CN115752314A - Method for measuring gap between abutting surfaces of aircraft assembly parts - Google Patents
Method for measuring gap between abutting surfaces of aircraft assembly parts Download PDFInfo
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- CN115752314A CN115752314A CN202211421618.6A CN202211421618A CN115752314A CN 115752314 A CN115752314 A CN 115752314A CN 202211421618 A CN202211421618 A CN 202211421618A CN 115752314 A CN115752314 A CN 115752314A
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Abstract
A method for measuring the gap between the butting surfaces of aircraft assembly parts comprises a first assembly part and a second assembly part, wherein the lower surface of the second assembly part is required to be attached to the upper surface of the first assembly part, the upper surface of the second assembly part is a pneumatic outer profile, the upper surface of the first assembly part is used as a fixed assembly surface, under the condition that the pneumatic outer profile of the upper surface of the second assembly part is not changed, the gap between the lower surface of the second assembly part and the upper surface of the first assembly part is measured, first point set data of the upper surface of the first assembly part is obtained according to a theoretical model of the assembly parts, and second point set data of the lower surface of the second assembly part is obtained; unifying the first point set data and the second point set data on a theoretical model of the assembly part on a computer to form point set data under the same coordinate system, respectively calculating the distance values from all measuring points in the first point set data to a fitting surface of the lower surface of the second assembly part, and forming a clearance set between the lower surface of the second assembly part and the upper surface of the first assembly part; and performing assembly compensation according to the measured clearance collection.
Description
Technical Field
The application relates to an aircraft assembly technology, in particular to a method for measuring the gap of a butt joint surface of an aircraft assembly part.
Background
The new generation of airplane has the characteristics of large size, complex structure and high performance requirement, which puts a very high requirement on the control of the assembly tolerance of the outer surface of the airplane, the number of face-to-face assembly connection among assembly parts is huge in the design and manufacturing stage of the airplane, in order to ensure the appearance precision of the airplane, a gap is generally reserved in the assembly region in the design so as to be convenient for compensating after the thickness error of parts is eliminated, the gap between the surfaces is assembled and connected, the gap cannot be measured by a traditional tool, the pneumatic appearance of the airplane is directly influenced if blind assembly compensation or uncompensation is carried out, the appearance is easily caused to be out of tolerance, and the pneumatic performance of the airplane is influenced. Therefore, a method for measuring the gap between the abutting surfaces of the aircraft assembly parts is urgently needed, so that the gap value between the aircraft assembly parts can be measured, a compensation basis is provided for subsequent assembly, and the aerodynamic appearance of the aircraft is ensured.
Disclosure of Invention
The method can meet the requirement of measuring the gap value between the surfaces of the aircraft assembly parts, and provides compensation basis for subsequent assembly, so that the aerodynamic appearance of the aircraft is ensured.
In order to achieve the purpose, the technical scheme is as follows:
a method for measuring the gap between the butt-joint surfaces of aircraft assembly parts comprises a first assembly part and a second assembly part, wherein the lower surface of the second assembly part is required to be attached to the upper surface of the first assembly part, the upper surface of the second assembly part is an aerodynamic profile, the upper surface of the first assembly part is used as a fixed assembly surface, and the gap between the lower surface of the second assembly part and the upper surface of the first assembly part is measured under the condition that the aerodynamic profile of the upper surface of the second assembly part is not changed, the theoretical model of the known assembly part is characterized by comprising the following steps: 1) Selecting three positioning holes which are not in a straight line on the upper surface of the first assembly part and the lower surface of the second assembly part respectively; 2) Respectively scanning the upper surface of the first assembly part, the lower surface of the second assembly part and the positioning holes on the upper surface of the second assembly part by using three-dimensional scanning equipment, and defining the obtained three-dimensional point cloud data of the edge outline of the positioning hole on the upper surface of the first assembly part as first point set data and the obtained three-dimensional point cloud data of the edge outline of the positioning hole on the lower surface of the second assembly part as second point set data; 3) Fitting the selected points into a circle by using the point cloud data of the edge profile of each positioning hole in the first point set data and the second point set data by adopting a least square method, and respectively obtaining the center point of each positioning hole; 4) On a computer, coinciding the position of a central point formed by fitting with the theoretical position of each positioning hole, unifying first point set data and second point set data on a theoretical model of an assembly part to form point set data under the same coordinate system, 5) on the computer, fitting a fitting surface of the lower surface of the second assembly part by using the second point set data under the unified coordinate system, 6) under the unified coordinate system, selecting a measuring point in the first point set data, and calculating the distance value between the measuring point in the first point set data and the fitting surface of the lower surface of the second assembly part, namely the assembly clearance value at the measuring point; 7) According to the step 6), respectively calculating the distance values from all the measuring points in the first point set data to the fitting surface of the lower surface of the second assembly part to form a clearance set between the lower surface of the second assembly part and the upper surface of the first assembly part; 8) And performing assembly compensation according to the measured clearance collection.
The method for measuring the gap between the butting surfaces of the aircraft assembly parts is characterized in that in the steps 6) and 7), when the distance value between the measuring point in the first point set data and the fitting surface of the lower surface of the second assembly part is calculated, one measuring point in the first point set data is selected under a unified coordinate system, the point where the normal line intersects with the fitting surface of the lower surface of the second assembly part is searched along the theoretical normal line of the upper surface of the first assembly part, and the distance value between the measuring point in the first point set data and the intersection point is calculated, namely the assembly gap value at the measuring point.
The method has the advantages that the gap value between the assembly part surfaces can be measured and calculated quickly and accurately, compensation data support is provided for subsequent assembly of the airplane, and then the assembly precision of the airplane is guaranteed.
The present application is described in further detail below with reference to the accompanying drawings of embodiments.
Drawings
FIG. 1 is a schematic view of an aircraft flap box and leading edge butt-joint assembly model;
fig. 2 is a schematic view of the upper surface of the first fitting.
Figure 3 is a first set of point data for the upper surface of the first assembly.
Figure 4 is a schematic view of the lower surface of the second fitting.
Figure 5 is second point set data for the lower surface of the second assembly.
Fig. 6 is a schematic diagram of the gap between the upper surface of the first assembly member and the lower surface of the second assembly member at a certain measurement point.
The numbering in the figures illustrates: 1 first assembly part, 2 second assembly part, 3 gap, 4 positioning hole, 5 first point set data, 6 second point set data, 7 fitting surface of the lower surface of the second assembly part, and 8 normal.
Detailed Description
The following description will further describe embodiments of the present invention with reference to the accompanying drawings, taking an aircraft flap assembly as an example.
When the flap is assembled, a box section assembly is formed firstly, the front edge and the box section upper skin are installed on the basis, and when the box section upper skin is installed, the box section upper skin and the belt plate are in face-to-face contact. The band plate is the first assembly member 1 and the upper skin is the second assembly member 2. According to a flap theoretical model, a compensation gap of 0.4mm is reserved between a first assembly part 1 and a second assembly part 2, the lower surface of the second assembly part 2 needs to be attached to the upper surface of the first assembly part 1, the upper surface of the second assembly part 2 is an aerodynamic outer profile, the upper surface of the first assembly part 1 serves as a fixed assembly surface, under the condition that the aerodynamic outer profile of the upper surface of the second assembly part is not changed, a gap 3 between the lower surface of the second assembly part 2 and the upper surface of the first assembly part 1 is measured, and compensation processing is performed after measurement is facilitated.
The method comprises the following steps:
1) Selecting a positioning hole: three positioning holes 4 which are not in a straight line are respectively selected on the upper surface of the first assembly part 1 and the lower surface of the second assembly part 2;
2) Acquiring assembly point cloud data: respectively scanning the upper surface of the first assembly part 1, the lower surface of the second assembly part 2 and the positioning holes 4 on the upper surface of the second assembly part by using a three-dimensional scanning device, and defining the obtained three-dimensional point cloud data of the edge contour of the upper surface of the first assembly part 1 and the positioning holes on the upper surface of the first assembly part as first point set data 5 and the obtained three-dimensional point cloud data of the edge contour of the lower surface of the second assembly part 2 and the positioning holes on the lower surface of the second assembly part as second point set data 6;
3) Obtaining a locating hole center point: on a computer, fitting selected points into a circle by using point cloud data of the edge contour of each positioning hole 4 in the first point set data 5 and the second point set data 6 by using a least square method, and respectively obtaining the center point of each positioning hole 4;
4) Unified coordinate system: on a computer, the position of a central point formed by fitting is superposed with the theoretical position of each positioning hole, and the first point set data 5 and the second point set data 6 are unified on a theoretical model of an assembly part to form point set data under the same coordinate system;
5) Generating a fitting surface: on a computer, fitting a fitting surface 7 of the lower surface of the second assembly by using second point set data 6 under a unified coordinate system;
6) Calculating gap data: selecting a measuring point in the first point set data 5 under a unified coordinate system, searching a point where the normal line 8 intersects with a fitting surface of the lower surface of the second assembly part 2 along a theoretical normal line 8 of the upper surface of the first assembly part 1, and calculating a distance value between the measuring point in the first point set data 5 and the intersection point, namely the assembly gap 3 at the measuring point;
7) Calculating a clearance set of the assembly: respectively calculating the distance values from all the measuring points in the first point set data to the fitting surface of the lower surface of the second assembly part to form a clearance collection between the lower surface of the second assembly part and the upper surface of the first assembly part;
8) And finally, assembling compensation is carried out according to the measured clearance collection.
Claims (2)
1. A method for measuring the gap between the butt-joint surfaces of aircraft assembly parts comprises a first assembly part and a second assembly part, wherein the lower surface of the second assembly part is required to be attached to the upper surface of the first assembly part, the upper surface of the second assembly part is an aerodynamic profile, the upper surface of the first assembly part is used as a fixed assembly surface, and the gap between the lower surface of the second assembly part and the upper surface of the first assembly part is measured under the condition that the aerodynamic profile of the upper surface of the second assembly part is not changed, the theoretical model of the known assembly part is characterized by comprising the following steps: 1) Selecting three positioning holes which are not in a straight line on the upper surface of the first assembly part and the lower surface of the second assembly part respectively; 2) Respectively scanning the upper surface of the first assembly part, the lower surface of the second assembly part and the positioning holes on the upper surface of the second assembly part by using three-dimensional scanning equipment, and defining the obtained three-dimensional point cloud data of the edge contour of the upper surface of the first assembly part and the positioning holes on the upper surface of the first assembly part as first point set data and the obtained three-dimensional point cloud data of the edge contour of the lower surface of the second assembly part and the positioning holes on the lower surface of the second assembly part as second point set data; 3) Fitting the selected points into a circle by using the point cloud data of the edge contour of each positioning hole in the first point set data and the second point set data by adopting a least square method, and respectively obtaining the center point of each positioning hole; 4) On a computer, coinciding the position of a central point formed by fitting with the theoretical position of each positioning hole, unifying first point set data and second point set data on a theoretical model of an assembly part to form point set data under the same coordinate system, 5) on the computer, fitting a fitting surface of the lower surface of the second assembly part by using the second point set data under the unified coordinate system, 6) under the unified coordinate system, selecting a measuring point in the first point set data, and calculating the distance value between the measuring point in the first point set data and the fitting surface of the lower surface of the second assembly part, namely the assembly clearance value at the measuring point; 7) According to the step 6), respectively calculating the distance values from all the measuring points in the first point set data to the fitting surface of the lower surface of the second assembly part to form a clearance set between the lower surface of the second assembly part and the upper surface of the first assembly part; 8) And performing assembly compensation according to the measured clearance collection.
2. An aircraft assembly docking surface clearance measurement method as claimed in claim 1, wherein in step 6) and step 7), when calculating the distance value between the measurement point in the first point set data and the fitting surface of the lower surface of the second assembly, under a unified coordinate system, one measurement point in the first point set data is selected, a point where the normal line intersects with the fitting surface of the lower surface of the second assembly is searched along the theoretical normal line of the upper surface of the first assembly, and the distance value between the measurement point in the first point set data and the intersection point is calculated as the value of the assembly clearance at the measurement point.
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| Application Number | Priority Date | Filing Date | Title |
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| CN202211421618.6A CN115752314A (en) | 2022-11-14 | 2022-11-14 | Method for measuring gap between abutting surfaces of aircraft assembly parts |
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| Application Number | Priority Date | Filing Date | Title |
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| CN202211421618.6A CN115752314A (en) | 2022-11-14 | 2022-11-14 | Method for measuring gap between abutting surfaces of aircraft assembly parts |
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