CN106599345B - Airplane structure section bar identification method and device - Google Patents
Airplane structure section bar identification method and device Download PDFInfo
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Abstract
The invention provides an airplane structure section identification method and device, wherein the method comprises the following steps: partitioning the airplane structural section; matching the segmented airplane structure section bar with the section bars in the database, and determining the type corresponding to the segmented airplane structure section bar; the corresponding dimensions of the profile of the type in question are determined. According to the airplane structure section identification method provided by the embodiment of the invention, equipment can automatically determine the size of the section without human participation, so that the accuracy of the determined size can be improved while the efficiency is improved.
Description
Technical Field
The invention relates to the technical field of aircraft structure stability and strength analysis, in particular to an aircraft structure section bar identification method and device.
Background
In the field of strength calculation, the section of a profile structure is the basis for various calculations, and the dimension of the profile section needs to be accurately obtained in order to accurately perform stress analysis and strength calculation. In current intensity calculations, the dimensions of such a profile section are generally obtained in two ways:
the first mode is as follows: manually cutting a section of the section bar in a three-dimensional CAD model, and then measuring the dimension of the section;
the second mode is as follows: the method is obtained by looking up a two-dimensional drawing and directly reading from the drawing.
In the above two methods, since more and more structures are not produced by two-dimensional drawings but are directly manufactured by three-dimensional models, the first method is becoming more and more mainstream.
However, the first method of obtaining the sectional dimension of the profile consumes a lot of time and manpower resources in the strength modeling, and therefore, the calculation of the sectional dimension of the profile becomes a core difficulty that restricts the strength calculation.
Disclosure of Invention
The invention provides an airplane structure section identification method and device, and aims to solve the problem that a large amount of time and human resources are consumed in the analysis process of a flight structure strength unit in the prior art.
In order to solve the problems, the invention discloses an identification method of an airplane structural section, which comprises the following steps: partitioning the airplane structural section; matching the segmented airplane structure section bar with the section bars in the database, and determining the type corresponding to the segmented airplane structure section bar; the corresponding dimensions of the profile of the type in question are determined.
Preferably, the step of matching the segmented aircraft structural profile with the profiles in the database and determining the type corresponding to the segmented aircraft structural profile includes: determining the number of blocks contained in the blocked airplane structure section; matching the block number with the block number corresponding to each type of section bar in a database; determining the airplane structure sectional materials which are partitioned in the database, wherein the sectional materials have the same number of partitions; and searching the type matched with the blocked airplane structure section bar from the determined various types of section bars according to a preset rule.
Preferably, the step of searching for the type matched with the segmented aircraft structural profile from the determined types of profiles according to a preset rule includes: if the determined types of the section bars are only one, the partitioned airplane structure section bars are the determined types of the section bars; and if the determined various types of section bars are various, determining the type corresponding to the partitioned airplane structural section bar according to the position relationship among the partitioned blocks contained in the partitioned airplane structural section bar and the position relationship among the partitioned blocks contained in the partitioned airplane structural section bar.
Preferably, the step of blocking the aircraft structural profile comprises: acquiring discrete points corresponding to the section; sequentially connecting all discrete points on the same straight line to form a straight line segment; determining the length of each line segment, and extracting the line segments serving as the side length of the first type rectangle according to the length of the line segments to form the first type rectangle; determining the distance between each pair of mutually parallel line segments which are not extracted; extracting the long sides of the second type rectangle according to the distances from each pair of mutually parallel line segments which are not extracted to form the second type rectangle; and extending the first rectangle and the second rectangle to form each block contained by the section bar.
Preferably, the step of extending the first and second rectangles to form the segments included in the profile includes: determining the second type of rectangle adjacent to each of the first type of rectangles, wherein the determined second type of rectangle is not in a parallel line with the first type of rectangle; determining each first type rectangle adjacent to each second type rectangle, wherein the determined first type rectangles and the second type rectangles are not on a parallel line; for each first-type rectangle, keeping the short side of the first-type rectangle unchanged, and extending a first length value from the long side of the first-type rectangle to one end of the first-type rectangle, which is close to the second-type rectangle, wherein the first length value is half of the length of the short side of the second-type rectangle corresponding to the first-type rectangle; keeping the width of the second type rectangle unchanged, and respectively extending two ends of the second type rectangle by a second length value, wherein the second length value is half of the length of the short side of the first type rectangle corresponding to the second type rectangle.
In order to solve the above problems, the present invention discloses an aircraft structural profile identification device, wherein the device comprises: the blocking module is used for blocking the airplane structural section; the matching type module is used for matching the partitioned airplane structure section bar with the section bars in the database and determining the type corresponding to the partitioned airplane structure section bar; and the size determining module is used for determining the corresponding size of the section bar of the type.
Preferably, the matching type module includes: the quantity determining submodule is used for determining the quantity of the blocks contained in the partitioned airplane structural section; the matching submodule is used for matching the block number with the block number corresponding to each type of section bar in the database; the section bar determining submodule is used for determining the airplane structure section bars which are in the database and are blocked, and each type of section bars with the same blocking quantity are provided; and the searching submodule is used for searching the type matched with the blocked airplane structure section bar from the determined various types of section bars according to a preset rule.
Preferably, the lookup sub-module comprises: the first type determining unit is used for determining the blocked airplane structure section bar as the determined type section bar if the determined type section bars are only one; and the second type determining unit is used for determining the type corresponding to the blocked airplane structure profile according to the position relationship among the blocks contained in the blocked airplane structure profile and the position relationship among the blocks contained in the blocked airplane structure profile if the determined types of profiles are multiple.
Preferably, the blocking module includes: the acquisition submodule is used for acquiring discrete points corresponding to the section bar; the connecting sub-modules are used for sequentially connecting all discrete points on the same straight line to form a straight line segment; the first construction submodule is used for determining the length of each line segment, extracting the line segment serving as the side length of the first type rectangle according to the length of the line segment, and forming the first type rectangle; a determining submodule for determining distances between pairs of mutually parallel line segments that are not extracted; the second construction submodule is used for extracting the long sides of the second type rectangle according to each distance from each pair of mutually parallel line segments which are not extracted to form the second type rectangle; and the processing submodule is used for extending the first type of rectangle and the second type of rectangle to form each block contained in the profile.
Preferably, the processing submodule includes: a first determining unit, configured to determine the second type rectangles adjacent to each of the first type rectangles, where the determined second type rectangles are not on a parallel line with the first type rectangles; a second determining unit, configured to determine each of the first type rectangles adjacent to each of the second type rectangles, where the determined first type rectangles and the second type rectangles are not on a parallel line; the first extension unit is used for keeping the short side of each first type rectangle unchanged and extending a first length value from the long side of the first type rectangle to one end, close to the second type rectangle, of the first type rectangle, wherein the first length value is half of the length of the short side of the second type rectangle corresponding to the first type rectangle; and the second extension unit is used for keeping the width of the second type rectangle unchanged and respectively extending two ends of the second type rectangle by a second length value, wherein the second length value is half of the length of the short side of the first type rectangle corresponding to the second type rectangle.
Compared with the prior art, the invention has the following advantages:
the invention provides a scheme for identifying an airplane structural section, which is characterized in that after an airplane structure is partitioned, the partitioned airplane structural section is matched with a section in a database, and finally the type of the partitioned airplane structural section and the size information of the corresponding type are determined so as to analyze the structural strength. Therefore, according to the scheme for identifying the airplane structural section, the equipment can automatically determine the size of the structural section without manual measurement, so that time and human resources can be saved, and the equipment can automatically determine the size of the section without human participation, so that the accuracy of the determined size can be improved while the efficiency is improved.
Drawings
Fig. 1 is a flowchart illustrating steps of a method for identifying an aircraft structural section according to a first embodiment of the present invention;
fig. 2 is a flowchart illustrating steps of a method for identifying an aircraft structural profile according to a second embodiment of the present invention;
fig. 3 is a structural block diagram of an aircraft structural section identification device according to a third embodiment of the present invention;
fig. 4 is a block diagram of an aircraft structural section identification device according to a fourth embodiment of the present invention;
FIG. 5 is a schematic illustration of an I-shaped aircraft structural section;
FIG. 6 is a dimensional schematic of an I-section;
fig. 7 is a schematic view of various types of profiles and their corresponding features in an embodiment of the invention.
Detailed Description
In order to make the aforementioned objects, features and advantages of the present invention comprehensible, embodiments accompanied with figures are described in further detail below.
Example one
Referring to fig. 1, a flowchart of steps of a method for identifying an aircraft structural profile according to a first embodiment of the present invention is shown.
The method for identifying the airplane structure section comprises the following steps:
step 101: the aircraft structural profile is segmented.
The aircraft structural section is partitioned according to a certain method, and each structural section is partitioned into a plurality of partitions.
Based on different types of structural profiles, the number and shape of the obtained blocks are different.
Step 102: and matching the segmented airplane structure section bar with the section bars in the database, and determining the type corresponding to the segmented airplane structure section bar.
There are several types of profiles in the database, different types of profiles having different characteristics. And matching the partitioned airplane structural section with the section in the database, so as to determine the type of the structural section.
The following description is given by way of example of the type of matching of the i-shaped aircraft structural section:
the I-shaped airplane structure section bar shown in figure 5 can be divided into five parts, namely F1, F2, F3, F4 and W1 after being divided into blocks.
Comparing the number of the blocks of the airplane structural section after the blocks are divided with the number of the blocks into which each section can be divided in a database, wherein the I shape can be divided into 5 blocks, 4 flange-shaped rectangles and 1 web-shaped rectangle, comparing the number of the blocks 5 with the number of the blocks into which each section in the database can be divided, and matching the section types in the database with the number of the I-shaped blocks. If the matched profile type cannot be determined only by the number of the blocks, the matched profile type needs to be determined by the shapes of the blocks and the position relationship among the blocks.
Step 103: the corresponding dimensions of the profile of the type are determined.
After determining the type of the aircraft structure profile according to the type determined in step 102, the type of the profile obtained is determined, taking I-profile as an example, as shown in fig. 6, the size of b1 is the sum of the lengths of F3 and F4 plates, the size of b2 is the sum of the lengths of F1 and F2 plates, t2 is the thickness of F4 plate, and h1 is the length of W1 plate plus the thickness of t2, so as to obtain the value required for size driving.
After the corresponding dimensions of the profile are determined, the structural strength of the aircraft structural profile can be analyzed according to the determined dimensions, if necessary.
The invention provides a method for identifying an airplane structural section, which is characterized in that after an airplane structure is partitioned, the partitioned airplane structural section is matched with a section in a database, and finally the type of the partitioned airplane structural section and the size information of the corresponding type are determined so as to analyze the structural strength. Therefore, the method for identifying the airplane structural section provided by the invention can automatically determine the size of the structural section without manual measurement, so that time and human resources can be saved, and the accuracy of the determined size can be improved while the efficiency is improved because the equipment automatically determines the size of the section without human participation.
Example two
Referring to fig. 2, a flowchart of steps of an aircraft structural profile identification method according to a second embodiment of the present invention is shown.
The method for identifying the airplane structure section comprises the following steps:
step 201: and acquiring discrete points corresponding to the sectional material.
All the profiles are discrete into innumerable points and stored in the background, and when one profile is partitioned, the discrete points corresponding to the profiles need to be acquired.
Step 202: and sequentially connecting the discrete points on the same straight line to form a straight line segment.
And connecting all the acquired discrete points clockwise by taking any one discrete point as a starting point to form a closed section. The closed plane contains multiple contour lines, and discrete points between the contours are connected in sequence to form multiple straight line segments
Step 203: and determining the length of each line segment, and extracting the line segments serving as the side length of the first type rectangle according to the length of the line segments to form the first type rectangle.
And determining the length of each line segment, comparing the line segments, and determining the side length of a first type rectangle according to a comparison result, wherein the first type rectangle is a flange type rectangle.
Step 204: the distance between each pair of mutually parallel line segments not extracted is determined.
The unextracted line segments are mutually parallel line segments, and the distance between every two mutually parallel line segments is respectively obtained.
Step 205: and extracting the long sides of the second type rectangle from each pair of mutually parallel line segments which are not extracted according to each distance to form the second type rectangle.
The unextracted line segments comprise a plurality of pairs of line segments which are parallel to each other, and in the embodiment of the invention, one or more pairs of line segments need to be extracted from the plurality of pairs of line segments which are parallel to each other as the side length of the second type rectangle.
And comparing the direct distances of the two acquired parallel line segments, and extracting the long edge of the second type rectangle according to the comparison result to form the second type rectangle, wherein the second type rectangle is a web type rectangle.
Step 206: and extending the first rectangle and the second rectangle to form each block contained in the section bar.
And extending the flange-type rectangle and the web-type rectangle, and then carrying out stability analysis on each extended block.
One preferred way is: determining the second type of rectangle adjacent to each of the first type of rectangles, wherein the determined second type of rectangle is not in a parallel line with the first type of rectangle.
And the determined second type rectangle is not on a parallel line with the first type rectangle.
Each first type rectangle is adjacent to one or more second type rectangles.
It should be noted that, the adjacent rectangles of each first-type rectangle may also be the first-type rectangles as long as the rectangles and the first-type rectangles are in a mutually perpendicular relationship.
Taking an i-shaped structural strength unit as an example: the I-shaped shape is provided with four first type rectangles and one second type rectangle, and the first type rectangles and the adjacent second type rectangles are not on the same horizontal line.
Determining each first type rectangle adjacent to each second type rectangle, wherein the determined first type rectangles and the second type rectangles are not on a parallel line.
And the determined first type rectangle and the second type rectangle are not on a parallel line.
Each second type rectangle is adjacent to one or more first type rectangles, taking the section bar as an I shape as an example: the I-shaped structure is provided with a second type rectangle, the number of the first type rectangles adjacent to the second type rectangle is four, and each first type rectangle and each second type rectangle are not on the same horizontal line. The second type rectangle has one end adjacent to the two first type rectangles and the other end adjacent to the two first type rectangles. After the first type rectangle and the second type rectangle are determined, extending each rectangle to obtain each block contained in the airplane structural section.
For each first type rectangle, keeping the short side of the first type rectangle unchanged, and extending a first length value from the long side of the first type rectangle and one end of the first type rectangle close to the second type rectangle, wherein the first length value is half of the length of the short side of the second type rectangle corresponding to the first type rectangle.
The first length value is half of the length of the short side of the second type rectangle corresponding to the first type rectangle.
Namely, the short side of the first type rectangle is kept unchanged, the long side of the first type rectangle close to the second type rectangle is extended by a first length value, and the first length value is half of the length of the short side of the second type rectangle corresponding to the first type rectangle.
It should be noted that, in an actual implementation process, a person skilled in the art may set the first length value according to actual needs, where the first length value may also be set to 1/4, 1/3, and the like of the short side length corresponding to the first type rectangle, and may also be 1/4, 1/3, and the like of the short side length of the second type rectangle corresponding to the first type rectangle, which is not limited to this, and it is sufficient to ensure that the extended first length value causes the first type rectangle and the second type rectangle to be merged.
Keeping the width of the second type rectangle unchanged, and respectively extending two ends of the second type rectangle by a second length value, wherein the second length value is half of the length of the short side of the first type rectangle corresponding to the second type rectangle.
And the second length value is half of the length of the short side of the first type rectangle corresponding to the second type rectangle.
That is, the short side of the second type rectangle remains unchanged, the long side of the second type rectangle close to the first type rectangle is extended by a second length value, and the second length value is half of the length of the short side of the first type rectangle corresponding to the second type rectangle.
Taking an i-shape as an example, two ends of the second type rectangle are respectively adjacent to the two first type rectangles, so that when the first end of the second type rectangle is extended, the short side of any one first type rectangle adjacent to the first end can be used as a reference value, and the first end is extended by half of the reference value; when extending the second end of the second type rectangle, the short side of any one of the first type rectangles adjacent to the second end may be used as a reference value, and the second end may be extended by half of the reference value.
Certainly, the second length value is not limited to half of the width of the first-type rectangle, and in a specific implementation process, a person skilled in the art may set the second length value according to actual needs, and the second length value may also be set to 1/4, 1/3, and the like of the short side length corresponding to the second-type rectangle, and may also be 1/4, 1/3, and the like of the short side length of the first-type rectangle corresponding to the second-type rectangle.
The steps 201 to 207 are specific procedures for partitioning an airplane structural section.
Step 207: and determining the number of the blocks contained in the airplane structural section after the blocks are blocked.
It is determined how many flange-type rectangles F and block-web-type rectangles W the aircraft structural profile contains.
Wherein the flange-type rectangle is a first-type rectangle and the block-web-type rectangle is a second-type rectangle.
Step 208: and matching the number of the blocks with the number of the blocks corresponding to each type of section bar in the database.
The profiles of the various types in the database and the corresponding characteristics are shown in fig. 7:
as shown in fig. 7, there are several types of profiles in the database, different types of profiles having different characteristics.
When the type of a certain airplane structure section is determined, the airplane structure section after being partitioned is matched with the section in the database.
Step 209: determining the airplane structure section bars which are partitioned in the database, wherein the airplane structure section bars have the same number of partitioned section bars.
The following description will be given for the specific matching process of the profile types by taking an i-shaped airplane structural profile as an example:
as shown in fig. 5, the i-shaped airplane structural section is divided into five parts, namely F1, F2, F3, F4 and W1 after being divided into blocks.
And comparing the number of the blocks of the airplane structural section after the blocks are divided with the number of the blocks which can be divided by each section in the database, wherein the type of the section determined at this time can be determined as the I shape if only the I-shaped section corresponds to five blocks in the database.
For another example, if the aircraft structural profile is divided into 3 blocks, and the number of the blocks divided from each type of profile in fig. 7 in the database is matched, it is possible to obtain a plurality of types of profiles including three blocks in the database, and therefore, it is necessary to further perform matching by using more detailed matching conditions until only one type of profile is matched from the database.
Step 210: if only one type of profile is determined, the segmented aircraft structural profile is the determined type of profile.
When the determined type is only one, the type of the segmented aircraft structure profile can be determined.
Step 211: and if the determined various types of section bars are various, determining the type corresponding to the partitioned airplane structural section bar according to the position relationship among the partitioned sections contained in the partitioned airplane structural section bar and the position relationship among the partitioned sections contained in the partitioned airplane structural section bar.
When the determined various types of section bars are various, the type of the section bar is determined according to the position relation among the blocks contained in the partitioned airplane structure section bar.
For example: if the profile of the aircraft structure to be processed is a Z-shaped profile, the profile of the type is partitioned to obtain 3 partitions, and the 5 matched types in the database are determined after matching is performed in fig. 7 stored in the database purely according to the number of the partitions, in which case the type matched with the Z-shaped profile in the database needs to be found out according to the position relationship among the partitions of the Z-shaped profile.
Step 212: the corresponding dimensions of the profile of the type are determined.
After determining the type of the airplane structure profile, determining the type of the obtained profile, taking the I profile as an example, the size of the I profile shown in fig. 6 is obtained, wherein the size of b1 is the sum of the lengths of the plates F3 and F4, the size of b2 is the sum of the lengths of the plates F1 and F2, t2 is the thickness of the plate F4, and h1 is the length of the plate W1 plus the thickness of t 2.
After the corresponding dimensions of the profile are determined, the structural strength of the aircraft structural profile can be analyzed according to the determined dimensions, if necessary.
The structural strength of the aircraft structural section is analyzed according to the corresponding dimension of the section, as seen in the related art, which is not limited in the embodiment of the present invention.
The invention provides a method for identifying an airplane structural section, which is characterized in that after an airplane structure is partitioned, the partitioned airplane structural section is matched with a section in a database, and finally the type of the partitioned airplane structural section and the size information of the corresponding type are determined so as to analyze the structural strength. Therefore, the method for identifying the airplane structural section provided by the invention can automatically determine the size of the structural section without manual measurement, so that time and human resources can be saved, and the accuracy of the determined size can be improved while the efficiency is improved because the equipment automatically determines the size of the section without human participation.
EXAMPLE III
Referring to fig. 3, a structural block diagram of an aircraft structural profile identification device according to a third embodiment of the present invention is shown.
The aircraft structure section bar recognition device provided by the embodiment of the invention comprises: the blocking module 301 is used for blocking the airplane structural section; a matching type module 302, configured to match the segmented aircraft structure profile with a profile in a database, and determine a type corresponding to the segmented aircraft structure profile; a dimensioning module 303 for dimensioning a profile of said type.
The invention provides a device for identifying an airplane structural section, which is used for matching the partitioned airplane structural section with sections in a database after partitioning an airplane structure, and finally determining the type of the partitioned airplane structural section and the size information of the corresponding type so as to analyze the structural strength. Therefore, through the device for identifying the airplane structural section provided by the invention, the equipment can automatically determine the size of the structural section without manual measurement, so that the time and the human resource can be saved, and the efficiency is improved and the accuracy of the determined size can be improved at the same time as the equipment automatically determines the size of the section without human participation.
Example four
Referring to fig. 4, a block diagram of an aircraft structural profile identification device according to a fourth embodiment of the present invention is shown.
The aircraft structure section bar recognition device provided by the embodiment of the invention comprises: the blocking module 401 is used for blocking the airplane structural section; a matching type module 402, configured to match the segmented aircraft structural profile with a profile in a database, and determine a type corresponding to the segmented aircraft structural profile; a dimension determining module 403 for determining the corresponding dimension of the profile of the type.
Preferably, the matching type module 402 comprises: the quantity determining sub-module 4021 is used for determining the quantity of the blocks contained in the blocked airplane structural section; the matching submodule 4022 is used for matching the block number with the block number corresponding to each type of section bar in the database; a section bar determining submodule 4023, configured to determine each type of section bar having the same number of blocks as the aircraft structural section bar after being blocked in the database; the searching submodule 4024 is configured to search, according to a preset rule, a type matched with the partitioned aircraft structural profile from the determined types of profiles.
Preferably, the search sub-module 4024 includes: a first type determining unit 40241, configured to determine that the segmented aircraft structural profile is the determined type of profile if the determined types of profiles are only one; a second type determining unit 40242, configured to determine, if the determined types of profiles are multiple, a type corresponding to the blocked aircraft structural profile according to a positional relationship between the blocks included in the blocked aircraft structural profile and a positional relationship between the blocks included in the determined types of profiles.
Preferably, the blocking module 401 includes: the obtaining sub-module 4011 is configured to obtain discrete points corresponding to the profile; the connecting sub-module 4012 is used for sequentially connecting the discrete points on the same straight line to form a straight line segment; the first construction submodule 4013 is configured to determine lengths of the line segments, extract a line segment serving as a side length of the first type rectangle according to the lengths of the line segments, and form the first type rectangle; a determination submodule 4014 configured to determine distances between pairs of mutually parallel line segments that are not extracted; the second construction submodule 4015 is configured to extract long sides of a second type rectangle according to each distance from each pair of mutually parallel line segments that are not extracted, so as to form the second type rectangle; a processing submodule 4016 for extending the first and second rectangles to form the segments comprised by the profile.
Preferably, the processing sub-module 4016 includes: a first determining unit 40161 configured to determine the second type rectangles adjacent to each of the first type rectangles, wherein the determined second type rectangles are not in a parallel line with the first type rectangles; a second determining unit 40162, configured to determine the first type rectangles adjacent to each second type rectangle, and the determined first type rectangles and the second type rectangles are not in a parallel line; a first extension unit 40163, configured to, for each first type rectangle, keep a short side of the first type rectangle unchanged, and extend a long side of the first type rectangle and an end of the first type rectangle that is close to the second type rectangle by a first length value, where the first length value is half of a length of the short side of the second type rectangle corresponding to the first type rectangle; the second extension unit 40164 is configured to keep the width of the second type rectangle unchanged, and extend two ends of the second type rectangle by a second length value, where the second length value is half of the length of the short side of the first type rectangle corresponding to the second type rectangle.
The invention provides a device for identifying an airplane structural section, which is used for matching the partitioned airplane structural section with sections in a database after partitioning an airplane structure, and finally determining the type of the partitioned airplane structural section and the size information of the corresponding type so as to analyze the structural strength. Therefore, through the device for identifying the airplane structural section provided by the invention, the equipment can automatically determine the size of the structural section without manual measurement, so that the time and the human resource can be saved, and the efficiency is improved and the accuracy of the determined size can be improved at the same time as the equipment automatically determines the size of the section without human participation.
The embodiments in the present specification are described in a progressive manner, each embodiment focuses on differences from other embodiments, and the same and similar parts among the embodiments are referred to each other. For the system embodiment, since it is basically similar to the method embodiment, the description is simple, and for the relevant points, refer to the partial description of the method embodiment.
The method and the device for identifying the aircraft structural section provided by the invention are described in detail, specific examples are applied in the method for explaining the principle and the implementation mode of the invention, and the description of the examples is only used for helping to understand the method and the core idea of the invention; meanwhile, for a person skilled in the art, according to the idea of the present invention, there may be variations in the specific embodiments and the application scope, and in summary, the content of the present specification should not be construed as a limitation to the present invention.
Claims (4)
1. An aircraft structural profile identification method, characterized in that the method comprises:
-partitioning an aircraft structural profile, comprising: acquiring discrete points corresponding to the section; sequentially connecting all discrete points on the same straight line to form a straight line segment; determining the length of each line segment, and extracting the line segments serving as the side length of the first type rectangle according to the length of the line segments to form the first type rectangle; determining the distance between each pair of mutually parallel line segments which are not extracted; extracting the long sides of the second type rectangle according to the distances from each pair of mutually parallel line segments which are not extracted to form the second type rectangle; extending the first rectangle and the second rectangle to form each block contained in the section bar;
matching the blocked airplane structure section bar with section bars in a database, and determining the type corresponding to the blocked airplane structure section bar, wherein the type of each section bar, the size information of the corresponding type and the blocking information of the corresponding type are stored in the database; the blocking information comprises the number of blocks corresponding to each type of section bar and the position relation among the blocks;
determining the corresponding size of the type of section bar from the database;
the step of matching the segmented airplane structure section bar with the section bars in the database and determining the type corresponding to the segmented airplane structure section bar comprises the following steps:
determining the number of blocks contained in the blocked airplane structure section;
matching the block number with the block number corresponding to each type of section bar in the database;
determining the airplane structure sectional materials which are partitioned in the database, wherein the sectional materials have the same number of partitions;
if the determined types of the section bars are only one, the partitioned airplane structure section bars are the determined types of the section bars;
and if the determined types of the section bars are multiple, matching according to the position relationship among the blocks contained in the partitioned airplane structural section bars and the position relationship among the blocks contained in the determined types of the section bars until only one type of the section bars is matched from the database, and determining the finally matched type of the section bars as the type corresponding to the partitioned airplane structural section bars.
2. The method according to claim 1, wherein said step of extending the first and second rectangles to form the segments of the profile comprises:
determining the second type of rectangle adjacent to each of the first type of rectangles, wherein the determined second type of rectangle is not in a parallel line with the first type of rectangle;
determining each first type rectangle adjacent to each second type rectangle, wherein the determined first type rectangles and the second type rectangles are not on a parallel line;
for each first-type rectangle, keeping the short side of the first-type rectangle unchanged, and extending a first length value from the long side of the first-type rectangle to one end of the first-type rectangle, which is close to the second-type rectangle, wherein the first length value is half of the length of the short side of the second-type rectangle corresponding to the first-type rectangle;
keeping the width of the second type rectangle unchanged, and respectively extending two ends of the second type rectangle by a second length value, wherein the second length value is half of the length of the short side of the first type rectangle corresponding to the second type rectangle.
3. An aircraft structural profile identification device, the device comprising:
a partitioning module for partitioning an aircraft structural profile, the partitioning module comprising: the acquisition submodule is used for acquiring discrete points corresponding to the section bar; the connecting sub-modules are used for sequentially connecting all discrete points on the same straight line to form a straight line segment; the first construction submodule is used for determining the length of each line segment, extracting the line segment serving as the side length of the first type rectangle according to the length of the line segment, and forming the first type rectangle; a determining submodule for determining distances between pairs of mutually parallel line segments that are not extracted; the second construction submodule is used for extracting the long sides of the second type rectangle according to each distance from each pair of mutually parallel line segments which are not extracted to form the second type rectangle; the processing submodule is used for extending the first type of rectangle and the second type of rectangle to form each block contained in the section bar;
the matching type module is used for matching the partitioned airplane structural section with the section in the database to determine the type corresponding to the partitioned airplane structural section, and the database stores the type of each section, the size information of the corresponding type and the partitioning information of the corresponding type; the blocking information comprises the number of blocks corresponding to each type of section bar and the position relation among the blocks;
the size determining module is used for determining the size corresponding to the type of the section bar from the database;
wherein the match type module comprises:
the quantity determining submodule is used for determining the quantity of the blocks contained in the partitioned airplane structural section;
the matching submodule is used for matching the block number with the block number corresponding to each type of section bar in the database;
the section bar determining submodule is used for determining the airplane structure section bars which are in the database and are blocked, and each type of section bars with the same blocking quantity are provided;
the first type determining unit is used for determining the blocked airplane structure section bar as the determined type section bar if the determined type section bars are only one;
and the second type determining unit is used for matching according to the position relationship among the blocks contained in the partitioned airplane structural section and the position relationship among the blocks contained in the partitioned airplane structural section until only one type of section is matched from the database if the determined types of sections are multiple, and determining the finally matched type of section as the type corresponding to the partitioned airplane structural section.
4. The apparatus of claim 3, wherein the processing submodule comprises:
a first determining unit, configured to determine the second type rectangles adjacent to each of the first type rectangles, where the determined second type rectangles are not on a parallel line with the first type rectangles;
a second determining unit, configured to determine each of the first type rectangles adjacent to each of the second type rectangles, where the determined first type rectangles and the second type rectangles are not on a parallel line;
the first extension unit is used for keeping the short side of each first type rectangle unchanged and extending a first length value from the long side of the first type rectangle to one end, close to the second type rectangle, of the first type rectangle, wherein the first length value is half of the length of the short side of the second type rectangle corresponding to the first type rectangle;
and the second extension unit is used for keeping the width of the second type rectangle unchanged and respectively extending two ends of the second type rectangle by a second length value, wherein the second length value is half of the length of the short side of the first type rectangle corresponding to the second type rectangle.
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| CN101710360A (en) * | 2009-12-23 | 2010-05-19 | 西北工业大学 | Optimization design method of skeleton structure of airplane assembly tool |
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| CN104778308A (en) * | 2015-03-19 | 2015-07-15 | 上海工仿软件有限公司 | Airplane structure profile identification method and device |
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| CN101712067A (en) * | 2009-11-23 | 2010-05-26 | 西安飞机工业（集团）有限责任公司 | Method for manufacturing soft oil tank disassembling die |
| CN101710360A (en) * | 2009-12-23 | 2010-05-19 | 西北工业大学 | Optimization design method of skeleton structure of airplane assembly tool |
| CN104778308A (en) * | 2015-03-19 | 2015-07-15 | 上海工仿软件有限公司 | Airplane structure profile identification method and device |
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