CN113420363B - Method for predicting matching of skin skeleton of aircraft component - Google Patents

Method for predicting matching of skin skeleton of aircraft component Download PDF

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CN113420363B
CN113420363B CN202110978623.6A CN202110978623A CN113420363B CN 113420363 B CN113420363 B CN 113420363B CN 202110978623 A CN202110978623 A CN 202110978623A CN 113420363 B CN113420363 B CN 113420363B
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hole
skin
skeleton
framework
holes
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CN113420363A (en
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陈雪梅
勾江洋
刘元吉
陈清良
匡勇
冯若琪
潘雨
周裕力
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Chengdu Aircraft Industrial Group Co Ltd
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    • G—PHYSICS
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    • G01B—MEASURING LENGTH, THICKNESS OR SIMILAR LINEAR DIMENSIONS; MEASURING ANGLES; MEASURING AREAS; MEASURING IRREGULARITIES OF SURFACES OR CONTOURS
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Abstract

The invention discloses a method for predicting the matching of an aircraft component skin skeleton, which relates to the technical field of aircraft assembly and comprises the following steps: step 1: measuring and acquiring data of a skin connecting hole and a framework connecting hole; step 2: removing gross errors from the measurement data of the framework connecting hole and the measurement data of the skin connecting hole; and step 3: solving a conversion relation between a coordinate system where the skeleton offset hole center measurement point set is located and a coordinate system where the skin hole center measurement point set is located; and 4, step 4: calculating the error hole amount; and 5: constructing a connection installation model; step 6: the method for predicting the assembly matching performance introduces the hole center of the skin and the hole center offset of the skeleton based on the actual measurement data after the skeleton and the skin are processed, so that the calculation of the hole error amount is closer to the actual situation, and also introduces the diameter value of the connecting piece, the prediction target is clear and closer to the situation of the skin during actual installation, the actual requirements of assembly are met, and the method has the advantage of accurately and effectively predicting the assembly matching performance between the skeleton and the skin.

Description

Method for predicting matching of skin skeleton of aircraft component
Technical Field
The invention relates to the technical field of airplane assembly, in particular to a method for predicting the matching of an airplane part skin skeleton.
Background
At present, in the design and manufacture of advanced airplanes at home and abroad, in order to further improve the interchangeability of covering covers and skins, improve the hole making efficiency and quality and reduce the labor intensity, numerical control equipment is used for replacing manpower to make holes on airplane parts, hole making is respectively carried out on a skeleton and a covering of the airplane parts according to a design digifax, and connecting pieces are directly installed after the hole making is finished. Different from the traditional method for repairing and preparing holes in skeleton skins, the problem that whether skins and skeletons can be matched or not under the condition that the interchangeability of the skeleton skins is met by a novel hole-preparing strategy is a key concern of aircraft manufacturers.
The existing skin skeleton assembly matching judgment method is to directly compare a hole site aperture measured value of a skeleton or a skin with a hole site theoretical value, the evaluation method only considers the conformity of the hole site state of the skeleton or the skin with the theoretical state, does not consider the influence of the actual assembly situation of the skeleton and the skin and the tolerance of a specific connecting piece, and lacks sufficient engineering guidance significance. For example, hole positions on the framework and the skin deviate, but the deviation directions of the hole positions are consistent, so that the assembly requirements can be met during actual assembly, the existing evaluation mode can be directly judged to be not met, the parts are processed by unqualified products, and great waste is caused to aircraft manufacturing resources.
Based on the above, a new method for predicting the matching of the skin skeleton of the aircraft component is urgently needed for determining whether the assembly requirement is met after the hole is formed in the skin of the skeleton of the aircraft component.
Disclosure of Invention
Aiming at the defects in the prior art, the invention provides a method for predicting the matching property of skin and framework of an aircraft component, so as to achieve the effect of accurately and effectively predicting the assembling matching property between the framework skins.
In order to solve the technical problems, the invention adopts the following technical scheme:
a method for predicting the matching performance of an aircraft component skin skeleton comprises the following steps:
step 1: measuring a connecting hole: measuring and acquiring data of a skin connecting hole and a framework connecting hole;
step 2: and (3) sorting measurement data: removing gross errors from the measured data of the framework connecting hole and the measured data of the skin connecting hole, and removing gross errorsSorting the post-measurement data according to actual hole positions, eliminating the measurement data with incomplete corresponding relation, enabling skin connecting holes and framework connecting holes in the eliminated measurement data to correspond one to one, and according to the offset between the theoretical hole center of the framework connecting holes and the theoretical hole center of the skin connecting holes
Figure 41733DEST_PATH_IMAGE001
Connecting each framework with a hole center
Figure 943829DEST_PATH_IMAGE002
Vector along the direction of connecting hole of framework
Figure 237539DEST_PATH_IMAGE003
And (3) shifting, wherein the theoretical hole center represented by the shifted hole center point and the skin theoretical hole center are the same geometric characteristic point, and the relation is as follows:
Figure 529980DEST_PATH_IMAGE004
；
in the formula (I), the compound is shown in the specification,
Figure 449394DEST_PATH_IMAGE005
the hole center of the deflected framework connecting hole is formed;
and step 3: solving a conversion relation: solving the coordinate system of the framework offset hole center measuring point set by using a singular value decomposition method
Figure 956730DEST_PATH_IMAGE006
And a coordinate system where the skin hole center measuring point set is located
Figure 670608DEST_PATH_IMAGE007
The conversion relationship between the two is respectively
Figure 528974DEST_PATH_IMAGE008
Wherein
Figure 924183DEST_PATH_IMAGE009
Represents all
Figure 535293DEST_PATH_IMAGE010
The set of points is formed by a set of points,
Figure 436384DEST_PATH_IMAGE011
represents the hole center of the skin connecting hole,
Figure 703417DEST_PATH_IMAGE012
represents the set of all the connecting hole cores,
Figure 699055DEST_PATH_IMAGE013
is a 3 multiplied by 3 rotation matrix which represents the spatial rotation attitude of the skin hole measurement coordinate system relative to the skeleton hole measurement coordinate system,
Figure 180983DEST_PATH_IMAGE014
the translation matrix is a translation matrix of 3 multiplied by 1 and represents the space translation information of the original point of the skin hole measurement coordinate system relative to the original point of the skeleton hole measurement coordinate system;
and 4, step 4: calculating the error hole amount: according to a conversion relation
Figure 439926DEST_PATH_IMAGE015
Converting the skin point to the skeleton coordinate system to obtain residual vector
Figure 990993DEST_PATH_IMAGE016
Considering the direction vector of the connecting hole of the framework
Figure 993584DEST_PATH_IMAGE017
Calculating the vector of the residual vector in the direction of the connecting hole of the framework
Figure 330019DEST_PATH_IMAGE017
Projection in a straight plane
Figure 556601DEST_PATH_IMAGE018
Projection vector
Figure 611276DEST_PATH_IMAGE019
The die is the amount of staggered holes
Figure 151978DEST_PATH_IMAGE020
Then the following relation is satisfied:
Figure 592187DEST_PATH_IMAGE021
Figure 192933DEST_PATH_IMAGE022
and 5: constructing a connecting and installing model:
Figure 469324DEST_PATH_IMAGE023
the conditions for installing the connecting piece are as follows:
Figure 876035DEST_PATH_IMAGE024
in the above formula, the first and second carbon atoms are,
Figure 374012DEST_PATH_IMAGE025
the diameter of the connecting hole of the skin is the same as the diameter of the connecting hole of the skin,
Figure 693129DEST_PATH_IMAGE026
the aperture of the connecting hole of the framework,
Figure 971664DEST_PATH_IMAGE027
the hole staggering amount of the connecting holes of the skin skeleton is determined,
Figure 854169DEST_PATH_IMAGE028
in order to install the space for the connecting piece,
Figure 7984DEST_PATH_IMAGE029
is the diameter of the connecting piece;
step 6: and assembling matching prediction, wherein the evaluation criterion of the matching prediction is as follows:
Figure 747270DEST_PATH_IMAGE030
the framework skin is provided with holes to meet the requirement of assembly matching;
Figure 185204DEST_PATH_IMAGE031
and the framework skin hole-making does not meet the requirement of assembly matching.
Preferably, in step 2, the gross error elimination is performed on the measurement data of the framework connecting holes and the measurement data of the skin connecting holes, and the elimination method includes the following steps:
step 2-1: calculating the hole site measurement deviation of the skeleton and the skin
Figure 684450DEST_PATH_IMAGE032
Average value of (2)
Figure 953757DEST_PATH_IMAGE033
And standard deviation of
Figure 67207DEST_PATH_IMAGE034
；
Step 2-2: judging the residual error of each hole site measurement data
Figure 805487DEST_PATH_IMAGE035
If there is more than 3 standard deviations
Figure 92112DEST_PATH_IMAGE034
Residual error of
Figure 419188DEST_PATH_IMAGE036
Measured value, i.e.
Figure 516588DEST_PATH_IMAGE037
If the error is large, the error is considered to be contained, and the error is eliminated;
step 2-3: repeating the step 2-1 and the step 2-2 until the residual errors of the hole position measurement data of all the connecting holes of the framework and the skin are all in
Figure 725852DEST_PATH_IMAGE038
Within.
Preferably, in step 2, the measurement data with incomplete correspondence includes: only the data of the hole positions of the skeleton connecting holes and the data of the hole positions of the skin connecting holes are lacked, and only the data of the hole positions of the skin connecting holes and the data of the hole positions of the skeleton connecting holes are lacked.
Preferably, the step 3 specifically includes:
step 3-1: to framework connecting hole measuring point set
Figure 753851DEST_PATH_IMAGE039
And skin connecting hole measuring point set
Figure 748483DEST_PATH_IMAGE040
The centers of gravity of the two sets of data are calculated respectively:
Figure 266052DEST_PATH_IMAGE041
Figure 978924DEST_PATH_IMAGE042
；
step 3-2: solving the displacement vector of each point relative to the gravity center:
Figure 545035DEST_PATH_IMAGE043
Figure 643441DEST_PATH_IMAGE044
；
step 3-3: by using the displacement vector of the center of gravity
Figure 269594DEST_PATH_IMAGE045
Matrix:
Figure 204183DEST_PATH_IMAGE046
；
step 3-4: to pair
Figure 636302DEST_PATH_IMAGE045
Performing singular value decomposition on the matrix:
Figure 605526DEST_PATH_IMAGE047
；
in the formula (I), the compound is shown in the specification,
Figure 464898DEST_PATH_IMAGE048
is an orthogonal matrix, and the matrix is,
Figure 73733DEST_PATH_IMAGE049
a diagonal matrix that is non-negative;
step 3-5: computing rotation matrices
Figure 794696DEST_PATH_IMAGE050
And translation matrix
Figure 867694DEST_PATH_IMAGE051
：
Figure 835650DEST_PATH_IMAGE052
Figure 744831DEST_PATH_IMAGE053
。
Preferably, the step 1 specifically includes:
step 1-1: after the holes are made in all the connecting holes on the skin part, measuring by using high-precision measuring equipment to obtain the hole site aperture of the connecting hole on the skin, and recording
Figure 518752DEST_PATH_IMAGE054
The hole site of each skin connecting hole is
Figure 649519DEST_PATH_IMAGE055
Pore diameter of
Figure 601426DEST_PATH_IMAGE056
；
Step 1-2: after the holes of all the connecting holes on the framework of the airplane part are manufactured, hole site apertures of the connecting holes on the framework are measured and obtained by using high-precision measuring equipment, and the hole site apertures are recorded
Figure 981592DEST_PATH_IMAGE054
The hole site of each framework connecting hole is
Figure 496887DEST_PATH_IMAGE057
Pore diameter of
Figure 295210DEST_PATH_IMAGE058
。
Preferably, the high-precision measuring device is a machine tool online probe or a three-coordinate measuring machine.
The invention has the beneficial effects that:
1. the invention provides a method for accurately and effectively predicting the assembly matching property between skeleton skins in the aspect of the problem of predicting the assembly matching property of airplane part skeleton holes and skin part holes, but no similar method exists in the related field at present.
2. According to the method, based on the measured data after the framework and the skin are processed, the skin hole center and the framework hole center offset are introduced, so that the calculation of the hole error amount is closer to the actual situation; the invention introduces the diameter value of the connecting piece when calculating the matching property
Figure 604968DEST_PATH_IMAGE059
The prediction target is clear, and the method is closer to the situation of actual installation of the skin and meets the actual requirements of assembly.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the embodiments or the prior art will be briefly described below. Throughout the drawings, like elements or portions are generally identified by like reference numerals. In the drawings, elements or portions are not necessarily drawn to scale.
FIG. 1 is a schematic flow chart of a method for predicting skin-skeleton matching of an aircraft component according to the present invention;
FIG. 2 is a schematic diagram of the principles of the present invention;
FIG. 3 is a schematic view of the mating of the skeletal skins of the present invention;
fig. 4 is a view showing an installation model of the connector of the present invention.
Detailed Description
In order to make the objects, technical solutions and advantages of the embodiments of the present invention clearer, the technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are some, but not all, embodiments of the present invention. The components of embodiments of the present invention generally described and illustrated in the figures herein may be arranged and designed in a wide variety of different configurations.
Thus, the following detailed description of the embodiments of the present invention, presented in the figures, is not intended to limit the scope of the invention, as claimed, but is merely representative of selected embodiments of the invention. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
It should be noted that: like reference numbers and letters refer to like items in the following figures, and thus, once an item is defined in one figure, it need not be further defined and explained in subsequent figures.
Example 1
As shown in fig. 1 to 4, the present embodiment provides a method for predicting the matching of an aircraft component skin skeleton, including the following steps:
step 1: measuring a connecting hole: measuring and acquiring data of a skin connecting hole and a framework connecting hole;
step 2: and (3) sorting measurement data: removing gross errors of the measured data of the framework connecting holes and the measured data of the skin connecting holes, sorting the removed measured data according to actual hole positions, removing the measured data with incomplete corresponding relation, enabling the skin connecting holes and the framework connecting holes to be in one-to-one correspondence in the removed measured data, and according to the offset between the theoretical hole center of the framework connecting holes and the theoretical hole center of the skin connecting holes
Figure 472430DEST_PATH_IMAGE060
Connecting each framework with a hole center
Figure 338886DEST_PATH_IMAGE061
Vector along the direction of connecting hole of framework
Figure 178666DEST_PATH_IMAGE062
And (3) shifting, wherein the theoretical hole center represented by the shifted hole center point and the skin theoretical hole center are the same geometric characteristic point, and the relation is as follows:
Figure 721643DEST_PATH_IMAGE063
；
in the formula (I), the compound is shown in the specification,
Figure 92712DEST_PATH_IMAGE064
the hole center of the deflected framework connecting hole is formed;
and step 3: solving a conversion relation: solving the coordinate system of the framework offset hole center measuring point set by using a singular value decomposition method
Figure 684231DEST_PATH_IMAGE065
And a coordinate system where the skin hole center measuring point set is located
Figure 706413DEST_PATH_IMAGE066
The conversion relationship between the two is respectively
Figure 171024DEST_PATH_IMAGE067
Wherein
Figure 950761DEST_PATH_IMAGE068
Represents all
Figure 408287DEST_PATH_IMAGE069
The set of points is formed by a set of points,
Figure 35709DEST_PATH_IMAGE070
represents the hole center of the skin connecting hole,
Figure 858171DEST_PATH_IMAGE071
represents the set of all the connecting hole cores,
Figure 187522DEST_PATH_IMAGE072
is a 3 multiplied by 3 rotation matrix which represents the spatial rotation attitude of the skin hole measurement coordinate system relative to the skeleton hole measurement coordinate system,
Figure 211190DEST_PATH_IMAGE073
the translation matrix is a translation matrix of 3 multiplied by 1 and represents the space translation information of the original point of the skin hole measurement coordinate system relative to the original point of the skeleton hole measurement coordinate system;
and 4, step 4: calculating the error hole amount: according to a conversion relation
Figure 880068DEST_PATH_IMAGE067
Converting the skin point to the skeleton coordinate system to obtain residual vector
Figure 935749DEST_PATH_IMAGE074
Considering the direction vector of the connection hole of the frame
Figure 706390DEST_PATH_IMAGE075
Calculating the vector of the residual vector in the direction of the connecting hole of the framework
Figure 708981DEST_PATH_IMAGE075
Projection in a vertical plane
Figure 91421DEST_PATH_IMAGE076
Throw inShadow vector
Figure 68735DEST_PATH_IMAGE076
The die is the amount of staggered holes
Figure 310361DEST_PATH_IMAGE077
Then the following relation is satisfied:
Figure 913381DEST_PATH_IMAGE078
Figure 104322DEST_PATH_IMAGE079
；
and 5: constructing a connecting and installing model:
Figure 705067DEST_PATH_IMAGE080
the conditions for installing the connecting piece are as follows:
Figure 433989DEST_PATH_IMAGE081
in the above formula, the first and second carbon atoms are,
Figure 388170DEST_PATH_IMAGE082
the diameter of the connecting hole of the skin is the same as the diameter of the connecting hole of the skin,
Figure 620568DEST_PATH_IMAGE026
the aperture of the connecting hole of the framework,
Figure 454532DEST_PATH_IMAGE083
the hole staggering amount of the connecting holes of the skin skeleton is determined,
Figure 421482DEST_PATH_IMAGE084
in order to install the space for the connecting piece,
Figure 303987DEST_PATH_IMAGE085
is the diameter of the connecting piece;
step 6: and assembling matching prediction, wherein the evaluation criterion of the matching prediction is as follows:
Figure 515526DEST_PATH_IMAGE086
the framework skin is provided with holes to meet the requirement of assembly matching;
Figure 474385DEST_PATH_IMAGE087
and the framework skin hole-making does not meet the requirement of assembly matching.
In this embodiment, carry out thick error through skeleton connecting hole measured data and covering connecting hole measured data and reject, measured data is according to actual hole site sequencing after rejecting, reject the incomplete measured data of corresponding relation that exists, covering connecting hole and skeleton connecting hole one-to-one in the measured data after making rejecting, thereby guarantee measured data's matching nature, and based on the actual measured data after skeleton and covering processing are accomplished, covering hole center and skeleton hole center offset have been introduced simultaneously, make wrong hole volume calculation more close to actual conditions, when calculating the matching nature, introduce connecting piece diameter value
Figure 912320DEST_PATH_IMAGE088
The connection installation model is constructed, guidance is carried out through a scientific and effective calculation model and an evaluation criterion, a prediction target is clear, the situation is closer to the situation of actual installation of the skin, and the actual requirements of fitting and assembling are met.
Specifically, in step 2, gross errors of the measurement data of the framework connecting holes and the measurement data of the skin connecting holes are removed, and the removing method comprises the following steps:
step 2-1: calculating the hole site measurement deviation of the skeleton and the skin
Figure 457571DEST_PATH_IMAGE089
Average value of (2)
Figure 477611DEST_PATH_IMAGE090
And standard deviation of
Figure 591060DEST_PATH_IMAGE091
；
Step 2-2: judging the residual error of each hole site measurement data
Figure 781870DEST_PATH_IMAGE092
If there is more than 3 standard deviations
Figure 615965DEST_PATH_IMAGE091
Residual error of
Figure 943041DEST_PATH_IMAGE093
Measured value, i.e.
Figure 227392DEST_PATH_IMAGE094
If the error is large, the error is considered to be contained, and the error is eliminated;
step 2-3: repeating the step 2-1 and the step 2-2 until the residual errors of the hole position measurement data of all the connecting holes of the framework and the skin are all in
Figure 452968DEST_PATH_IMAGE095
Within.
Specifically, in step 2, the measurement data with incomplete correspondence includes: only the data of the hole positions of the skeleton connecting holes and the data of the hole positions of the skin connecting holes are lacked, and only the data of the hole positions of the skin connecting holes and the data of the hole positions of the skeleton connecting holes are lacked.
Specifically, the step 3 specifically includes:
step 3-1: to framework connecting hole measuring point set
Figure 480967DEST_PATH_IMAGE096
And skin connecting hole measuring point set
Figure 521604DEST_PATH_IMAGE097
The centers of gravity of the two sets of data are calculated respectively:
Figure 993168DEST_PATH_IMAGE098
Figure 627411DEST_PATH_IMAGE099
；
step 3-2: solving the displacement vector of each point relative to the gravity center:
Figure 52577DEST_PATH_IMAGE100
Figure 370557DEST_PATH_IMAGE101
；
step 3-3: by using the displacement vector of the center of gravity
Figure 59027DEST_PATH_IMAGE102
Matrix:
Figure 180567DEST_PATH_IMAGE103
；
step 3-4: to pair
Figure 160155DEST_PATH_IMAGE102
Performing singular value decomposition on the matrix:
Figure 581909DEST_PATH_IMAGE104
；
in the formula (I), the compound is shown in the specification,
Figure 378964DEST_PATH_IMAGE105
is an orthogonal matrix, and the matrix is,
Figure 800849DEST_PATH_IMAGE106
a diagonal matrix that is non-negative;
step 3-5: computing rotation matrices
Figure 771079DEST_PATH_IMAGE108
And translation matrix
Figure 781760DEST_PATH_IMAGE110
：
Figure 562766DEST_PATH_IMAGE111
Figure 517952DEST_PATH_IMAGE112
。
Specifically, the step 1 specifically includes:
step 1-1: after the holes are made in all the connecting holes on the skin part, measuring by using high-precision measuring equipment to obtain the hole site aperture of the connecting hole on the skin, and recording
Figure 245868DEST_PATH_IMAGE114
The hole site of each skin connecting hole is
Figure 111056DEST_PATH_IMAGE115
Pore diameter of
Figure 312230DEST_PATH_IMAGE116
；
Step 1-2: after the holes of all the connecting holes on the framework of the airplane part are manufactured, hole site apertures of the connecting holes on the framework are measured and obtained by using high-precision measuring equipment, and the hole site apertures are recorded
Figure 696989DEST_PATH_IMAGE114
The hole site of each framework connecting hole is
Figure 212284DEST_PATH_IMAGE117
Pore diameter of
Figure 994295DEST_PATH_IMAGE118
。
Specifically, the high-precision measuring equipment is a machine tool online probe or a three-coordinate measuring machine, or other high-precision measuring equipment meeting the requirements can also be adopted.
Example 2
As shown in fig. 1 to 4, in this embodiment, based on embodiment 1, when the skeleton skin fitting is a high-precision fitting, the tolerance of the skeleton aperture is 0.03mm, and the skin aperture is 0.13mm, there is provided a method for predicting the matching property of the skin skeleton of an aircraft component, including the following steps:
step 1: measuring a connecting hole: after the holes are made in all the connecting holes on the skin part, the hole site aperture of the connecting hole on the skin is obtained by using the online probe of the machine tool to measure, and the second step is recorded
Figure 117103DEST_PATH_IMAGE114
The hole site of each skin connecting hole is
Figure 250144DEST_PATH_IMAGE115
Pore diameter of
Figure 303550DEST_PATH_IMAGE116
After the holes are made in all the connecting holes on the framework of the airplane part, the hole site aperture of the connecting hole on the framework is obtained by using the online probe of the machine tool for measurement, and the second step is recorded
Figure 956380DEST_PATH_IMAGE114
The hole site of each framework connecting hole is
Figure 437040DEST_PATH_IMAGE117
Pore diameter of
Figure 57377DEST_PATH_IMAGE118
In the present embodiment, there are 50 skin pores, and the measurement data results are shown in table 1 below:
TABLE 1 framework skin and attachment hole measurement data results
Figure 461945DEST_PATH_IMAGE119
Figure 156231DEST_PATH_IMAGE120
Figure 135688DEST_PATH_IMAGE121
Step 2: the measurement data arrangement specifically comprises the following steps:
step 2-1: calculating skeleton connection hole measurement data
Figure 728475DEST_PATH_IMAGE122
Average value of hole site deviation
Figure 123684DEST_PATH_IMAGE123
The calculation formula is as follows:
Figure 373DEST_PATH_IMAGE124
in the formula (I), the compound is shown in the specification,
Figure 635885DEST_PATH_IMAGE125
is a theoretical value of the framework connecting hole;
step 2-2: calculating skeleton connection hole measurement data
Figure 902918DEST_PATH_IMAGE122
Standard deviation of hole site
Figure 164135DEST_PATH_IMAGE126
The calculation formula is as follows:
Figure 646064DEST_PATH_IMAGE127
；
step 2-3: judgment of
Figure 701744DEST_PATH_IMAGE129
Whether the residual error of each framework connecting hole is less than
Figure 456074DEST_PATH_IMAGE130
Namely:
Figure 6135DEST_PATH_IMAGE131
if yes, reserving the point; if not, the point is eliminated, and the steps 2-1 to 2-3 are repeated until all the points meet the condition that the connecting piece can be installed:
Figure 529520DEST_PATH_IMAGE132
(in this embodiment, there are no points to be culled);
step 2-4: calculating skin attachment hole measurement data
Figure 21681DEST_PATH_IMAGE133
Average value of hole site deviation
Figure 76356DEST_PATH_IMAGE134
The calculation formula is as follows:
Figure 413796DEST_PATH_IMAGE135
in the formula (I), the compound is shown in the specification,
Figure 57267DEST_PATH_IMAGE136
the theoretical data of the skin connecting hole are shown;
step 2-5: calculating skin attachment hole measurement data
Figure 205483DEST_PATH_IMAGE133
Standard deviation of hole site
Figure 996722DEST_PATH_IMAGE126
The calculation formula is as follows:
Figure 75536DEST_PATH_IMAGE137
step 2-6: using the criterion of Leife to judge
Figure 386563DEST_PATH_IMAGE129
Whether the hole site residual error of each skin connecting hole is a coarse error point or not is determined as follows:
Figure 220527DEST_PATH_IMAGE138
if yes, reserving the point; if not, the point is eliminated, and the steps 2-4 to 2-6 are repeated until all the points meet the condition that the connecting piece can be installed:
Figure 171165DEST_PATH_IMAGE132
(in this embodiment, there are no points to be culled);
step 2-7, measuring data after elimination
Figure 866720DEST_PATH_IMAGE122
And
Figure 219204DEST_PATH_IMAGE133
screening and sorting according to actual hole sites, and eliminating independently existing skeleton connecting hole data or skin connecting hole data to ensure that the eliminated data correspond to skeleton holes one by one (points needing to be eliminated do not exist in the embodiment);
step 2-8, according to the offset between the theoretical hole center of the framework connecting hole and the theoretical hole center of the skin connecting hole
Figure 224069DEST_PATH_IMAGE139
The hole center of the framework connecting hole is arranged along the direction of theoretical normal vector
Figure 475053DEST_PATH_IMAGE140
And (3) shifting, wherein the geometric point represented by the hole center of the framework connecting hole after shifting and the geometric point represented by the hole center of the skin connecting hole are the same, and the relation is as follows:
Figure 895670DEST_PATH_IMAGE141
；
and step 3: solving a conversion relation:
solving framework offset hole center measurement point set by using singular value decomposition method
Figure 430556DEST_PATH_IMAGE122
Coordinate system and skin hole center measuring point set
Figure 357055DEST_PATH_IMAGE133
Conversion relation between coordinate systems
Figure 282286DEST_PATH_IMAGE142
：
Figure 568911DEST_PATH_IMAGE143
Figure 443457DEST_PATH_IMAGE144
；
And 4, step 4: according to a conversion relation
Figure 727808DEST_PATH_IMAGE142
Converting the skin point to the skeleton coordinate system to obtain residual vector
Figure 202651DEST_PATH_IMAGE145
Considering the direction vector of the connection hole of the frame
Figure 43700DEST_PATH_IMAGE140
Calculating the vector of the residual vector in the direction of the connecting hole of the framework
Figure 225282DEST_PATH_IMAGE146
Projection in a vertical plane
Figure 477272DEST_PATH_IMAGE147
Projection vector
Figure 201863DEST_PATH_IMAGE147
Die ofIs the amount of wrong hole
Figure 767973DEST_PATH_IMAGE148
Then the following relation is satisfied:
Figure 131959DEST_PATH_IMAGE149
Figure 305582DEST_PATH_IMAGE150
；
the results of the calculation of the amount of mispriming are shown in Table 2 below:
TABLE 2 calculation of the amount of mispriming
Figure 755018DEST_PATH_IMAGE151
Figure 124820DEST_PATH_IMAGE152
And 5: constructing a connecting and installing model:
Figure 828464DEST_PATH_IMAGE153
the conditions for installing the connecting piece are as follows:
Figure 687836DEST_PATH_IMAGE154
in the formula (I), the compound is shown in the specification,
Figure 109721DEST_PATH_IMAGE155
the diameter of the connecting hole of the skin is the same as the diameter of the connecting hole of the skin,
Figure 283214DEST_PATH_IMAGE156
the aperture of the connecting hole of the framework,
Figure 356212DEST_PATH_IMAGE157
the hole staggering amount of the connecting holes of the skin skeleton is determined,
Figure 137217DEST_PATH_IMAGE158
in order to install the space for the connecting piece,
Figure 233349DEST_PATH_IMAGE159
is the diameter of the connecting piece;
step 6: and (3) predicting the assembly matching property, namely calculating the movable gap of the installed connecting piece according to the diameter of the connecting piece corresponding to the connecting hole, and further judging the assembly matching property of the skin skeleton, wherein the evaluation criterion of the matching property prediction is as follows:
Figure 685507DEST_PATH_IMAGE162
the framework skin is provided with holes to meet the requirement of assembly matching;
Figure 824365DEST_PATH_IMAGE163
and the framework skin hole-making does not meet the requirement of assembly matching.
The calculation results are shown in table 3 below:
TABLE 3 installation backlash calculation results
Figure 470110DEST_PATH_IMAGE164
Figure 532875DEST_PATH_IMAGE165
And (4) conclusion: the requirement of matching property is met.
Finally, it should be noted that: the above embodiments are only used to illustrate the technical solution of the present invention, and not to limit the same; while the invention has been described in detail and with reference to the foregoing embodiments, it will be understood by those skilled in the art that: the technical solutions described in the foregoing embodiments may still be modified, or some or all of the technical features may be equivalently replaced; such modifications and substitutions do not depart from the spirit and scope of the present invention, and they should be construed as being included in the following claims and description.

Claims (6)

1. A method for predicting the matching of an aircraft component skin skeleton is characterized by comprising the following steps:
step 1: measuring a connecting hole: measuring and acquiring data of a skin connecting hole and a framework connecting hole;
step 2: and (3) sorting measurement data: removing gross errors of the measured data of the framework connecting holes and the measured data of the skin connecting holes, sorting the removed measured data according to actual hole positions, removing the measured data with incomplete corresponding relation, enabling the skin connecting holes and the framework connecting holes to be in one-to-one correspondence in the removed measured data, and according to the offset between the theoretical hole center of the framework connecting holes and the theoretical hole center of the skin connecting holes
Figure 819143DEST_PATH_IMAGE001
Connecting each framework with a hole center
Figure 171627DEST_PATH_IMAGE002
Vector along the direction of connecting hole of framework
Figure 51858DEST_PATH_IMAGE003
And (3) shifting, wherein the theoretical hole center represented by the shifted hole center point and the skin theoretical hole center are the same geometric characteristic point, and the relation is as follows:
Figure 489793DEST_PATH_IMAGE004
；
in the formula (I), the compound is shown in the specification,
Figure 848093DEST_PATH_IMAGE005
the hole center of the deflected framework connecting hole is formed;
and step 3: solving a conversion relation: using singular value decompositionThe method comprises the step of solving a coordinate system where the skeleton offset hole center measuring point set is located
Figure 258346DEST_PATH_IMAGE006
And a coordinate system where the skin hole center measuring point set is located
Figure 371795DEST_PATH_IMAGE007
The conversion relationship between the two is respectively
Figure 297026DEST_PATH_IMAGE008
Wherein
Figure 459017DEST_PATH_IMAGE009
Represents all
Figure 458197DEST_PATH_IMAGE010
The set of points is formed by a set of points,
Figure 742548DEST_PATH_IMAGE011
represents the hole center of the skin connecting hole,
Figure 155074DEST_PATH_IMAGE012
represents the set of all the connecting hole cores,
Figure 120756DEST_PATH_IMAGE013
is a 3 multiplied by 3 rotation matrix which represents the spatial rotation attitude of the skin hole measurement coordinate system relative to the skeleton hole measurement coordinate system,
Figure 302339DEST_PATH_IMAGE014
the translation matrix is a translation matrix of 3 multiplied by 1 and represents the space translation information of the original point of the skin hole measurement coordinate system relative to the original point of the skeleton hole measurement coordinate system;
and 4, step 4: calculating the error hole amount: according to a conversion relation
Figure 426765DEST_PATH_IMAGE008
Turning the skin point by pointConverting the frame coordinate system to obtain a residual vector
Figure 264271DEST_PATH_IMAGE015
Considering the direction vector of the connection hole of the frame
Figure 830382DEST_PATH_IMAGE016
Calculating the vector of the residual vector in the direction of the connecting hole of the framework
Figure 69733DEST_PATH_IMAGE016
Projection in a vertical plane
Figure 430308DEST_PATH_IMAGE017
Projection vector
Figure 755110DEST_PATH_IMAGE018
The die is the amount of staggered holes
Figure 124911DEST_PATH_IMAGE019
Then the following relation is satisfied:
Figure 953190DEST_PATH_IMAGE020
Figure 687928DEST_PATH_IMAGE021
；
and 5: constructing a connecting and installing model:
Figure 296763DEST_PATH_IMAGE022
the conditions for installing the connecting piece are as follows:
Figure 407939DEST_PATH_IMAGE023
in the above formula, the first and second carbon atoms are,
Figure 418620DEST_PATH_IMAGE024
the diameter of the connecting hole of the skin is the same as the diameter of the connecting hole of the skin,
Figure 324259DEST_PATH_IMAGE025
the aperture of the connecting hole of the framework,
Figure 420391DEST_PATH_IMAGE026
the hole staggering amount of the connecting holes of the skin skeleton is determined,
Figure 66749DEST_PATH_IMAGE027
in order to install the space for the connecting piece,
Figure 931937DEST_PATH_IMAGE028
is the diameter of the connecting piece;
step 6: and assembling matching prediction, wherein the evaluation criterion of the matching prediction is as follows:
Figure 8477DEST_PATH_IMAGE029
the framework skin is provided with holes to meet the requirement of assembly matching;
Figure 529588DEST_PATH_IMAGE030
and the framework skin hole-making does not meet the requirement of assembly matching.
2. The method for predicting the skin-skeleton matching of the aircraft component according to claim 1, wherein in step 2, gross errors of the measured data of the skeleton connecting holes and the measured data of the skin connecting holes are removed, and the removing method comprises the following steps:
step 2-1: calculating the hole site measurement deviation of the skeleton and the skin
Figure 779304DEST_PATH_IMAGE031
Average value of (2)
Figure 702261DEST_PATH_IMAGE032
And standard deviation of
Figure 12019DEST_PATH_IMAGE033
；
Step 2-2: judging the residual error of each hole site measurement data
Figure 20427DEST_PATH_IMAGE034
If there is more than 3 standard deviations
Figure 73833DEST_PATH_IMAGE035
Residual error of
Figure 851296DEST_PATH_IMAGE036
Measured value, i.e.
Figure 331956DEST_PATH_IMAGE037
If the error is large, the error is considered to be contained, and the error is eliminated;
step 2-3: repeating the step 2-1 and the step 2-2 until the residual errors of the hole position measurement data of all the connecting holes of the framework and the skin are all in
Figure 562080DEST_PATH_IMAGE038
Within.
3. The method for predicting the skin-skeleton matching of the aircraft component according to claim 1 or 2, wherein in step 2, the incomplete corresponding relation measurement data includes: only the data of the hole positions of the skeleton connecting holes and the data of the hole positions of the skin connecting holes are lacked, and only the data of the hole positions of the skin connecting holes and the data of the hole positions of the skeleton connecting holes are lacked.
4. The method for predicting skin-skeleton compatibility of an aircraft component according to claim 1, wherein the step 3 specifically includes:
step 3-1: to framework connecting hole measuring point set
Figure 419178DEST_PATH_IMAGE039
And skin connecting hole measuring point set
Figure 51148DEST_PATH_IMAGE040
The centers of gravity of the two sets of data are calculated respectively:
Figure 702709DEST_PATH_IMAGE041
Figure 682779DEST_PATH_IMAGE042
；
step 3-2: solving the displacement vector of each point relative to the gravity center:
Figure 77988DEST_PATH_IMAGE043
Figure 564464DEST_PATH_IMAGE044
；
step 3-3: by using the displacement vector of the center of gravity
Figure 652506DEST_PATH_IMAGE045
Matrix:
Figure 857222DEST_PATH_IMAGE046
；
step 3-4: to pair
Figure 56122DEST_PATH_IMAGE047
Performing singular value decomposition on the matrix:
Figure 397105DEST_PATH_IMAGE048
；
in the formula (I), the compound is shown in the specification,
Figure 656048DEST_PATH_IMAGE049
is an orthogonal matrix, and the matrix is,
Figure 348060DEST_PATH_IMAGE050
a diagonal matrix that is non-negative;
step 3-5: computing rotation matrices
Figure 85072DEST_PATH_IMAGE051
And translation matrix
Figure 546141DEST_PATH_IMAGE052
：
Figure 913668DEST_PATH_IMAGE053
Figure 889714DEST_PATH_IMAGE054
。
5. The method for predicting skin-skeleton compatibility of an aircraft component according to claim 1, wherein the step 1 specifically includes:
step 1-1: after the holes are made in all the connecting holes on the skin part, measuring by using high-precision measuring equipment to obtain the hole site aperture of the connecting hole on the skin, and recording
Figure 368100DEST_PATH_IMAGE055
The hole site of each skin connecting hole is
Figure 11571DEST_PATH_IMAGE056
Pore diameter of
Figure 281491DEST_PATH_IMAGE057
；
Step 1-2: after the holes of all the connecting holes on the framework of the airplane part are manufactured, hole site apertures of the connecting holes on the framework are measured and obtained by using high-precision measuring equipment, and the hole site apertures are recorded
Figure 10413DEST_PATH_IMAGE058
The hole site of each framework connecting hole is
Figure 26910DEST_PATH_IMAGE059
Pore diameter of
Figure 524888DEST_PATH_IMAGE060
。
6. The method for predicting the skin-skeleton matching of the aircraft component according to claim 5, wherein the high-precision measuring device is a machine tool online probe or a three-coordinate measuring machine.
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