CN-116551468-B - Large aviation component attitude control method

CN116551468BCN 116551468 BCN116551468 BCN 116551468BCN-116551468-B

Abstract

The invention relates to the field of numerical control machining processes of aviation components, in particular to a large-scale aviation component gesture control method, which comprises the steps of determining gesture control references, measuring gesture control references and adjusting gestures of components to be machined, wherein the gesture control references meet the measurement accessibility of the components to be machined before and after turning, the measurement comprises on-machine measurement, the adjustment is carried out based on the on-machine measurement result, and the adjustment aims at enabling the gestures of the components to be machined to meet the maximum envelope principle. The method has the advantages that the components to be processed are subjected to unified attitude control standard before and after turning processing, and the maximum envelope principle is met during numerical control processing, so that the attitude deviation of the components to be processed under the machine clamping is reduced, the processing reliability and accuracy of the whole components to be processed with the weak rigidity flexible body can be ensured, the manufacturing precision and the appearance accuracy of the components to be processed are improved, and the appearance tolerance of the formed whole components with the weak rigidity flexible body meets the design and delivery requirements.

Inventors

Ren Dezu
HU YIMIN
XU YAJUN
DU XIAOWEN
Wang Pengguan
LIAO SHUANGQUAN
ZHANG CHAO

Assignees

成都飞机工业（集团）有限责任公司

Dates

Publication Date: 20260512
Application Date: 20230407

Claims (4)

1. The attitude control method of the large aviation component is characterized by comprising the steps of analyzing the structure of the component to be processed, determining an attitude control reference, measuring the attitude control reference and adjusting the attitude of the component to be processed, wherein the attitude control reference meets the measurement accessibility of the component to be processed before and after the turnover processing; The measurement comprises on-machine measurement, the adjustment is carried out based on the result of the on-machine measurement, and the adjustment aims at meeting the maximum envelope principle of the gesture of the component to be processed; the attitude control reference comprises a reference hole (11), wherein the reference hole (11) is obtained by screening from a process hole for assembling and positioning a component to be processed and/or is provided by assembling a reference block (1) on the component to be processed; the attitude control reference comprises a reference surface (12), wherein the reference surface (12) is provided by assembling a reference block (1) on a component to be processed; the step of analyzing the structure of the component to be processed is used for determining the maximum contour position of the component to be processed, and the positions of the reference hole (11) and the reference surface (12) both comprise the maximum contour position of the component to be processed; The on-machine measurement refers to that components to be processed are arranged on a machine tool to perform measurement; The method comprises the following steps of: S0, analyzing the structure of the component to be processed, and determining the maximum contour position of the component to be processed; s1, determining an attitude control reference; s1.1, screening out a process hole for assembly and positioning on a component to be processed; S1.2, screening out a fine hole with the precision grade of at least H8 in the process hole obtained by the S1.1; s1.3, analyzing whether the position of the obtained fine hole in S1.2 contains the maximum outline of the component to be processed, if so, checking the obtained fine hole, and if not, performing supplementary selection from the obtained process hole in S1.1 and then checking; The verification comprises the steps of applying fixed constraint to each two fine holes through finite element analysis and calculation, judging whether the deformation amount of a structure between the two fine holes, which is affected by the dead weight, is smaller than 0.05mm, if the deformation amount is smaller than 0.05mm, determining that the fine holes can be used as reference holes for attitude control, if the deformation amount is not smaller than the deformation amount, positioning one of the fine holes, acquiring a process hole from the S1.1, and performing verification again; s1.4, analyzing and judging the measurement accessibility of the fine hole meeting the condition after verification, if the measurement accessibility is not met, installing a reference block at the position of acquiring the fine hole, and providing an auxiliary attitude control reference through the reference block (1); S2, measuring an attitude control reference, and measuring the attitude control reference in an on-machine measurement mode; S3, adjusting the gesture of the component to be processed, and adjusting the gesture of the component to be processed according to the measurement result of S2; S4, repeating the steps S2-S3 until the position of the component to be processed meets the maximum envelope principle.
2. A large aircraft component attitude control method according to claim 1, characterized in that the reference block (1) is manufactured by machining, the reference block (1) comprises a positioning molded surface (13) which is matched with the shape of a component to be machined, the reference block (1) is detachably connected with the component to be machined, and the reference block (1) is provided with a reference hole (11) and/or a reference surface (12).
3. A large aircraft component attitude control method according to claim 2, wherein the reference hole (11) comprises a process hole of a precision level of at least H8, and the reference surface (12) comprises a machined surface having a flatness of not less than 0.02 mm.
4. The method for controlling the attitude of a large aviation component according to claim 1, wherein the maximum envelope principle satisfies: (DX 2 +DY 2 +DZ 2 ) 1/2 ≤Δ DX is the difference between the actual measurement value and the theoretical value of the attitude control reference in the X direction in a three-dimensional coordinate system, DY is the difference between the actual measurement value and the theoretical value of the attitude control reference in the Y direction in the three-dimensional coordinate system, DZ is the difference between the actual measurement value and the theoretical value of the attitude control reference in the Z direction in the three-dimensional coordinate system, and delta is the design appearance tolerance of the component to be processed.

Description

Large aviation component attitude control method Technical Field The invention relates to the field of numerical control machining processes of aviation components, in particular to a large-scale aviation component attitude control method. Background With the technical progress, the numerical control machining components and parts are continuously developed towards large-scale, integral and complex, a large number of component machining processes occur in the numerical control machining process, and the tooling fixture is developed towards simplified and universal. At present, before numerical control machining, no matter large parts or components exist, the initial state changes are caused by the problems of large size, weak self rigidity and the like, but increasingly simplified tools cannot correct or compensate the state changes, so that during numerical control machining, the initial state deformation of the components causes the postures which do not accord with the theoretical positions, the standards of the large components during different procedures of machining cannot be unified, particularly the whole soft body components which need to be turned over are machined, and the manufacturing errors are extremely large due to the fact that different standards are adopted before and after turning over. In the current manufacturing process scheme of the large aviation component, a plurality of process holes on the measurement component are generally adopted to control the gesture of the large aviation component, but the whole weak-rigidity flexible body component is larger in gesture deformation before and after turning, the manufacturing error caused by gesture deviation can reach 0.5mm, the requirements of economy and society on the performance of the aircraft are continuously improved, and the manufacturing tolerance of the appearance of the aircraft body is generally +/-0.1 mm, so that the contradiction between high manufacturing error and low manufacturing tolerance is prominent, and the precise manufacturing and high-quality delivery of the existing large aviation component are restricted for a long time. Therefore, a technical scheme is needed at present to solve the technical problems that the precision manufacture and high-quality delivery of the large aviation components are greatly affected by the attitude deviation caused by the deformation of the initial state when the existing large aviation components are processed by adopting different references before and after turning. Disclosure of Invention The invention aims to solve the technical problems that the precision manufacture and high-quality delivery of large aviation components are greatly affected by the attitude deviation caused by initial state deformation due to the fact that different references are adopted before and after the turnover of the existing large aviation components, and provides a large aviation component attitude control method. In order to achieve the above purpose, the technical scheme adopted by the invention is as follows: the attitude control method of the large aviation component comprises the steps of determining an attitude control reference, measuring the attitude control reference and adjusting the attitude of the component to be processed, wherein the attitude control reference meets the measurement accessibility of the component to be processed before and after turning processing, the measurement comprises on-machine measurement, the adjustment is carried out based on the on-machine measurement result, and the adjustment aims at enabling the attitude of the component to be processed to meet the maximum envelope principle. According to the attitude control method for the large aviation component, the attitude of the component to be processed is adjusted according to the attitude control references with measurement accessibility before and after the turnover processing of the component to be processed, so that the component to be processed adopts unified references before and after the turnover processing, and meets the maximum envelope principle during numerical control processing, the attitude deviation of the component to be processed under the condition of machine clamping is reduced, the processing reliability and accuracy of the integral component to be processed with weak rigidity flexible body can be ensured, the manufacturing precision and the appearance precision of the integral component to be processed are improved, and the appearance tolerance of the integral component to be processed with weak rigidity flexible body is in accordance with design and delivery requirements. As a preferred aspect of the present invention, the attitude control reference includes a reference hole obtained by screening from a process hole for fitting and positioning the component to be machined and/or provided by fitting a reference block on the component to be machined. The machining standard and the assembly standar