Methods and equipment for machining structural components of aircraft.

Abstract

This invention relates to a method for machining structural components (2) of aircraft vehicles using a machining equipment (1), wherein the machining equipment (1) has a drilling unit (3a) and a riveting unit (3b), wherein a manufacturing process control unit (9) is provided for controlling the components of the machining equipment (1), wherein the manufacturing process control unit (9) processes a series of drilling processes by means of the drilling unit (3a) and a series of riveting processes by means of the riveting unit (3b) according to manufacturing rules (10) using tool control data (9a), wherein the machining equipment (1) has an optical sensor (12) and a projection unit (13), wherein the method includes the following steps: • Projecting a pattern (2) using the projection unit (13) M) is projected onto the processing part (B), which has a riveting element (4) inserted into the drill hole (11) of the processing part (B); - The processing part (B) including the projection of the pattern (M) is detected by the sensor (12), and corresponding detection data (14) is generated by the sensor (12); - The detection data (14) is analyzed by the analysis unit (15); - The manufacturing process control unit (9) adapts the tool control data (9a) to the drill hole (11) to be drilled according to the manufacturing rule (10) at another processing part (B1) based on the analysis of the detection data (14), especially adapting the sinking depth (T) of the drill hole (11) to be drilled.

Description

Technical Field

[0001] The present invention relates to a method for machining structural components of aircraft according to the present invention, and a machining equipment for machining structural components of aircraft according to the present invention. Background Technology

[0002] Various processing equipment for aircraft structural components are known from existing technology. The so-called drilling and riveting machine also falls into this category, as it enables drilling and riveting of aircraft structural components.

[0003] Typically, such machining equipment has an end effector with a drilling unit and a riveting unit, which perform a series of drilling and riveting processes according to manufacturing rules when machining structural components of aircraft.

[0004] The aircraft manufacturing industry places particularly high demands on riveted joints. Therefore, the drilled holes and the riveting elements inserted into them must be precisely matched to meet narrow tolerance requirements. Riveting elements are typically not allowed to have a head protrusion, or only a very small head protrusion is permitted. The head of the riveting element is thus allowed to protrude very little relative to the surface of the aircraft structural component.

[0005] If the head protrudes too much, the riveting element must be drilled out and replaced with a new one. This is usually done manually after machining with equipment. This finishing process is very costly and labor-intensive.

[0006] To reduce the number of riveted joints requiring finishing at structural components of aircraft, the drill hole is typically measured after drilling, with particular emphasis on checking the depth of the drill hole. For example, DE 10 2014 108 629 A1 describes the use of a measuring gun to measure the drill hole.

[0007] EP 2 766 135 B1 also describes acquiring the geometric data of the drill hole. It proposes using a camera to detect the drill hole from above and using the drill hole's subsidence diameter, borehole diameter, and subsidence angle to correct the subsidence depth of the subsequent borehole to be constructed.

[0008] In addition, a measurement method for measuring the head of a drilled hole, such as a riveted component, is known from US 6,154,279.

[0009] Although much effort has been made in the past to reduce the number of riveted joints outside tolerances in aircraft structural components, such riveted joints persist. These riveted joints must be painstakingly drilled out and replaced. Summary of the Invention

[0010] The problem upon which this invention is based is to further improve the manufacturing of known structural components of aircraft so that fewer riveted joints outside tolerances occur during manufacturing, thereby reducing finishing costs and manufacturing costs.

[0011] The above problems are resolved by the features described in this disclosure.

[0012] The basic concept is as follows: a pattern is projected onto a machining area having riveting elements inserted into a drill hole, and a sensor detects the projected pattern on the machining area. Analysis of the pattern projection allows for the evaluation of the sum of the tolerances of the drill holes and the batch tolerances of the riveting elements used in the riveted joint, both before and after production, and automatic adaptation to drilling at other machining areas. This adaptation is achieved through the adaptation of tool control data based on the analysis of the detection data. Thus, the probability of exceeding the tolerance range of the riveted joint due to the sum of the tolerances of the riveting elements and the drill holes is minimized at other machining areas.

[0013] In detail, a method for machining structural components of aircraft vehicles using machining equipment is proposed. The machining equipment includes a drilling unit and a riveting unit. A manufacturing process control unit is provided to operate the components of the machining equipment. The manufacturing process control unit, using tool control data and according to manufacturing rules, processes a series of drilling processes using the drilling unit and a series of riveting processes using the riveting unit. The machining equipment includes optical sensors and a projection unit. The method includes the following steps:

[0014] - A pattern is projected onto a machining area using a projection unit. This machining area has a riveting element inserted into a drill hole in the machining area.

[0015] - Sensors are used to detect the processing area, including the projection of the pattern, and the sensors generate corresponding detection data.

[0016] - Analyze the detection data using the analysis unit.

[0017] - The manufacturing process control department analyzes the inspection data to control the drilling tool for other processing parts according to the manufacturing rules, especially the drilling depth of the drill hole to be drilled.

[0018] According to a preferred embodiment of the invention, the head protrusion and / or tilt position of the riveting element are determined during the analysis. Preferably, based on this analysis, the sinking depth is adapted in the tool control data for subsequent drill holes. By precisely determining the position of the riveting element in the drill hole, the sinking depth can be recalibrated with particular precision for subsequent drill holes.

[0019] Preferred designs for the projected patterns are described in other parts of this disclosure. This enables particularly precise determination of the position and / or orientation of the riveting element within the drill hole in terms of head protrusion and / or tilt position.

[0020] Preferred methods for determining the head protrusion and tilt position of the riveted element in the drill hole are described in other parts of this disclosure.

[0021] Other parts of this disclosure describe a preferred arrangement of the projection unit and the sensor relative to each other or with respect to the drill hole of the machining area, which enables particularly reliable and stable detection of the machining area having riveting elements in the drill hole.

[0022] The preferred analysis and fitting are based on inspection data generated when the riveting element has been inserted but the riveted joint has not yet been established, and / or when the riveting element has been inserted and the riveted joint has already been manufactured. The advantage of analysis and fitting when the riveting element has been inserted but the riveted joint has not yet been established is that the riveting element can be simply removed if tolerance deviations are identified or anticipated. Analysis and fitting of inserted riveting elements with already manufactured riveted joints allows for a final evaluation in terms of tolerance compliance, as the riveting element is positioned between itself and the aircraft structural components, and within the same part (Setzen).

[0023] According to a preferred embodiment of the invention, a measuring device for measuring riveting elements is provided, and it is described how the adaptation of tool control data can be further improved based on the measurement of the riveting elements.

[0024] Other parts of this disclosure describe how the method can be repeated at other machining locations as new machining locations, and how tool data can be adapted for machining locations following this new machining location. This allows for continuous optimization of tool control data for drilling.

[0025] According to the invention, the method can be performed at other machining locations, especially if a new batch of riveting elements is to be inserted into the drill hole at this machining location. Because the tolerance of the riveting elements relative to the same batch of riveting elements varies more drastically with batch changes, it is particularly important in this case to repeat the process for subsequent riveting elements from the same new batch.

[0026] According to another teaching of the present invention, a machining apparatus for machining structural components of aircraft is claimed. The machining apparatus includes a drilling unit, a riveting unit, a manufacturing process control unit for operating components of the machining apparatus, optical sensors, and a projection unit. It is proposed that the machining apparatus is constructed and configured for machining structural components of aircraft according to the method described above. Reference is also permitted to all embodiments relating to the proposed method regarding the machining apparatus. Attached Figure Description

[0027] The invention will be explained in more detail below with the aid of the accompanying drawings, which only illustrate embodiments. In the drawings:

[0028] Figure 1 The recommended machining apparatus is shown for machining structural components of aircraft vehicles, and for performing the recommended methods.

[0029] Figure 2 It shows a) according to Figure 1 The end effector of the machining equipment, and b) a second embodiment of the end effector of the machining equipment.

[0030] Figure 3 A schematic diagram of projection, detection, and analysis is shown.

[0031] Figure 4 The diagram illustrates different locations for riveted components, which can be positioned within the structural members of the aircraft. It also demonstrates how these locations can be detected and analyzed using the recommended methods for adapting tool control data.

[0032] Figure 5 Different embodiments are shown that allow patterns to be projected onto the processing area in order to perform the method. Detailed Implementation

[0033] The proposed machining equipment 1 is used to machine the structural components 2 of the aircraft. The structural components 2 are particularly structural components for the fuselage or wings of an aircraft. These structural components preferably have multiple material layers, which are connected to each other by the machining equipment 1. In an embodiment, the machining equipment 1 is configured for drilling and riveting the structural components 2. Correspondingly, the machining equipment 1 has: a drilling unit 3a for creating holes in the structural components 2; and a riveting unit 3b for inserting riveting elements 4, especially countersunk rivet elements, into the created drill holes and for establishing riveted joints. The material layers of the structural components 2 are connected to each other by establishing riveted joints.

[0034] In this embodiment, and preferably, the machining equipment 1 has an end effector 3, and the drilling unit 3a and the riveting unit 3b are components of the end effector 3. These components at the end effector 3 can be adjusted to either an active working position or a resting position, depending on the machining to be performed by the end effector 3. This can be achieved, for example, by linear movement of the drilling unit 3a and / or the riveting unit 3b, or, for example, by a turntable device.

[0035] Here, and preferably, the end effector 3 is carried by an adjustment unit 5 for the end effector 3. The adjustment unit 5 preferably has multiple adjustment axes 5a, thereby enabling the end effector 3 to be moved relative to the flight tool structural member 2 to be processed for processing different parts.

[0036] Furthermore, the machining equipment 1, as in the embodiment, can have a second end effector 6. The second end effector 6 is here, and preferably, arranged on the side of the flight tool structural member 2 opposite to the end effector 3 during machining of the flight tool structural member 2. This second end effector participates in establishing the riveting connection and, in this respect, forms a mating tool with the tool relative to the end effector 3. In this sense, the second end effector 6 and the end effector 3 together form a tool pair.

[0037] In this embodiment, the riveting unit 3b places the riveting element 4 at the end effector 3, and the second end effector 6 establishes the riveting connection. This is achieved here by screwing the so-called rivet collar 4a onto the riveting element 4.

[0038] In this embodiment, and preferably, the second end effector 6 is adjusted by an adjustment unit 5 for the end effector 3. Figure 1 This is illustrated in the diagram. The second end effector, however, is also capable of having its own adjustment unit.

[0039] Here, and preferably, the processing equipment 1 further includes a rivet memory 7. The rivet memory 7 is arranged separately from the end effector 3, and especially separately from the adjustment unit 5 of the processing equipment. Here, and preferably, the riveting element 4 is conveyed from the rivet memory 7 to the end effector 3 via a delivery hose 8.

[0040] Furthermore, a manufacturing process control unit 9 is provided. Preferably, the machining equipment 1 has a manufacturing process control unit 9. This manufacturing process control unit, through the manipulation of the components of the machining equipment 1, uses tool control data 9a to process a series of drilling processes using a drilling unit 3a and a series of riveting processes using a riveting unit 3b, according to manufacturing rules 10. Components include, for example, adjustment units 5 for adjusting one or more end effectors 3, 6, or drive devices 5b for adjusting multiple adjustment units of these end effectors.

[0041] Here, and preferably, the manufacturing process control unit 9 is a central control unit. However, it is also conceivable that the manufacturing process control unit is arranged in a decentralized, i.e., distributed manner. In particular, the manufacturing process control unit may be an NC control unit for the machining equipment 1.

[0042] An example of manufacturing rule 10 is... Figure 1 (b) The drilling and riveting of the rows of drill holes 11 in sequence. Here, each drill hole 11 already has a riveting element 4, while a drill hole 11 is not yet equipped with a riveting element 4 and is shown by a dotted line as a drill hole 11 to be manufactured.

[0043] Furthermore, the proposed processing equipment 1 includes an optical sensor 12 and a projection unit 13. The optical sensor 12 is, in this case, a camera. In the embodiment and preferably, the optical sensor 12 and the projection unit 13 are components of the end effector 3 and are disposed at this end effector. Specifically, the optical sensor 12 can be securely disposed at the end effector 3, as shown in… Figure 2 As shown in b), the riveting unit 3b can be configured to move out of its working position to detect the machining part B via the sensor 12. This allows the riveting unit to then release the sensor 12's line of sight to the machining part B.

[0044] Alternatively, the optical sensor 12 can also be movably positioned at the end effector 3. For example, in Figure 2As shown in a), the optical sensor 12 can be, for example, a component of sensor unit 3c, which is adjustably arranged at the end effector 3. Specifically, sensor unit 3c can be adjustably arranged at the end effector 3, just like drilling unit 3a and riveting unit 3b, and one of units 3a, 3b, and 3c can be moved to an active position. Preferably, drilling unit 3a, riveting unit 3b, and sensor unit 3c can be linearly moved at the end effector 3 and / or housed in a turntable.

[0045] Here, and preferably, when processing the manufacturing rules for the drilling process performed by the drilling unit 3a and the riveting process performed by the riveting unit 3b using tool control data 9a, the following method is performed:

[0046] Pattern M is projected onto processing part B, which has a riveting element 4 inserted into a drill hole 11 in processing part B. Projection is achieved here by means of projection unit 13. Optical sensor 12 is used to detect processing part B, including the projection of pattern M, and corresponding detection data 14 is generated by sensor 12.

[0047] The test data 14 is then analyzed. The analysis is preferably performed by an analysis unit 15, which is further preferably associated with and / or part of the manufacturing process control unit 9.

[0048] Based on the analysis of the inspection data 14, tool control data 9a is adapted for the drill hole 11 to be drilled at another processing part B1 according to manufacturing rule 10. This is achieved here by the manufacturing process control unit 9.

[0049] By projecting, inspecting, and analyzing, the quality of the riveted joint at machining location B, or the predicted quality of the riveted joint at machining location B, can be evaluated. This enables, with particular precision, the adaptation of tool control data 9a to the subsequent drill hole 11 at another machining location B1, so as to produce a riveted joint at the other machining location B1 with improved reliability within tolerance. The proposed method not only allows for automated quality evaluation of the riveted joint at machining location B, but also allows for automated optimization of the drilling process at the other machining location B1, and therefore the riveted joint at this other machining location B1. The manufacturing process control unit 9 can autonomously, that is, without operator intervention, adapt tool control data 9a based on inspection and analysis. This other machining location B1 is, and preferably, the machining location B1 that directly follows machining location B according to manufacturing rule 10.

[0050] Preferably, before performing the recommended method, the drilling unit 3a of the end effector 3 has already drilled a hole 11 at the processing part B in accordance with manufacturing rule 10, and the riveting unit 3b has placed the riveting element 4 into the hole 11.

[0051] Particularly advantageous is that the head protrusion K of the riveting element 4 is determined during the analysis, and / or the tilt position of the riveting element 4 is determined during the analysis. The tilt position of the riveting element 4 is here the inclination of the longitudinal axis of the riveting element 4 relative to the longitudinal axis 11b of the drill hole. Here, and preferably, the sinking depth T is then adapted in the tool control data 9a for the drill hole 11 to be drilled subsequently based on this analysis and the determination of the head protrusion K and / or the tilt position S. Here, it should be noted that the head protrusion K can be a positive head protrusion in the sense described above, whereby the head 4b of the riveting element 4 protrudes relative to the surface of the flight tool structural member 2 at the machining part B, or it can be a negative head protrusion K, whereby the head 4b of the riveting element 4 does not protrude from the sinking area 11a of the drill hole 11. As an additional or alternative solution, it is also possible to determine multiple head protrusions K for a single riveting element 4. This can then, for example, be the maximum head protrusion K. max This refers to the distance between the furthest points of the riveted elements protruding from the surface 2a of the aircraft structural component, or the minimum head protrusion K. min This refers to the head component of the riveted element 4 that protrudes the least relative to the surface 2a of the aircraft structural member, and / or the average head protrusion K is determined. m This refers to the distance between the surface 2a of the aircraft structural component and the nose end 4b, about the longitudinal axis 4c of the riveting element 4. Figure 3 This is illustrated in b).

[0052] As an additional or alternative solution, it is also possible to address one, two, or all three specific head protrusions K. max K min K m Following the analysis, tool control data 9a was adapted for the subsequent drill hole 11 to be drilled at another processing part B1.

[0053] To accurately determine the protrusion K and / or tilt position of the riveted element 4 relative to the head of the aircraft structural member 2, a specific design scheme for pattern M is preferred. Particularly preferred is the use of patterns such as those in… Figure 3 and Figure 4 The strip projection shown is illustrated.

[0054] Preferably, pattern M has at least one stripe 16. In particular, pattern M can be a stripe projection having at least two or at least three particularly parallel stripes 16. Figure 3The diagram shows such a pattern M. Here, and preferably, at least one strip 16 is wider or narrower than one or more other strips 16, and / or the strips 16 have different spacing relative to each other. If this is the case, then, provided the direction of the projection is known, and the projection unit 13 projects the image onto the machining part B from that direction, it is possible to determine from the projection whether the riveting element 4 protrudes or sinks relative to the aircraft tool structural member 2 at the machining part B. As an additional option, it is possible to verify whether, despite the riveting element 4 being inserted, the sinking diameter of the drill hole can be detected optically at least segmentally by the sensor 12. If this is the case, then there is at least a negative head protrusion K in this region. The analysis unit 15 can perform a reliability check in this manner.

[0055] exist Figure 5 The embodiments illustrate alternative patterns M. Pattern M can consist, for example, only of parallel stripes 16, or pattern M can consist of a predetermined point cloud 17, or pattern M can be a grid pattern 18. Preferably, the grid pattern 18 is then constructed from polygons, especially triangles 18a or quadrilaterals 18b, as this is shown in Figure 5 As shown in the image.

[0056] We should use Figure 3 and Figure 4 The following is a brief description of how the head protrusion K and / or tilt position S of the riveting element 4 can be determined by means of the projected pattern M.

[0057] Figure 3 A schematic view of the machining section B is shown, which has a riveting element 4 inserted into a drill hole 11. The longitudinal axes 4c and 11b of the riveting element 4 and the drill hole 11 are coaxial here.

[0058] Projection unit 13 projects pattern M from the side onto the machining area B. This is achieved through the inserted riveting element 4 and the section extending around the drill hole 11 of the aircraft structural member 2 containing the inserted riveting element 4. The head 4b of the riveting element 4 protrudes slightly relative to the surface of the aircraft structural member. As shown in the top view, the projection of pattern M onto the surface of the aircraft structural member differs from its projection onto the head 4b of the riveting element 4. This is due to the different height positions, specifically the protrusion K of the head of the riveting element 4.

[0059] Preferably, the head protrusion K is determined by determining the deviation of the pattern M on the head 4b of the riveting element 4 relative to the pattern M on the aircraft structural member 2 at the machined part B and / or relative to the reference R. In an embodiment, the deviation V of one or more stripes 16 of the pattern M is determined for this purpose. This is also additionally... Figure 4As shown in a)i). The reference R can be a reference detection, which has been recorded in particular by sensor 12 within the framework of the calibration method, and / or can be a reference model generated for this purpose. Figure 4 Such a benchmark is shown in b).

[0060] As an additional or alternative solution, the tilt position of the riveting element 4 at the machining part B can be determined by determining the torsion D of the pattern M on the head 4b of the riveting element 4 relative to the pattern M on the aircraft structural member 2 at the machining part B and / or relative to a reference R, and / or by determining the compression or elongation S of the pattern M on the head 4b of the riveting element 4 relative to the pattern M on the aircraft structural member 2 at the machining part B and / or relative to a reference R. This can be done, for example, by determining the ratio of the spacing b of the lines on the head of the riveting element to the spacing a of the lines on the aircraft structural member 2 at the machining part B. The reference R can be a reference detection, which has been recorded in particular by sensor 12 within the framework of the calibration method, and / or can be a reference model generated for this purpose. In particular, this is the same reference detection and / or the same reference model used to determine the head protrusion K.

[0061] In the top view, the tilt position along the direction of projection P is preferably determined by determining the compression or elongation S of the pattern M on the head 4b of the riveting element 4 relative to the pattern M on the flight tool structural member 2 at the machined part B and / or relative to the reference R. Figure 4 This is illustrated in a) and ii). Here, the compression or elongation S is determined by the ratio of the spacing a, b on the riveting element 4 relative to the strips 16 on the flight vehicle structural member 2.

[0062] Preferably, the tilt position transverse to the projection direction is determined by determining the pattern M on the head 4b of the riveting element 4 relative to the pattern M on the flight tool structural member 2 at the machined part B and / or the torsion D relative to the reference R. Figure 4 This is shown in a) and iii). Here, the torsion D of the strip 16 on the head 4b of the riveting element 4 relative to the strip on the flight tool structural member 2 is determined.

[0063] When the head protrusion K and tilt position are superimposed, especially along the direction of projection P and laterally to the direction of projection P, such as in Figure 4 As shown in iv), it is preferable to consider not only deviation V, compression or elongation S, but also torsion V, in order to adapt tool control data 9a.

[0064] The projection unit 13 and the sensor 12 point towards the machining area B at an angle α when detecting the machining area B. Figures 1 to 3 This is illustrated in the diagram. An angle α is formed between the optical axis of sensor 12 and the direction of projection P of projection unit 13. This angle α is between 20° and 90°, more preferably between 45° and 75°, more preferably between 55° and 65°, and here it is essentially 60°.

[0065] During inspection, the projection unit 13 is preferably angled toward the machining area about the longitudinal axis of the drill hole 11. The angle β between the direction of the projection P of the projection unit and the longitudinal axis 11b of the drill hole 11 is preferably between 45° and 75°, more preferably between 55° and 65°, and here substantially 60°. The distance between the projection unit 13 and the drill hole 11 is preferably a maximum of 30 cm, more preferably a maximum of 20 cm, and even more preferably a maximum of 15 cm during inspection.

[0066] Sensor 12 is positioned orthogonally from above towards the machining area B during detection. Preferably, sensor 12, and especially the point from which its optical axis emerges, is arranged in a conical manner during detection. The central axis of this cone is coaxial with the longitudinal axis 11b of the drill hole, and the tip of this cone lies on the (theoretically) surface of the aircraft structural member 2 before the drill hole 11 is drilled out. The apex angle (γ) of this cone is preferably less than or equal to 10°, more preferably less than or equal to 5°, and more preferably less than or equal to 2°. Figure 3 This is illustrated in b). In the embodiment, the optical axis of sensor 12 and the longitudinal axis 11b of drill hole 11 are substantially coaxial.

[0067] The analysis and adaptation are preferably based on detection data generated when the riveting element 4 has been inserted but the riveted connection has not yet been established. This allows for consideration not only of the tolerances of the riveting element 4 but also of the tolerances of the drill hole 11, particularly those caused by drill bit wear, in order to adapt the tool control data 9a. Furthermore, this has the advantage of allowing the riveting element 4 to be easily removed from the drill hole 11.

[0068] As an additional or alternative solution, it is possible to set, analyze, and adapt based on detection data generated when the riveting element 4 is inserted and the riveting connection has been established. In this case, the placement process caused by the riveting connection can also be additionally considered for adapting tool control data 9a. Figure 3 In embodiment a), a riveted connection is established. Here, the second end effector 6 has already screwed the rivet collar 4a onto the riveting element 4.

[0069] Preferably, tool control data 9a is also adapted to the drill hole 11 to be drilled subsequently at another machining location B1, based on measurements of the riveting element 4 to be placed in this drill hole 11, according to manufacturing rule 10. For example... Figure 1 As shown, a measuring device 19 can be provided for measuring the riveting element 4 before it is inserted into the drill hole 11. In an embodiment, the measuring device 19 is provided in the delivery hose 8 from the rivet memory 7 to the end effector 3. Such a measuring device 19 can be constructed, for example, as described in DE 10 2014 106 312 A1.

[0070] As an additional or alternative solution, it is possible to set up a system in which the riveting element 4 is placed in the drill hole of the machining part B is measured before the measuring device 19 is inserted, and additionally, the tool control data 9a is adapted to the drill hole 11 to be drilled in another machining part B according to the manufacturing rule 10 based on the measurement of the riveting element 4 in the drill hole 11 of the machining part B.

[0071] The suggested method, including alternative preferred design schemes, can be repeated at another machining location B as a new machining location B1. Tool control data 9a is then adapted for the machining location B2 following this new machining location B1. Alternatively, the projection, inspection, and analysis, along with the subsequent adaptation of tool control data, can be repeated after a predetermined number of drill holes, particularly every 5 or 10 drill holes according to manufacturing rule 10.

[0072] Furthermore, the manufacturing process control unit 9 can be configured to detect whether the riveting element 4 to be placed at another processing location B1 belongs to the same batch as the riveting element 4 placed at processing location B, or whether it belongs to a new batch. Preferably, if the riveting element 4 to be placed at another processing location B1 belongs to a new batch, then the method is repeated at the other processing location B1 as a new processing location B, and tool control data 9a is adapted for the processing location B2 after this new processing location B1.

[0073] It can be configured such that if the riveting element 4 to be inserted into the drill hole 11 of this other processing part B belongs to the same batch as the riveting element 4 inserted at processing part B, then the method is not performed for each processing part in the other processing part B1.

[0074] For example, the riveting element 4 can be measured in the measuring device described above and / or when the riveting element 4 is loaded or sorted into the rivet memory 7. Such measurement can, for example, determine which riveting elements 4 belong to a batch.

[0075] Furthermore, it is possible to configure the process at part B, before inserting the riveting element 4 into the drill hole 11, to project a pattern M onto part B using the projection unit 13, and to detect part B, including the projection of the pattern M, using the sensor 12. As an additional option, the drilling hole 11 at part B can also be analyzed using the projection unit 13 and the sensor 12. For example, the sinking diameter and / or the drilling diameter can be determined. Preferably, the sinking depth T of the drill hole for part B is determined from the sinking diameter and information about the drill bit used for the drill hole 11. For other parts B, the sinking depth T of the drill hole 11 to be drilled according to manufacturing rule 10 can then be additionally adapted to tool control data 9a based on the analysis of these detection data.

[0076] As an additional or alternative solution, a pattern M, in particular, can be projected onto another machining location B1 by means of a projection unit 13 before the riveting element 4 is inserted into the drill hole 11. A sensor 12, in particular, can be used to detect the other machining location B1, including the drill hole 11 without the riveting element 4 inserted, encompassing the projection of the pattern M. Alternatively, the projection unit 13 and sensor 12 can also be used to analyze the drill hole 11 of the other machining location B1. For example, the sinking diameter and / or hole diameter can be determined. Preferably, the sinking depth T is determined from the sinking diameter and information about the drill bit used for the drill hole 11 of the other machining location B1. Therefore, based on the analysis of these test data 14, the adapted tool control data 9a, especially the higher sink depth T, can be reused to re-drill holes, and / or for the additional drill holes 11 to be drilled according to manufacturing rule 10 at the subsequent processing part B2, especially the sink depth T of the drill holes 11 to be drilled, the tool control data 9a can also be adapted based on the analysis of these test data 14.

[0077] Finally, an additional lighting unit 20 can be provided to illuminate the processed area during projection and inspection. This allows for improved inspection accuracy through the additional light falling on the processed area B.

Claims

1. A method for machining structural components (2) of aircraft vehicles using machining equipment (1), wherein, The processing equipment (1) has a drilling unit (3a) and a riveting unit (3b). The equipment includes a manufacturing process control unit (9) for controlling the components of the processing equipment (1). The manufacturing process control unit (9) uses tool control data (9a) to process a series of drilling processes according to manufacturing rules (10) using the drilling unit (3a) and uses the riveting unit (3b) to process a series of riveting processes. The processing equipment (1) includes an optical sensor (12) and a projection unit (13). The method includes the following steps: - The pattern (M) is projected onto the processing part (B) using the projection unit (13), the processing part having a riveting element (4) inserted into a drill hole (11) of the processing part (B). - The processing part (B) including the projection of the pattern (M) is detected using an optical sensor (12), and corresponding detection data (14) is generated by the sensor (12). - The detection data (14) is analyzed by the analysis unit (15). - The manufacturing process control unit (9) adapts the tool control data (9a) to the drill hole (11) to be drilled in accordance with the manufacturing rules (10) at another processing part (B1) based on the analysis of the detection data (14).

2. The method according to claim 1, characterized in that, The manufacturing process control unit (9) adapts the sinking depth (T) of the drill hole (11) to be drilled according to the manufacturing rule (10) for another processing part (B1) based on the analysis of the detection data (14).

3. The method according to claim 1, characterized in that, The head protrusion (K) of the riveting element (4) is determined during the analysis, and / or the tilt position of the riveting element (4) is determined during the analysis.

4. The method according to claim 3, characterized in that, Based on this analysis, the sinking depth (T) is adapted in the tool control data (9a) for the subsequent drill hole (11).

5. The method according to claim 1, characterized in that, The pattern (M) has at least one stripe (16).

6. The method according to claim 1, characterized in that, The pattern (M) is a strip projection having at least two or at least three stripes (16).

7. The method according to claim 1, characterized in that, The pattern (M) is a strip projection having at least two or at least three parallel stripes (16).

8. The method according to claim 5, characterized in that, At least one strip (16) is wider or narrower than one or more other strips (16), and / or the spacing of the strips (16) is different from that of each other.

9. The method according to claim 1, characterized in that, The pattern (M) consists only of parallel stripes (16), or the pattern (M) consists of a predetermined point cloud (17).

10. The method according to claim 1, characterized in that, The pattern (M) is a grid pattern (18), which is composed of polygons.

11. The method according to claim 1, characterized in that, The pattern (M) is a grid pattern (18) which is composed of triangles (18a) and / or quadrilaterals (18b).

12. The method according to any one of claims 1 to 11, characterized in that, The head protrusion (K) is determined at the machining part (B) by determining the deviation (V) of the pattern (M) on the head (4b) of the riveting element (4) relative to the pattern (M) on the flight tool structural member (2) at the machining part (B) or relative to the reference (R).

13. The method according to any one of claims 1 to 11, characterized in that, The head protrusion (K) is determined at the machining part (B) by determining the deviation (V) of one or more stripes (16) of the pattern (M) on the head (4b) of the riveting element (4) relative to the pattern (M) on the flight vehicle structural member (2) at the machining part (B) or relative to the reference (R).

14. The method according to any one of claims 1 to 11, characterized in that, The tilt position of the riveting element (4) at the machining part (B) is determined by determining the torsion (D) of the pattern (M) on the head (4b) of the riveting element (4) relative to the pattern (M) on the flight vehicle structural member (2) at the machining part (B) or relative to the reference (R), and / or by determining the compression or elongation (S) of the pattern (M) on the head (4b) of the riveting element relative to the pattern (M) on the flight vehicle structural member (2) at the machining part (B) or relative to the reference (R), the tilt position of the riveting element (4) is determined at the machining part (B).

15. The method according to any one of claims 1 to 11, characterized in that, The projection unit (13) and the sensor (12) point to the processing part (B) at an angle (α) relative to each other when detecting the processing part (B).

16. The method according to claim 15, characterized in that, The angle (α) is between 20° and 90°.

17. The method according to claim 15, characterized in that, The angle (α) is between 45° and 75°.

18. The method according to claim 15, characterized in that, The angle (α) is between 55° and 65°.

19. The method according to claim 15, characterized in that, The angle (α) is 60°.

20. The method according to any one of claims 1 to 11, characterized in that, During inspection, the projection unit (13) is angled about the longitudinal axis of the drill hole (11) and pointed onto the processing part (B).

21. The method according to claim 20, characterized in that, The angle (β) between the direction of the projection (P) of the projection unit (13) and the longitudinal axis (11b) of the drill hole (11) is between 45° and 75°.

22. The method according to claim 20, characterized in that, The angle (β) between the direction of the projection (P) of the projection unit (13) and the longitudinal axis (11b) of the drill hole (11) is between 55° and 65°.

23. The method according to claim 20, characterized in that, The angle (β) between the direction of the projection (P) of the projection unit (13) and the longitudinal axis (11b) of the drill hole (11) is 60°.

24. The method according to any one of claims 1 to 11, characterized in that, The sensor (12) points upwards onto the processing part (B) during detection.

25. The method according to any one of claims 1 to 11, characterized in that, The sensor (12) points orthogonally from above onto the processing part (B) during detection.

26. The method according to any one of claims 1 to 11, characterized in that, The analysis and the adaptation are based on detection data (14), which is generated when the riveting element (4) is inserted and the riveting connection has not yet been established, and / or the analysis and the adaptation are based on detection data (14), which is generated when the riveting element is inserted and the riveting connection has been manufactured.

27. The method according to any one of claims 1 to 11, characterized in that, A measuring device (19) is provided for measuring the riveting element (4) before it is placed into the drill hole (11), and additionally, the tool control data (9a) is adapted to the drill hole (11) to be subsequently drilled at the other machining location (B1) according to the manufacturing rules (10) based on the measurement of the riveting element (4) to be placed into this drill hole (11).

28. The method according to any one of claims 1 to 11, characterized in that, The riveting element (4) in the drill hole (11) of the machining part (B) was measured before the measuring device (19) was placed, and the tool control data (9a) was adapted to the drill hole (11) of the other machining part (B1) to be drilled according to the manufacturing rule (10) based on the measurement of the riveting element (4) in the drill hole (11) of the machining part (B).

29. The method according to any one of claims 1 to 11, characterized in that, The method is repeated at the other machining location (B1) as a new machining location (B1), and the tool control data (9a) is adapted for the machining location (B2) following this new machining location (B1).

30. The method according to any one of claims 1 to 11, characterized in that, The manufacturing process control unit (9) detects whether the riveting element (4) to be placed at the other processing part (B1) belongs to the same batch as the riveting element (4) placed at the processing part (B).

31. The method according to any one of claims 1 to 11, characterized in that, The manufacturing process control unit (9) detects whether the riveting element (4) to be placed at the other processing location (B1) belongs to a new batch. If the riveting element (4) to be placed at the other processing location (B1) belongs to a new batch, then the method is repeated at the other processing location (B1) as a new processing location (B1), and the tool control data (9a) is adapted for the processing location (B2) after this new processing location (B1).

32. A processing equipment for processing structural components (2) of aircraft vehicles, wherein, The processing equipment (1) includes: a drilling unit (3a), a riveting unit (3b), a manufacturing process control unit (9) for controlling the components of the processing equipment (1), an optical sensor (12), and a projection unit (13). Its features are, The processing equipment (1) is constructed and set up for processing the structural components (2) of the flight vehicle in accordance with any one of claims 1 to 31.

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