Simulation method for simulating correction parameters, assembly method, assembly program, computer-readable data carrier, computing device and assembly apparatus

Abstract

The invention provides a simulation method, an assembly method, an assembly program, a computer-readable data carrier, a computing device and an assembly apparatus for simulating correction parameters. A simulation method for simulating a correction parameter for aligning a first mating surface (13a) of a first section (3a) and a second mating surface (13b) of a second section (3b) of a device (1), in particular an aircraft frame, with respect to each other, comprises: obtaining design coordinates of a simulation set (40) of measurement points (p) on each of the first section (3a) and the second section (3b); measuring the specific coordinates of at least some of the measurement points (p) of the analog set (40) when the first mating surface (13a) and the second mating surface (13b) are arranged such that they face each other within a predetermined distance range from each other; comparing the design coordinates with specific coordinates; and deriving at least one correction parameter (K) from the comparison. An assembly method and an assembly apparatus for assembling a first section and a second section of an apparatus.

Description

Technical Field

[0001] The present disclosure relates to the field of assembling large equipment from different sections into precise alignment relative to each other. In particular, the present disclosure relates to a simulation method for simulating correction parameters for aligning a first mating surface of a first section of a device, in particular an aircraft fuselage, and a second mating surface of a second section relative to each other, an assembly method for assembling a first section and a second section of a device, in particular an aircraft fuselage, along the first mating surface of the first section and the second mating surface of the second section, an assembly program comprising instructions, a computer-readable data carrier, a computing device, and an assembly device for assembling a first section and a second section of a device, in particular an aircraft fuselage, along the first mating surface of the first section and the second mating surface of the second section. Background Art

[0002] Methods for assembling large equipment from different sections into precise alignment relative to each other are known from the prior art. Equipment, in particular a vehicle such as an aircraft, is usually assembled in an assembly shop or a hangar. In the assembly shop or hangar, the equipment sections are first roughly aligned with each other. Then, fine alignment occurs when the corresponding equipment sections are repeatedly joined and fixed to each other. Such a repetitive process can be cumbersome and time-consuming. According to the prior art, computer-aided methods have been proposed to improve the accuracy and reliability of such assembly methods.

[0003] For example, EP 4 181 009A1 describes a reliable and high-precision computer-implemented method for determining the final geometry of two or more real aircraft components, in particular even at invisible or non-measurable gaps and overlaps in the real aircraft components and predicting the final measurements when there is kinematics between the real aircraft components. The computer-implemented method includes the steps of obtaining digital data by independently scanning all real aircraft components; creating a digital twin model based on the obtained digital data, performing virtual assembly of the digital aircraft components; and reporting the final measurements.

[0004] US11 526 636B2 relates to methods and systems related to the design and testing of systems including articulated flight control surfaces of an aircraft. The systems and methods disclosed herein utilize a structural model that represents the structural environment of the system in a relatively simple manner. In various embodiments, the structural model includes one or more actuation branches having a common linear actuation direction, a load mass, and a massless connector representing the hinge line of the flight control surface. The massless connector is connected to one or more actuation branches and the load mass and is disposed between the one or more actuation branches and the load mass and is capable of moving along the common linear actuation direction such that the linear movement of the massless connector is associated with the rotational movement of the articulated flight control surface.

[0005] US10 430 548B2 relates to a computer-implemented method for space frame design that involves constructing a load stress diagram in a geometric boundary representation of a design space, defining additional points and load application points in the design space, creating an initial network of interconnecting lines between each pair of the additional points and load application points in the design space, assigning load application factors to each line of the initial network of interconnecting lines based on the values of the load stress diagram, generating potential space frame designs by removing different subsets of lines of the initial network of interconnecting lines according to variable removal parameters for each potential space frame design, evaluating the potential space frame designs with respect to optimization parameters, combining the removal parameters for potential space frame designs whose performance scores are higher than a predetermined performance threshold, and iteratively generating potential space frame designs and evaluating the potential space frame designs based on the combined removal parameters.

[0006] Assembly methods known from the prior art do not seem to meet the requirements for joining together relatively large components of a device, such as sections of an aircraft fuselage, in particular. Generally, a manual fuselage joining process is carried out, in which the sections to be joined are positioned on a rigid fixture at a certain distance from each other. During section joining, the two sections are moved in a translational direction (preferably only in the flight direction) until they occupy their final positions. Summary of the Invention

[0007] Accordingly, the object can be seen as reducing the built-in stress during the assembly of the device and reducing the setup time that actively contributes to the ramp-up. In other words, the object can be seen as providing an efficient and fast, while at the same time highly reliable and accurate, device assembly. These objects are achieved at least in part by the subject matter of the main aspects.

[0008] In particular, a simulation method for simulating correction parameters for aligning a first mating surface of a first section and a second mating surface of a second section of a device, in particular an airframe of an aircraft, relative to each other includes the following steps: obtaining the design coordinates of a simulated set of measurement points on each of the first section and the second section; measuring the specific coordinates of at least some of the measurement points of the simulated set when the first mating surface and the second mating surface are arranged such that they face each other within a predetermined distance range from each other; comparing the design coordinates with the specific coordinates; and deriving at least one correction parameter from the comparison.

[0009] An assembly method for assembling a first section and a second section of a device, in particular an airframe of an aircraft, along a first mating surface of the first section and a second mating surface of the second section is provided. The assembly method includes the following steps: arranging the first mating surface and the second mating surface such that they face each other within a predetermined distance range from each other; and aligning the first mating surface and the second mating surface in a projection along a straight mating line based on at least one correction parameter obtained from a corresponding computer-implemented simulation method of the first mating surface and / or the second mating surface.

[0010] An assembly program is provided, which includes instructions that cause a computing device to execute a corresponding simulation method and / or a corresponding assembly method when the program is executed by the computing device.

[0011] A computer-readable data carrier is provided, which has a corresponding assembly program stored thereon.

[0012] A computing device is provided, which is configured to execute a corresponding assembly program and / or includes a corresponding computer-readable data carrier.

[0013] An assembly device for assembling a first section and a second section of a device, in particular an airframe of an aircraft, along a first mating surface of the first section and a second mating surface of the second section is provided. The assembly device is configured to execute a corresponding assembly method, includes a corresponding assembly program, includes a corresponding computer-readable data carrier and / or includes a corresponding computing device.

[0014] The first section and the second section can be provided as mating sections of complementary shapes of the airframe. The mating surfaces can be arched, elliptical and / or circular and can be provided at flanges or the like. A semi-automatic assembly process can be developed based on experience in production tests and mass production to optimize the joining of mating surfaces, for example the flanges of the rear central box of the airframe. The assembly sequence can be based on on-site measurements and mathematical calculation models on a main component assembly line (MCA).

[0015] The positions of two mating surfaces can be determined using measurements. A laser tracker and a handheld probe with a spherical probe tip can be used as measuring instruments for the measurements. The measured coordinates can correspond to the design coordinates. The correction values required for positioning the flange can be calculated using mathematical methods. Thus, the two segments can be optimally aligned with each other using the calculated correction parameters and / or the corresponding parameter values. Thus, the gap between the structural components can be minimized, and inadmissible stresses can be prevented.

[0016] For example, the first mating surface and the second mating surface can be arranged at a distance range of about 500 mm relative to each other. By alignment, the mating surfaces can be arranged to be substantially parallel to each other. The assembly method can also include the following steps: moving the first segment and the second segment relative to each other along a straight mating line until the first mating surface abuts the second mating surface; and joining the first segment and the second segment together. Thus, the assembly method can involve joining the first segment and the second segment together.

[0017] A computer-readable data carrier can include and / or consist of a computer-readable medium and / or a data carrier signal, and the computer-readable medium and / or the data carrier signal carry an assembly program and / or include corresponding instructions, which cause a computing device to perform a simulation method and / or an assembly method when the program is executed by the computing device.

[0018] The proposed solution provides an innovative assembly process to achieve gapless and stress-free assembly of equipment segments. The solution can be particularly advantageous for joining segments of an aircraft fuselage. This is especially the case if the segments include relatively complex structures, such as when the aircraft fuselage is provided with a rear central box module or the like.

[0019] Other improvements can be derived from the various additional aspects and from the following description. Features described with reference to devices and equipment can be implemented as method steps, or features described with reference to method steps can be implemented as devices and equipment. Thus, the description provided in the context of a computing device and / or an assembly device also applies in a similar manner to the corresponding method. In particular, the functions of the computing device and / or the assembly device and their or their corresponding components can be implemented as method steps of a method, and the method steps can be implemented as functions of the computing device and / or the assembly device.

[0020] According to one aspect of the simulation method, the step of obtaining measurement points involves extracting design parameters related to design coordinates from a design dataset that at least partially represents a first segment and a second segment. The relevant area for simulation can be extracted from the design dataset, for example, in the form of computer-aided design (CAD) data for the first segment and the second segment, particularly for the first mating surface and the second mating surface of the first segment and the second segment respectively. The relevant area for simulation can contain information about the measurement points, such as the area. The corresponding metadata can include the coordinates (X, Y, Z) to be measured of the corresponding measurement points and / or the corresponding positions of the measurement points (where the measurement should be carried out). The measurement can be compared with, analyzed, and then stored in a database with the extracted CAD data. This can help organize, allocate, and / or verify the measurement, and thus further improve the efficiency of the corresponding assembly process.

[0021] According to one aspect of the simulation method, the number of specific coordinates of at least some of the measurement points in the simulation set for comparison reaches at least 3, preferably at least 10, and most preferably at least 20. A separate label can be assigned to each measurement point. This will allow for the clear assignment of measurement points in the simulation.

[0022] According to one aspect of the simulation method, the simulation set contains a surface subset of measurement points related to the first mating surface and the second mating surface and / or a reference subset of measurement points related to reference points on the first segment and the second segment. Therefore, the step of obtaining design coordinates can involve determining theoretical reference points from the extracted design data. The step of measuring the measurement points can involve measuring the specific coordinates of the reference points corresponding to the theoretical reference points. This helps to further improve the reliability and accuracy of the corresponding assembly process.

[0023] According to one aspect of the simulation method, at least some of the reference points refer to positioning holes for mechanically connecting the first segment and the second segment to each other. A distinction can be made between measuring the flange contact surface and measuring the positioning holes. When measuring the positioning holes, a positioning element, such as a measuring sensor ball, can represent the holes produced by the suppliers of the segments to be joined together. Thereby, the optimal position of the positioning holes can be defined. Once the measurement has been carried out, the coordinates of the measurement points can be depicted in the form of a point cloud in a simulation environment. The generated point cloud contains information about the position and orientation of the flange (connection surface), such as the position of the reference holes / positioning holes, which is required for the alignment and attachment of the complete frame. The (flange and reference hole) points should be considered separately in the data record for the associated frame. This helps to further improve the reliability and accuracy of the corresponding assembly process.

[0024] According to one aspect of the simulation method, the correction parameter describes the rotational movement and / or translational movement of at least one of the first section and the second section. Separating the surface points from the reference points can help to respectively define the translational movement and / or rotational movement for achieving the alignment of the first mating surface and the second mating surface. Thereby, the efficiency, reliability, and accuracy of the corresponding assembly process can be further improved.

[0025] According to one aspect of the simulation method, the method may further include the step of determining the centroid and / or surface normal of at least one of the first mating surface and the second mating surface. All translational corrections and rotational corrections may involve the centroid, i.e., the center point. Thereby, the efficiency, reliability, and accuracy of the corresponding assembly process can be further improved.

[0026] According to one aspect of the simulation method, the method may further include the step of determining the relative distance between the centroid of the first mating surface and the centroid of the second mating surface. Then, the rotational movement can be easily converted into a translational correction, such as a vertical movement, for the support points of at least one of the first section and the second section. Thereby, the execution of the corresponding assembly process can be further facilitated and / or automated, further improving its efficiency, reliability, and accuracy.

[0027] According to one aspect of the simulation method, the method may further include the step of determining the relative tilt angle between the first mating surface and the second mating surface. Calculating the centroid and the surface normal helps to determine the relative tilt angle. The relative tilt angle may include the assembly tolerance of the corresponding manufacturing station and the detailed part tolerance related to the perpendicularity of the mating surface, and the mating surface may be provided at the flange on the first section and / or the second section. The relative angle between the parts can be calculated on the surface normal of the mating surface, and the mating surface can be formed as part of a milling frame. This helps to further facilitate the corresponding assembly process and / or automate the corresponding assembly process, thereby further improving its efficiency, reliability, and accuracy.

[0028] According to one aspect of the simulation method, the first section serves as the main component with a fixed position, and the second section serves as the slave component with a variable position. The fixed position can be used as a reference position and can thus help to facilitate the provision of at least one correction parameter. This can again help to further facilitate the corresponding assembly process and / or automate the corresponding assembly process, thereby further improving its efficiency, reliability, and accuracy. Description of the Drawings

[0029] The subject matter will be described hereinafter in conjunction with the following drawings, wherein like reference numerals denote like elements, and in the drawings:

[0030] Figure 1Is a schematic side view of a device in the form of an aircraft including a fuselage, the fuselage having a plurality of sections joined together.

[0031] Figure 2 Is a schematic side view of an assembly device including two sections of the device arranged at a distance from each other and to be joined together.

[0032] Figure 3 Is as Figure 2 Schematic diagrams of corresponding details of two sections of the device as illustrated in

[0033] Figure 4 Is a schematic diagram of a measuring device applied to provide measurements for determining the specific coordinates of measurement points on a section of the device.

[0034] Figure 5 Is another schematic diagram of a measuring device applied to provide measurements for determining the specific coordinates of other measurement points on a section of the device.

[0035] Figure 6 Is a schematic rear view of the first section of the device.

[0036] Figure 7 Is a schematic front view of the second section of the device.

[0037] Figure 8 Is a schematic diagram of a computing device for implementing a simulation method and / or an assembly method by means of a corresponding assembly program and / or a computer-readable data carrier that is part of the assembly device.

[0038] Figure 9 Is a schematic perspective view of the measurement points of two sections of the device.

[0039] Figure 10 Is Figure 9 Another schematic perspective view of the measurement points of two sections of the device as shown in

[0040] Figure 11 Is a schematic diagram of correction parameters for aligning two sections of the device with each other.

[0041] Figure 12 Is a schematic diagram of the reference points of two sections of the device before their alignment.

[0042] Figure 13 Is Figure 12 Schematic diagram of the reference points of two sections of the device as shown in

[0043] Figure 14 Is a schematic diagram of one of the reference points of the reference points of two sections of the device before its alignment.

[0044] Figure 15 is Figure 14 A schematic view after alignment of the reference points of two sections of the device shown in

[0045] Figure 16 A schematic view of steps of a simulation method and / or an assembly method. DETAILED DESCRIPTION

[0046] The following detailed description is merely exemplary in nature and is not intended to limit the invention and its applications. Further, it is not intended to be bound by any theory presented in the foregoing background or the following detailed description. The representations and illustrations in the drawings are schematic and not to scale. Identical reference numerals represent identical elements. A better understanding of the subject matter described can be obtained by reviewing the illustrations as well as the subsequent detailed description.

[0047] Figure 1 A schematic side view of a device 1 in the form of an aircraft including a fuselage 2 having a number of device sections 3 joined together is shown. For example, the section 3 includes a first section 3a, a second section 3b, a third section 3c, a fourth section 3d, and / or a fifth section 3e. The first section 3a may be a central section of the fuselage 2. The second section 3b may be a rear section of the fuselage 2. The third section 3c may be a front section of the fuselage 2. The fourth section 3d may be a tail section of the fuselage 2. The fifth section 2e may be a head section of the fuselage 2. The fuselage 2 may be rested on the ground 4 by means of a landing gear 5.

[0048] Figure 2 A schematic side view of an assembly device 10 including two sections 3, namely for example the first section 3a and the second section 3b, of a device 2 arranged to be joined together with a distance d therebetween is shown. The sections 3 are rested on support points 11 on the ground 4 instead of on the landing gear 5. The support points may be provided by corresponding jigs 12 rested on the ground 4.

[0049] The device 1 and thus the assembly device 10 extend along a longitudinal direction X, a lateral direction Y, and a height direction Z that together form a Cartesian coordinate system. The distance d is measured substantially parallel to the longitudinal direction X between the mating surfaces 13 of the sections 3 to be joined together. The first section 3a has a mating surface 13a and the second section 3b has a mating surface 13b, the mating surfaces 13a and 13b facing each other with a distance d therebetween.

[0050] For example, prior to the joining process, the two segments are roughly synchronized on a major component assembly (MCA) station (not shown) that provides the support points 11 for the fixture 12. The first forward-facing segment 3a can be placed on the fixed support points 11 (with no degrees of freedom). The second rear-facing segment 3b can be placed on the floating support points 11, which allow translational movement in the plane generated by the longitudinal direction X and the transverse direction Y, while the floating support points 11 can allow rotational adjustment about the transverse direction Y. After the segments 3 are positioned on the support points 11, the second segment 3b can be guided towards the first segment 3a in a translational movement.

[0051] Figure 3 Shows a schematic view of the corresponding details of two segments 3 of the device 1 to be joined together and arranged at a distance d from each other as Figure 2 illustrated. The mating surfaces 13, 13a, 13b can be provided at the flanges 12 formed at the first segment 3a and the second segment 3b, respectively. In this example, instead of the conventional riveting of the transverse joint (not shown), the fuselage 2, i.e., the segments 3 of the fuselage 2, can be bolted together at the flanges 14 by means of corresponding bolts (not shown).

[0052] The significant challenge that can be seen is that the flanges 14 of the segments 13 must be aligned parallel to each other to have the minimum possible initial stress on the frame of the device 1. During the joining process, the second segment 3a can move towards the first segment 3a until the distance d between the flanges, e.g., the distance d measured parallel to the longitudinal direction X between the corresponding centroids c of the mating surfaces 13, reaches approximately 500 mm. Depending on the detail components and assembly tolerances, large gaps can be formed between the flanges 14. These gaps can induce major stresses in the structure of the fuselage 2 during the bolting operation, which may lead to premature material failure.

[0053] To avoid such stresses, the flanges 14, i.e., the mating surfaces 13 on the flanges 14, should be perfectly aligned with each other before and during the start of the bolting operation. To achieve this, at least one correction parameter K, such as the angle α measured between the corresponding surface normals N of the mating surfaces 13, should be provided. For example, by tilting the first segment 3a by an amount corresponding to the angle α, the first mating surface 13a and the second mating surface 13b can be aligned with each other.

[0054] The angle α can be calculated by means of a simulation based on the measurement points p provided at each mating surface 13. Some of these measurement points can be provided on the surface s of the corresponding mating surface 13, while other measurement points can be provided as reference points r associated with the mounting points 15, for example, which can be provided in the form of positioning holes on the flanges 14 (see Figure 4 andFigure 5 ).

[0055] Figure 4 A schematic diagram of a measuring device 20 applied to provide measurements for determining specific coordinates of a measuring point p on a section 3 of an apparatus 1 in an assembly apparatus 10 is shown. The measuring device 20 comprises a control unit 21, a probe tip 22 and a sensor ball 23. The control unit 21 is mechanically connected to the probe tip 22 in a well-defined manner and may comprise any reference means, such as laser communication means, in order to reference the control unit 21 and thus the probe tip 22 in any of the longitudinal direction X, the transverse direction Y and / or the height direction Z. The probe tip engages the sensor ball 23, the surface of which may thus be accurately referenced in any of the longitudinal direction X, the transverse direction Y and / or the height direction Z.

[0056] exist Figure 4 In the assembly device 10 shown in FIG. 1 , the sensor ball 23 is located exactly at the mounting point 15, for example in the form of a positioning hole. The outer surface of the sensor ball 23 is therefore located below the surface s on the corresponding mating surface 13, while the sensor ball 23 is centered exactly on the mounting point 15, for example by means of the circumferential edge of the positioning hole. Therefore, the measurement point p measured in this position of the sensor ball 23 can be used as one of the reference points r, for example formed at the flange 14, for joining the segments 3 together.

[0057] Figure 5 Another schematic diagram of a measuring device applied to provide measurements for determining specific coordinates of other measuring points p on section 3 of device 1 is shown. Here, sensor ball 23 abuts surface s on mating surface 13. Thus, the corresponding measuring point p is located exactly where sensor ball 23 contacts surface s.

[0058] Figure 6 A schematic rear view of a first section 3a of the device is shown. Figure 7 A schematic front view of the second section 3b of the device 10 is shown. It becomes apparent here how the measuring points p constituting the reference points r can be distributed along the mating surface 13 such that when the first mating surface 13a and the second mating surface 13b are opposite each other in the assembled device 10, the measuring points p are arranged substantially in a mirror-symmetrical manner on the first mating surface 13a and the second mating surface 13b, respectively.

[0059] Figure 8The schematic diagram of a computing device 30 for implementing an analog method and / or an assembly method by means of a corresponding assembly program 31 and / or a computer-readable data carrier 32 which is part of an assembly device 10 is shown. The computing device 30 is configured to execute the assembly program 31. The computer-readable data carrier 32 has a computer system integration program 31 stored thereon and may be in the form of a computer-readable medium 33 and / or a data carrier signal 34. When the assembly program 31 is executed, the computing device 30 provides an assembly operation module 35 for managing, processing, disposing and / or visualizing and thus operating all data used in conjunction with the analog method and / or the assembly method as described herein.

[0060] To prevent high mechanical stresses in the structural components of the device 2, the mating surfaces 13 must be aligned parallel to each other. The assembly process based on the actual measured values p, r should first be simulated and verified for the ideal orientation, e.g., positioning, of the section 3 which is a structural component of the device 1. The simulation results provide a correction value K and setting for the support points 11.

[0061] The design coordinates with reference to a coordinate system composed of a longitudinal direction X, a transverse direction Y and / or a height direction Z of the measurement points p including a reference point r can be obtained as a simulation set 40 derived from a design data set 50. After the corresponding specific coordinates of the measurement points p in the respective coordinate systems are obtained for each section 3 to be joined together by means of the measuring device 20, the measurement points p should be separated from the reference point r. Then, the number M of measurement points p and / or the number N of reference points r can be processed together as the simulation set 40, as listed in the following table for the first section 3a and the second section 3b respectively:

[0062] Table 1: Measurement Points

[0063]

[0064] The simulation sets 40 for the first section 3a and the second section 3b respectively can be displayed in a simulation environment by means of the assembly operation module 35. Using the following mathematical method, the relative inclination angle α between the first mating surface 13a and the second mating surface 13b can be calculated. For this purpose, the centroid c and the surface normal n of the mating surface 13 must be calculated, possibly by fitting a plane f to the measurement points p. All translational corrections and rotational corrections involve the centroid c (center point) of the corresponding flange 14.

[0065] The orthogonal regression method should be used to calculate the surface normal n (for calculating the overall shape of the fitting plane f passing through all measurement points p) according to the following equation 1.1:

[0066]

[0067] A plane f should first be drawn through all measurement points p to calculate the surface normal n.

[0068] The next step may involve calculating the centroid, such as the centroid of the center of gravity as the reference point r (calculating the center of gravity of the surface for the complete frame) according to Equation 1.2 below:

[0069]

[0070] The following algorithm can be selected to calculate the fitting plane (determining the centroid c, such as the centroid c of the center of gravity for the surface of the entire flange 14):

[0071]

[0072] In another step, the surface normal n for the plane f can be determined using singular value decomposition according to Equation 1.3 below:

[0073] A = [p i – c, …, p n – c] (1.3)

[0074] The implementation of singular value decomposition can be achieved through Equation 1.4 below:

[0075] USV T = A (1.4)

[0076] The surface normal n (orthogonal to the plane) can be calculated through Equation 1.5 below:

[0077] N = U(:, 3) (1.5)

[0078] Figure 9 A schematic perspective view of a simulated set 40 of measurement points p of two sections 3 of the device in the initial state A is shown, which has a corresponding initial angle α between the surface normals n of the first section 3a and the second section 3b respectively. Rotating the simulated set 40, which is in the form of points for example, can be achieved by using a rotation and translation matrix as follows:

[0079] M 点 = translation

[0080] The corresponding tilt angle α for the quantitative parameter K for the section 3 can be referenced to a neutral reference system that is valid for two sections by providing a common longitudinal direction X, a transverse direction Y, and / or a height direction Z. The tilt angle α used as the correction parameter K can be calculated on the surface normal n for the corresponding section 3. Generating the plane f (passing through all the measurement points p for the relevant section 3) can be achieved by the above formula 1.1. The surface normal n extending perpendicular to the substantially vertical plane f can be calculated on three gaps of the nxn matrix according to the above formula 1.5, and the surface normal n is generated by the decomposition of the corresponding singular values (see formula 1.4).

[0081] The tilt angles α for the first section 3a and the second section 3b can be added, and the total angle between the mating surfaces 13 of the sections, such as the corresponding flange 14, can be obtained according to the following equation:

[0082] Total angle 3a / 3b = Angle 3b - Angle 3a

[0083] Figure 10 Shows another schematic perspective view of the simulated set 40 of measurement points p of the two sections 3 of the device 1 in the tilted state and / or the transition state T. Here, a certain tilting movement has been performed between the two sections 3. Therefore, the tilt angle α has been adjusted. Figure 9

[0084] Figure 11 Shows a schematic diagram of the correction parameter K for aligning the two sections 3 of the device 1 with each other in the tilted state T. In this example, the first section 3a can be used as the main component fixed to the support point 11 carrying it. The second section 3b can be defined as the secondary component, and the position of the secondary component will be adapted to the main component. Thus, for example, the rotation around the transverse direction Y can be performed by adjusting the corresponding height measured in the height direction Z at its corresponding lengths L 1 2 L 2 to the corresponding distance from the second mating surface 13a.

[0085] Using the corresponding correction angle α, the second mating surface 13b can be aligned to extend parallel to the first mating surface 13a. The second section 3b can rotate around its centroid c (see the above equation 1.2). Due to the calculation relationship between the angle and the aspect ratio, the parameter (the Z correction value of the support point 11 at the corresponding lengths L 1 L 2 2

[0086] After applying the correction parameter K for correcting the angle α, it is assumed that the section 3 is aligned along the transverse direction Y and the height direction Z. For the remaining translational corrections, the calculated centroid c of the reference points r listed in Table 1 above can be combined. The centroid distances of the reference points r will preferably be calculated together along the longitudinal direction X and the transverse direction Y in a common coordinate system.

[0087] The corresponding correction parameter K can be calculated in two steps. In the first step of these two steps, the relative distances between the centroids c of the reference points r can be calculated as follows (for example, for 5 positioning hole positions respectively):

[0088] Y 距离 = the second section 3b 质心XYC - the first section 3a 质心XYZ

[0089] In the second step of the two steps, the correction parameter K along the transverse direction Y and the height direction Z can be calculated on the following translation matrix:

[0090] K = T * MT = 1 0 0 1 0 0 0 Y_Dist 0 0 0 0 1 Z_Dist 0 1 * x1 y1 xn yn z1 1 1 zn1

[0091] Figure 12 Shows a schematic diagram of the reference points r of the two sections 3 of the device in the tilted state T before their alignment, that is, before applying the final correction parameter K along the transverse direction Y and the height direction Z. Figure 13 Shows Figure 12 A schematic diagram of the reference points of the two sections of the device shown in 1 to r 5 after their alignment. In this example, the five reference points r 1 to r 5 have been used as an overall reference system effective for each of the two sections 3, that is, for the first section 3a and the second section 3b. Considering the corresponding correction parameter K providing correction values for the transverse direction Y and the height direction Z, the reference points r Figure 13 for the first section 3a and the second section 3b can be optimally aligned relative to each other as shown in 1 to r 5 and thus the first section 3a and the second section 3b are converted into the aligned state B, for example, by minimizing their deviations by the method of least squares.

[0092] Figure 14 Shows a schematic diagram of one of the reference points r of the two sections 3 of the device 1 in the tilted state T before its alignment. Figure 15 ShowsFigure 14 Schematic diagram of the alignment state B of the reference points r of the two sections 3 of the device shown in the figure after their alignment. As can be seen, in the alignment state B, the reference points r are completely aligned with each other in the projection along the straight mating line extending parallel to the longitudinal direction X, such that the first section 3a and the second section 3b can now be joined by a simple translational movement along the longitudinal direction X.

[0093] Figure 16 Schematic diagram showing the steps of the simulation method and / or the assembly method. In the start step S1, the method can be started. In step S2, design data can be obtained from the design data set 40. In step S3, measurements of the measurement points p included in the simulation set 40 derived from the design data set 50 can be performed. In the data collection step S4, all the data collected regarding the respective sections 3 to be joined can be loaded by the computing device 30. In step S5, corresponding noise data with artificial errors, especially artificial errors along the longitudinal direction X and rotational errors about the longitudinal direction X, the transverse direction Y, and / or the height direction Z, can be applied. In step S6, the corresponding noise frames created in step S5 can be visualized, possibly by creating corresponding graphics in step S7 with the aid of the assembly operation module 35.

[0094] In step S8, the centroid c can be calculated. In step S9, the fitting plane f can be calculated through all the available measurement points p, and the surface normal n can be determined. In step S10, the corresponding angle α between the surface normals n of the sections 3 facing each other can be calculated. In step S11, the correction parameter K for the support points 11 can be calculated. Additionally, in step S12, the results can be visualized. Thus, in step S13, a 3D scatter plot of the entire process can be generated. In step S14, a 2D scatter plot of the reference points r can be generated. In step S15, at least the simulation method can end.

[0095] List of reference numerals

[0096] 1 Device / aircraft

[0097] 2 Fuselage

[0098] 3 Section

[0099] 3a to 3e First section to fifth section

[0100] 4 Ground

[0101] 5 Landing gear

[0102] 10 Assembly device

[0103] 11 Support point

[0104] 12 Fixture

[0105] 13 mating surface

[0106] 13a First mating surface

[0107] 13b Second mating surface

[0108] 14 flange

[0109] 15 mounting point

[0110] 20 measuring device

[0111] 21 control unit

[0112] 22 probe tip

[0113] 23 sensor ball

[0114] 30 computing device

[0115] 31 assembly procedure

[0116] 32 computer-readable data carrier

[0117] 33 computer-readable medium

[0118] 34 data carrier signal

[0119] 35 assembly operation module

[0120] 40 simulation set

[0121] 50 design data set

[0122] c center of mass

[0123] d distance

[0124] n surface normal

[0125] p measurement point

[0126] r reference point

[0127] s surface

[0128] A initial state

[0129] B alignment state

[0130] K correction parameter

[0131] L length

[0132] T tilt state / transition state

[0133] X longitudinal direction

[0134] Y transverse direction

[0135] Z height direction

[0136] α angle

[0137] S1 Start

[0138] S2 Obtain design data

[0139] S3 Measure

[0140] S4 Collect data

[0141] S5 Generate noise data

[0142] S6 Visualize noise frames

[0143] S7 Create graph

[0144] S8 Calculate centroid

[0145] S9 Calculate fitting plane and surface normal

[0146] S10 Calculate angle

[0147] S11 Calculate correction parameter

[0148] S12 Visualize results

[0149] S13 Generate 3D scatter plot

[0150] S14 Generate 2D scatter plot

[0151] S15 End

Claims

1. A simulation method for simulating correction parameters (K), wherein the correction parameters (K) are used to align a first mating surface (13a) of a first section (3a) and a second mating surface (13b) of a second section (3b) of a device (1), in particular an aircraft frame, relative to each other, the simulation method comprising the following steps: obtaining design coordinates of a simulation set (40) of measurement points (p) on each of the first section (3a) and the second section (3b); measuring specific coordinates of at least some of the measurement points (p) of the simulation set (40) when the first mating surface (13a) and the second mating surface (13b) are arranged so that the first mating surface (13a) and the second mating surface (13b) face each other within a predetermined distance range from each other; comparing the design coordinates with the specific coordinates; and deriving at least one correction parameter (K) from the comparison.

2. The simulation method according to claim 1, wherein: The step of obtaining the measurement points (p) involves extracting design parameters related to the design coordinates from a design data set (50) at least partially representing the first section (3a) and the second section (3b).

3. The simulation method according to claim 1 or 2, wherein: The number of specific coordinates of at least some of the measurement points (p) of the simulation set (40) used for comparison reaches at least 3, preferably at least 10, most preferably at least 20.

4. The simulation method according to at least one of claims 1 to 3, wherein: The simulation set (40) comprises: a surface subset of measurement points (p) associated with the first mating surface (13a) and the second mating surface (13b), and / or A reference subset of measurement points (p) associated with reference points (r) on the first section (3a) and the second section (3b).

5. The simulation method according to claim 4, wherein: At least some of the reference points (r) are positioning holes for mechanically connecting the first section (3a) and the second section (3b) to each other.

6. The simulation method according to at least one of claims 1 to 5, wherein: The correction parameter (K) describes a rotational movement and / or a translational movement of at least one of the first section (3a) and the second section (3b).

7. The simulation method according to at least one of claims 1 to 6, further comprising the step of determining a center of mass (c) and / or a surface normal (n) for at least one of the first mating surface (13a) and the second mating surface (13b).

8. The simulation method according to claim 7, further comprising the step of determining a relative distance (d) between the center of mass (c) of the first mating surface (13a) and the center of mass (c) of the second mating surface (13b).

9. The simulation method according to at least one of claims 1 to 8, further comprising the step of determining a relative inclination angle (a) between the first mating surface (13a) and the second mating surface (13b).

10. The simulation method according to at least one of claims 1 to 9, wherein: The first section (3a) serves as a master component with a fixed position and the second section serves as a slave component with a variable position.

11. An assembly method for assembling a first section (3a) and a second section (3b) of a device (1), in particular a frame of an aircraft, along a first mating surface of the first section (3a) and a second mating surface (13b) of the second section (3b), the assembly method comprising the following steps: arranging the first mating surface (13a) and the second mating surface (13b) so that the first mating surface (13a) and the second mating surface (13b) face each other within a predetermined distance range from each other; and The first mating surface (13a) and the second mating surface (13b) are aligned in a projection along a straight mating line based on at least one correction parameter (K) of the first mating surface (13a) and / or the second mating surface (13b) derived by a computer-implemented simulation method according to at least one of claims 1 to 10.

12. An assembly program (31), comprising instructions which, when the program is executed by a computing device (30), cause the computing device (30) to execute the simulation method according to at least one of claims 1 to 10 and / or the assembly method according to claim 11.

13. A computer-readable data carrier (32, 33, 34) having stored thereon an assembly program (31) according to claim 12.

14. A computing device (30) configured to execute an assembly program (31) according to claim 12 and / or comprising a computer-readable data carrier (32, 33, 34) according to claim 13.

15. An assembly device (10) for assembling a first section (3a) and a second section (3b) of a device (1), in particular a frame of an aircraft, along a first mating surface of the first section (3a) and a second mating surface of the second section (3b), the assembly device (10) being configured to execute an assembly method according to claim 11, including an assembly program according to claim 12, including a computer-readable data carrier (32, 33, 34) according to claim 13 and / or including a computing device according to claim 14.

Images