CN111661362B - Method for determining actual hole making position of aircraft skin digital hole making - Google Patents

Method for determining actual hole making position of aircraft skin digital hole making Download PDF

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CN111661362B
CN111661362B CN202010441014.2A CN202010441014A CN111661362B CN 111661362 B CN111661362 B CN 111661362B CN 202010441014 A CN202010441014 A CN 202010441014A CN 111661362 B CN111661362 B CN 111661362B
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hole
holes
processed
machined
actual
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CN111661362A (en
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付建超
樊西锋
何凤涛
谢颖
张龙
薛松
谢明伟
王维
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Chengdu Aircraft Industrial Group Co Ltd
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Chengdu Aircraft Industrial Group Co Ltd
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    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
    • B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
    • B64F5/10—Manufacturing or assembling aircraft, e.g. jigs therefor
    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01B—MEASURING LENGTH, THICKNESS OR SIMILAR LINEAR DIMENSIONS; MEASURING ANGLES; MEASURING AREAS; MEASURING IRREGULARITIES OF SURFACES OR CONTOURS
    • G01B11/00—Measuring arrangements characterised by the use of optical techniques
    • G01B11/002—Measuring arrangements characterised by the use of optical techniques for measuring two or more coordinates

Abstract

The application relates to the technical field of aircraft assembly, and discloses a method for determining an actual hole making position during skin digital hole making, which comprises the following steps: selecting a part of holes to be machined as measuring reference holes, and prefabricating holes on the part in a numerical control machining mode; completing the structural assembly of the airplane components; establishing an airplane coordinate system by using a laser tracker; measuring the position of the reference hole, and comparing the measured value with the theoretical value to obtain the deviation of the spatial position of the reference hole; solving the space position adjustment quantity of the hole to be processed according to the position relation between the hole to be processed and the adjacent reference hole; and adding the theoretical coordinate of the hole to be machined and the adjustment quantity to obtain the actual machining position of the hole to be machined. The method and the device improve the position precision of the reference holes relative to the parts, reduce the number of required reference holes, calculate the influence of the spatial position deviation and deformation of the parts on the processing hole positions, and solve the problem of position adjustment of corner areas.

Description

Method for determining actual hole making position of aircraft skin digital hole making
Technical Field
The application relates to the technical field of aircraft assembly, in particular to a method for determining an actual hole making position of an aircraft skin digital hole making.
Background
Because the structure of the aircraft is complicated, therefore, when the parts are assembled, the deviation between the assembled parts and the theoretical position is difficult to avoid, and the reasons mainly include: manufacturing errors, inaccurate positioning, assembly deformation and the like of parts. After the digital hole making equipment is applied, if the digital hole making equipment makes holes according to hole making holes on a theoretical digifax, due to appearance deviation after the parts are assembled, the problems that the hole edge distance is not enough, the holes enter a part R area and the like can occur, so that the position deviation of the parts needs to be input into the digital hole making equipment for adjusting the actual hole making position.
At present, the methods for determining the position deviation of the component and calculating the actual hole making position mainly include two methods: (1) the appearance of the part is directly measured, but the method is easily influenced by operation and structural curvature in the measuring process, and the measuring period is long; (2) the method comprises the steps of measuring a reference hole which is preset on a part through a laser tracker or a CCD camera, and calculating an actual hole making hole position according to the position deviation of the reference hole, wherein the reference hole is usually made manually after the part is assembled at present, so that the position error of the reference hole is large, and the assembly state of the part cannot be well reflected. Meanwhile, in the existing calculation method, the skins are usually taken as units for correction, the reference holes between the skins are relatively independent, the number of the reference holes required for calculation is large, the measurement efficiency and the use efficiency of digital hole making equipment are influenced, and the hole making positions of corner areas are difficult to calculate due to the irregular shapes of the skins.
Disclosure of Invention
In order to overcome the problems and the defects in the prior art, the method for determining the actual hole making position of the aircraft skin in the digital hole making process is provided, the calculation of the processing hole position can be completed under the scheme of setting fewer reference holes, and the influence of the spatial position deviation, the deformation and the corner area of the part is considered in the whole calculation process.
In order to achieve the above purpose, the specific technical solution of the present application is as follows:
a method for determining the actual hole making position of the digital hole making of an aircraft skin specifically comprises the following steps:
s1, selecting a part of holes from the processed target holes as measurement reference holes, and prefabricating holes on parts;
s2, completing structural assembly of airplane components in the assembly fixture;
s3, selecting a mark point on the assembly type frame, carrying out measurement, and establishing an airplane coordinate system by using a laser tracker;
s4, measuring the position of the reference hole, and comparing the measured value with a theoretical value to obtain the position deviation of the reference hole in each direction of the space;
s5, solving the spatial position adjustment quantity of the hole to be machined according to the position relation between the hole to be machined and the adjacent reference hole and the position deviation of the adjacent reference hole;
and S6, adding the theoretical coordinate of the hole to be machined and the adjustment quantity to obtain the actual machining position of the hole to be machined.
Preferably, in step S1, the measurement reference hole is made by numerical control machining.
Preferably, in step S1, the range of the reference hole is selected so as to cover all the structural parts connected to the skin to be processed, and a reference hole needs to be set on each related structural part; for parts with good rigidity and difficult deformation, the reference holes are respectively arranged at the positions close to the two sides and used for reflecting the space positions of the parts; for parts with weak structural rigidity and easy deformation, the number of reference holes needs to be increased properly for reflecting the spatial position and the deformation condition of the parts.
Preferably, the step S3 specifically includes the following steps:
s3.1, selecting mark points on the assembly type frame, wherein the mark points should envelop the distribution range of the measured reference holes as much as possible; the range of the selected reference hole is required to cover all structural parts connected with the skin to be processed, the reference hole is required to be arranged on each related structural part, and the parts with good rigidity and difficult deformation are provided with one reference hole respectively at positions close to two sides for reflecting the space positions of the parts. For parts with weak structural rigidity and changeability, the number of reference holes needs to be increased properly to reflect the spatial position and the deformation condition of the parts.
S3.2, erecting a laser tracker, and placing the laser tracker at a position where the laser tracker can measure the mark point and the reference hole simultaneously;
and S3.3, measuring the actual coordinates of the mark points in the laser tracker coordinate system, fitting the actual coordinates with the theoretical coordinates of the mark points in the airplane coordinate system, and establishing the airplane coordinate system.
Preferably, in step S3.2, if one position cannot measure all the reference holes, the reference holes may be measured at multiple positions, and the mark points used in each position measurement should envelop the distribution range of the reference holes in this measurement as much as possible.
Preferably, the step S4 specifically includes the following steps:
s4.1, acquiring reference hole Q from theoretical digital analogyiTheoretical coordinates in the plane coordinate system
Qi＝(xi，yi，zi)T,i＝1...n；
S4.2 measuring the actual position of the reference hole using the target ball in the aircraft coordinate system established in step S3
Figure BDA0002504051840000021
S4.3, obtaining a reference hole QiPositional deviation in three spatial directions
Figure BDA0002504051840000022
Where i is the single reference well and n is the total number of reference wells.
Preferably, the step S5 specifically includes the following steps:
s5.1, obtaining a hole P to be machined from a theoretical digital analogyjTheoretical coordinates in the plane coordinate system
Pj＝(xj，yj，zj)T,j＝1...m；
Wherein j is a single hole to be processed, and m is the total number of the holes to be processed;
s5.2, classifying the datum holes according to the structural parts, and classifying the datum holes belonging to a certain part into one class;
s5.3, calculating a hole P to be machinedjTheoretical distance d from all reference holes on the structural partk
Figure BDA0002504051840000031
And k is the total number of the reference holes on the structural part to which the holes to be machined belong.
S5.4, two reference holes Q closest to the hole to be machined are determined by comparing the distance values in the step S5.3s、QtThe theoretical coordinates of which in the plane coordinate system are respectively
Qs＝(xs，ys，zs)T；
Qt＝(xt，yt，zt)T；
Wherein Q issIs the reference hole, Q, closest to the hole to be machinedtIs a reference hole next to the hole to be processed;
s5.5, calculating a hole P to be processedjAt the reference hole Qs、QtProjection point H on the connecting lined＝(xd，yd，zd)TAnd satisfies the following conditions:
Figure BDA0002504051840000032
Figure BDA0002504051840000033
s5.6, judging the projection point HdAnd a reference hole Qs、QtRelative position of
If it is
Figure BDA0002504051840000034
Then projection point HdAt the reference hole Qs、QtAnd (3) between the connecting lines, adopting a double-datum hole calculation method, wherein the position adjustment amount of the point to be processed is as follows:
Figure BDA0002504051840000035
if it is
Figure BDA0002504051840000036
Then projection point HdAt the reference hole Qs、QtOutside the connecting line, a single reference hole calculation method is adopted, and a hole P to be processedjThe position adjustment amount of (2) is the nearest reference hole QsAnd if the measured position deviation exists, the position adjustment amount of the hole to be processed is as follows:
△Pj＝(△xj，△yj，△zj)T＝(△xs,△ys,△zs)T；
wherein (. DELTA.x)s,△ys,△zs)TAnd ([ delta ] x)t,△yt,△zt)TAre respectively a reference hole Qs、QtThe measured positional deviation.
And S5.7, traversing until the position adjustment amount of all holes to be processed is calculated.
Preferably, the step S6 specifically includes the following steps:
s6.1, calculating single hole P to be processedjActual machining position P in the aircraft coordinate systemj *
Pj *＝Pj+△Pj＝(xj+△xj，yj+△yj，zj+△zj)T；
And S6.2, traversing until the actual machining positions of all the holes to be machined are calculated.
The beneficial effect of this application:
(1) in the method for determining the actual hole making position during the digital hole making of the aircraft skin, the processing mode of the reference hole is determined to be part workshop numerical control processing, and therefore compared with the existing manual hole making mode, the position accuracy of the reference hole and the hole to be processed is remarkably improved.
(2) In the application, when the positions of the holes to be processed are adjusted by adopting the reference holes, whether the holes to be processed and the reference holes belong to the same structural part or not is only considered, whether the holes to be processed and the reference holes belong to the same skin or not is not considered, the classification condition is simplified, the number of the reference holes required by calculating all position adjustment amounts is reduced by 1/3-1/2, and therefore the working efficiency is greatly improved.
(3) In the application, the position relation between the hole to be processed and the adjacent reference hole is compared in the position adjusting amount calculating process, and the calculating method of the single reference hole and the double reference holes is provided, so that the influence of the spatial position deviation and the deformation of the part on the processing hole position is considered, and the position adjusting problem of the corner area is solved.
(4) The method and the device for calculating the position adjustment amount are simple and efficient in process and suitable for engineering application.
Drawings
FIG. 1 is a schematic flow chart of the method of the present application;
fig. 2 is a schematic structural diagram of calculating a position adjustment amount of a hole to be processed according to the present application.
In the drawings:
1. a weak rigid structural part A; 2. a strong rigid structural part B; 3. covering C; 4. covering D; 5. reference hole Q4(ii) a 6. Reference hole Q5(ii) a 7. Reference hole Q3(ii) a 8. Reference hole Q2(ii) a 9. Reference hole Q1(ii) a 10. To-be-machined hole P1(ii) a 11. To-be-machined hole P2(ii) a 12. Reference hole Q1、Q2Connecting wires; 13. p1At Q1、Q2Projection point H on the connecting lined1；14、P2At Q1、Q2Projection point H on the connecting lined2。
Detailed Description
The present application will be described in further detail with reference to examples, but the embodiments of the present application are not limited thereto.
The embodiment discloses a method for determining the actual hole making position of the digital hole making of an aircraft skin, which specifically comprises the following steps:
s1, selecting a part of holes from the processed target holes as measurement reference holes, and prefabricating the measurement reference holes on a part:
the measuring reference hole needs to be manufactured in advance on the structural part, so that in order to ensure the position precision of the reference hole relative to the part, a part manufacturing unit performs prefabrication on the part in a numerical control machining mode, and the hole position precision of the relative part meets +/-0.1 mm; in addition, the range of the selected reference hole covers all the structural parts connected with the skin to be processed, and each related structural part is required to be provided with the reference hole; for parts with good rigidity and difficult deformation, the reference holes are respectively arranged at the positions close to the two sides and used for reflecting the space positions of the parts; for parts with weak structural rigidity and easy deformation, the number of reference holes needs to be increased properly to reflect the spatial position and the deformation condition of the parts;
referring to FIG. 2 of the specification, a hole Q is selected from a target hole to be machined1、Q2、Q3、Q4、Q5The structural parts of the skin C and the skin D connected in the drawing are a weak rigid structural part A and a strong rigid structural part B which are used as measuring reference holes (the processed target holes are more and are not all drawn in the drawing), so that the weak rigid structural part A and the strong rigid structural part B are both provided with reference holes, the parts B are good in rigidity and not prone to deformation, and the reference holes Q are arranged near the two sides4And Q5For reflecting the spatial position of the component B, while the component A has weak structural rigidity and is easy to change, so that the reference hole Q is provided1、Q2、Q3Wherein, the reference hole Q1、Q3For reflecting the spatial position of part A, reference hole Q2For reflecting the deformation of the part A.
And S2, completing the structural assembly of the airplane components in the assembly fixture.
S3, selecting a mark point on the assembly type frame, measuring by using a laser tracker, and establishing an airplane coordinate system:
s3.1, selecting mark points on the assembly type frame, wherein the mark points should envelop the measured reference hole Q as much as possible1、Q2、Q3、Q4、Q5The distribution range of (c);
s3.2, erecting a laser tracker, and placing the laser tracker to a position where the mark point and the reference hole can be measured simultaneously:
if one position cannot measure all the reference holes Q1、Q2、Q3、Q4、Q5The reference hole can be measured at multiple positions, and the mark points used in the measurement at each position should envelop the distribution range of the reference hole at the current measurement as much as possibleEnclosing;
and S3.3, measuring the actual coordinates of the mark points in the laser tracker coordinate system, fitting the actual coordinates with the theoretical coordinates of the mark points in the airplane coordinate system, and establishing the airplane coordinate system.
S4, measuring a reference hole Q1、Q2、Q3、Q4、Q5Comparing the measured value with the theoretical value to obtain the position deviation of the reference hole in each direction of the space:
s4.1, acquiring reference hole Q from theoretical digital analogy1、Q2、Q3、Q4、Q5Theoretical coordinates in the plane coordinate system
Qi＝(xi，yi，zi)T,i＝1...5；
S4.2 measuring the actual position of the reference hole using the target ball in the aircraft coordinate system established in step S3
Figure BDA0002504051840000051
S4.3, obtaining a reference hole QiPositional deviation in three spatial directions
Figure BDA0002504051840000052
Where i is a single fiducial hole.
S5, according to the hole P to be processed1、P2And solving the spatial position adjustment quantity of the hole to be processed according to the position relation between the hole to be processed and the adjacent reference hole and the position deviation of the adjacent reference hole:
s5.1, obtaining a hole P to be machined from a theoretical digital analogy1Theoretical coordinates in the plane coordinate system
P1＝(x1，y1，z1)T；
And S5.2, classifying the reference holes according to the structural parts, wherein the reference holes belonging to a certain part are classified into one type. Referring to the attached figure 2 of the specification, the base on the strong rigid part BQuasi-hole Q4And Q5Is a reference hole Q of a weak rigid part A1、Q2、Q3Is a class;
s5.3, calculating a hole P to be machined1Theoretical distance d from all reference holes on the structural partk
Figure BDA0002504051840000061
To-be-machined hole P1The part A is provided with 3 reference holes Q1、Q2、Q3；
S5.4, determining the distance P from the hole to be processed by comparing the distance values in the step S5.31Two nearest reference holes Q1、Q2The theoretical coordinates of which in the plane coordinate system are respectively
Q1＝(xs，ys，zs)T，Q2＝(xt，yt，zt)T；
Wherein Q is2Is a distance P from the hole to be processed1Nearest reference hole, Q1Is a distance P from the hole to be processed1A second closest reference hole;
s5.5, calculating a hole P to be processed1At the reference hole Q1、Q2Projection point H on the connecting lined1＝(xd1，yd1，zd1)TAnd satisfies the following conditions:
Figure BDA0002504051840000062
Figure BDA0002504051840000063
s5.6, judging the projection point Hd1And a reference hole Q1、Q2Relative position of
Due to the fact that
Figure BDA0002504051840000064
Illustrating projected point Hd1At the reference hole Q1，Q2And (3) between the connecting lines, adopting a double-datum hole calculation method, wherein the position adjustment amount of the point to be processed is as follows:
Figure BDA0002504051840000065
wherein (. DELTA.x)s,△ys,△zs)TAnd ([ delta ] x)t,△yt,△zt)TAre respectively a reference hole Q1、Q2The measured positional deviation.
S5.7, traversing and calculating the hole P to be processed2Amount of position adjustment of (D), P2Compared with P1The difference of (A) is as follows:
P2the theoretical coordinate in the plane coordinate system is
P2＝(x2，y2，z2)T；
Wherein Q is1Is a distance P from the hole to be processed2Nearest reference hole, Q2Is a distance P from the hole to be processed2A second closest reference hole;
calculating a hole P to be machined2At the reference hole Q1、Q2Projected point H on the connecting line ofd2＝(xd2，yd2，zd2)TAnd satisfies the following conditions:
Figure BDA0002504051840000071
Figure BDA0002504051840000072
due to the fact that
Figure BDA0002504051840000073
Illustrating projected point Hd2At the reference hole Q1、Q2Connection of wiresBesides, a single reference hole calculation method is adopted, and a hole P to be processed2The position adjustment amount of (2) is the nearest reference hole Q1And if the measured position deviation exists, the position adjustment amount of the hole to be processed is as follows:
△P2＝(△x2，△y2，△z2)T＝(△xs,△ys,△zs)T。
s6, adding the theoretical coordinate of the hole to be machined and the adjustment quantity to obtain the actual machining position of the hole to be machined:
s6.1, calculating a hole P to be machined1Actual machining position in the aircraft coordinate system
Figure BDA0002504051840000074
Figure BDA0002504051840000075
S6.2, traversing and calculating a hole P to be processed2Actual machining position in the aircraft coordinate system
Figure BDA0002504051840000076
Figure BDA0002504051840000077
In the description of the present application, it is to be understood that the terms "center", "longitudinal", "lateral", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", and the like indicate orientations or positional relationships based on those shown in the drawings, and are used merely for convenience in describing the present application and for simplifying the description, and do not indicate or imply that the referenced device or element must have a particular orientation, be constructed in a particular orientation, and be operated, and therefore should not be construed as limiting the scope of the present application.
The foregoing is directed to embodiments of the present invention, which are not limited thereto, and any simple modifications and equivalents thereof according to the technical spirit of the present invention may be made within the scope of the present invention.

Claims (7)

1. A method for determining an actual hole making position during digital hole making of an aircraft skin is characterized by comprising the following steps of: the method specifically comprises the following steps:
s1, selecting a part of holes from the processed target holes as measurement reference holes, and prefabricating holes on parts;
s2, completing structural assembly of airplane components in the assembly fixture;
s3, selecting a mark point on the assembly type frame, measuring by using a laser tracker, and establishing an airplane coordinate system;
s4, measuring the position of the reference hole, and comparing the measured value with a theoretical value to obtain the position deviation of the reference hole in each direction of the space;
s5, solving the spatial position adjustment quantity of the hole to be machined according to the position relation between the hole to be machined and the adjacent reference hole and the position deviation of the adjacent reference hole;
s6, adding the theoretical coordinate of the hole to be machined and the adjustment quantity to obtain the actual machining position of the hole to be machined;
the step S5 specifically includes the following steps:
s5.1, obtaining a hole P to be machined from a theoretical digital analogyjTheoretical coordinates in the plane coordinate system
Pj＝(xj，yj，zj)T,j＝1...m；
Wherein j is a single hole to be processed, and m is the total number of the holes to be processed;
s5.2, classifying the datum holes according to the structural parts, and classifying the datum holes belonging to a certain part into one class;
s5.3, calculating a hole P to be machinedjTheoretical distance d from all reference holes on the structural partk
Figure FDA0003166380930000011
Wherein k is the total number of reference holes on the structural part to which the hole to be machined belongs;
s5.4, two reference holes Q closest to the hole to be machined are determined by comparing the distance values in the step S5.3s、QtThe theoretical coordinates of which in the plane coordinate system are respectively
Qs＝(xs，ys，zs)T；
Qt＝(xt，yt，zt)T；
Wherein Q issIs the reference hole, Q, closest to the hole to be machinedtIs a reference hole next to the hole to be processed;
s5.5, calculating a hole P to be processedjAt the reference hole Qs、QtProjection point H on the connecting lined＝(xd，yd，zd)TAnd satisfies the following conditions:
Figure FDA0003166380930000012
Figure FDA0003166380930000013
s5.6, judging the projection point HdAnd a reference hole Qs、QtRelative position of
If it is
Figure FDA0003166380930000021
Then projection point HdAt the reference hole Qs、QtAnd (3) between the connecting lines, adopting a double-datum hole calculation method, wherein the position adjustment amount of the point to be processed is as follows:
Figure FDA0003166380930000022
if it is
Figure FDA0003166380930000023
Then projection point HdAt the reference hole Qs、QtOutside the connecting line, a single reference hole calculation method is adopted, and a hole P to be processedjThe position adjustment amount of (2) is the nearest reference hole QsAnd if the measured position deviation exists, the position adjustment amount of the hole to be processed is as follows:
△Pj＝(△xj，△yj，△zj)T＝(△xs,△ys,△zs)T；
wherein (. DELTA.x)s,△ys,△zs)TAnd ([ delta ] x)t,△yt,△zt)TAre respectively a reference hole Qs、QtA measured positional deviation;
and S5.7, traversing until the position adjustment amount of all holes to be processed is calculated.
2. The method for determining the actual hole making position in the digital hole making process of the aircraft skin according to claim 1, wherein the method comprises the following steps: in the step S1, the measurement reference hole is made by numerical control machining.
3. The method for determining the actual hole making position in the digital hole making process of the aircraft skin according to claim 1, wherein the method comprises the following steps: in the step S1, the range of the selected reference hole is to cover all the structural parts connected to the skin to be processed, and each related structural part needs to be provided with the reference hole; for parts with good rigidity and difficult deformation, the reference holes are respectively arranged at the positions close to the two sides and used for reflecting the space positions of the parts; for parts with weak structural rigidity and easy deformation, the number of reference holes needs to be increased properly for reflecting the spatial position and the deformation condition of the parts.
4. The method for determining the actual hole making position in the digital hole making process of the aircraft skin according to claim 1, wherein the method comprises the following steps: the step S3 specifically includes the following steps:
s3.1, selecting mark points on the assembly type frame, wherein the mark points should envelop the distribution range of the measured reference holes as much as possible;
s3.2, erecting a laser tracker, and placing the laser tracker at a position where the laser tracker can measure the mark point and the reference hole simultaneously;
and S3.3, measuring the actual coordinates of the mark points in the laser tracker coordinate system, fitting the actual coordinates with the theoretical coordinates of the mark points in the airplane coordinate system, and establishing the airplane coordinate system.
5. The method for determining the actual hole making position in the digital hole making process of the aircraft skin as claimed in claim 4, wherein the step of: in the step S3.2, if one position cannot measure all the reference holes, the reference holes may be measured at multiple positions, and the mark points used in each position measurement should envelop the distribution range of the reference holes of this measurement as much as possible.
6. The method for determining the actual hole making position in the digital hole making process of the aircraft skin according to claim 1, wherein the method comprises the following steps: the step S4 specifically includes the following steps:
s4.1, acquiring reference hole Q from theoretical digital analogyiTheoretical coordinates in the plane coordinate system
Qi＝(xi，yi，zi)T,i＝1...n；
S4.2 measuring the actual position of the reference hole using the target ball in the aircraft coordinate system established in step S3
Figure FDA0003166380930000031
S4.3, obtaining a reference hole QiPositional deviation in three spatial directions
Figure FDA0003166380930000032
Where i is the single reference well and n is the total number of reference wells.
7. The method for determining the actual hole making position in the digital hole making process of the aircraft skin according to claim 1, wherein the method comprises the following steps: the step S6 specifically includes the following steps:
s6.1, calculating single hole P to be processedjActual machining position in the aircraft coordinate system
Figure FDA0003166380930000033
Figure FDA0003166380930000034
And S6.2, traversing until the actual machining positions of all the holes to be machined are calculated.
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CN112763486B (en) * 2020-11-30 2022-05-10 成都飞机工业（集团）有限责任公司 Composite material wall plate array hole detection method based on line laser scanning
CN112623262B (en) * 2020-12-30 2023-02-28 中航贵州飞机有限责任公司 Assembling tool installation and maintenance method
CN112589442B (en) * 2021-03-07 2021-06-08 成都飞机工业（集团）有限责任公司 Pulse production system and method for group hole drilling and countersinking of machine body part
CN113086238A (en) * 2021-03-29 2021-07-09 中国航空制造技术研究院 Automatic hole making and position online correction method based on reference hole position measurement
CN113460326B (en) * 2021-06-25 2023-07-21 成都飞机工业（集团）有限责任公司 Deformation calculation and auxiliary control method for main positioning frame of vertical assembly of machine body
CN113443166B (en) * 2021-06-25 2022-06-14 成都飞机工业（集团）有限责任公司 Laminated hole-making and flexible assembling system for complex curved surface of airplane front body component
CN113369990B (en) * 2021-07-06 2022-05-10 成都飞机工业（集团）有限责任公司 On-line detection device for non-contact measuring hole and use method thereof
CN114061448A (en) * 2021-10-26 2022-02-18 成都飞机工业（集团）有限责任公司 Method and device for obtaining assembling position deviation of assembling hole of composite material wallboard
CN115179065B (en) * 2022-06-20 2023-12-08 成都飞机工业（集团）有限责任公司 Air inlet channel composite tool template processing supporting structure and allowance adjusting method

Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN109211104A (en) * 2018-03-22 2019-01-15 中国航空制造技术研究院 A kind of processing hole location normal direction on-line amending method
CN109794938A (en) * 2019-02-01 2019-05-24 南京航空航天大学 A kind of robot hole error-compensating apparatus and its method suitable for curved-surface structure

Family Cites Families (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US9352435B2 (en) * 2013-06-28 2016-05-31 The Boeing Company Magnet sensing hole driller and method therefor
CN103895877B (en) * 2014-03-27 2016-08-24 浙江大学 Position, a kind of hole based on skeleton scanning survey modification method
CN107421476A (en) * 2017-05-11 2017-12-01 成都飞机工业（集团）有限责任公司 A kind of spatial hole position Measuring datum error compensation method
CN110672006A (en) * 2019-08-21 2020-01-10 成都飞机工业（集团）有限责任公司 Positioning system and method for digital positioning during aircraft assembly
CN110530326B (en) * 2019-09-17 2021-06-08 成都飞机工业（集团）有限责任公司 Reference hole arrangement method

Patent Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN109211104A (en) * 2018-03-22 2019-01-15 中国航空制造技术研究院 A kind of processing hole location normal direction on-line amending method
CN109794938A (en) * 2019-02-01 2019-05-24 南京航空航天大学 A kind of robot hole error-compensating apparatus and its method suitable for curved-surface structure

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