• 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:
    One method includes producing a first frame (26) with a first plurality of pre-drilled holes (52) at predefined locations, producing a second frame (28) with a second plurality of pre-drilled holes (50) at pre-defined locations. defined, produce a third frame (30) without pre-drilled full-size holes, measure the location and orientation of the first and second pluralities of pre-drilled holes in the first and second structures, determine the location of a third plurality of holes ( 64t, 64s) to be drilled in the third frame corresponding to the first and second pluralities of pre-drilled holes measured in the first and second frames, create a program (89) for drilling the third plurality of holes in the third frame that align with the measured location and orientation of the first and second pluralities of pre-drilled holes in the first and second structures based on the measured location and orientation of the first and second pluralities of pre-drilled holes in the first and second frames, drill the third plurality of holes (64t, 64s) in the third frame (30) based on the program, position the third frame over the first and second frames so that the third plurality of holes in the third frame are aligned with the first and second pluralities of pre-drilled holes in the first and second frames, and insert fasteners (68) through the third plurality of holes and the first and second pluralities of pre-drilled holes that are aligned with the third plurality of holes for securing the second frame to the first frame using the third frame.
    公开号:BR102018000883A2
    申请号:R102018000883-8
    申请日:2018-01-16
    公开日:2019-02-19
    发明作者:Craig A. Charlton；Branko Lakic；Jerald A. Hull；Christopher A. Greer；Justin H. Pratt
    申请人:The Boeing Company；
    IPC主号:
    专利说明:

    “METHOD, SYSTEM FOR CARRYING OUT THE METHOD, AND, STRUCTURAL ASSEMBLY FOR AN AIRCRAFT”
    FIELD [001] This order refers to a system and method for joining structural components and, more particularly, for joining structural components, such as aircraft structure parts, by drilling and fixing fasteners to structural components.
    FUNDAMENTALS [002] The precise location of holes is critical for attaching parts or parts of an assembly during a manufacturing process. To achieve this goal, overlapping parts are typically drilled while being assembled together using a drilling template to ensure that the holes in each part match each other. However, the use of drilling templates to drill primary structural joints, especially titanium, is not a stable drilling platform, which results in a large percentage of oversized holes and associated production waste. In addition, the areas in which the joints are drilled may not be ergonomically accessible for drilling and assembly, as in large-scale integration and larger joint areas associated with the main structural components around the perimeter of the fuselage and / or in the box cavity of an aircraft's wings. This type of drilling is also very time-consuming. In addition, drilling the main structural components in aircraft creates a significant amount of foreign object debris, which requires manual cleaning. Also, large hand tools are required to drill holes for some of the large fasteners for integration of the fuselage and wings. These large hand tools can create access problems for drilling in the confined area.
    SUMMARY [003] In one embodiment, a method is provided. The method includes
    Petition 870180003827, of 01/16/2018, p. 67/115 / 28 produce a first structure with a first plurality of pre-drilled holes in predefined locations, produce a second structure with a second plurality of pre-drilled holes in predefined locations, produce a third structure without actual size holes pre-drilled, measure the location and orientation of the first and second pluralities of pre-drilled holes in the first and second structures, determine the location of a third plurality of holes to be drilled in the third structure that correspond to the first and second pluralities of pre-holes -perforated measured in the first and second structures, create a program to drill the third plurality of holes in the third structure that align with the measured location and orientation of the first and second pluralities of pre-drilled holes in the first and second structures based on the location and orientation measured from the first and second pluralities of pre-drilled holes in the first and second structures, drill the third plurality of holes in the third structure based on the program, position the third structure over the first and second structures so that the third plurality of holes in the third structure is aligned with the first and second pluralities of pre-drilled holes in the first and second structures, and insert fasteners through the third plurality of holes in the third structure and the first and second pluralities of pre-drilled holes in the first and second structures which are aligned with the third plurality of holes in the third structure to secure the second frame to the first frame using the third frame. [004] In another modality, a method is provided. The method includes producing the first structure with first pre-drilled holes at predefined locations, producing the second structure without pre-drilled full-size holes, measuring the location and orientation of the first pre-drilled holes in the first structure, determining the location of seconds holes to be drilled in the second structure that correspond to the first holes measured in the first structure, create a program to drill the second holes in the
    Petition 870180003827, of 01/16/2018, p. 68/115 / 28 second structure that aligns with the measured location and orientation of the first pre-drilled holes in the first structure based on the measured location and orientation of the first pre-drilled holes in the first structure, drill the second holes in the second structure with Based on the program, position the second frame on the first frame so that the second holes in the second frame are aligned with the first pre-drilled holes in the first frame, and insert fasteners through the first and second aligned holes of the first and second frames to attach the second frame to the first frame.
    [005] In another embodiment, a system for attaching a first structure to a second structure is provided. The system includes a measuring machine. The measuring machine is configured to take measurements of the location and orientation of a first plurality of pre-drilled holes in the first structure and a second plurality of pre-drilled holes in the second structure. The system includes a measurement program. The measurement program is configured to execute a measurement plan for the measuring machine to make measurements of the location and orientation of the first plurality of pre-drilled holes in the first structure and the second plurality of pre-drilled holes in the second structure. The system includes at least one processor for processing the measurement of the first plurality of pre-drilled holes in the first structure and the second plurality of pre-drilled holes in the second structure. The system also includes an ODEM station. The ODEM station is configured to generate a CN program for drilling holes in the third structure based on the processed measurements of the first plurality of pre-drilled holes in said first structure and second plurality of holes in the second structure. The system also includes a CNC machine. The CNC machine is configured to drill holes in the third structure based on the CN program. The system also includes fasteners. The fasteners are inserted into the drilled holes of the third structure and the first and second
    Petition 870180003827, of 01/16/2018, p. 69/115 / 28 pluralities of the pre-drilled holes in the first and second structures which are aligned with the drilled holes of the third structure to fix the first structure to the second structure.
    [006] In another modality, a structural set for an aircraft is provided. The structural set includes a reinforcement beam, a cross beam, a splice part, and fasteners. The reinforcement beam includes a first plurality of pre-drilled holes. The cross beam includes a second plurality of pre-drilled holes. The reinforcement beam is joined to the cross beam by the splice part. The splice part includes holes drilled by a CNC machine. The location of the drilled holes in the splice part is based on the measured locations and orientation of the first plurality of pre-drilled holes in the reinforcement beam and the second plurality of pre-drilled holes in the crossbeam. A first plurality of fasteners is inserted into aligned holes of the first plurality of pre-drilled holes in the reinforcement beam and a first group of the drilled holes of said splicing part. A second plurality of fasteners is inserted into aligned holes of the second plurality of pre-drilled holes in the cross beam and a second group of the drilled holes in the splice part.
    [007] Other modalities of the method and system described and associated structural set will become apparent from the following detailed description, the attached drawings and the attached claims.
    BRIEF DESCRIPTION OF THE DRAWINGS [008] Figure 1 is a block diagram of the system for joining structural components according to a modality;
    figure 2 is a partial exploded view of the structure having the structural components according to the embodiment of figure 1 figure 3 is a schematic side view of the arrangement of the reinforcement beam, transverse beam, and upper seam with a shim according with the modality of figure 1;
    Petition 870180003827, of 01/16/2018, p. 70/115 / 28 figure 4 is a perspective view of a portion of an aircraft fuselage showing the whole of the modality of figure 1;
    figure 5 is a perspective view of a portion of an aircraft fuselage showing the part of the structure and a ROMER arm machine (a type of articulated arm coordinate measuring machine) mounted on a platform according to embodiment of figure 1;
    figure 6A is a perspective view of a portion of an aircraft fuselage showing the combined structure and surfaces part illustrating a better fit of the exaggerated surface profile measured according to the embodiment of figure 1;
    figure 6B is similar to figure 6A, except that the exaggerated surface is shown to be displaced along the normal plane to the conjugated surfaces;
    figure 7 is a side perspective view of the reinforcement beam and crossbeam arrangement according to the embodiment of figure 1;
    figure 8 is a top perspective view of the upper splice part fixed to a fixing device according to the embodiment of figure 1;
    figure 9 is a bottom perspective view of the lower display part attached to a fixation device according to the embodiment of figure 1;
    figure 10 is a perspective view of the upper seam part being fixed to a fixing device and having holes drilled in it by a CNC machine;
    Figure 11 is a perspective view of the crossbeam and reinforcement beam arrangement and ROMER arm mounted in a support box that simulates the portion of the pressure platform on which the crossbeam and reinforcement beam would be mounted according to the modality
    Petition 870180003827, of 01/16/2018, p. 71/115 / 28 of figure 1;
    figure 12 is a flow chart of the method for joining the structural assembly according to the embodiment of figure 1;
    figure 13 is a flow chart of an aircraft manufacturing and service methodology; and figure 14 is a block diagram of an aircraft.
    DETAILED DESCRIPTION [009] Figure 1 illustrates a system 20 for joining structural components by drilling and fixing fasteners to structural components. In one application, the structural components can be workpieces of an aircraft structure 24 (figure 2). However, those skilled in the art will appreciate that various types of structural elements can be connected together using the described system and method 20, or for aerospace or non-aerospace applications, without departing from the scope of the present invention.
    [0010] Figure 2 shows a portion of an aircraft 22 that has an example structure 24 that is mounted on the aircraft 22. The structure 24 includes a reinforcement beam 26 and a cross beam 28 that is joined to the reinforcement beam 26 by an upper splice part 30 and a lower display part 32. The frame 24 is mounted on the horizontal pressure platform 34 of the fuselage 36 of the aircraft 22 on a waterline surface 62. The reinforcement beam 26 includes a base 40 which extends vertically with respect to the pressure platform 34 and an upper plate 42 which is affixed to the top of the base 40. The edge of the upper plate 42 which is adjacent to the cross beam 28 extends slightly beyond the base 40. The cross beam 28 includes an upper plate 44 and a side plate 46 which are affixed to a base 48. Side plate 46 faces the reinforcement beam 26. Six pre-drilled holes 50 are located in the upper plate 44 of the cross beam 28 and six holes pr punch 52 are located on the top plate 42 of the reinforcement beam 26.
    Petition 870180003827, of 01/16/2018, p. 72/115 / 28
    Six pre-drilled holes 54 are located on the side plate 46 of the base 48 along the mating top line surfaces 56. Nine pre-drilled holes 58 are located on the station surface 60 of the base 40 of the reinforcement beam 26. Ten pre-drilled holes perforated 61 are located on the horizontal pressure platform 34 on the mating waterline surfaces 62.
    [0011] The upper splice part 30 includes twelve drilled holes
    64T, 64S. Six of these perforated holes 64T are aligned with the six holes 50 of the upper plate 44 of the cross beam 28. The other six holes 64S are aligned with the six holes 52 of the upper plate 42 of the reinforcement beam 26. The mating surface 66 between the upper junction 30 and the cross beam 28 can be chocked by a shim 69, if the conjugated surface 66 does not coincide with the conjugated surface of the upper seam part 30, as schematically illustrated in figure 3. The flatness profile tolerances for the conjugate surface 66 can be, for example, 0.254 mm (0.010 inch). Fasteners 68 (figure 4), conjugated, spaced and footed with the surfaces of the upper seam part 30, are installed through the drilled holes 50, 52, 64T, 64S, by hand, without the use of any tools.
    [0012] The bottom display part 32 includes twenty-five drilled holes 70, 72, 74. Nine perforated holes 70 are aligned with holes 58 on the mating surfaces of station 60, ten drilled holes 72 are aligned with the ten pre-holes perforated 61 located on the horizontal pressure platform 34 on the waterline surface 62, and six perforated holes 74 are aligned with the six pre-drilled holes 54 located on the side plate 46 of the base 48 along the mating top line surfaces 56. The lower display part 32 must be installed as follows. First, the mating surfaces of station 60 of the lower display part 32 and the reinforcement beam 26 must be adjusted according to the requirements of the project. Second, the lower display part 32 must be positioned against the
    Petition 870180003827, of 01/16/2018, p. 73/115 / 28 combined surfaces of top line 56 and sidewalk, when necessary. Third, the lower display part 32 must be positioned against the mating waterline surfaces 62 of the horizontal pressure platform 34, and the sidewalk, when necessary. With the surfaces of the lower display part 32 retained and pavement (if required), fasteners 68 (figure 4) are installed through the drilled holes 70, 72, 74, by hand, without using any tools until the gap between the head fastener and the outer surface of the lower display part 32 is less than a predetermined amount.
    [0013] With reference to figure 1, system 20 makes accurate measurements of the structure 24 while on the aircraft, processes those measurements and then machines conjugated blanks (for example, drill holes) and chocks that satisfy the tolerances required. System 20 includes a measuring system 80 located in a control station 82. The measuring system 80 includes a coordinate measuring machine (CMM) 84 and a computer system 86. Measurements on CMM 84 are sent to the system computer 86. Computer system 86 provides the interface for a user to execute a measurement plan, process measurements, and provide measurements processed in an XML format for an emergent on-demand manufacturing service (ODEM) 88. [0014] CMM 84 measures an object in a coordinate system of
    3D, often compared to a computer aided design (CAD) model. CMM 84 measures the structural components of the structure to drill the holes and add the necessary shims. The CMM 84 can be mounted on a stable platform 85 (figure 5) that prevents the CMM 84 from swinging in order to make accurate measurements. The CMM 84 can be any suitable metrological machine. The CMM 84 can be a portable coordinate measuring machine. For example, CMM 84 can be an articulated measuring arm (measuring arm), such as a
    Petition 870180003827, of 01/16/2018, p. 74/115 / 28 ROMER arm, as shown in figure 5. The ROMER 84 arm machine includes a robotic arm 90 that operates in 3D space with six or seven joints, comprising six degrees of freedom, which means that the arm 90 can move in three-dimensional space forward / backward, up / down, left / right, combining rotation around three perpendicular geometric axes (bearing, yaw, side tilt). The movement along each of the three geometric axes is independent of each other and independent of the rotation around any one of these geometric axes, comprising the six degrees of freedom. The ROMER 84 arm machine can be slidably mounted on track 92 (figure 5) of platform 85, adjacent to structures 24, for movement along track 92 to take measurements of selected areas on structures 24. As seen in figure 5, four fasteners 94 (two are shown) are threaded through the base 96 of the arm machine ROMER 84 and base plate 97 and into the rail 92 to secure the arm machine ROMER 84 to the rail 92. Loosening the fasteners 94 allows the ROMER 84 arm machine to slide along track 92 to a selected position. The fasteners 94 can then be tightened to stably attach the ROMER 84 arm machine to the rail 92 in the selected position to measure an area on frame 24. Repeated measurements are made on frame 24 and compared to ensure that the ROMER 84 arm machine is robust . When repeated measurements are close enough to each other to be within the allowable predetermined margin of error, the ROMER 84 arm machine is sufficiently robust. Other suitable types of CMMs with sufficient accuracy can be used to take measurements of areas of the structure 24, such as a portable measuring device or a laser scanner. The stable platform 85 is positioned adjacent to the first and second structures and attached to the fuselage 36, and preferably is of sufficient length to be positioned
    Petition 870180003827, of 01/16/2018, p. 75/115 / 28 adjacent to (and tightening along) a plurality of the first and second structures, so that the ROMER 84 arm machine is slidably mounted on the rail 92 to take measurements, in a plurality of the first and second structures, the location and orientation of the first plurality of pre-drilled holes in the first structure and the second plurality of pre-drilled holes in the second structure. Consequently, the system can be configured to generate a plurality of NC programs for drilling holes in a plurality of third structures based on successively obtained measurements, in a plurality of the first and second structures, of the first plurality of pre-drilled and second holes plurality of holes in said second structure.
    [0015] The system can also include collected three-dimensional (3D) measurement models that correspond to each set of reinforcement beam 26, cross beam 28, and horizontal pressure platform 34 in nominal configurations including nominal life-size holes, directions, and surface geometry. For example structure 24, the measurement of said model must identify the five conjugated surfaces 56, 60, 62, 66 and 67, as shown in figure 2. The measurement of said models can contain a measurement point for each central point of real size hole and point of adjacent conjugated surfaces with marking.
    [0016] The computer system may include a measurement software platform. The measurement software platform can be any appropriate type that includes programs that help to make and process measurements. An example measurement software platform can be a spatial analyzer 98. The spatial analyzer 98 can link the three-dimensional (3D) measurement of said models. For each reinforcement beam 28 to the joint locations of the cross beam 28, the space analyzer 98 guides the operator through a measurement plane to obtain the collected model measurements, consistent with certain measurement practices, defined as follows.
    Petition 870180003827, of 01/16/2018, p. 76/115 / 28 [0017] For each of the joint locations, and each gasket or splice part, the space analyzer 98 operates to guide the operator through the measurements and process, when necessary, resulting in the transformation of the coordinate system to from the CMM coordinate system, as mounted, to the collected 3D NC model for a nominal aircraft coordinate system for each top splice part, bottom display part or other component. The flatness profile tolerances for all of the conjugated surfaces of the example structure is 0.254 mm (0.010 inch), thus compromising the tolerance requirements of the total system. To compensate for this potential error without changing the current flatness requirements, the spatial analyzer 98 can restrict all values of measured conjugate surfaces to be located within, or between, the respective derived reference conjugate surface plane and the nominal conjugate surface of the same part as built measure. For example, as shown in figure 6A, the surface shown is a better fit of the measured exaggerated surface profile. The same surface must be moved along the normal plane, as shown in figure 6B; thus, all peaks are within or below the derived surface. Surface measurements must include at least one measurement at each fixer location across the entire matched surface.
    [0018] For each of the upper junction pieces 30, the spatial analyzer 98 must derive the plane of conjugated surfaces for the upper seam part, thus representing the translation alignment transformation components along the Z axis, rotation in around the geometric axis X, and rotation around the geometric axis Y. In this example structure 24, since the reinforcement beam surface makes an angle of 7.8923 degrees with respect to an XY plane of the aircraft, rotated around of the aircraft geometric axis X, a transformation is included as multipliers over the measured values along Y, Z, V, and W.
    Petition 870180003827, of 01/16/2018, p. 77/115 / 28 example, a rotation φ of the reinforcement beam surface around a geometric axis that lies on the nominal surface plane and parallel to the aircraft's YZ plane, represents component rotations of φV around Y and φW around Z, as shown in figure 7.
    [0019] After creating the alignment transform of the upper splice part, the space analyzer 98 can guide the operator to measure the remaining hole points of the reinforcement beam 26 and cross beam. After performing the alignment transformation of the lower display part, the space analyzer 98 can guide the operator to measure the remaining measurements of the lower display part. After all of the measuring points have been obtained and validated within acceptable tolerances of deviation and scale, the spatial analyzer 98 must identify mating surfaces for paving and / or potential spacing for the connections of the upper splice part 30 to the reinforcement beam 26 and transverse beam 28. Once the potential shim and spacer surfaces of the upper seam have been measured and designed, the space analyzer 98 must determine its geometry. Depending on the reference orthogonality, as mounted, of the lower display part 32, the geometry requirements of the lower display part may need to include sample measurements of the connection as mounted to determine the total shim thickness.
    [0020] Then, the space analyzer 98 must determine the geometry of the shim for the conjugated surfaces of the top line 56 and the conjugated surfaces of the waterline 62. For each shim 69, each upper seam part measurement set 30, and each lower display part 32, the spatial analyzer generates a corresponding XML measurement file incorporating the processed measurements that comply with the requirements of the ODEM format.
    [0021] As illustrated in figure 1, computer system 86 provides measurements processed in .XML format for the manufacturing service
    Petition 870180003827, of 01/16/2018, p. 78/115 / 28 emerging on request (ODEM) 88. The ODEM 88 service generates and then validates network computer (NC) 89 programs to drill life-size holes, machine all connections, and manufacture all shims and spacers necessary, when provided with .XML measurement files, compatible formatted, and models collected from NC. Each hole to be drilled will have an XYZ point to be drilled and an associated plane, which determine the orientation of the hole to be drilled. The ODEM 88 service also monitors the state of manufacture of the drilled or machined part. The ODEM 88 service also transfers programs from network computers to a server 102 at an emerging operations machine shopping station 100. Server 102 includes configuration files 104 that reflect the allowable tolerances for drilled holes and shims and the provisions of quality assurance, by product definition data, together with measurement plans, index plans, and installation plans. The emerging operations machine 100 also includes a 5-axis milling machine by computer numerical control (CNC) 106, or equivalent. CNC machine 106 includes a network computer controller 108 that receives programs from CN 89. System 20 makes measurements, processes measurements according to the application document in an .XML format. The ODEM 88 service then updates the NC collection model with the data formatted in. XML, and then automatically creates the required CN 89 program.
    [0022] The 5-axis CNC machine 106 drills the holes in the workpiece 21 and mills by thinning the shims based on the CN 89 programs. As illustrated in figures 8 and 9, the trim or workpiece 21 can be secured to a clamping device 110 or 112. Specifically, once when each workpiece 21 has been indexed in its respective clamping device 110 or 112, workpiece 21 must be placed on a base 114 of the clamping device 110 or 112 and fixed by fasteners 116 in the
    Petition 870180003827, of 01/16/2018, p. 79/115 / 28 place with sufficient clamping forces to ensure that the workpiece does not move in relation to its clamping device during machining operations. Figure 10 shows the CNC machine 106 drilling the holes in a workpiece clamp 21 on the clamping device 110 based on the CN 89 programs.
    [0023] Method 200 of fixation is illustrated in figure 12. In step
    201, the cross beam 28 and reinforcement beam 26 are made with the pre-drilled holes 50, 52 in their previously drilled locations. So, in the step
    202, the upper splice part 30 is made without pre-drilled holes, but with a nominal predefined location indicating approximately where the actual size holes can be drilled later. In step 204, the cross beam 28 and the reinforcement beam 26 are placed together and positioned in a manner similar to that of the final assembly of the structure
    24. Then, in step 206, the crossbeam 28 and reinforcement beam 26 are locked together so that the beams have negligible freedom of movement in relation to each other. This can be done in the fuselage 36, as shown in figure 5. Alternatively, the cross beam 28 and reinforcement beam 26 can be mounted in a support box 118 that simulates the portion of the pressure platform on which the cross beam and the reinforcement beam would be assembled, as shown in figure 11.
    [0024] In step 208, the location and orientation of the pre-drilled holes 50, in the cross beam 28 and in the reinforcement beam 26 are then measured within a single geometric reference frame, so that the relative location of the pre-drilled holes perforated 50 in the cross beam 28 is measured with respect to the location of the pre-drilled holes 52 in the reinforcement beam 26. This step can use the space analyzer 98 to guide the operator on what to measure. The measurement is performed by an operator operating the ROMER 84 arm machine with the space analyzer 98 guiding the operator on what to measure. In particular, an operator positions the measuring robotic arm 90 of the arm machine
    Petition 870180003827, of 01/16/2018, p. 80/115 / 28
    ROMER 84 over each drilled hole of the reinforcement beam 26 and cross beam 28, so that the arm machine ROMER 84 makes a measurement of each drilled hole.
    [0025] The measurements include the values measured along the geometric axes X, Y, Z and the geometric axes of rotation U, V, and W. For example, the rotation φ of the reinforcement beam surface around a geometric axis which is in the nominal surface plane and parallel to the aircraft's YZ plane, represents component rotations of φV around Y and φW around Z, as shown in figure 7. As shown in figure 5, the ROMER arm machine 84 can be slidably mounted on rail 92 in order to take measurements of the drilled holes when the ROMER 84 arm machine slides along rail 92. In step 210, a determination is made as to whether shims 69 are required.
    [0026] The computer system 86 then processes the measurements to determine the relative location of the drilled holes 64T, 64S in the upper splice part 30. In particular, the computer system 86 determines the relative location of the drilled holes 50 in the cross beam 28 with respect to the measured location of the pre-drilled holes 52 in the reinforcement beam 26, in step 212. Then, in step 214, the computer system 86 determines the relative location of the holes 64S to be drilled in the upper splice part 30, that correspond to the pre-drilled holes 52 in the reinforcement beam 26 by translating the measured pre-drilled hole locations 52 in the reinforcement beam 26 to the hole locations in the upper seam 30. This translation can be a better fit to the corresponding predetermined nominal hole locations in the upper splice part 30, using a least squares method or other appropriate method.
    [0027] Then, in step 216, the computer system 86 determines the location of the holes to be drilled in the upper seam part 30 that correspond to pre-drilled holes 50 in the cross beam 28 for transfer.
    Petition 870180003827, of 01/16/2018, p. 81/115 / 28 the measured locations of the pre-drilled holes 50 in the cross beam 28 to the relative location of holes 50 in the cross beam 28 in relation to the measured location of pre-drilled holes 52 in the reinforcement beam 26. The computer system 86 transfers the measured hole locations from the reinforcement beam 26 to the relative locations on the transverse beam 28, implementing a reference sequence that forces the residual measurement error onto the mating surfaces that also include shims.
    [0028] In step 218, the measurement data set is sent to the ODEM 88 service and converted to the CN 89 machine program. Specifically, the CN 89 program is created and validated to drill 64S actual size holes, 64T in the upper splice part 30 to substantially align with the measured location and orientation of the corresponding pre-drilled holes 52, 50 in the reinforcement beam 26 and in the cross beam 28. The CN 89 program is then sent to the CNC machine 106. The upper splice part 30 is indexed to a fixture 110 (figure 8), and then held in place with sufficient clamping forces to ensure that the upper splice part 30 does not move with respect to the fixture 110 during drilling or other machining operations. Then, in step 220, actual size holes 64S, 64T are drilled in the top seam 30 using CNC machine 106 according to the CN 89 program. This step 220 also includes installing any required fabricated shims with size holes corresponding. In step 222, the upper splice part 30 is then positioned on the conjugated surface 66, 67 of the cross beam 28 and reinforcement beam 26. In step 224, the drilled holes 64S, 64T in the upper splice part 30 are then aligned with the pre-drilled holes 52, 50 in the reinforcement beam 26 and in the cross beam 28. In step 226, any required shims 69 are machined and installed in the structural components.
    [0029] In step 228, the fasteners 68 are inserted through the holes
    Petition 870180003827, of 01/16/2018, p. 82/115 / 28 aligned 64S, 52 of the upper splice part 30 and the reinforcement beam 26, and fasteners 68 are also inserted through the aligned holes 64T, 50 of the upper splice part 30 and the cross beam 28. This step also includes attaching fasteners 68 to their respective structural components. In step 230, steps 201 to 228 are repeated to fix the lower fixing part 32 to the crossbeam and reinforcement beam 26, 28. In this step, the lower fixing part can be mounted on the fixture 112 shown in figure 9 This step also includes drilling holes 61 in the pressure platform 34, measuring the location and orientation of the holes 61 in the pressure platform 34, determining the location of the holes 72 of the lower display part 32 that correspond to the holes 61 in the pressure platform 34, creating the CN 89 program to drill holes 72 in the lower display part 32 that correspond to holes 61 in the pressure platform 34, drilling holes 72 in the lower display part 32 that correspond to holes 61 in the pressure platform 34 , and then aligning, inserting, and securing the fasteners 68 in the holes 72 in the lower attachment part 34, which correspond to the holes 61 in the pressure platform 34.
    [0030] In an example structure 24, twelve holes are drilled having a diameter of approximately 1.11 cm (7/16 ”) through the upper joint pieces 30 made of titanium. Twenty-two holes are drilled with a diameter of approximately 0.96 cm (3/8 ”) through the four short bottom display parts of titanium 32. Twenty-five holes are drilled with a diameter of approximately 0.96 cm (3/8”) ”) Through the four long lower titanium 32 display parts. A thinner shim 69 including oversized 1.11 cm (7/16”) holes is machined, when necessary, for each of the top 30 joint pieces. One thinned shim 69 including oversized 0.96 cm (3/8 ”) holes is machined, when necessary, for each of the eight lower display parts 32. The moment the machined connections or fittings are installed, the
    Petition 870180003827, of 01/16/2018, p. 83/115 / 28 relative translation between any reinforcement beam life size hole and any cross beam life size hole, from an instant when CMM measurements were made, should not exceed 0.00127 cm (0, 0005 inches) on any geometry axis. The moment the machined connections or fittings are installed, the relative angle between the reinforcement beam normal to the upper seam surface and the beam transverse to normal to the upper seam surface, from an instant when the measurements of CMM were made, it should not exceed 0.02 degrees. Each hole in each workpiece must be checked for diameter, roundness, burr, and adjustment. Each shim is checked for functional fit to a plane.
    [0031] System 20 and method for joining structural components by drilling and fixing fasteners to structural components can be used for other structures, such as, for example, support linings or T-clips. The system and method described for joining components structural by drilling and fixing fasteners to structural components provides several advantages. First, since the holes are drilled at a location away from the aircraft, no time-consuming drilling or cleaning of the debris created by the drilling is carried out when attaching structural components to the aircraft. Also, the holes are drilled on a platform that is more stable than the aircraft, thus resulting in a lower percentage of oversized holes and associated production waste. In addition, the ergonomic risk factors that result from operators drilling holes in the main junction areas associated with the main structural components around the perimeter of the fuselage and / or in an aircraft's wing box cavity are eliminated. In addition, this method can be used in areas where the confined volume does not allow sufficient space for the use of manual drilling equipment.
    Petition 870180003827, of 01/16/2018, p. 84/115 / 28 [0032] Examples of the invention can be described in the context of an aircraft manufacturing and service method 400, as shown in figure 13, and an aircraft 402, as shown in figure 14. During pre-production, The aircraft manufacturing and service method 400 may include specification and design 404 of aircraft 402 and material acquisition 406. During production, manufacture of components / subassemblies 408 and systems integration 410 of aircraft 402 take place. Thereafter, aircraft 402 may pass through certification and delivery 412 in order to be placed in service 414. While in service by a customer, aircraft 402 is scheduled for routine maintenance and service 416, which may also include modification, reconfiguration , remodeling and the like.
    [0033] Each of the 400 method processes can be performed or executed by a systems integrator, a third party, and / or an operator (for example, a customer). For the purposes of this description, a system integrator may include, without limitation, any number of aircraft manufacturers and subcontractors for the main systems; a third party may include, without limitation, any number of vendors, subcontractors, and suppliers; and an operator can be an air transport company, rental company, military organization, service organization, and others.
    [0034] As shown in figure 14, aircraft 402 produced by example method 400 may include a fuselage 418 with a plurality of systems 420 and an interior 422. Examples of the plurality of systems 420 may include one or more of a propulsion system 424, an electrical system 426, a hydraulic system 428, and an environmental system 430. Any number of other systems can be included.
    [0035] The system described for joining structural components by drilling and fixing fasteners to structural components can be used during any one or more of the stages of the method of
    Petition 870180003827, of 01/16/2018, p. 85/115 / 28 aircraft manufacturing and service 400. As an example, the system described for joining structural components by drilling and fixing fasteners to structural components can be used during the acquisition of material 406. As another example, corresponding components or subassemblies the manufacture of components / subassemblies 408, systems integration 410, and / or maintenance and service 416 can be produced or manufactured using the described fixation system. As another example, the fuselage 418 and / or the interior 422 can be produced using the mechanical fluid impermeable fixing system described. Also, one or more device examples, method examples, or a combination thereof can be used during the manufacture of components / subassemblies 408 and / or systems integration 410, for example, by substantially speeding up assembly or reducing the cost of an aircraft 402, such as the fuselage 418 and / or the interior 422. Similarly, one or more of system examples, method examples, or a combination thereof can be used while aircraft 402 is in service, for example, and without limitation, in maintenance and service 416.
    [0036] The system described for joining structural components by drilling and fixing fasteners to structural components is described in the context of an aircraft; however, a person of ordinary skill in the art will readily recognize that the system described for joining structural components by drilling and fixing fasteners to structural components can be used for a variety of vehicles, as well as for non-vehicle applications. For example, implementations of the modalities described here can be implemented on any type of vehicle, including, for example, helicopters, passenger ships, automobiles and the like.
    [0037] Additionally, the invention comprises modalities according to the following clauses:
    Clause 1. Method comprising:
    Petition 870180003827, of 01/16/2018, p. 86/115 / 28 produce a first structure with a first plurality of pre-drilled holes in predefined locations;
    producing a second structure with a second plurality of pre-drilled holes at predefined locations;
    produce a third structure without pre-drilled actual size holes;
    measure the location and orientation of the first and second pluralities of pre-drilled holes in the first and second structures;
    determining the location of a third plurality of holes to be drilled in the third structure that correspond to the first and second pluralities of pre-drilled holes measured in the first and second structures;
    create a program to drill the third plurality of holes in the third structure that align with the measured location and orientation of the first and second pluralities of pre-drilled holes in the first and second structures based on the measured location and orientation of the first and second pluralities of pre-drilled holes in the first and second structures;
    drill the third plurality of holes in the third structure based on the program;
    positioning the third structure on the first and second structures so that the third plurality of holes in the third structure is aligned with the first and second pluralities of pre-drilled holes in the first and second structures; and insert fasteners through the third plurality of holes in the third structure and the first and second pluralities of pre-drilled holes in the first and second structures which are aligned with the third plurality of holes in the third structure to secure the second structure to the first structure using the third structure.
    Petition 870180003827, of 01/16/2018, p. 87/115 / 28
    Clause 2. Method according to clause 1, additionally comprising positioning the first and second structures together in a position that resembles a final assembly of the first and second structures before measuring the location and orientation of the first and second pluralities of pre-drilled holes in the first and second structures.
    Clause 3. Method according to clause 2, in which measuring the location and orientation of the first and second pluralities of pre-drilled holes in the first and second structures is carried out within a single geometric frame of reference so that the relative location of the second plurality of pre-drilled holes is determined with respect to the measured location of the first plurality of pre-drilled holes.
    Clause 4. Method according to clause 3, in which determining the location of the holes to be drilled in the third structure that correspond to the first plurality of holes measured in the first structure comprises translating the first measured plurality from pre-drilled hole locations to hole locations in the third structure.
    Clause 5. Method according to clause 4, in which determining the location of the holes to be drilled in the third structure that correspond to the second plurality of holes measured in the second structure comprises determining the location of the holes to be drilled in the third structure that correspond to the second plurality of pre-drilled holes in the second structure by transferring the measured locations of the second plurality of pre-drilled holes to the relative location of the second plurality of pre-drilled holes in relation to the measured location of the first plurality of pre-drilled holes.
    Clause 6. Method according to clause 5, additionally comprising locking the first and second structures together so that the first structure and the second structure have
    Petition 870180003827, of 01/16/2018, p. 88/115 / 28 negligible freedom of movement in relation to each other before or during the measurement of the location and orientation of the first plurality of pre-drilled holes in the first structure.
    Clause 7. Method according to clause 6, in which translating the first measured plurality of pre-drilled hole locations to hole locations in the third structure is performed using a least squares method.
    Clause 8. Method according to clause 5, additionally comprising the steps of securing a stable platform having an adjacent rail first and second structures, slidably mount a measuring machine to the rail so that the measuring machine is slidable to make measurements of selected areas in the structures, and determine whether repeated measurements of the structures are within a permissible predetermined margin of error to verify that the measuring machine is sufficiently robust to make measurements, on which measuring machine is used to carry out the measurement step measure the location and orientation of the first and second pluralities of pre-drilled holes in the first and second structures.
    Clause 9. Method according to clause 8, in which the first structure comprises a reinforcement beam, in which the second structure comprises a transverse beam, where the third structure comprises a splice part, and the step of locking the first and the second structure together comprises securing the reinforcement beam and cross beam in a fuselage, before the step of measuring the location and orientation of the first and second pluralities of pre-drilled holes in each of said first structure and second structure.
    Clause 10. Method comprising:
    produce a first structure with first pre-drilled holes in pre-defined locations;
    Petition 870180003827, of 01/16/2018, p. 89/115 / 28 produce a second structure without pre-drilled actual size holes;
    measure the location and orientation of the first pre-drilled holes in the first structure;
    determining the location of second holes to be drilled in the second structure that correspond to the first holes measured in the first structure;
    create a program to drill the second holes in the second structure that align with the measured location and orientation of the first pre-drilled holes in the first structure based on the measured location and orientation of the first pre-drilled holes in the first structure;
    drill the second holes in the second structure based on the program;
    positioning the second structure on the first structure so that the second holes in the second structure are aligned with the first pre-drilled holes in the first structure; and inserting fasteners through the first and second aligned holes of the first and second frames to secure the second frame to the first frame.
    Clause 11. System for attaching a first structure to a second structure comprising:
    a measuring machine, wherein said measuring machine is configured to take measurements of the location and orientation of a first plurality of pre-drilled holes in said first structure and a second plurality of pre-drilled holes in said second structure;
    a measurement program, wherein said measurement program is configured to execute a measurement plan for said measuring machine to make measurements of the location and orientation of said first plurality of pre-drilled holes in said first structure and said second
    Petition 870180003827, of 01/16/2018, p. 90/115 / 28 plurality of pre-drilled holes in said second structure;
    at least one processor for processing the measurement of said first plurality of pre-drilled holes in said first structure and said second plurality of pre-drilled holes in said second structure;
    an ODEM station, wherein said ODEM station is configured to generate a CN program for drilling holes in said third structure based on the processed measurements of said first plurality of pre-drilled holes in said first structure and said second plurality of holes in said second structure;
    a CNC machine, in which said CNC machine is configured to drill holes in said third structure based on said CN program; and a plurality of fasteners, wherein said fasteners are inserted into said drilled holes of said third structure and said first and second pluralities of said pre-drilled holes in said first and second structures which are aligned with said drilled holes of said third structure for securing said first structure to said second structure.
    Clause 12. System according to clause 11, in which said measuring machine comprises a coordinate measuring machine, in which said coordinate measuring machine is configured to measure said first structure in a 3D coordinate system.
    Clause 13. System according to clause 12, in which said coordinate measuring machine comprises a ROMER arm machine, in which said ROMER arm machine comprises an arm configured to move around the three perpendicular geometric axes, and in that the measurement program is configured to use a measurement model that includes measurement points for each pre-drilled hole and points of adjacent mating surfaces for one of said first structure and said second structure.
    Petition 870180003827, of 01/16/2018, p. 91/115 / 28
    Clause 14. System according to clause 13, additionally comprising a stable platform having a rail, being positioned adjacent to the first and second structures, in which said ROMER arm machine is slidably mounted on the rail and movable along said rail to make measurements of selected areas of said first and second structures, and the ROMER arm machine is configured to obtain repeated measurements of the structure which are compared to ensure that the ROMER arm machine is robust enough to make measurements of the location and orientation of said first plurality of pre-drilled holes in said first structure and said second plurality of pre-drilled holes in said second structure.
    Clause 15. System according to clause 11, in which said measurement program comprises a spatial analyzer, in which said processor processes measurements in an .XML format.
    Clause 16. System according to clause 11, comprising a fixing device, in which said third structure is fixed to said fixing device when said CNC machine drills holes in said third structure.
    Clause 17. System according to clause 11, in which said ODEM station is configured to validate said NC program.
    Clause 18. Structural assembly for an aircraft, comprising:
    a reinforcement beam, wherein said reinforcement beam comprises a first plurality of pre-drilled holes;
    a cross beam, wherein said cross beam comprises a second plurality of pre-drilled holes;
    a splice part, in which said reinforcement beam is joined to said transverse beam by said splice part, in which said splice part comprises holes drilled by a CNC machine, in which the place of
    Petition 870180003827, of 01/16/2018, p. 92/115 / 28 said drilled holes of said splice part are based on the measured locations and orientation of said first plurality of pre-drilled holes of said reinforcement beam and said second plurality of pre-drilled holes of said cross beam;
    fasteners, in which a first plurality of said fasteners is inserted into aligned holes of said first plurality of pre-drilled holes of said reinforcement beam and a first group of said drilled holes of said seam part, in which a second plurality of fasteners is inserted in aligned holes of said second plurality of pre-drilled holes of said cross beam and a second group of said drilled holes of said seam part.
    Clause 19. Structural assembly according to clause 18, wherein said reinforcement beam comprises a third plurality of pre-drilled holes, wherein said cross beam comprises a fourth plurality of pre-drilled holes, wherein said structural assembly comprises a affixing part attached to said reinforcement beam and said transverse beam, wherein said affixing part comprises holes drilled by a CNC machine, in which the location of said drilled holes of said affixing part are based on the measured locations and orientation of said third plurality of pre-drilled holes of said reinforcement beam and said fourth plurality of pre-drilled holes of said cross beam, wherein a third plurality of said fasteners is inserted into aligned holes of said third plurality of pre-drilled holes of said reinforcement beam and a fourth plurality of said drilled holes of said display part, wherein a fourth plurality of f fixers are inserted into aligned holes of said fourth plurality of pre-drilled holes of said cross beam and a fifth plurality of said holes drilled from said attachment part.
    Clause 20. Structural assembly according to clause 18. additionally comprising a block, in which said transverse beam is
    Petition 870180003827, of 01/16/2018, p. 93/115 / 28 sidewalk by said block.
    [0038] Although various modalities of the system for joining structural components by drilling and fixing fasteners to structural components have been shown and described, modifications can occur for those specialized in the technique of reading the description. The present application includes such modifications and is limited only by the scope of the claims.
    权利要求:
    Claims (15)
    [1]
    1. Method, characterized by the fact that it comprises: producing a first structure (26) with a first plurality of pre-drilled holes (52) in predefined locations;
    producing a second structure (28) with a second plurality of pre-drilled holes (50) at predefined locations;
    producing a third structure (30) without pre-drilled full-size holes;
    measure the location and orientation of the first and second pluralities of pre-drilled holes in the first and second structures;
    determining the location of a third plurality of holes (64T, 64S) to be drilled in the third structure that correspond to the first and second pluralities of pre-drilled holes measured in the first and second structures;
    create a program (89) to drill the third plurality of holes (64T, 64S) in the third structure (30) which align with the measured location and orientation of the first and second plurality of pre-drilled holes in the first and second structures based on the location and measured orientation of the first and second pluralities of pre-drilled holes in the first and second structures;
    drill the third plurality of holes (64T, 64S) in the third structure (30) based on the program;
    positioning the third structure (30) on the first and second structures (26, 28) so that the third plurality of holes in the third structure is aligned with the first and second pluralities of pre-drilled holes in the first and second structures; and inserting fasteners (68) through the third plurality of holes in the third structure and the first and second pluralities of pre-drilled holes in the first and second structures which are aligned with the third
    Petition 870180003827, of 01/16/2018, p. 95/115
    [2]
    2. Method according to claim 1, characterized by the fact that it additionally comprises positioning the first and second structures together in a position that resembles a final assembly of the first and second structures before measuring the location and orientation of the first and second pluralities of pre-drilled holes in the first and second structures.
    2/7 plurality of holes in the third frame for attaching the second frame to the first frame using the third frame.
    [3]
    3/7 fact that it additionally comprises locking the first and second structures together so that the first structure and the second structure have negligible freedom of movement in relation to each other before or during the measurement of the location and orientation of the first plurality of pre-drilled holes in the first structure.
    3. Method according to claim 2, characterized by the fact that measuring the location and orientation of the first and second pluralities of pre-drilled holes in the first and second structures is carried out within a single geometric frame of reference so that the location relative to the second plurality of pre-drilled holes is determined with respect to the measured location of the first plurality of pre-drilled holes.
    [4]
    4/7 of claims 1 to 9, for attaching a first structure to a second structure, characterized by the fact that the system comprises:
    a measuring machine (84), wherein said measuring machine is configured to make measurements of the location and orientation of a first plurality of pre-drilled holes (52) in said first structure (26) and a second plurality of pre-drilled holes perforated (50) in said second structure (28);
    a measurement program, wherein said measurement step includes using the measurement program configured to execute a measurement plan for said measuring machine (84) to make measurements of the location and orientation of said first plurality of pre-drilled holes in said first structure and said second plurality of pre-drilled holes in said second structure;
    at least one processor for processing measurements to determine the locations of said first plurality of pre-drilled holes in said first structure and said second plurality of pre-drilled holes in said second structure;
    an ODEM station, wherein said ODEM station is configured to generate a CN program (89) for drilling holes (64T, 64S) in said third structure (30) based on the processed measurements of said first plurality of pre-drilled holes in said first structure and said second plurality of holes in said second structure;
    a CNC machine, in which said CNC machine is configured to drill holes (64T, 64S) in said third structure (30) based on said CN program (89); and a plurality of fasteners (68), wherein said fasteners are inserted into said drilled holes (64T, 64S) of said third structure (30) and said first and second plurality of said pre-drilled holes in said first and second structures that are aligned with said drilled holes of said third structure to fix said first structure to said second
    Petition 870180003827, of 01/16/2018, p. 98/115 structure.
    Method according to claim 3, characterized in that determining the location of the holes to be drilled in the third structure that correspond to the first plurality of holes measured in the first structure comprises translating the first measured plurality of pre-drilled hole locations for hole locations in the third frame.
    [5]
    Method according to claim 4, characterized in that determining the location of the holes to be drilled in the third structure that correspond to the second plurality of holes measured in the second structure comprises determining the location of the holes to be drilled in the third structure that correspond to the second plurality of pre-drilled holes in the second structure by transferring the measured locations of the second plurality of pre-drilled holes to the relative location of the second plurality of pre-drilled holes in relation to the measured location of the first plurality of pre-drilled holes .
    [6]
    6. Method according to claim 5, characterized by the
    Petition 870180003827, of 01/16/2018, p. 96/115
    [7]
    Method according to claim 6, characterized by the fact that translating the first measured plurality of pre-drilled hole locations to hole locations in the third structure is carried out using a least squares method.
    [8]
    Method according to any of claims 5 to 7, characterized in that it comprises the steps of securing a stable platform (85) having a track (92) adjacent to the first and second structures, slidably assemble a measuring machine (84) to the rail so that the measuring machine is slidable to take measurements of selected areas on the structures, and to determine whether the repeated measurements of the structures are within an allowable predetermined margin of error to verify that the measuring machine is sufficiently robust for making measurements, where the measuring machine is used to carry out the step of measuring the location and orientation of the first and second pluralities of pre-drilled holes in the first and second structures.
    [9]
    Method according to claim 8, characterized in that the first structure comprises a reinforcement beam (26), in which the second structure comprises a transverse beam (28), in which the third structure comprises a splice part (30), and the step of locking the first and second structures together comprises attaching the reinforcement beam and cross beam to a fuselage, before the step of measuring the location and orientation of the first and second pluralities of pre-drilled holes in each of said first structure and second structure.
    [10]
    10. System to perform the method as defined in any
    Petition 870180003827, of 01/16/2018, p. 97/115
    [11]
    System according to claim 10, characterized in that said measuring machine comprises a coordinate measuring machine (84), in which said coordinate measuring machine is configured to measure said first structure in a coordinate system of 3D.
    [12]
    System according to claim 11, characterized in that said coordinate measuring machine (84) comprises a ROMER arm machine, in which said ROMER arm machine comprises an arm configured to move around the three axes perpendicular geometries, and where the measurement program is configured to use a measurement model that includes measurement points for each pre-drilled hole and points of adjacent combined surfaces for one of said first structure and said second structure.
    [13]
    13. System according to claim 12, characterized in that it additionally comprises a stable platform (85) having a track (92), being positioned adjacent to the first and second structures, in which said ROMER arm machine is slidably mounted on the rail and movable along said rail to make measurements of selected areas of said first and second structures, and the ROMER arm machine is configured to obtain repeated measurements of the structure that are compared to ensure that the ROMER arm machine is robust enough to making measurements of the location and orientation of said first plurality of pre-drilled holes in said first structure and said second plurality of pre-drilled holes in said second structure.
    [14]
    14. Structural set for an aircraft, characterized by the fact that it comprises:
    a reinforcement beam (26), wherein said reinforcement beam comprises a first plurality of pre-drilled holes (52);
    Petition 870180003827, of 01/16/2018, p. 99/115 a cross beam (28), wherein said cross beam comprises a second plurality of pre-drilled holes (50);
    a splice part (30), in which said reinforcement beam is joined to said transverse beam by said splice part, in which said splice part comprises holes (64T, 64S) drilled by a CNC machine, in which the location of said drilled holes of said seam part are based on the measured locations and orientation of said first plurality of pre-drilled holes of said reinforcement beam and said second plurality of pre-drilled holes of said cross beam;
    fasteners (68), wherein a first plurality of said fasteners is inserted into aligned holes of said first plurality of pre-drilled holes (52) of said reinforcement beam (26) and a first group of said drilled holes (64S) of said splice part, wherein a second plurality of fasteners is inserted into aligned holes of said second plurality of pre-drilled holes (50) of said cross beam (28) and a second group of said drilled holes (64T) of said part splicing (30).
    [15]
    Structural assembly according to claim 14, characterized in that said reinforcement beam comprises a third plurality of pre-drilled holes, wherein said transverse beam comprises a fourth plurality of pre-drilled holes, in which said structural assembly comprises an affixing part attached to said reinforcement beam and said transverse beam, wherein said affixing part comprises holes drilled by a CNC machine, wherein the location of said drilled holes of said affixing part are based on the locations and measured orientation of said third plurality of pre-drilled holes of said reinforcement beam and said fourth plurality of pre-drilled holes of said cross beam, wherein a third plurality of said fasteners is inserted into aligned holes of said third plurality of pre-holes -perforated of said reinforcement beam and a fourth plurality of said perforated holes of said
    Petition 870180003827, of 01/16/2018, p. 100/115 display part, wherein a fourth plurality of fasteners is inserted into aligned holes of said fourth plurality of pre-drilled holes of said cross beam and a fifth plurality of said drilled holes of said display part.
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    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    US5898590A|1996-08-21|1999-04-27|The Boeing Company|Method and apparatus for numerically controlled pattern determination|
    GB0008302D0|2000-04-06|2000-05-24|British Aerospace|Assembly method|
    US6931294B2|2002-10-08|2005-08-16|The Boeing Company|Method for generating three-dimensional CAD models of complex products or systems|
    GB0309662D0|2003-04-28|2003-06-04|Crampton Stephen|Robot CMM arm|
    US8733707B2|2008-04-17|2014-05-27|The Boeing Company|Line transfer system for airplane|
    AU2009240105B2|2008-04-22|2011-12-22|Leica Geosystems Ag|Measuring method for an articulated-arm coordinate measuring machine|
    US8010226B2|2008-12-19|2011-08-30|The Boeing Company|Apparatus and method for measuring and modifying components using reverse engineering|
    US20110119919A1|2009-11-23|2011-05-26|The Boeing Company|Determinant Assembly System for Manufacturing Objects|
    US8756792B2|2011-06-08|2014-06-24|The Boeing Company|Digitally designed shims for joining parts of an assembly|
    US8960606B2|2012-10-31|2015-02-24|The Boeing Company|Circumference splice for joining shell structures|
    US9958854B2|2013-06-10|2018-05-01|The Boeing Company|Systems and methods for robotic measurement of parts|
    US9586667B2|2014-12-02|2017-03-07|The Boeing Company|Splice assembly for joining structural components|
    US9952580B2|2016-01-29|2018-04-24|The Boeing Company|Method and an apparatus for machining a part for an assembly|US10807662B2|2017-11-20|2020-10-20|Ford Global Technologies, Llc|Method of producing a cross car beam utilizing net, form and pierce technology|
    JP6663414B2|2017-11-29|2020-03-11|株式会社Ｓｕｂａｒｕ|Manufacturing method and manufacturing apparatus|
    FR3094255A1|2019-03-27|2020-10-02|Airbus Operations|structural parts assembly process|
    US10783659B1|2019-06-28|2020-09-22|The Boeing Company|Hole location targets and measurement systems, and methods for measuring a location of a hole|
    US11017559B2|2019-06-28|2021-05-25|The Boeing Company|Hole location targets and measurement systems, and methods for measuring a location of a hole|
    US11248896B2|2019-06-28|2022-02-15|The Boeing Company|Hole location targets and measurement systems, and methods for measuring a location of a hole|
    US10989671B2|2019-09-16|2021-04-27|The Boeing Company|Method and system for determining alignment and orientation of a target|
    US11170495B2|2019-10-21|2021-11-09|The Boeing Company|Scanning apparatus and method of scanning|
    JP2021074829A|2019-11-11|2021-05-20|株式会社Ｓｕｂａｒｕ|Assembling device|
    FR3103790A1|2019-11-29|2021-06-04|Airbus|ARRANGEMENT OF ROBOTS TO WORK ON AN AIRCRAFT STRUCTURE|
    EP3922567A4|2020-06-11|2021-12-15|Airbus Sas|Method for joining two pieces|
    法律状态:
    2019-02-19| B03A| Publication of a patent application or of a certificate of addition of invention [chapter 3.1 patent gazette]|
    优先权:
    申请号 | 申请日 | 专利标题
    US15/415,172|2017-01-25|
    US15/415,172|US10934020B2|2017-01-25|2017-01-25|Method and system for joining structures|
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