order to overcome the problems. oxidation. Due to the constitution of the nozzle 41, the metal grains ejected from the nozzle 41 to the area to be covered are simultaneously subjected to laser radiation which melts them. The material deposition means 6 5 thus deposit a homogeneous and dense deposit. During this step, the articulated arm 5 moves according to the instructions of the central unit 2 so as to completely scan the area to be covered. It should be noted that the melt (whether plastic or metallic) deposited on the fuselage T adheres to the latter.
    [0012] Finally, the central unit 2 compares, in a tenth step El 0, via the three-dimensional scanner 30, the three-dimensional modeling of the splice during manufacture to the modeling of the adjusted splice AJST calculated in step E8. Step El0 continues as long as the correspondence is not exact, to a tolerance to the nearest micron. Once the correspondence is established, the central unit 2 proceeds again to the steps E1 to E10 as described above for another part to be manufactured at a predetermined position Z2. The invention makes it possible to manufacture parts directly on a structure via a homogeneous and precise deposition of material. The piece thus manufactured is perfectly adjusted to the geometry of the area where the deposit takes place and any stalling operation is then superfluous. In addition, the device in the form of a mobile robot 100 and autonomous relieves the teams of operators for the accomplishment of long and tedious tasks and makes it possible to separate the production rate of the capabilities of the parts supply chain. Thus, no human intervention is necessary for implementation and control. of the device 1, apart from any steps of preparation of the surfaces on which will be deposited metal or plastic material. The invention is applicable, in addition to fuselages, the wings of the aircraft and other structures such as boat hulls, the structure of a railway vehicle or in the automobile.
    [0013] Although described for making a fishplate, the invention makes it possible to manufacture pieces of different shapes according to the data recorded in the second database DB2. The virtual parts registered in the second DB2 database are, for example, fishplates, back splints, clips, supports, etc. In the case where the material deposition means 6 are provided for the implementation of a method of direct construction by deposition of molten plastic powder, the latter 5 then comprise a coaxial nozzle mounted at the free end of the pivoting head. , a plastic powder dispensing system and a laser arranged in the nozzle so as to emit a ray through the free opening of the nozzle. In a first variant of the invention, position sensors are arranged on the nozzle 41 and connected to the central unit. The central unit 2 calculates, via these sensors, the position of the nozzle 41 and is able to modify the flow rate of the pumps of the material deposition means 6 and the position of the nozzle 41 in order to correct the trajectory of the grains modified by gravity when the deposition of matter is in directions other than verticality.
    [0014] In a second variant of the invention, and with reference to FIGS. 3 and 7, it will be noted that through holes 12c are arranged on each of the two frames 12 at the joint of which a splint is to be manufactured, the unit Central 2 implements a hole recognition algorithm that makes it possible to recognize the presence of holes 20 made on the surfaces on which the part to be laid is to rest. This algorithm is translated, when it is implemented, and by repeating the description of the process carried out above, by an additional step E8 ', directly successive to step E8, in which the central unit 2 calculates a projection of the holes 12c frames 25 scanned in step E4 on the three-dimensional modeling AJST adjusted splint. In step E9, the AJST adjusted splint is manufactured by excluding a deposit of material on the projection of the holes 12c. The AJST adjusted splint finally manufactured thus includes through holes 14c, concentric with those 12c arranged in the frames. This variant is advantageous in that it makes it possible to directly fix the AJST fitted splice 30 to the frame by riveting or screwing without requiring drilling operations, in fine cleaning, of said splint. Thus according to this variant, it is possible to directly manufacture a splint and a back splint (not shown) on either side of each frame 12 at the junction of two coplanar frames in which through holes are arranged, the splice and the splice are fixed to one another via screw-nut systems passing through the holes 14c, 12c and thus to grip said two frames in order to couple them to one another.
    [0015] Without departing from the scope of the present invention, the device can be used to add geometries to existing parts already installed, or to add additional local functions such as generic specific parts such as media intended for routing system components such as electrical pipes or harnesses, or for the repair of structural elements that have been damaged or that have for example been subjected to non-conforming holes or else fault departures such as cracks for example.
    权利要求:
    Claims (2)
    [0001]
    CLAIMS1 °) A method of directly manufacturing at least one part at a predetermined position (Z1, ... Zn) of a structure (T), said method comprising the following successive steps: a) scan, via a three-dimensional scanner ( 30), the structure at the predetermined position (Z1); b) comparing, by a central unit (2), a virtual surface mesh (MV) of the predetermined position (Z1, ... Zn) with a real surface mesh (MR) of said predetermined position, said virtual surface mesh (MV) being calculated by the central unit (2) from modeling data recorded in a first database (DB1) and said actual surface mesh (MR) being calculated by the central unit from data obtained the scan performed in step a); c) determining, by the central unit (2), deviations (d) between said two meshes, said deviations being representative of sets of assemblies present in the structure; d) calculating, by the central unit (2), part modeling data, called insert (INT), whose dimensions fill said gaps calculated in step c) in order to obtain a model of an insert; e) merging, by the central unit (2), a virtual model of a part (14) associated with said predetermined position (Z1, ... Zn) recorded in a second database (DB2) with the model of the spacer (INT) calculated in step d) to obtain a model of a fitted part, called adjusted model (AJST), to the geometry of the structure (T) at the predetermined position ( Z1, ... Zn); f) manufacturing by deposition of material, by deposition means (6), the piece adjusted to the predetermined position (Z1, ... Zn) from the adjusted model (AJST) calculated in step e.
    [0002]
    2) Method according to claim 1, characterized in that the method comprises a step, prior to step a), moving in the structure (T) via displacement means (3), the three-dimensional scanner (30) and deposition means (6) at the predetermined position. Method according to one of claims 1 to 2, characterized in that the structure comprises at least one hole (12c) at the predetermined position (Z1) scanned in step a), the method comprises: an additional step e ', following step e, in which the central unit (2) calculates a projection of the at least one hole (12c) and defers the projection of the at least one hole on the adjusted model (AJST); in step f, the fitted part is manufactured by excluding a deposit of material at the location of the projection of the at least one hole so that the manufactured manufactured part comprises a hole (14c) crossing concentrically with each hole of the Structure (T). 4) Method according to any one of claims 1 to 3, characterized in that step f) comprises the implementation of a method of direct additive laser construction by deposition of molten metal or plastic powder. 5 °) Device (1) for implementing the method of directly manufacturing at least one part at a predetermined position (Z1, ... Zn) on a structure (T) according to any one of the preceding claims , said device comprising a central unit (2), characterized in that it comprises material deposition means (6), measurement means (4) comprising at least one three-dimensional scanner (30) and a first and a second database (DB1, DB2), the first database comprising modeling data of a virtual structure (Tg) and the second database comprising a virtual model of a part (14) to be fabricated on said predetermined position (Z1 ... Zn), said at least one scanner (30) providing to the central unit (2), in use, data relating to the geometry of the predetermined position (Z1 ... Zn), the central unit (2) being designed to calculate a model of a fitted part (A JST) from the virtual model (14) and the data provided by the at least one scanner (30) and to control the material deposition means (6) for the manufacture of a workpiece by deposition of material on the predetermined position (Z1, 30 ... Zn) according to the model of the adjusted part (AJST). 6 °) Device according to claim 5, characterized in that it further comprises displacement means (3) controlled by the central unit (2). Device according to any one of claims 5 to 6, characterized in that it comprises an articulated arm (5), said at least one scanner (30) being mounted on the articulated arm 58 °) according to any one of claims 5 to 7, characterized in that the material deposition means (6) comprise a coaxial nozzle (41) mounted at a free end (21) of the articulated arm and a powder distribution system ( 42) for supplying the powder to a free opening (41a) of the coaxial nozzle (41) 10 9 °) Device according to claim 8, characterized in that the powder is selected from a plastic powder or a metal powder. 10 °) Device according to claim 8, characterized in that the powder is a metal powder, the material deposition means (6) further comprise a neutral gas distribution system (43) and a laser (44) arranged in the nozzle (41) so as to emit a radius through the free opening (41a) of the nozzle. 20
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    优先权:
    申请号 | 申请日 | 专利标题
    FR1455753A|FR3022527B1|2014-06-23|2014-06-23|METHOD AND DEVICE FOR THE DIRECT MANUFACTURE OF A WORKPIECE ON A STRUCTURE|FR1455753A| FR3022527B1|2014-06-23|2014-06-23|METHOD AND DEVICE FOR THE DIRECT MANUFACTURE OF A WORKPIECE ON A STRUCTURE|
    US14/730,401| US9827716B2|2014-06-23|2015-06-04|Process and device for direct fabrication of a part on a structure|
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