An information collection method, system and medium for large airliners

Abstract

The present invention discloses an information acquisition method, system and medium for large airliners. The method includes the following steps: setting precision parameters and acquiring airliner information; creating a set of information of components to be measured according to the airliner information; performing a partition acquisition operation based on the precision parameters and the set of information of components to be measured to obtain data to be processed; performing a data splicing and processing operation based on the precision parameters and the data to be processed to obtain airliner scan information. The present invention can adapt different precision parameters to different component areas of large airliners and perform partition scanning using different scanning methods. Moreover, only half of the fuselage needs to be measured during the on-site scanning process. Subsequently, through the designed data processing logic, all point cloud data for the entire large airliner can be generated, and a complete aircraft model can be generated based on the point cloud data. The information acquisition has high precision, high acquisition efficiency, strong operational expandability, and extremely high applicability and foresight.

Description

Technical Field

[0001] The present invention relates to the technical field of optical measurement, and particularly to an information acquisition method, system and medium for large airliners. Background Art

[0002] In the prior art, the information acquisition process for large airliners is relatively single, and it is impossible to adopt the most suitable acquisition method for different parts of the airliner. Both the accuracy and efficiency of information acquisition are relatively low. With the rapid development of optical measurement technology, it is necessary to design an information acquisition method that can adapt different precision parameters to different component areas of the aircraft based on optical photogrammetry technology and laser technology, and perform zonal scanning, so as to generate relatively accurate airliner model information in a shorter acquisition time, make up for the deficiencies of the prior art, and improve the diversity and intelligence of equipment detection for large airliners and the like. Summary of the Invention

[0003] The main object of the present invention is to design an information acquisition method that can adapt different precision parameters to different component areas of the aircraft based on optical photogrammetry technology and laser technology, and perform zonal scanning, so as to generate relatively accurate airliner model information in a shorter acquisition time, make up for the deficiencies of the prior art, and improve the diversity and intelligence of equipment detection for large airliners and the like.

[0004] To achieve the above object, a technical solution adopted by the present invention is: to provide an information acquisition method for large airliners, including the following steps:

[0005] Parameter information creation step: set precision parameters and obtain airliner information; create a set of information on components to be measured according to the airliner information;

[0006] Zonal measurement and acquisition step: perform zonal acquisition operations based on the precision parameters and the set of information on components to be measured to obtain data to be processed;

[0007] Data splicing and processing step: perform data splicing and processing operations based on the precision parameters and the data to be processed to obtain airliner scanning information.

[0008] As an improved solution, the precision parameters include: the precision of the first precision component, the precision of the second large component, the precision of the third component splicing, and the precision of surface fitting;

[0009] The airliner information includes: airliner model information, airliner component information and airliner plane drawings matching the airliner model information.

[0010] As an improved solution, the step of creating a set of information on components to be measured according to the airliner information further includes:

[0011] Set the information of the components to be scanned and the information of the precision components to be measured based on the information of the airliner components; integrate the information of the components to be scanned and the information of the precision components to be measured to obtain the set of information of the components to be measured.

[0012] As an improved solution, the information of the components to be scanned includes: the fuselage of the airliner and the cockpit of the airliner;

[0013] The information of the precision components to be measured includes: the wings of the airliner;

[0014] The partition acquisition operation includes:

[0015] Divide the wings of the airliner into several high-precision measurement engineering areas; perform coding measurement steps on the several high-precision measurement engineering areas according to the precision of the first precision components to obtain several first data to be spliced corresponding to the several high-precision measurement engineering areas respectively;

[0016] Perform a global laser scanning step on the fuselage of the airliner according to the precision of the second large components to obtain several second data to be spliced;

[0017] Perform a spatial laser scanning on the cockpit of the airliner according to the precision of the second large components to obtain the third cockpit data;

[0018] Integrate the third cockpit data, several of the first data to be spliced and several of the second data to be spliced to obtain the data to be processed.

[0019] As an improved solution, the coding measurement step includes:

[0020] Set the splicing identification layout specification; identify the area value of the high-precision measurement engineering area, and set the coding point layout specification based on the area value;

[0021] First, set several coding points and several non-coding points in the high-precision measurement engineering area according to the coding point layout specification, and then set several splicing identifications in the high-precision measurement engineering area according to the splicing identification layout specification to obtain the engineering area to be measured;

[0022] Set the station point layout specification, set the station points for the engineering area to be measured according to the station point layout specification, configure the first total station at the station points; call the first total station to perform photogrammetry on the engineering area to be measured to obtain the global coordinate system of the engineering area for the high-precision measurement engineering area;

[0023] Perform surface scanning processing on the high-precision measurement engineering area based on the global coordinate system of the engineering area to obtain the first data to be spliced.

[0024] As an improved solution, the global laser scanning step includes:

[0025] Set the scanning range; configure a second total station instrument, and build a measurement control network for the passenger aircraft fuselage based on the second total station instrument;

[0026] Set the layout specification of the reflective units; first, configure a number of reflective units in the measurement space where the passenger aircraft fuselage is located according to the layout specification of the reflective units, and then confirm the visible positions; at the visible positions, perform global measurement of the passenger aircraft fuselage according to the scanning range and based on the measurement control network and the second total station instrument to obtain a number of global measurement coordinates; then perform resection measurement based on the measurement control network and the second total station instrument to obtain a number of resection point coordinates; integrate a number of the global measurement coordinates and a number of the resection point coordinates to obtain the fuselage global coordinate system;

[0027] Perform a block layout process on the passenger aircraft fuselage to obtain a number of sub-measurement scanning blocks; configure a number of splicing spheres and a number of measurement stations respectively corresponding to the number of sub-measurement scanning blocks; set a number of measurement strategies respectively matching the number of measurement stations; call the number of measurement stations respectively according to the number of measurement strategies to perform laser scanning on the number of sub-measurement scanning blocks respectively to obtain a number of scanning data; convert the number of scanning data into a number of first fuselage point cloud data based on the fuselage global coordinate system; set the number of first fuselage point cloud data as the number of second data to be spliced respectively.

[0028] As an improved solution, the data splicing process operation includes:

[0029] Configure a data processing program and a point cloud preprocessing program;

[0030] Input a number of the third cockpit data, a number of the first data to be spliced, and a number of the second data to be spliced into the data processing program;

[0031] Call the data processing program to perform noise reduction processing on a number of the third cockpit data, a number of the first data to be spliced, and a number of the second data to be spliced respectively;

[0032] Call the data processing program to perform multi-view splicing on the number of the first data to be spliced after noise reduction processing according to the number of splicing identifiers to obtain precise component point cloud data;

[0033] Call the data processing program to perform multi-view splicing on the number of the second data to be spliced after noise reduction processing based on the sphere spacing between the number of splicing spheres to obtain large component point cloud data;

[0034] Perform fusion processing on the point cloud data of the precision component, the point cloud data of the large component, and the third cockpit data based on the data processing program and the point cloud preprocessing program to obtain a point cloud model;

[0035] Identify the shape features of the point cloud model, perform block processing on the point cloud model based on the shape features to obtain a number of model blocks; perform data patching processing on the number of model blocks respectively to obtain a number of to-be-converted models;

[0036] Construct a surface model according to the surface fitting accuracy and based on the number of to-be-converted models; obtain the required format, and convert the surface model into the required format to obtain the airliner scan information.

[0037] As an improved solution, the steps of the fusion processing further include:

[0038] Call the data processing program to perform triangulation processing on the point cloud data of the precision component, the point cloud data of the large component, and the third cockpit data respectively to obtain a number of to-be-fused point clouds with consistent normal vectors;

[0039] Call the point cloud preprocessing program to read the number of to-be-fused point clouds, call the point cloud preprocessing program to calculate the fusion point information of the number of to-be-fused point clouds using the clustering fusion algorithm, and call the point cloud preprocessing program to fuse the number of to-be-fused point clouds according to the fusion point information to obtain the point cloud model.

[0040] The present invention also provides an information acquisition system for a large airliner, including:

[0041] A parameter information creation module for setting precision parameters and obtaining airliner information; the parameter information creation module creates a set of to-be-measured component information according to the airliner information;

[0042] A partition measurement and acquisition module for performing partition acquisition operations according to the precision parameters and the set of to-be-measured component information to obtain to-be-processed data;

[0043] A data splicing processing module for performing data splicing processing operations according to the precision parameters and the to-be-processed data to obtain airliner scan information.

[0044] The present invention also provides a computer-readable storage medium, on which a computer program is stored, and when the computer program is executed by a processor, the steps of the information acquisition method for a large airliner are implemented.

[0045] The beneficial effects of the present invention are:

[0046] 1. The information acquisition method for large airliners according to the present invention can adapt different precision parameters to different component areas of large airliners and use different scanning methods for zonal scanning. Moreover, the on-site scanning process only needs to measure half of the fuselage. Subsequently, through the designed data processing logic, all point cloud data for the entire large airliner can be generated, and a complete aircraft model can be generated based on the point cloud data. The information acquisition has high precision, high acquisition efficiency, strong operational expandability, and extremely high applicability and foresight.

[0047] 2. The information acquisition system for large airliners according to the present invention can, through the mutual cooperation of the parameter information creation module, the zonal measurement and acquisition module, and the data splicing and processing module, adapt different precision parameters to different component areas of large airliners and use different scanning methods for zonal scanning. Moreover, the on-site scanning process only needs to measure half of the fuselage. Subsequently, through the designed data processing logic, all point cloud data for the entire large airliner can be generated, and a complete aircraft model can be generated based on the point cloud data. The information acquisition has high precision, high acquisition efficiency, strong operational expandability, and extremely high applicability and foresight.

[0048] 3. The computer-readable storage medium according to the present invention can guide the parameter information creation module, the zonal measurement and acquisition module, and the data splicing and processing module to cooperate, thereby adapting different precision parameters to different component areas of large airliners and using different scanning methods for zonal scanning. Moreover, the on-site scanning process only needs to measure half of the fuselage. Subsequently, through the designed data processing logic, all point cloud data for the entire large airliner can be generated, and a complete aircraft model can be generated based on the point cloud data. The information acquisition has high precision, high acquisition efficiency, strong operational expandability, makes up for the deficiencies of the prior art, and effectively improves the operability of the information acquisition method for large airliners. BRIEF DESCRIPTION OF THE DRAWINGS

[0049] In order to more clearly illustrate the specific embodiments of the present invention or the technical solutions in the prior art, the following will briefly introduce the drawings required for use in the description of the specific embodiments or the prior art. Obviously, the drawings in the following description are some embodiments of the present invention. For those of ordinary skill in the art, without creative efforts, other drawings can be obtained based on these drawings.

[0050] Figure 1 is the flowchart of the information acquisition method for large airliners according to Embodiment 1 of the present invention;

[0051] Figure 2 is the specific process schematic diagram of the information acquisition method for large airliners according to Embodiment 1 of the present invention;

[0052] Figure 3 It is a schematic plan view of the layout specification of the reflective units in the information collection method for large airliners described in Embodiment 1 of the present invention;

[0053] Figure 4 It is a schematic plan view of the block layout processing in the information collection method for large airliners described in Embodiment 1 of the present invention;

[0054] Figure 5 It is an architecture diagram of the information collection system for large airliners described in Embodiment 2 of the present invention. Detailed implementation manners

[0055] The following elaborates on the preferred embodiments of the present invention in conjunction with the accompanying drawings, so that the advantages and features of the present invention can be more easily understood by those skilled in the art, thereby making the protection scope of the present invention more clearly defined.

[0056] In the description of the present invention, it should be noted that the embodiments described in the present invention are some embodiments of the present invention, rather than all embodiments; all other embodiments obtained by those of ordinary skill in the art based on the embodiments in the present invention without creative efforts belong to the scope of protection of the present invention.

[0057] In the description of the present invention, it should be noted that the terms "first", "second", and "third" are only used for descriptive purposes and cannot be construed as indicating or implying relative importance.

[0058] In the description of the present invention, it should be noted that unless otherwise clearly defined and limited, the terms "precision of precision components", "precision of large components", "precision of component splicing", "precision of surface fitting", "precision parameters", "airliner information", "set of information of components to be measured", "partitioned acquisition operation", "data splicing processing operation", "airliner scanning information", "airliner component information", "airliner plane drawing", "information of components to be scanned", "information of precision components to be measured", "coding measurement step", "global laser scanning step", "spatial laser scanning", "layout specification of splicing marks", "layout specification of coding points", "layout specification of standing points", "global coordinate system of the engineering area", "surface scanning processing", "", "measurement control network", "layout specification of reflective units", "global measurement coordinate", "resection measurement", "global coordinate system of the fuselage", "block layout processing", "sub-measurement scanning block", "fusion processing", "block processing", "data repair processing", "required format", "triangulation processing", "normal consistency", "parameter information creation module", "partitioned measurement acquisition module", "data splicing processing module" should be understood in a broad sense. For those of ordinary skill in the art, the specific meanings of the above terms in the present invention can be understood according to specific situations.

[0059] In the description of the present invention, it should be noted that: 2D is a planar animation method; Faro Photon 80 is a laser scanner model; NET05 is a total station model; FARO is a laser scanner model; Geomagic is a reverse engineering software; Imageware is a reverse engineering software; UGII is an engineering software; VC6 ++ is a programming tool; matlab is a programming software; XJTUOM is a three-dimensional optical scanning system; NURBS is a modeling method; CAD is a drafting software; IGES is a graphics file format.

[0060] Embodiment 1

[0061] This embodiment provides an information acquisition method for large airliners, as Figures 1 to 4 shown, including the following steps:

[0062] S100. Parameter information creation step, specifically including:

[0063] S110. Set accuracy parameters; obtain airliner information; create a set of information on components to be measured according to the airliner information;

[0064] Specifically, the accuracy parameters include: the accuracy of the first precision component, the accuracy of the second large component, the accuracy of the third component splicing, and the surface fitting accuracy; in this embodiment, all measurement and scanning steps are carried out based on a certain detection accuracy. Correspondingly, in this method, different measurement accuracy requirements are adapted to different measurement steps of large airliners, thereby improving the measurement adaptability for different components of airliners to a certain extent and improving the measurement accuracy and measurement efficiency; correspondingly, the accuracy of the first precision component is the measurement accuracy parameter for high-precision components in the airliner; the accuracy of the second large component is the measurement accuracy parameter for large components in the airliner; the accuracy of the third component splicing is the accuracy parameter for the splicing of large components in the airliner; the surface fitting accuracy is the accuracy requirement when generating a surface model according to point cloud data subsequently; specifically, in this embodiment, the accuracy of the first precision component is: the measurement accuracy in the airfoil direction of the wing, wing-body fairing, and tail wing of the airliner is not less than 0.1 mm, and the measurement accuracy in the wingspan direction of the airliner is not less than 1 mm; the accuracy of the second large component is: the measurement accuracy of the nose and the rear fuselage of the airliner is not less than 0.5 mm, and the measurement accuracy of the middle fuselage section of the airliner is not less than 1 mm; the accuracy of the third component splicing is: when the measured data is docked, the docking accuracy of large components is not less than 2 mm; the surface fitting accuracy is: when generating a surface with the measured data in subsequent data processing operations, the deviation in the surface normal direction from the original data is not less than 0.2 mm; based on the above accuracy parameter requirements, the measurement accuracy and measurement diversity of this method are ensured.

[0065] Specifically, the airliner information includes: airliner model information, airliner component information and airliner plane drawings that match the airliner model information; the airliner information is the basic information of the airliner for which information collection is to be performed; the airliner model information is, for example, "airliner manufacturer + airliner model"; the airliner plane drawing is a 2D drawing of the external frame structure of the airliner fuselage, which includes the outlines of positions such as the fuselage, wings and engines; the airliner component information is the component names and dimensional parameters respectively corresponding to each graphic outline in the airliner plane drawing, etc.

[0066] Specifically, the step of creating the set of parts to be measured according to the airliner information further includes: setting the parts to be scanned and the precision parts to be measured based on the airliner component information; integrating the parts to be scanned information and the precision parts to be measured information to obtain the set of parts to be measured; in this embodiment, the parts to be scanned information includes: the airliner fuselage and the airliner cockpit; specifically, the precision parts to be measured information includes: the airliner wings; correspondingly, in this embodiment, for high-precision parts such as airliner wings, photogrammetry is used for information collection, and for large parts such as the airliner fuselage and the airliner cockpit, laser scanning is used for information collection.

[0067] S200. Zoning measurement and collection step, which specifically includes:

[0068] S210. Perform a zoning collection operation based on the precision parameters and the set of parts to be measured to obtain the data to be processed;

[0069] Specifically, the partitioned acquisition operation includes: dividing the airliner wing into several high-precision measurement engineering areas; in this embodiment, the airliner wing is divided into the upper wing, lower wing, aileron, trailing edge flap, winglet, fuselage joint (wing-body fairing), flap bulge, leading edge slat, and spoiler; correspondingly, the above several components are respectively several high-precision measurement engineering areas. Specifically, each engineering area is approximately 36 square meters, and both the upper surface and the lower surface of each area need to be measured; first, start photogrammetry, so perform the encoding measurement step according to the precision of the first precision component and the several high-precision measurement engineering areas, and obtain several first data to be stitched respectively corresponding to the several high-precision measurement engineering areas; the several first data to be stitched are the point cloud data respectively corresponding to the upper wing, lower wing, aileron, trailing edge flap, winglet, fuselage joint (wing-body fairing), flap bulge, leading edge slat, and spoiler, which are used for subsequent stitching processing to generate the complete point cloud data of the aircraft; correspondingly, it is also necessary to perform a global laser scanning step on the airliner fuselage according to the precision of the second large component to obtain several second data to be stitched; the several second data to be stitched are the point cloud data for the airliner fuselage, which are used for subsequent stitching processing to generate the complete point cloud data of the aircraft; perform a spatial laser scanning on the airliner cockpit according to the precision of the second large component to obtain the third cockpit data; the spatial laser scanning of the airliner cockpit is a large-space laser scanning, which is realized by using a Faro Photon 80 scanner, and the obtained third cockpit data is also the point cloud data to be stitched; therefore, integrate the third cockpit data, the several first data to be stitched, and the several second data to be stitched to obtain the data to be processed.

[0070] Specifically, the encoding measurement step for any one of the above high-precision measurement engineering areas includes:

[0071] Set the splicing mark layout specification; identify the area value of the high-precision measurement engineering area, and set the coding point layout specification based on the area value; in this embodiment, the area value of the engineering area is about 36 square meters, and the corresponding coding point layout specification is: use 15mm coding points and non-coding points, and set the shooting distance to about 6m. Therefore, the operation area of a corresponding high-precision measurement engineering area is about 72 square meters. So, according to two coding points per square meter, about 150 coding points are needed, and according to eight non-coding points per square meter, about 560 non-coding points are needed; for different positions of the wing, use coding points with rubber on the upper surface of the wing, and use pasteable non-coding points without rubber on the lower surface of the wing; correspondingly, for each high-precision measurement engineering area, 5 to 6 15mm non-coding points with crosshairs are also needed for the total station; correspondingly, during application, for the wing root, the coding points / non-coding points can be directly placed on the wing connection part, and for the thinner parts of the wing, the coding points / non-coding points can be placed on the foam or placed on the wing edge through auxiliary devices; correspondingly, in this embodiment, the splicing mark layout specification is: set corresponding splicing marks for subsequent aircraft point cloud data splicing. For the splicing marks on the upper and lower surfaces of the wing root, use the scaffolding, fuselage, connecting parts of the upper and lower surfaces of the wing, engine, and wing fairing parts as splicing mark settings; for the thinner parts outside the wing, use the scaffolding and foam as splicing mark settings; correspondingly, if foam is used for splicing mark setting, for the outside of the wing, use foam of a certain size, cut a 200mm - 500mm notch in the foam, and clamp it on the wing to ensure that the protruding part of the foam is more than 1m for use as a splicing mark; correspondingly, in this embodiment, the size of the foam is selected as 1.3 meters * 6 meters * 0.3 meters; therefore, first, a number of coding points and a number of non-coding points are set in the high-precision measurement engineering area according to the coding point layout specification, and then a number of splicing marks are set in the high-precision measurement engineering area according to the splicing mark layout specification to obtain the engineering area to be measured; a station point layout specification is set. In this embodiment, the station point layout specification is to set a total station for photogrammetry at 4 stations, and the maximum distance between each station and the marked points to be measured needs to be about 20 m; therefore, the station points for the engineering area to be measured are set according to the station point layout specification, and a first total station is configured at the station points; the first total station is called to perform photogrammetry on the engineering area to be measured to obtain the global coordinate system of the engineering area for the high-precision measurement engineering area; after the global coordinate system of the high-precision measurement engineering area is obtained through total station photogrammetry, large-format scanning of components can be performed, and the point cloud coordinates of the corresponding scanned components are determined according to the global coordinate system, and finally the corresponding component point cloud data is obtained. Therefore, surface scanning processing is performed on a number of the high-precision measurement engineering areas based on the global coordinate system of the engineering area to obtain the first data to be spliced; the surface scanning processing in this embodiment is large-format scanning processing.

[0072] Specifically, the global laser scanning steps include:

[0073] Set the scanning range; configure a second total station, and build a measurement control network for the fuselage of the airliner based on the second total station; in this embodiment, the second total station uses a Sokkia NET05 total station for overall control to improve the measurement accuracy; correspondingly, the scanning range is a scanning distance of 15 m; set the layout specification of the reflective unit. First, a number of reflective units are configured in the measurement space where the fuselage of the airliner is located according to the layout specification of the reflective unit. Correspondingly, in this embodiment, such as Figure 3As shown, the layout specification of the reflective unit is to paste reflective sheets on the walls of the hangar where the airliner is located, and auxiliary equipment such as on-site tripods can be used as a support and reflective sheets are pasted; when pasting the reflective sheets, it is necessary to consider the positions blocked by the baffle of the landing gear and the engines on both sides of the airliner and make adaptive adjustments to the pasting positions of the reflective sheets; correspondingly, then confirm the unobstructed positions; perform left-disk and right-disk photogrammetry at the unobstructed positions, and at the same time, according to the scanning range, that is, only take the measurement data within the scanning range as the calculation data, and at the same time, based on the measurement control network and the second total station, perform global measurement on the fuselage of the airliner to obtain a number of global measurement coordinates; correspondingly, in order to further improve the coordinate system, so then perform resection measurement based on the second total station to obtain a number of resection point coordinates. In this embodiment, a plurality of resection measurement positions are set. When performing resection measurement on each resection measurement position in sequence, select 4 to 6 reflective sheets at different horizontal heights for resection measurement, and at the same time measure 3 reflective sheets that are not for resection measurement. Compare the measured coordinates with the global measurement coordinates. If the deviation is within 1 mm, then continue with the resection measurement of the next position. If the deviation is not within 1 mm, it means that the error is large and the resection measurement calculation for this position needs to be redone. Finally, a number of resection point coordinates can be obtained; therefore, integrate a number of the global measurement coordinates and a number of the resection point coordinates to obtain the global coordinate system of the fuselage; correspondingly, after obtaining the global coordinate system of the fuselage based on the total station, the corresponding scanning measurement can be carried out; perform block layout processing on the fuselage of the airliner to obtain a number of sub-scanning blocks, such as Figure 4As shown, in this embodiment, the passenger aircraft fuselage is divided into 4 large sections, namely the nose, the left wing, the right wing, and the tail; several splicing balls, several auxiliary identifiers, and several measurement stations corresponding to several of the sub-measurement scanning blocks are configured; correspondingly, in this embodiment, splicing balls are used as the point cloud splicing identifiers for each block, and plane circles are used for auxiliary splicing, that is, as the auxiliary identifiers; correspondingly, in this embodiment, there are 4 - 6 splicing balls between each pair of measurement stations, and it is ensured that there are 4 - 6 plane circles in each measurement station; the plane circles are used to convert a single-frame point cloud to the total station when splicing based on the splicing balls fails; correspondingly, in this embodiment, the measurement stations include measurement stations at different distances and a bottom surface measurement station, for example: the measurement station facing the engine, the ground measurement station, the 10 - 13m measurement station, and the 2 - 3m measurement station; the splicing balls include: standard balls (fixed splicing spherical balls), splicing spherical balls placed on the ground, splicing spherical balls placed on a 1m high tripod, and splicing spherical balls placed at a 3m high fixed position; in this embodiment, the step of configuring several splicing balls, several auxiliary identifiers, and several measurement stations corresponding to several of the sub-measurement scanning blocks further includes: setting 4 standard balls on the fuselage of the passenger aircraft, setting 2 - 3 standard balls on each of the left and right wings of the passenger aircraft, and setting 1 standard ball on each side of the horizontal tail of the passenger aircraft. Correspondingly, they are evenly placed from above the nose of the passenger aircraft to below the vertical tail, and these standard balls do not move during the overall scanning process; correspondingly, for the nose part of the passenger aircraft, 15 splicing balls, 21 plane circles, 4 laser scanning ground measurement stations, and 3 10 - 13m measurement stations are set; for the left wing of the passenger aircraft, a total of 19 splicing balls, 27 plane circles, 5 laser scanning ground measurement stations, 2 10 - 13m measurement stations, and 1 measurement station facing the engine are set; for the right wing of the passenger aircraft, a total of 19 splicing balls, 27 plane circles, 5 laser scanning ground measurement stations, 2 10 - 13m measurement stations, and 1 measurement station facing the engine are set; for the tail of the passenger aircraft, a total of 12 splicing balls, 14 plane circles, 4 laser scanning ground measurement stations, and 2 10 - 13m measurement stations are set; correspondingly, in this embodiment, the measurement stations further include a gantry crane, and the gantry crane is set at a high place and 2 stations are set; then several measurement strategies respectively matching several of the measurement stations are set; according to several of the measurement strategies, several of the measurement stations are respectively called to perform laser scanning on several of the sub-measurement scanning blocks to obtain several sets of scanning data; in this embodiment, the measurement strategy is the measurement logic for the ground measurement station and the high-altitude measurement station, and specifically includes: all use FARO laser scanning for scanning, and the scanning logic for the ground measurement station is: first use 1 / 16 global scanning, then use 1 / 5 for key area scanning of components, and finally use 1 / 1 for detailed scanning at the splicing balls and plane circles; the scanning logic for the high-altitude measurement station is: when the high-altitude measurement station is stable and does not shake, adopt the same scanning logic as the ground measurement station;If the high-altitude measurement station is unstable and shakes, first use 1 / 5 for global scanning, and then increase the number of plane circles (auxiliary marks) of each high-altitude measurement station. When increasing, place the plane circles close to the high-altitude measurement stations, and directly convert the data of each high-altitude measurement station scanned by the laser into the same total station coordinate system; correspondingly, after scanning, based on the global coordinate system of the fuselage, convert the scanned data into a number of first fuselage point cloud data; set the number of first fuselage point cloud data as a number of second data to be stitched; through FARO laser scanning in cooperation with stitching balls and plane circles, higher scanning accuracy and scanning resolution can be achieved.

[0074] S300. Data stitching and processing steps, specifically including:

[0075] S310. Perform data stitching and processing operations based on the accuracy parameters and the data to be processed to obtain the scanned information of the airliner; correspondingly, after obtaining the above point cloud data, perform corresponding post-data processing to obtain the complete aircraft model of the large airliner;

[0076] Specifically, the data stitching and processing operations include:

[0077] Configure a data processing program and a point cloud preprocessing program; in this embodiment, the point cloud preprocessing program uses the XJTUOM point cloud preprocessing software, and the data processing program includes: Geomagic, Imageware, and UGII, etc.; when performing data processing calculations, use VC6++ and matlab as auxiliary calculation software;

[0078] First, data input is required. Therefore, a number of the third cockpit data, a number of the first data to be spliced, and a number of the second data to be spliced are input into the data processing program. In this embodiment, the data is input into Geomagic. Then, the data processing program (Geomagic) is called to perform noise reduction processing on a number of the third cockpit data, a number of the first data to be spliced, and a number of the second data to be spliced respectively. Correspondingly, noise reduction processing is beneficial to subsequent splicing processing of the data. The steps of noise reduction processing further include: First, delete the background noise points and significant outliers in the point cloud data in the Geomagic software. Then, calculate the noise amplitude of the scanned coordinate points. According to the noise amplitude of the scanned points, determine the filtering parameters to be used, and perform smoothing processing on the scanned point data according to the filtering parameters. Correspondingly, during noise reduction processing, for point cloud data containing detailed features, it is necessary to segment the point cloud according to the curvature feature, and perform noise reduction processing on each segmented point cloud respectively. Thus, while achieving noise reduction, the detailed geometric features of the point cloud data are also retained. After noise reduction processing, it is necessary to splice the scattered point cloud data. For high-precision components, that is, the point cloud data measured by the coded points of the wing part, the data processing program is called to perform multi-view splicing on a number of the first data to be spliced after noise reduction processing according to a number of the splicing identifiers to obtain the point cloud data of the precision component. For the point cloud data obtained by laser scanning of the fuselage part, the data processing program is called to perform multi-view splicing on a number of the second data to be spliced after noise reduction processing based on the spherical distance between a number of the splicing balls to obtain the point cloud data of the large component. Correspondingly, the steps of performing multi-view splicing on a number of the second data to be spliced after noise reduction processing further include: First, fit the standard balls in each point cloud data, and then calculate the center distance between the standard balls. After the calculation, in order to ensure the splicing accuracy, the error of the distance between the same-name standard balls is checked to ensure that the distance between the fitting balls of the measured point cloud is within the set error range (the error range is less than 0.2 mm). Then, the Geomagic software is used to perform multi-view point cloud splicing with error averaging according to the distance between the standard balls. Correspondingly, when performing point cloud multi-view splicing based on the spherical distance of the standard balls, the icp algorithm is used by the Geomagic software to perform precise point cloud matching to ensure the precise positional relationship between two point clouds and improve the splicing accuracy. Correspondingly, after all splicing is completed, the precision component point cloud data, the large component point cloud data, and the third cockpit data are subjected to fusion processing based on the data processing program and the point cloud preprocessing program to obtain a point cloud model. In this embodiment, because there is a large amount of data redundancy in multiple point cloud data, which will cause a multi-layer phenomenon in local point clouds, it is necessary to perform point cloud data fusion, thereby deleting a large amount of point cloud data redundancy, so as to fuse multiple point clouds into a single point cloud, improving the subsequent processing efficiency and point cloud accuracy.In this embodiment, the steps of the fusion process further include: calling the data processing program to perform triangulation processing on the point cloud data of the precision component, the point cloud data of the large component, and the third cockpit data respectively, to obtain a number of point clouds to be fused with consistent normal directions. That is, first call Geomagic to perform triangulation processing on multiple point cloud data (i.e., the point cloud data of the precision component, the point cloud data of the large component, and the third cockpit data), and obtain point cloud data with consistent normal directions (i.e., a number of point clouds to be fused); then call the point cloud preprocessing program to read a number of the point clouds to be fused, call the point cloud preprocessing program to calculate the fusion point information of a number of the point clouds to be fused using the clustering fusion algorithm, and call the point cloud preprocessing program to fuse a number of the point clouds to be fused according to the fusion point information to obtain the point cloud model; correspondingly, in this embodiment, after obtaining the point cloud data with consistent normal directions, save the text file containing normal information, and then call the point cloud preprocessing program (i.e., XJTUOM point cloud preprocessing software) to read a number of the point clouds to be fused, and calculate the point cloud fusion points based on the clustering-based fusion algorithm, and then call the point cloud preprocessing program to fuse the point cloud data according to the point cloud fusion points, and the obtained point cloud model is a single-layer point cloud model; correspondingly, in order to further improve the subsequent data processing efficiency, the shape features of the point cloud model (such as shape features of the wing, fuselage, and nose, etc.) are identified, and the point cloud model is segmented based on the shape features to obtain a number of model blocks; correspondingly, in this embodiment, the number of model blocks are respectively model blocks corresponding to the front part of the fuselage, the rear part of the fuselage, the front wing, the rear wing, the tail wing, the engine, and the vertical tail; in this embodiment, the segmentation process is carried out in a human-computer interaction manner, and manual selection of the point cloud area is used for segmentation, and the selection of the point cloud area needs to ensure that the boundary of the point cloud area is a part with a low curvature change, and the shape integrity of each area needs to be ensured; after segmentation, in order to further improve the data accuracy, data repair processing is performed on a number of the model blocks respectively to obtain a number of models to be converted; the principle of the data repair processing is to repair the holes caused by local scanning in the point cloud data, so the corresponding holes need to be filled; in this embodiment, the steps of the data repair processing further include: calling Geomagic software to perform point cloud triangulation processing, and then supplementing the small gaps and hole positions of the point cloud according to the curvature of the local area; after the data repair processing, surface construction can be carried out, so a surface model is constructed according to the surface fitting accuracy and based on a number of the models to be converted; in this embodiment, the surface model is directly constructed from the triangular patches; specifically, the step of constructing the surface model according to the surface fitting accuracy, that is, it is necessary to ensure that the accuracy requirements set at the beginning are met when constructing the surface, and based on a number of the models to be converted, the steps of constructing the surface model further include: constructing corresponding boundary lines on the triangular mesh surface according to the geometric shape of each model to be converted;Construct a quadrilateral mesh surface, then adjust the mesh parameter lines, and then convert the quadrilateral mesh surface into a NURBS surface CAD model; correspondingly, the obtained CAD model is the surface model; finally, error verification is required, that is, analyze and compare the constructed CAD surface model with the original point cloud model before construction to detect the digital model construction error between the two; for the model parts with more errors, the quadrilateral mesh surface needs to be readjusted and the CAD model needs to be regenerated to ensure the accuracy of the model; finally, obtain the required format of the user, convert the surface model into the required format, and convert the constructed CAD surface model into a common exchange data format for output to the customer; correspondingly, in this embodiment, the exchange data format includes but is not limited to the IGES format; the file after converting the format of the surface model is the required airliner scan information of the user; correspondingly, in this embodiment, the step of converting the surface model into the required format to obtain the airliner scan information further includes: performing surface sampling on the CAD surface model on the premise of controlling the error, converting the sampling data into a point cloud model, and saving the obtained point cloud model in the text file format containing three-dimensional coordinate points.;

[0079] Embodiment 2

[0080] Based on the same inventive concept as the information acquisition method for a large airliner described in Embodiment 1, this embodiment provides an information acquisition system for a large airliner, as Figure 5 shown, including:

[0081] A parameter information creation module for setting accuracy parameters and obtaining airliner information; the parameter information creation module creates a set of information on components to be measured according to the airliner information;

[0082] Specifically, the accuracy parameters include: the accuracy of the first precision component, the accuracy of the second large component, the accuracy of the third component splicing, and the accuracy of surface fitting; the airliner information includes: airliner model information, airliner component information and airliner plane drawings matching the airliner model information.

[0083] Specifically, the parameter information creation module sets the information on components to be scanned and the information on precision components to be measured based on the airliner component information; the parameter information creation module integrates the information on components to be scanned and the information on precision components to be measured to obtain the set of information on components to be measured.

[0084] A partition measurement and acquisition module for performing partition acquisition operations according to the accuracy parameters and the set of information on components to be measured to obtain data to be processed;

[0085] Specifically, the information on components to be scanned includes: the airliner fuselage and the airliner cockpit; the information on precision components to be measured includes: the airliner wing;

[0086] Specifically, the partitioned acquisition operation includes: the partitioned measurement acquisition module divides the wing of the airliner into several high-precision measurement engineering areas; the partitioned measurement acquisition module performs coded measurement steps on the several high-precision measurement engineering areas respectively according to the precision of the first precision component to obtain several first data to be spliced corresponding to the several high-precision measurement engineering areas respectively; the partitioned measurement acquisition module performs a global laser scanning step on the fuselage of the airliner according to the precision of the second large component to obtain several second data to be spliced; the partitioned measurement acquisition module performs a spatial laser scanning on the cockpit of the airliner according to the precision of the second large component to obtain third cockpit data; the partitioned measurement acquisition module integrates the third cockpit data, the several first data to be spliced, and the several second data to be spliced to obtain the data to be processed.

[0087] Specifically, the coded measurement step includes: the partitioned measurement acquisition module sets the splicing identification layout specification; the partitioned measurement acquisition module identifies the area value of the high-precision measurement engineering area and sets the coded point layout specification based on the area value; first, the partitioned measurement acquisition module sets several coded points and several non-coded points in the high-precision measurement engineering area according to the coded point layout specification, and then the partitioned measurement acquisition module sets several splicing identifications in the high-precision measurement engineering area according to the splicing identification layout specification to obtain the engineering area to be measured; the partitioned measurement acquisition module sets the station point layout specification, the partitioned measurement acquisition module sets the station points for the engineering area to be measured according to the station point layout specification, and the partitioned measurement acquisition module configures a first total station at the station points; the partitioned measurement acquisition module calls the first total station to perform photogrammetry on the engineering area to be measured to obtain the global coordinate system of the engineering area for the high-precision measurement engineering area; the partitioned measurement acquisition module performs surface scanning processing on the high-precision measurement engineering area based on the global coordinate system of the engineering area to obtain the first data to be spliced.

[0088] Specifically, the global laser scanning step includes: the partition measurement acquisition module sets the scanning range; the partition measurement acquisition module configures a second total station, and the partition measurement acquisition module builds a measurement control network for the airliner fuselage based on the second total station; the partition measurement acquisition module sets the layout specification of the reflective units; first, the partition measurement acquisition module configures a number of reflective units in the measurement space where the airliner fuselage is located according to the layout specification of the reflective units, and then the partition measurement acquisition module confirms the clear view positions; at the clear view positions, the partition measurement acquisition module performs global measurement on the airliner fuselage according to the scanning range and based on the measurement control network and the second total station to obtain a number of global measurement coordinates; then, the partition measurement acquisition module performs resection measurement based on the measurement control network and the second total station to obtain a number of resection point coordinates; the partition measurement acquisition module integrates a number of the global measurement coordinates and a number of the resection point coordinates to obtain a fuselage global coordinate system; the partition measurement acquisition module performs block layout processing on the airliner fuselage to obtain a number of sub-measurement scanning blocks; the partition measurement acquisition module configures a number of splicing balls and a number of measurement stations respectively corresponding to the number of sub-measurement scanning blocks; the partition measurement acquisition module sets a number of measurement strategies respectively matching the number of measurement stations; the partition measurement acquisition module respectively calls the number of measurement stations according to the number of measurement strategies to perform laser scanning on the number of sub-measurement scanning blocks to obtain a number of scanning data; the partition measurement acquisition module converts the number of scanning data into a number of first fuselage point cloud data based on the fuselage global coordinate system; the partition measurement acquisition module sets a number of the first fuselage point cloud data as a number of the second data to be spliced.

[0089] The data splicing processing module is used to perform data splicing processing operations according to the accuracy parameters and the data to be processed to obtain airliner scanning information;

[0090] Specifically, the data splicing and processing operation includes: the data splicing and processing module configures a data processing program and a point cloud preprocessing program; the data splicing and processing module inputs a number of the third cockpit data, a number of the first data to be spliced, and a number of the second data to be spliced into the data processing program; the data splicing and processing module calls the data processing program to perform noise reduction processing on a number of the third cockpit data, a number of the first data to be spliced, and a number of the second data to be spliced respectively; the data splicing and processing module calls the data processing program to perform multi-view splicing on the noise-reduced first data to be spliced according to a number of the splicing identifiers to obtain precise component point cloud data; the data splicing and processing module calls the data processing program to perform multi-view splicing on the noise-reduced second data to be spliced based on the spherical distances between a number of the splicing spheres to obtain large component point cloud data; the data splicing and processing module performs fusion processing on the precise component point cloud data, the large component point cloud data, and the third cockpit data based on the data processing program and the point cloud preprocessing program to obtain a point cloud model; the data splicing and processing module identifies the shape features of the point cloud model, and the data splicing and processing module performs block processing on the point cloud model based on the shape features to obtain a number of model blocks; the data splicing and processing module performs data patching processing on a number of the model blocks respectively to obtain a number of models to be converted; the data splicing and processing module constructs a surface model according to the surface fitting accuracy and based on a number of the models to be converted; the data splicing and processing module obtains a required format, and the data splicing and processing module converts the surface model into the required format to obtain the airliner scan information.

[0091] Specifically, the operation of the data splicing and processing module for performing the fusion processing further includes: the data splicing and processing module calls the data processing program to perform triangulation processing on the precise component point cloud data, the large component point cloud data, and the third cockpit data respectively to obtain a number of point clouds to be fused with consistent normal vectors; the data splicing and processing module calls the point cloud preprocessing program to read a number of the point clouds to be fused, the data splicing and processing module calls the point cloud preprocessing program to calculate the fusion point information of a number of the point clouds to be fused by using a clustering fusion algorithm, and the data splicing and processing module calls the point cloud preprocessing program to fuse a number of the point clouds to be fused according to the fusion point information to obtain the point cloud model.

[0092] Embodiment 3

[0093] This embodiment provides a computer-readable storage medium, including:

[0094] The storage medium is used to store computer software instructions for implementing the information acquisition method for large airliners described in the above-mentioned Embodiment 1, and it includes a program for executing the procedures set for the information acquisition method for large airliners. Specifically, the executable program can be built into the information acquisition system for large airliners described in Embodiment 2. In this way, the information acquisition system for large airliners can implement the information acquisition method for large airliners described in the above-mentioned Embodiment 1 by executing the built-in executable program.

[0095] In addition, the computer-readable storage medium of this embodiment can adopt any combination of one or more readable storage media. Among them, the readable storage medium includes systems, devices or components of electricity, light, electromagnetism, infrared rays or semiconductors, or any combination of the above.

[0096] Different from the prior art, by using an information acquisition method, system and medium for large airliners of the present application, different precision parameters can be adapted to different component areas of the large airliner and different scanning methods can be used for zonal scanning. Moreover, only half of the fuselage needs to be measured in the on-site scanning process. Subsequently, through the designed data processing logic, all point cloud data for the entire large airliner can be generated, and a complete aircraft model can be generated based on the point cloud data. The system provides effective technical support for this method. Finally, the information acquisition achieved has high precision, high acquisition efficiency, strong operation expandability, and extremely high applicability and foresight.

[0097] The serial numbers of the disclosed embodiments in the present invention above are only for description and do not represent the advantages or disadvantages of the embodiments.

[0098] Those of ordinary skill in the art can understand that all or part of the steps for implementing the above-mentioned embodiments can be completed by hardware, or can be completed by a program instructing relevant hardware. The program can be stored in a computer-readable storage medium. The above-mentioned storage medium can be a read-only memory, a magnetic disk or an optical disc, etc.

[0099] The above are only the embodiments of the present invention, and do not limit the patent scope of the present invention accordingly. Any equivalent structure or equivalent process transformation made by using the content of the specification and drawings of the present invention, or directly or indirectly applied in other related technical fields, shall be equally included in the patent protection scope of the present invention.

Claims

1. An information collection method for large airliners, characterized in that It includes the following steps: Parameter information creation step: Set the precision parameters and obtain the airliner information; Based on the airliner component information, set the information of the components to be scanned and the precision components to be measured; Integrate the information of the components to be scanned and the information of the precision components to be measured to obtain a set of information of the components to be measured; The precision parameters include: the precision of the first precision component, the precision of the second large component, the precision of the third component splicing, and the precision of surface fitting; Partition measurement and acquisition step: Perform a partition acquisition operation based on the precision parameters and the set of information of the components to be measured to obtain the data to be processed; The partition acquisition operation includes: Divide the airliner wing into several high-precision measurement engineering areas; Perform coded measurement steps on several of the high-precision measurement engineering areas respectively according to the precision of the first precision component to obtain several first data to be spliced corresponding to several of the high-precision measurement engineering areas respectively; Perform a global laser scanning step on the airliner fuselage according to the precision of the second large component to obtain several second data to be spliced; Perform a spatial laser scanning on the airliner cockpit according to the precision of the second large component to obtain the third cockpit data; Integrate the third cockpit data, several of the first data to be spliced, and several of the second data to be spliced to obtain the data to be processed; The global laser scanning step includes: Set the scanning range; Configure the second total station, and build a measurement control network for the airliner fuselage based on the second total station; Set the layout specification of the reflector units; First, configure several reflector units in the measurement space where the airliner fuselage is located according to the layout specification of the reflector units, and then confirm the visible positions; At the visible positions, perform a global measurement of the airliner fuselage according to the scanning range and based on the measurement control network and the second total station to obtain several global measurement coordinates; Then perform resection measurement based on the measurement control network and the second total station to obtain several resection point coordinates; Integrate several of the global measurement coordinates and several of the resection point coordinates to obtain the global coordinate system of the fuselage; Perform a block layout process on the airliner fuselage to obtain several sub-measurement scanning blocks; Configure several splicing balls and several measurement stations corresponding to several of the sub-measurement scanning blocks respectively; Set several measurement strategies respectively matched with several of the measurement stations; Call several of the measurement stations respectively according to several of the measurement strategies to perform laser scanning on several of the sub-measurement scanning blocks respectively to obtain several scanning data; Convert several of the scanning data into several first fuselage point cloud data based on the global coordinate system of the fuselage; Set several of the first fuselage point cloud data as several of the second data to be spliced; Data splicing and processing step: Perform a data splicing and processing operation based on the precision parameters and the data to be processed to obtain the airliner scanning information.

2. The information acquisition method for a large airliner according to claim 1, wherein: The airliner information includes: the airliner model information, the airliner component information and the airliner plane drawing that match the airliner model information.

3. The information collection method for a large airliner according to claim 2, wherein: The information of the components to be scanned includes: the fuselage of the airliner and the cockpit of the airliner; The information of the precision components to be measured includes: the wings of the airliner.

4. The information collection method for a large airliner according to claim 3, wherein: The encoding measurement step includes: Setting the layout specification of the splicing marks; identifying the area value of the high-precision measurement engineering area, and setting the layout specification of the encoding points based on the area value; First, set a number of encoding points and a number of non-encoding points in the high-precision measurement engineering area according to the encoding point layout specification, and then set a number of splicing marks in the high-precision measurement engineering area according to the splicing mark layout specification to obtain the engineering area to be measured; Set the layout specification of the station points, set the station points for the engineering area to be measured according to the layout specification of the station points, and configure a first total station at the station points; call the first total station to perform photogrammetry on the engineering area to be measured to obtain the global coordinate system of the engineering area for the high-precision measurement engineering area; Perform surface scanning processing on the high-precision measurement engineering area based on the global coordinate system of the engineering area to obtain the first data to be spliced.

5. The information collection method for a large airliner according to claim 4, wherein: The data splicing processing operation includes: Configuring a data processing program and a point cloud preprocessing program; Inputting a number of the third cockpit data, a number of the first data to be spliced, and a number of the second data to be spliced into the data processing program; Calling the data processing program to perform noise reduction processing on a number of the third cockpit data, a number of the first data to be spliced, and a number of the second data to be spliced respectively; Calling the data processing program to perform multi-view splicing on the noise-reduced first data to be spliced according to a number of the splicing marks to obtain the point cloud data of the precision components; Calling the data processing program to perform multi-view splicing on the noise-reduced second data to be spliced based on the spherical distance between a number of the splicing spheres to obtain the point cloud data of the large components; Performing fusion processing on the point cloud data of the precision components, the point cloud data of the large components, and the third cockpit data based on the data processing program and the point cloud preprocessing program to obtain a point cloud model; Identifying the shape features of the point cloud model, performing block processing on the point cloud model based on the shape features to obtain a number of model blocks; performing data repair processing on a number of the model blocks respectively to obtain a number of models to be converted; Constructing a surface model according to the surface fitting accuracy and based on a number of the models to be converted; obtaining the required format, and converting the surface model into the required format to obtain the scanned information of the airliner.

6. The information collection method for a large airliner according to claim 5, wherein: The steps of the fusion processing further include: Call the data processing program to perform triangulation processing on the precision component point cloud data, the large component point cloud data, and the third cockpit data respectively, to obtain a number of point clouds to be fused with consistent normal vectors; Call the point cloud preprocessing program to read a number of the point clouds to be fused, call the point cloud preprocessing program to calculate the fusion point information of a number of the point clouds to be fused using a clustering fusion algorithm, and call the point cloud preprocessing program to fuse a number of the point clouds to be fused according to the fusion point information to obtain the point cloud model.

7. An information collection system for a large airliner, which is based on the information collection method for a large airliner according to any one of claims 1 to 6, characterized in that, It includes: A parameter information creation module, configured to set precision parameters and obtain airliner information; The parameter information creation module creates a set of information on components to be measured according to the airliner information; A partition measurement and acquisition module, configured to perform partition acquisition operations according to the precision parameters and the set of information on components to be measured to obtain data to be processed; A data splicing and processing module, configured to perform data splicing and processing operations according to the precision parameters and the data to be processed to obtain airliner scanning information.

8. A computer-readable storage medium, characterized in that, A computer program is stored on the computer-readable storage medium, and when the computer program is executed by a processor, the steps of the information acquisition method for a large airliner according to any one of claims 1 to 6 are implemented.

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