CN113467372B - Method for determining machining reference of aircraft component - Google Patents
Method for determining machining reference of aircraft component Download PDFInfo
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- CN113467372B CN113467372B CN202111037727.3A CN202111037727A CN113467372B CN 113467372 B CN113467372 B CN 113467372B CN 202111037727 A CN202111037727 A CN 202111037727A CN 113467372 B CN113467372 B CN 113467372B
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- G05B—CONTROL OR REGULATING SYSTEMS IN GENERAL; FUNCTIONAL ELEMENTS OF SUCH SYSTEMS; MONITORING OR TESTING ARRANGEMENTS FOR SUCH SYSTEMS OR ELEMENTS
- G05B19/00—Programme-control systems
- G05B19/02—Programme-control systems electric
- G05B19/18—Numerical control [NC], i.e. automatically operating machines, in particular machine tools, e.g. in a manufacturing environment, so as to execute positioning, movement or co-ordinated operations by means of programme data in numerical form
- G05B19/401—Numerical control [NC], i.e. automatically operating machines, in particular machine tools, e.g. in a manufacturing environment, so as to execute positioning, movement or co-ordinated operations by means of programme data in numerical form characterised by control arrangements for measuring, e.g. calibration and initialisation, measuring workpiece for machining purposes
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- G—PHYSICS
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- G05B—CONTROL OR REGULATING SYSTEMS IN GENERAL; FUNCTIONAL ELEMENTS OF SUCH SYSTEMS; MONITORING OR TESTING ARRANGEMENTS FOR SUCH SYSTEMS OR ELEMENTS
- G05B2219/00—Program-control systems
- G05B2219/30—Nc systems
- G05B2219/37—Measurements
- G05B2219/37221—Probe fixture to know datum points
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Abstract
The application discloses a method for determining a machining standard of an aircraft component, which comprises the following steps: designing N reserved reference holes on the airplane component, wherein the hole centers of the reference holes are not arranged in the same plane of the airplane component; acquiring actual measurement data and theoretical data of a reference hole center of an airplane component; constructing a conversion relation matrix and an evaluation function between the reference hole center actual measurement point set and the reference hole center theoretical point set; calculating and solving by using a singular value decomposition method to obtain a matching transformation relation matrix R, t which enables the evaluation function value to be minimum; calculating a conversion residual error Ei of the actual measurement point position of the hole center of each reference hole; and screening and rejecting thresholds to obtain a final conversion relation matrix R ´, t ´ from a machine tool coordinate system to an airplane coordinate system.
Description
Technical Field
The application relates to the technical field of airplane assembly, in particular to a method for determining machining reference of airplane components.
Background
At present, in the process of aircraft assembly and manufacturing, in order to improve hole making precision and efficiency, after the framework parts of the aircraft components are assembled, a large-scale multi-axis linkage numerical control machine tool is adopted to process numerical control holes and molded surfaces, the correctness of the establishment of a component processing benchmark is used as a key for ensuring the processing of the aircraft components, and the success or failure of the processing task of the aircraft components is determined.
The essence of establishing the machining benchmark of the aircraft component is to solve the problem of how to map the machining information in the theoretical state of the aircraft to the actual structure of the aircraft through a certain conversion relation. The traditional method for establishing the workpiece machining coordinate system cannot be suitable for machining the airplane components and cannot accurately reflect the relationship between the actual state and the theoretical state of the airplane components.
Disclosure of Invention
The main purpose of the present application is to provide a method for determining an aircraft component machining standard, so as to effectively determine the aircraft component machining standard and accurately reflect the relationship between the actual state and the theoretical state of the aircraft component.
In order to achieve the above object, the present application provides an aircraft component machining reference determining method, including the steps of:
designing N reserved reference holes on the aircraft component, wherein the hole centers of the reference holes are not arranged in the same plane of the aircraft component; wherein N is the number of the reference holes, and N is more than or equal to 4;
acquiring measured data and theoretical data of a reference hole center of the aircraft component, and specifically comprising the following steps:
step S1: establishing a machine tool coordinate system C2, measuring a reference hole center on the airplane component through a numerical control machine tool based on the machine tool coordinate system C2, and recording a set of actual measuring points of the reference hole center as { Qi=[Xqi Yqi Zqi]T|QiE.g. Q, i =1,2, ·, n }; wherein Q isiThe measured point is a reference hole center measured point, and Q is a set of reference hole center measured points;
step S2: establishing an airplane coordinate system C1, acquiring a theoretical value corresponding to the measured reference hole center based on the airplane coordinate system C1,the reference hole center theory point set is marked as { Pi=[Xpi Ypi Zpi]T|PiE.g. P, i =1,2, ·, n }; wherein, PiThe reference hole theoretical point is P, and the P is a reference hole theoretical point set;
step S3: according to the corresponding relation between the theoretical position and the actual measurement position of the hole center of the reference hole, arranging the actual measurement data point and the theoretical data point to ensure that each measured hole center of the reference hole has a data pair; the data pairs are measured data and theoretical data corresponding to the hole center of the reference hole;
constructing a conversion relation matrix and an evaluation function between the reference hole center actual measurement point set and the reference hole center theoretical point set based on the actual measurement data and the theoretical data of the reference hole center;
according to the evaluation function and the conversion relation matrix, calculating and solving by using a singular value decomposition method to obtain a matching conversion relation matrix R, t which enables the evaluation function to take the minimum value; wherein R is a rotation matrix from the reference hole center actual measurement point to the theoretical point, and t is a translation matrix from the reference hole center actual measurement point to the theoretical point;
calculating a conversion residual error Ei of the actual measurement point position of the hole center of each reference hole according to the matching conversion relation matrix R, t;
and judging whether the conversion residual errors Ei of all the reference hole centers are smaller than or equal to a threshold value e, if not, removing the data pair with the largest conversion residual error Ei, returning the measured data and the theoretical data based on the reference hole centers by using the residual data pairs, and constructing a conversion relation matrix and an evaluation function between the reference hole center measured point set and the reference hole center theoretical point set until the conversion residual errors Ei of all the reference hole centers are smaller than or equal to the threshold value e, and acquiring a final conversion relation matrix R ´, t ´.
Optionally, the reference hole center is obtained by intersecting a reference hole boss small plane and a reference hole axis, wherein the reference hole boss small plane is obtained by fitting M measurement points on a reference hole boss, the reference hole axis is an axis of a fitting cylinder with K measurement points on the inner wall of the reference hole, and the reference hole axis is divided into R layers, and S layers meet the following relations:
optionally, the thickness H of the boss of the reference hole satisfies 8mm or more and H is not less than 4mm, the aperture D of the reference hole satisfies 20mm or more and D is not less than 4mm, and the distance between the reference holes is as follows: at least 3 reference holes are arranged at intervals L which is more than or equal to 2000mm and more than or equal to 200 mm.
Optionally, the number of data pairs is greater than or equal to 4.
Optionally, the expression of the evaluation function is:
in the formula, PiIs a reference hole center theory point, QiAnd measuring the actual point of the hole center of the reference hole.
Optionally, the calculating a conversion residual Ei of each reference hole center actual measurement point location according to the matching conversion relationship matrix R, t specifically includes:
according to the matching conversion relation matrix R, t, measuring the reference hole center real measuring point QiConverted to the aircraft coordinate system C1 and marked as Qi´=R*Qi-t; in the formula, Qi´ is a reference hole center real measuring point QiA representation under aircraft coordinate system C1 after transformation;
calculating a conversion residual error Ei = | | P of each measured point of the hole center of the reference holei-Qi´||2。
Optionally, the threshold e is a reference allowable error, and a value range of the threshold e is 1/4-1/3 of the requirement of the machining precision of the molded surface of the aircraft component.
Optionally, after the step of obtaining the final transformation relation matrix R ´, t ´, the method further includes the following steps:
and according to the final conversion relation matrix R ´, t ´, taking the machine tool coordinate system C2 as a workpiece coordinate system of the airplane component machining, taking the origin of the machine tool coordinate system C2 as the original point of the airplane component machining, converting theoretical data of the center of a reference hole in the airplane component in the airplane coordinate system C1 into the machine tool coordinate system C2, and carrying out machining tasks.
Optionally, the numerical control machine is a multi-axis linkage numerical control machine, an online probe is arranged on the multi-axis linkage numerical control machine, and the online probe is used for measuring a reference hole center on the aircraft component.
The beneficial effect that this application can realize is as follows:
the method has the advantages that the reference holes are reserved on the airplane components, the arrangement and the measurement of the reference holes are clearly defined, the operation guidance is strong, and the accuracy of the method is guaranteed; by establishing the relation between the reference allowable error and the machining precision requirement of the airplane component, a threshold judgment and rejection mechanism is designed for assisting in solving a matching transformation relation matrix, and the quantitative control of the machining precision requirement of the airplane component on the component reference establishment is realized; the conversion residual errors of all the reference holes are solved based on the established coordinate system conversion relation, and the conversion residual errors can be used for evaluating the error condition of the reference solution on one hand and evaluating the local deformation condition of the structure of the airplane component on the other hand.
Drawings
In order to more clearly illustrate the detailed description of the present application or the technical solutions in the prior art, the drawings that are needed in the detailed description of the present application or the technical solutions in 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 determining a machining reference for an aircraft component according to the present application;
fig. 2 is a schematic view of an application scenario of the method for determining the machining reference of the aircraft component according to the present application;
FIG. 3 is a schematic illustration of a reference hole center measurement according to the present application;
FIG. 4 is a schematic diagram illustrating the principle of matching conversion between an actual measurement reference hole center and a theoretical reference hole center in the present application;
FIG. 5 is a schematic view (partially enlarged) of the positional relationship of a datum hole boss on an aircraft component according to the present application.
Reference numerals:
1-an aircraft part, 2-a reference hole, 3-a numerical control machine tool, 4-an online probe, 5-a reference hole center and 6-a reference hole boss.
The implementation, functional features and advantages of the objectives of the present application will be further explained with reference to the accompanying drawings.
Detailed Description
The technical solutions in the embodiments of the present application will be described clearly and completely with reference to the drawings in the embodiments of the present application, and it is obvious that the described embodiments are only a part of the embodiments of the present application, and not all of the embodiments. 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 application.
It should be noted that all the directional indications (such as up, down, left, right, front, and back … …) in the embodiment of the present application are only used to explain the relative position relationship between the components, the motion situation, and the like in a specific posture, and if the specific posture is changed, the directional indication is changed accordingly.
In this application, unless expressly stated or limited otherwise, the terms "connected," "secured," and the like are to be construed broadly, and for example, "secured" may be a fixed connection, a removable connection, or an integral part; can be mechanically or electrically connected; they may be directly connected or indirectly connected through intervening media, or they may be connected internally or in any other suitable relationship, unless expressly stated otherwise. The specific meaning of the above terms in the present application can be understood by those of ordinary skill in the art as appropriate.
In addition, if there is a description of "first", "second", etc. in the embodiments of the present application, the description of "first", "second", etc. is for descriptive purposes only and is not to be construed as indicating or implying relative importance or implicitly indicating the number of technical features indicated. Thus, a feature defined as "first" or "second" may explicitly or implicitly include at least one such feature. In addition, the meaning of "and/or" appearing throughout includes three juxtapositions, exemplified by "A and/or B" including either A or B or both A and B. In addition, technical solutions between various embodiments may be combined with each other, but must be realized by a person skilled in the art, and when the technical solutions are contradictory or cannot be realized, such a combination should not be considered to exist, and is not within the protection scope of the present application.
Example 1
Referring to fig. 1 to 5, the present embodiment provides an aircraft component machining reference determining method, including the following steps:
designing N reserved reference holes 2 on the aircraft component 1, wherein the hole centers 5 of the reference holes are not arranged in the same plane of the aircraft component 1; wherein N is the number of the reference holes, and N is more than or equal to 4;
acquiring measured data and theoretical data of a reference hole center 5 of the aircraft component 1, specifically comprising the following steps:
step S1: establishing a machine tool coordinate system C2, measuring a reference hole center 5 on the airplane component 1 through a numerical control machine 3 based on the machine tool coordinate system C2, and recording a set of actual measurement points of the reference hole center 5 as { Q }i=[Xqi Yqi Zqi]T|QiE.g. Q, i =1,2, ·, n }; wherein Q isiThe measured points are the measured points of the hole center 5 of the reference hole, and Q is the measured point set of the hole center 5 of the reference hole;
step S2: establishing an airplane coordinate system C1, and acquiring the measured reference hole center 5 corresponding to the reference hole center based on the airplane coordinate system C1The theoretical value of (1), the set of 5 theoretical points of the reference hole center is marked as { Pi=[Xpi Ypi Zpi]T|PiE.g. P, i =1,2, ·, n }; wherein, PiIs a reference hole center 5 theoretical point, and P is a reference hole center 5 theoretical point set;
step S3: according to the corresponding relation between the theoretical position and the actual measurement position of the reference hole center 5, arranging the actual measurement data points and the theoretical data points to enable each measured reference hole center 5 to have a data pair; wherein, the data pair is measured data and theoretical data corresponding to the reference hole center 5;
constructing a conversion relation matrix and an evaluation function between the actual measurement point set of the reference hole center 5 and the theoretical point set of the reference hole center 5 based on the actual measurement data and the theoretical data of the reference hole center 5;
according to the evaluation function and the conversion relation matrix, calculating and solving by using a singular value decomposition method to obtain a matching conversion relation matrix R, t which enables the evaluation function to take the minimum value; wherein R is a rotation matrix from the reference hole center actual measurement point to the theoretical point, and t is a translation matrix from the reference hole center actual measurement point to the theoretical point;
calculating a conversion residual error Ei of the actual measurement point position of the hole center of each reference hole according to the matching conversion relation matrix R, t;
and judging whether the conversion residual errors Ei of all the reference hole centers 5 are smaller than or equal to a threshold value e, if not, removing the data pairs with the largest conversion residual errors Ei, returning the measured data and the theoretical data based on the reference hole centers 5 by using the residual data pairs, constructing a conversion relation matrix and an evaluation function between the actual measurement point set of the reference hole centers 5 and the theoretical point set of the reference hole centers 5, and obtaining a final conversion relation matrix R ´, t ´ until the conversion residual errors Ei of all the reference hole centers 5 are smaller than or equal to the threshold value e.
Because the traditional numerical control part machining determines a workpiece machining coordinate system through methods such as leveling and alignment, the method is simple and convenient to operate, the aircraft component 1 has the characteristics of large size, large number of parts and complex structural form, the actual state of the aircraft component 1 is greatly different from the theoretical state due to the influence of factors such as part manufacturing errors, structural assembly errors and structural deformation, and the traditional workpiece machining coordinate system establishing method cannot be suitable for machining the aircraft component 1. Therefore, it is necessary to design a method for establishing a machining reference of the aircraft component 1 in a targeted manner according to the structural characteristics of the machining of the aircraft component 1, wherein the method can quickly complete the establishment of the machining reference and accurately reflect the relationship between the actual state and the theoretical state of the aircraft component 1.
Therefore, in the embodiment, the reserved reference hole 2 is designed on the aircraft component 1 for assisting the establishment of the machining reference; when the hole center data of the reference hole 2 is acquired, the data comprises actual measurement data under a machine tool coordinate system and theoretical data under an airplane coordinate system; when the mapping transformation matrix is solved, constructing a transformation relation evaluation function, and solving parameter values under the condition of a function minimum value by using a singular value decomposition method to obtain a mapping transformation relation matrix; then, evaluating the conversion residual errors of the reference hole 2, comparing the conversion residual errors under an airplane coordinate system based on the solved conversion matrix, eliminating residual error values and performing cyclic iteration until all the reference conversion residual errors meet the threshold requirement; the final mapping transformation matrix is determined, and then the processing task of the aircraft component 1 can be carried out, the method uses the aircraft state actual measurement data on the data input source, and evaluates the transformation error and the difference between the aircraft actual state and the theoretical state through the transformation residual error, the method has simple principle and good operability, and can meet the requirement of establishing the processing reference of the aircraft component 1 under the condition that the measurement capability of the numerical control machine 3 and the assembly precision of the framework of the aircraft component 1 are considered to be at the conventional level. Based on the method, the method does not depend on external tools, is simple, quick and convenient, and can be used for other similar processing scenes which need to be processed but cannot find a reliable reference.
Meanwhile, in the embodiment, the machine coordinate system C2 is respectively established, the data of the set of actual measurement points of the reference hole center 5 is measured, and then the set of theoretical points of the reference hole center 5 is obtained based on the theoretical value corresponding to the actual measurement of the reference hole center 5 according to the established aircraft coordinate system C1, so that a data pair is ensured to exist in each measured reference hole 2 according to the corresponding relationship between the theoretical position and the actual measurement position of the reference hole center 5, the data acquisition is efficient and accurate, and a foundation is laid for solving the subsequent conversion relationship.
It should be noted that, in the step of solving the mapping transformation relationship, the singular value decomposition method is an important matrix decomposition in linear algebra, and the singular value decomposition method is a generalization of feature decomposition on any matrix, and has important applications in the fields of signal processing, statistics, and the like. The singular value decomposition method belongs to the well-known theory and is not described in detail here.
As an optional implementation manner, the reference hole center 5 is obtained by intersecting a reference hole boss 6 facet with the axis of the reference hole 2, wherein the reference hole boss 6 facet is obtained by fitting M measurement points on the reference hole boss 6, the axis of the reference hole 2 is the axis of a fitting cylinder with K measurement points on the inner wall of the reference hole 2, and the fitting cylinder is divided into R layers, and each layer is S, and the following relationships are satisfied:
in the embodiment, the reference hole center 5 is clearly defined, the operation guidance is strong, and the acquisition mode and the relational expression of the reference hole boss 6 facet are clearly given, so that the accurate measurement of the reference hole center 5 is ensured.
As an optional implementation mode, the thickness H of the boss 6 of the datum hole meets the condition that H is more than or equal to 8mm and more than or equal to 4mm, the aperture D of the datum hole 2 meets the condition that D is more than or equal to 20mm and more than or equal to 4mm, and the distance between datum holes 2 is as follows: at least 3 reference holes 2 are mutually spaced at intervals L which are more than or equal to 2000mm and more than or equal to 200 mm.
In this embodiment, rationally define 2 aperture D of benchmark hole, interval requirement and 6 thickness H of benchmark hole boss, make the follow-up measured data more reliable really, more representative.
As an optional implementation manner, the number of the data pairs is greater than or equal to 4, so that the reliability of the data is ensured.
As an alternative implementation, the expression of the evaluation function is:
in the formula, PiIs a reference hole center 5 theoretical point, QiAnd measuring the actual point of the hole center 5 of the reference hole.
According to the evaluation function, the matching transformation relation matrix R, t can be obtained through accurate calculation and solving, and the method has better guiding significance.
As an optional implementation manner, the calculating, according to the matching transformation relationship matrix R, t, a transformation residual Ei of the measured point location of each reference hole center 5 specifically includes:
according to the matching conversion relation matrix R, t, measuring the reference hole center 5 actual measuring point QiConverted to the aircraft coordinate system C1 and marked as Qi´=R*Qi-t; in the formula, Qi´ is a reference hole center 5 actual measurement point QiA representation under aircraft coordinate system C1 after transformation;
calculating a conversion residual Ei = | | | P of each measured point position of the hole center 5 of the reference holei-Qi´||2。
In this embodiment, a calculation formula of the conversion residual Ei is specifically given, and according to the calculation formula, the conversion residual of the actual measurement point location of each reference hole center 5 can be accurately calculated.
As an optional implementation mode, the threshold e is a reference allowable error, and the value range of the threshold e is 1/4-1/3 of the requirement of the machining precision of the molded surface of the aircraft component. The threshold e is guaranteed to be within a reasonable error range.
As an alternative implementation, after the step of obtaining the final transformation relation matrix R ´, t ´, the method further includes the following steps:
and according to the final conversion relation matrix R ´, t ´, converting theoretical data of the center of a reference hole in the airplane component 1 in the airplane coordinate system C1 into the machine tool coordinate system C2 by taking the machine tool coordinate system C2 as a workpiece coordinate system for processing the airplane component 1 and the origin of the machine tool coordinate system C2 as a processing origin of the airplane component 1, and carrying out processing tasks.
As an alternative embodiment, the numerical control machine 3 is a multi-axis linkage numerical control machine, an online probe 4 is arranged on the multi-axis linkage numerical control machine, and the online probe 4 is used for measuring the reference hole center 5 on the aircraft component 1 without using another measuring device.
Example 2
Referring to fig. 1 to 4, in this embodiment, in combination with specific practical applications, a method for determining a machining standard of an aircraft component is provided, where relevant parameters are first set as shown in table 1:
TABLE 1 reference hole measurements and theoretical values
| Variables of | Assignment of value |
| Number of reference holes N | 16 |
| Thickness H of boss of reference hole | 4mm |
| Reference hole pitch L | 600~2000mm |
| Reference hole diameter D | Φ12mm |
| Reference hole accuracy A | H8 |
| Number M of fitting points of |
4 |
| Number of points R taken from inner wall of |
2 |
| Number of spot taking layers S on inner wall of |
4 |
| Tolerance of machining reference e | 0.2 |
The following is a description of specific steps:
step 1: arrangement of reference holes:
in the embodiment, the datum holes 2 are arranged on the aircraft component 1 in advance according to the parameter setting of the table 1, and the positions of the hole centers 5 of the datum holes are not in the same plane of the aircraft component 1;
step 2: collecting datum hole data:
step 2-1: measuring a reference hole center 5 on the airplane component 1 by using a multi-axis linkage numerical control machine tool, wherein the measurement uncertainty of an online probe 4 of the multi-axis linkage numerical control machine tool is 0.04mm as shown in a table 2;
step 2-2: obtaining theoretical values of the corresponding reference holes 5 in an airplane coordinate system according to the measured information of the reference holes 2, and referring to table 2;
TABLE 2 statistical table of measured and theoretical values of reference holes
And step 3: solving a mapping conversion relation:
an error evaluation function is constructed by using a least square method, a singular value decomposition method is used for solving an error minimum value of the evaluation function, and a hole center point set { Q) is matched and measuredi=[Xqi Yqi Zqi]T|QiE.g. Q, i =1,2,.., n } to a set of theoretical hole center points { P }i=[Xpi Ypi Zpi]T|PiE.g. P, i =1,2,.. n }, and obtaining a matching transformation relation matrix R1,t1Namely:
and 4, step 4: calculating the transformation residual error of each real measuring point:
using a transformation relation matrix R1,t1To determine the pore site QiConverted into an airplane coordinate system and recorded as Qi´, calculating an actually measured point location transformation residual error Ei, as shown in Table 3:
TABLE 3 hole center points and residuals after transformation
And 5: threshold screening and elimination:
comparing whether the residual error Ei of the hole center 5 of the reference hole is less than or equal to 0.2mm, if the point 14 is not full and is the maximum point of the residual error, eliminating the point 14, repeating the steps 3-5 by using the residual data pairs until the conversion residual errors of all the hole center points meet the threshold value requirement, and finally, adding 11 residual reference holes into the reference calculation, wherein the reference calculation is shown in a table 4:
TABLE 4 reference hole and residual information ultimately involved in the calculation
Step 6: acquiring a final conversion relation matrix:
to this end, the finally obtained transformation relation R ´, t ´ is the relation of the machine coordinate system with respect to the aircraft coordinate system:
by utilizing the conversion relation and taking the original point of the machine tool as the original point of the machining coordinate system, the part machining information of the design digifax can be converted into the machine tool coordinate system to carry out part machining work.
The above description is only a preferred embodiment of the present application, and not intended to limit the scope of the present application, and all modifications of equivalent structures and equivalent processes, which are made by the contents of the specification and the drawings of the present application, or which are directly or indirectly applied to other related technical fields, are included in the scope of the present application.
Claims (9)
1. An aircraft component machining reference determining method is characterized by comprising the following steps:
designing N reserved reference holes on the aircraft component, wherein the hole centers of the reference holes are not arranged in the same plane of the aircraft component; wherein N is the number of the reference holes, and N is more than or equal to 4;
acquiring measured data and theoretical data of a reference hole center of the aircraft component, and specifically comprising the following steps:
step S1: establishing a machine tool coordinate system C2, measuring a reference hole center on the airplane component through a numerical control machine tool based on the machine tool coordinate system C2, and recording a set of actual measuring points of the reference hole center as { Qi=[Xqi Yqi Zqi]T|QiE.g. Q, i =1,2, ·, n }; wherein Q isiThe measured point is a reference hole center measured point, and Q is a set of reference hole center measured points;
step S2: establishing an airplane coordinate system C1, and acquiring a theoretical value corresponding to the actually measured reference hole center based on the airplane coordinate system C1, wherein the reference hole center theoretical point set is marked as { P }i=[Xpi Ypi Zpi]T|PiE.g. P, i =1,2, ·, n }; wherein, PiThe reference hole theoretical point is P, and the P is a reference hole theoretical point set;
step S3: according to the corresponding relation between the theoretical position and the actual measurement position of the hole center of the reference hole, arranging the actual measurement data point and the theoretical data point to ensure that each measured hole center of the reference hole has a data pair; the data pairs are measured data and theoretical data corresponding to the hole center of the reference hole;
constructing a conversion relation matrix and an evaluation function between the reference hole center actual measurement point set and the reference hole center theoretical point set based on the actual measurement data and the theoretical data of the reference hole center;
according to the evaluation function and the conversion relation matrix, calculating and solving by using a singular value decomposition method to obtain a matching conversion relation matrix R, t which enables the evaluation function to take the minimum value; wherein R is a rotation matrix from the reference hole center actual measurement point to the theoretical point, and t is a translation matrix from the reference hole center actual measurement point to the theoretical point;
calculating a conversion residual error Ei of the actual measurement point position of the hole center of each reference hole according to the matching conversion relation matrix R, t;
and judging whether the conversion residual errors Ei of all the reference hole centers are smaller than or equal to a threshold value e, if not, removing the data pair with the largest conversion residual error Ei, returning the measured data and the theoretical data based on the reference hole centers by using the residual data pairs, and constructing a conversion relation matrix and an evaluation function between the reference hole center measured point set and the reference hole center theoretical point set until the conversion residual errors Ei of all the reference hole centers are smaller than or equal to the threshold value e, and acquiring a final conversion relation matrix R ´, t ´.
2. The method for determining the machining reference of the aircraft component as claimed in claim 1, wherein the reference hole center is obtained by intersecting a reference hole boss small plane with a reference hole axis, wherein the reference hole boss small plane is obtained by fitting M measuring points on a reference hole boss, the reference hole axis is an axis of a fitting cylinder which is obtained by fitting K measuring points on the inner wall of a reference hole, and the reference hole axis is divided into R layers, and each layer is S, and the following relation is satisfied:
3. the method for determining the machining reference of the aircraft component as claimed in claim 2, wherein the boss thickness H of the reference hole is more than or equal to 8mm and more than or equal to H and more than or equal to 4mm, the bore diameter D of the reference hole is more than or equal to 20mm and more than or equal to D and more than or equal to 4mm, and the distance between the reference holes is as follows: at least 3 reference holes are arranged at intervals L which is more than or equal to 2000mm and more than or equal to 200 mm.
4. An aircraft component machining reference determining method as claimed in claim 1, wherein the number of said data pairs is 4 or more.
5. An aircraft component machining reference determining method as claimed in claim 1, wherein the evaluation function is expressed by:
in the formula, PiIs a reference hole center theory point, QiAnd measuring the actual point of the hole center of the reference hole.
6. The method for determining the machining reference of the aircraft component according to claim 5, wherein the calculating a conversion residual Ei of the actual measurement point location of the hole center of each reference hole according to the matching conversion relation matrix R, t specifically includes:
according to the matching conversion relation matrix R, t, measuring the reference hole center real measuring point QiConverted to the aircraft coordinate system C1 and marked as Qi´=R*Qi-t; in the formula, Qi´ is a reference hole center real measuring point QiA representation under aircraft coordinate system C1 after transformation;
calculating a conversion residual error Ei = | | P of each measured point of the hole center of the reference holei-Qi´||2。
7. The method for determining the machining reference of the aircraft component as claimed in claim 1, wherein the threshold e is a reference allowable error, and the value range of the threshold e is 1/4-1/3 of the machining precision requirement of the profile of the aircraft component.
8. An aircraft component machining reference determining method as claimed in claim 1, wherein said step of obtaining a final transformation relationship matrix R ´, t ´ is followed by the further steps of:
and according to the final conversion relation matrix R ´, t ´, taking the machine tool coordinate system C2 as a workpiece coordinate system of the airplane component machining, taking the origin of the machine tool coordinate system C2 as the original point of the airplane component machining, converting theoretical data of the center of a reference hole in the airplane component in the airplane coordinate system C1 into the machine tool coordinate system C2, and carrying out machining tasks.
9. The method for determining the machining reference of the aircraft component as claimed in claim 1, wherein the numerical control machine is a multi-axis linkage numerical control machine, an online probe is arranged on the multi-axis linkage numerical control machine, and a reference hole center on the aircraft component is measured through the online probe.
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| Application Number | Priority Date | Filing Date | Title |
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| CN202111037727.3A CN113467372B (en) | 2021-09-06 | 2021-09-06 | Method for determining machining reference of aircraft component |
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| CN114065406B (en) * | 2022-01-17 | 2022-05-10 | 成都飞机工业（集团）有限责任公司 | Method, device and equipment for designing fabrication hole and storable medium |
| CN114897448B (en) * | 2022-07-12 | 2022-12-13 | 成都飞机工业（集团）有限责任公司 | Airplane movable part evaluation method and device, storage medium and equipment |
| CN115090917B (en) * | 2022-08-25 | 2023-01-10 | 成都飞机工业（集团）有限责任公司 | Hole making method and device, storage medium and equipment |
| CN116382191A (en) * | 2023-04-07 | 2023-07-04 | 成都飞机工业（集团）有限责任公司 | Numerical control machining method and coordinate system establishment method for finished part based on part characteristics |
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