Aircraft structure shape compensation machining method

Abstract

The application discloses an aerostructure shape compensation processing method, comprising the following steps: establishing a part processing coordinate system; based on the part processing coordinate system, completing first surface processing of the part; based on the part processing coordinate system, performing semi-finishing processing on the second surface of the part to uniformly process a plurality of shape verification reference edges on the edge of the second surface of the part; measuring the shape verification reference edges by using a probe and correcting the probe to eliminate the measurement error of the probe; based on the corrected probe, measuring the shape step difference value between the first surface of the part and the second surface of the part; obtaining the shape compensation value of the part according to the shape step difference value; and correcting the part processing origin according to the shape compensation value and completing the shape processing of the second surface of the part, so that the aerostructure shape compensation processing method has the advantages of avoiding shape dislocation of the front and back surfaces of the part and improving the shape processing quality of the part.

Description

TECHNICAL FIELD

[0001] The application relates to the technical field of numerical control machining, in particular to an appearance compensation machining method for an aviation structural part. BACKGROUND

[0002] In the numerical control machining process of a large aviation structural part, the part product is almost machined on both sides, and the part appearance is also completed by twice machining. When the first side of the part is precisely machined, the upper half of the part appearance is machined in place, the part is clamped after being turned over, and when the second side is precisely machined, the lower half of the part appearance is machined in place. However, in the part appearance machining process, manual intervention is too much, the machining efficiency is low, the machining process is complicated, and there are too many manual operation links. If any operation link fails, the part appearance on the front and back sides will be misaligned, which will cause fatal damage to the part and equipment and cause huge economic losses. SUMMARY

[0003] The main purpose of the application is to provide an appearance compensation machining method for an aviation structural part, which aims to solve the technical problem that the existing aviation structural part is prone to misalignment of the part appearance on the front and back sides in the appearance machining process due to too much manual intervention.

[0004] To achieve the above purpose, the application provides an appearance compensation machining method for an aviation structural part, which comprises the following steps:

[0005] establishing a part machining coordinate system;

[0006] completing first side machining of the part based on the part machining coordinate system;

[0007] performing semi-finish machining of the second side of the part based on the part machining coordinate system to uniformly machine a plurality of appearance verification edges on the edge of the second side of the part; wherein the first side of the part and the second side of the part are the front and back sides of the part respectively;

[0008] measuring the appearance verification edges with a probe, correcting the probe, and eliminating the measurement error of the probe;

[0009] measuring the appearance step difference between the first side of the part and the second side of the part based on the corrected probe;

[0010] obtaining an appearance compensation value of the part according to the appearance step difference;

[0011] correcting the part machining origin according to the appearance compensation value and completing the appearance machining of the second side of the part.

[0012] Optionally, the semi-finish machining of the second side of the part based on the part machining coordinate system to uniformly machine a plurality of appearance verification edges on the edge of the second side of the part comprises:

[0013] Based on the part machining coordinate system, the contour verification reference edge located at the edge of the part is machined in four different directions of X positive direction, X negative direction, Y positive direction and Y negative direction.

[0014] Optionally, when the contour verification reference edge is machined, the machining condition is:

[0015] The part contour in the area where the contour verification reference edge is located is not machined to the theoretical size, and the tool has a preset machining allowance in the radial direction.

[0016] Optionally, the contour verification reference edge is machined by milling.

[0017] Optionally, the contour verification reference edge is measured by the probe, and the probe is corrected to eliminate the measurement error of the probe, including:

[0018] The contour verification reference edge is measured by the probe to obtain measurement data;

[0019] The measurement data is compared with the data in the numerical control measurement program, if the data is consistent, the next step is executed, if there is a difference value between the data, the measurement coordinate value in the numerical control measurement program is adjusted until the data is consistent, to correct the probe and eliminate the measurement error of the probe.

[0020] Optionally, based on the corrected probe, the contour step difference values of the first surface of the part and the second surface of the part are measured, including:

[0021] The machined contour surface of the first surface of the part is measured by the corrected probe to measure the contour step difference values of the first surface of the part and the second surface of the part in X positive direction, X negative direction, Y positive direction and Y negative direction, respectively.

[0022] Optionally, the contour compensation value of the part is obtained according to the contour step difference values, including:

[0023] All contour step difference values measured in X positive direction are compared respectively, and the maximum contour step difference value in X positive direction is determined, all contour step difference values measured in X negative direction are compared respectively, and the minimum contour step difference value in X negative direction is determined, and the average value of the maximum contour step difference value in X positive direction and the minimum contour step difference value in X negative direction is taken as the contour compensation value of the part in X direction coordinate.

[0024] All contour step difference values measured in Y positive direction are compared respectively, and the maximum contour step difference value in Y positive direction is determined, all contour step difference values measured in Y negative direction are compared respectively, and the minimum contour step difference value in Y negative direction is determined, and the average value of the maximum contour step difference value in Y positive direction and the minimum contour step difference value in Y negative direction is taken as the contour compensation value of the part in Y direction coordinate.

[0025] Optionally, the maximum contour step difference value in X positive direction is ΔX 最大, the minimum profile step difference value of X negative direction is ΔX 最小 , the profile compensation value of the part in X direction coordinate is ΔX 补偿值 =(ΔX 最大+ ΔX 最小 ) / 2.

[0026] Suppose the maximum profile step difference value of Y positive direction is ΔY 最大 , the minimum profile step difference value of Y negative direction is ΔY 最小 , the profile compensation value of the part in Y direction coordinate is ΔY 补偿值 =(ΔY 最大+ ΔY 最小 ) / 2.

[0027] Optionally, the correcting the part machining origin according to the profile compensation value and completing the profile machining of the second surface of the part comprises:

[0028] adding a correction program for correcting the part machining origin in the part profile machining program;

[0029] automatically compensating the profile compensation value of X direction coordinate and the profile compensation value of Y direction coordinate into the part machining origin automatically according to the correction program when executing the part profile machining program;

[0030] machining the part profile by using the compensated part machining origin to complete the profile machining of the second surface of the part.

[0031] Optionally, the machining the part profile by using the compensated part machining origin to complete the profile machining of the second surface of the part comprises:

[0032] machining the part profile by milling by using the compensated part machining origin to complete the profile machining of the second surface of the part.

[0033] The application can achieve the following beneficial effects:

[0034] The second surface of the part is finished, first semi-finished, and then a plurality of shape verification reference edges are uniformly processed on the edge of the second surface of the part, then all the shape verification reference edges are measured by the probe, so as to correct the probe and eliminate the measurement error of the probe, and then the shape step value of the first surface and the second surface of the part is measured by the corrected probe, so as to reduce the risk of large errors caused by manual measurement, measure accurately, automatically obtain the shape compensation value of the part according to the shape step value, correct the part processing origin by using the shape compensation value, and complete the finishing of the second surface of the part. This process does not need to be measured multiple times, and the measurement efficiency is high and accurate. Therefore, the application can reduce the product quality failure and equipment failure caused by manual intervention and manual operation failure in part shape processing, avoid the part product quality problem caused by the shape misplacement of the front and back surfaces of the part, improve the part processing efficiency, shorten the part product processing cycle, and lay a foundation for realizing numerical control intelligent braking in the future. BRIEF DESCRIPTION OF DRAWINGS

[0035] In order to more clearly illustrate the specific embodiments of the application or the technical solutions in the prior art, the drawings needed to be used in the specific embodiments or the prior art description will be briefly introduced below. In all the drawings, similar elements or parts are generally identified by similar reference numerals. In the drawings, each element or part is not necessarily drawn according to the actual proportion.

[0036] Figure 1 The flowchart of the shape compensation processing method of an aviation structural part in an embodiment of the application is shown.

[0037] Figure 2 The distribution diagram of the shape verification reference edge processed on the part in an embodiment of the application is shown.

[0038] Figure 3 The structure diagram when the shape verification reference edge is processed on the part in an embodiment of the application is shown.

[0039] Figure 4 The flowchart when the probe is corrected in an embodiment of the application is shown.

[0040] The implementation, functional features and advantages of the application will be further described with reference to the embodiments and the drawings. DETAILED DESCRIPTION

[0041] The technical solutions in the embodiments of the application will be described clearly and completely below with reference to the drawings in the embodiments of the application. Obviously, the described embodiments are only a part of the embodiments of the application, not all the embodiments. Based on the embodiments in the application, all other embodiments obtained by those skilled in the art without creative labor fall within the scope of protection of the application.

[0042] It should be noted that all directional indications, such as upper, lower, left, right, front, back, etc. in the embodiments of the present application are only used to explain the relative positional relationship, movement condition, etc. between components in a certain posture, and if the certain posture changes, the directional indications will also change accordingly.

[0043] In the present application, unless otherwise explicitly specified and limited, the terms "connection", "fixation", etc. should be understood in a broad sense, for example, "fixation" can be fixed connection, or detachable connection, or integral; can be mechanical connection, or electrical connection; can be direct connection, or indirect connection through an intermediate medium; can be internal communication of two elements or interaction relationship between two elements, unless otherwise explicitly limited. For those skilled in the art, the specific meaning of the above terms in the present application can be understood according to the specific circumstances.

[0044] In addition, if the present application has a description of "first", "second", etc., the description of "first", "second", etc. is only for the purpose of description, and cannot be understood as indicating or implying the relative importance of the indicated technical features or implicitly indicating the number of the indicated technical features. Therefore, the features limited by "first" and "second" can explicitly or implicitly include at least one of the features. In addition, the meaning of "and / or" appearing throughout the text includes three parallel solutions. For example, "A and / or B" includes A solution, or B solution, or A and B solution. In addition, the technical solutions of each embodiment can be combined with each other, but it must be based on the realization of ordinary skilled in the art, when the combination of technical solutions appears contradictory or unachievable, it should be considered that the combination of technical solutions does not exist, nor within the scope of protection claimed by the present application.

[0045] Embodiments

[0046] Reference Figures 1-4 The embodiment provides an aerostructure shape compensation processing method, comprising the following steps:

[0047] Step S100: establishing a part processing coordinate system;

[0048] Step S200: completing first surface processing of the part based on the part processing coordinate system;

[0049] Step S300: based on the part processing coordinate system, semi-finishing the second surface of the part to uniformly process a plurality of shape verification reference edges on the edge of the second surface of the part; wherein the first surface of the part and the second surface of the part are the front and back surfaces of the part respectively;

[0050] Step S400: measuring the shape verification reference edge with a probe, and correcting the probe to eliminate the measurement error of the probe;

[0051] Step S500: based on the corrected probe, measure the profile step difference value between the first surface of the part and the second surface of the part;

[0052] Step S600: according to the profile step difference value, obtain the profile compensation value of the part;

[0053] Step S700: according to the profile compensation value, correct the part machining origin, and complete the profile machining of the second surface of the part.

[0054] In the prior art, before finishing the profile of the second surface of the aviation structural part, the first surface and the second surface profile tool step difference value need to be manually measured, the part profile machining compensation value is calculated and manually input into the part machining origin, and after the part profile is machined by using the corrected part machining origin, the part profile tool step difference value is checked again. If the part profile tool step difference value exceeds the tolerance range, the part machining origin needs to be corrected again, and the part profile machining program is repeatedly executed until the part profile tool step difference value meets the process technical requirements. The part profile machining relies on manual measurement of the profile tool step difference by the on-site workers, the measurement efficiency is slow, the measurement profile step difference error is large, the part profile machining compensation value is manually calculated and offset to the part machining origin, the part profile machining process involves more manual intervention, the machining efficiency is low, the machining process is complicated, and there are many manual operation links. Any operation link failure will cause fatal damage to the part and equipment, resulting in huge economic losses.

[0055] Therefore, in the embodiment, when finishing the second surface of the part, semi-finishing is first performed, so that a plurality of profile verification reference edges are uniformly machined on the edge of the second surface of the part, then the probe is used to measure all the profile verification reference edges, so as to correct the probe and eliminate the measurement error of the probe, and then the profile step difference value between the first surface and the second surface of the part is measured by using the corrected probe, so as to reduce the risk of large error caused by manual measurement, measure accurately, automatically obtain the profile compensation value of the part according to the profile step difference value, correct the part machining origin by using the profile compensation value, and complete the finishing of the second surface of the part. This process does not need to be measured multiple times, the measurement efficiency is high and accurate, therefore, the embodiment can reduce the product quality failure and equipment failure caused by manual intervention and manual operation failure in part profile machining, avoid the part product quality problem caused by the profile misplacement of the front and back surfaces of the part, improve the part machining efficiency, shorten the part product machining cycle, and lay a foundation for realizing numerical control intelligent braking in the future.

[0056] It should be noted that the established part machining coordinate system can be established based on the center of the part as the origin, the straightness and flatness of the part need to be aligned and clamped according to the process specification, and the part machining coordinate system is correctly established.

[0057] As an optional implementation, the step S200 of performing semi-finishing on the second surface of the part based on the part machining coordinate system to uniformly process a plurality of profile verification reference edges on the edge of the second surface of the part comprises the following steps:

[0058] Based on the part machining coordinate system, the profile verification reference edges on the edge of the part are uniformly processed in four different directions of X positive direction, X negative direction, Y positive direction and Y negative direction of the part.

[0059] In the embodiment, the established part machining coordinate system is an XY axis coordinate system. Based on the coordinate system, the profile verification reference edges are uniformly processed on the four side walls of the part to ensure coverage, thereby ensuring the comprehensiveness and accuracy of the measurement data.

[0060] As an optional implementation, when the profile verification reference edges are processed, the processing condition is:

[0061] The part profile in the area where the profile verification reference edge is located is not processed to the theoretical size, and the cutter has a certain processing allowance in the radial direction. Thus, when the subsequent finishing is performed after the probe is corrected, a preset processing allowance can be ensured.

[0062] As an optional implementation, the profile verification reference edges are processed by milling, which is efficient and easy to control.

[0063] As an optional implementation, the step S400 of measuring the profile verification reference edge by the probe and correcting the probe to eliminate the measurement error of the probe comprises the following steps:

[0064] Step S410: measuring the profile verification reference edge by the probe to obtain measurement data;

[0065] Step S420: comparing the measurement data with the data in the numerical control measurement program. If the data is consistent, the next step is performed. If there is a difference between the data, the measurement coordinate value in the numerical control measurement program is adjusted until the data is consistent, so as to correct the probe and eliminate the measurement error of the probe.

[0066] In the embodiment, the probe is a measuring probe in the numerical control machine tool. When measuring, the probe measures the coordinate data of all the profile verification reference edges to obtain measurement data (i.e. measured values), and then compares the measurement data with the data in the numerical control measurement program (i.e. theoretical values). If the data is consistent, it indicates that the probe measurement is normal, and the next step can be continued. If there is a difference value between the data, the measurement coordinate value in the numerical control measurement program is adjusted, and then the step S410 is returned to continue measuring the profile verification reference edge by the probe until the data is consistent, so as to correct the probe and eliminate the measurement error of the probe. The process automatically measures by the probe and automatically corrects without human intervention, which greatly reduces the failure rate.

[0067] As an optional embodiment, the step S500 comprises the following steps:

[0068] The profile step difference values of the first surface and the second surface of the part are measured by the corrected probe.

[0069] In the embodiment, the profile step difference values of the first surface and the second surface of the part are measured by the corrected probe.

[0070] As an optional embodiment, the step S600 comprises the following steps:

[0071] The step S610 comprises the following steps: comparing all the profile step difference values measured in the X positive direction, determining the maximum profile step difference value in the X positive direction, comparing all the profile step difference values measured in the X negative direction, determining the minimum profile step difference value in the X negative direction, and taking the average value of the maximum profile step difference value in the X positive direction and the minimum profile step difference value in the X negative direction as the profile compensation value of the X coordinate of the part.

[0072] The step S620 comprises the following steps: comparing all the profile step difference values measured in the Y positive direction, determining the maximum profile step difference value in the Y positive direction, comparing all the profile step difference values measured in the Y negative direction, determining the minimum profile step difference value in the Y negative direction, and taking the average value of the maximum profile step difference value in the Y positive direction and the minimum profile step difference value in the Y negative direction as the profile compensation value of the Y coordinate of the part.

[0073] In the embodiment, the average value of the maximum profile step difference value in the X / Y positive direction and the minimum profile step difference value in the X / Y negative direction is taken as the profile compensation value of the part in the X / Y direction coordinate, and the profile compensation value is the final value, so as to maximize the reduction of compensation error and improve the part product precision after subsequent processing.

[0074] As an optional embodiment, the maximum profile step difference value in the X positive direction is ΔX 最大 , the minimum profile step difference value in the X negative direction is ΔX 最小 , and the profile compensation value of the part in the X direction coordinate is ΔX 补偿值 =(ΔX 最大+ -ΔX 最小 ) / 2.

[0075] The maximum profile step difference value in the Y positive direction is ΔY 最大 , the minimum profile step difference value in the Y negative direction is ΔY 最小 , and the profile compensation value of the part in the Y direction coordinate is ΔY 补偿值 =(ΔY 最大+ -ΔY 最小 ) / 2.

[0076] As an optional embodiment, the step S700: correcting the part processing origin according to the profile compensation value and completing the profile processing of the second surface of the part, specifically includes the following steps:

[0077] Step S710: adding a correction program for correcting the part processing origin in the part profile processing program;

[0078] Step S720: automatically compensating the profile compensation value of the X direction coordinate and the profile compensation value of the Y direction coordinate into the part processing origin according to the correction program when executing the part profile processing program;

[0079] Step S730: processing the part profile with the compensated part processing origin to complete the profile processing of the second surface of the part.

[0080] In the embodiment, according to the calculated profile compensation value, the profile compensation value can be input into the correction program, and the processing origin of the tool in the numerical control machine tool can be corrected, and then the second surface of the part is finished by using the corrected tool, so as to finally realize the automatic compensation processing of the part profile.

[0081] As an optional embodiment, the part profile is processed with the compensated part processing origin to complete the profile processing of the second surface of the part, which includes:

[0082] The part is processed in a milling manner with the compensated part machining origin to complete the contour machining of the second surface of the part. The milling manner is more efficient and easy to control.

[0083] The above merely describes the preferred embodiments of the present application, and does not limit the patent scope of the present application. Any equivalent structure or equivalent process transformation, or direct or indirect application in other related technical fields, which is made by using the content of the present application specification and drawings, is also included in the patent protection scope of the present application.

Claims

1. A method for machining shape compensation of aerospace structural components, characterized in that, Includes the following steps: Establish a coordinate system for part machining; Based on the part machining coordinate system, the first surface of the part is machined. Based on the part machining coordinate system, the second surface of the part is semi-finished to uniformly machine multiple shape verification reference edges on the edge of the second surface of the part; wherein, the first surface and the second surface of the part are the front and back surfaces of the part, respectively; including: based on the part machining coordinate system, uniformly machining shape verification reference edges located on the edge of the part in four different directions: positive X direction, negative X direction, positive Y direction and negative Y direction; Measuring the shape verification reference edge with a probe and calibrating the probe to eliminate the probe's measurement error includes: measuring the shape verification reference edge with a probe to obtain measurement data; comparing the measurement data with data in a CNC measurement program; if the two data are consistent, proceeding to the next step; if the two data have differences, adjusting the measurement coordinate values ​​in the CNC measurement program until the two data are consistent, thereby calibrating the probe and eliminating the probe's measurement error. Based on the calibrated probe, the shape step difference between the first surface and the second surface of the part is measured; including: measuring the machined shape surface of the first surface of the part with the calibrated probe to measure the shape step difference between the first surface and the second surface of the part in the positive X direction, negative X direction, positive Y direction, and negative Y direction, respectively. Based on the shape step difference values, the shape compensation value of the part is obtained, including: comparing all shape step difference values ​​measured in the positive X direction and determining the maximum shape step difference value in the positive X direction; comparing all shape step difference values ​​measured in the negative X direction and determining the minimum shape step difference value in the negative X direction; and using the average of the maximum shape step difference value in the positive X direction and the minimum shape step difference value in the negative X direction as the shape compensation value of the part in the X direction coordinate; comparing all shape step difference values ​​measured in the positive Y direction and determining the maximum shape step difference value in the positive Y direction; comparing all shape step difference values ​​measured in the negative Y direction and determining the minimum shape step difference value in the negative Y direction; and using the average of the maximum shape step difference value in the positive Y direction and the minimum shape step difference value in the negative Y direction as the shape compensation value of the part in the Y direction coordinate. Based on the shape compensation value, the part machining origin is corrected, and the shape machining of the second surface of the part is completed; including: adding a correction program to the part shape machining program to correct the part machining origin; based on the correction program, when the part shape machining program is executed, the shape compensation value of the X-axis coordinate and the shape compensation value of the Y-axis coordinate are automatically compensated into the part machining origin; the part shape is machined using the compensated part machining origin to complete the shape machining of the second surface of the part.

2. The method for machining the shape compensation of an aerospace structural component as described in claim 1, characterized in that, When machining the aforementioned shape verification reference edge, the machining conditions are as follows: The part in the area where the shape verification reference edge is located has not been machined to the theoretical size, and the tool has a preset machining allowance in the radial direction.

3. The method for machining the shape compensation of an aerospace structural component as described in claim 1, characterized in that, The outer shape verification reference edge is machined by milling.

4. The method for machining the shape compensation of an aerospace structural component as described in claim 1, characterized in that, a The maximum shape step difference in the positive X direction is ΔX. 最大 The minimum shape difference in the negative X direction is ΔX. 最小 The shape compensation value of the part in the X-axis coordinate is: ΔX 补偿值 =(ΔX 最大 +ΔX 最小 ) / 2; Let the maximum shape step difference in the positive Y direction be ΔY. 最大 The minimum shape step difference in the negative Y direction is ΔY. 最小 The shape compensation value of the part in the Y-axis coordinate is: ΔY 补偿值 =(ΔY 最大 +ΔY 最小 ) / 2.

5. The method for machining the shape compensation of an aerospace structural component as described in claim 1, characterized in that, The step of machining the part's outer shape using the compensated part machining origin to complete the outer shape machining of the second surface of the part includes: The part's shape is machined by milling using the compensated part machining origin to complete the machining of the second surface of the part.

Images