CN-122020889-A - Design method of aircraft complex curvature skin clamp

CN122020889ACN 122020889 ACN122020889 ACN 122020889ACN-122020889-A

Abstract

The application discloses a design method of a complex curvature skin clamp of an airplane, which relates to the technical field of tool design and comprises the following steps of obtaining the number of skin parts and hole site information, carrying out data sampling, generating different reference planes based on sampling information obtained by the data sampling, carrying out analog calculation on all sampling information under the different reference planes to obtain a reference plane and tool height when the minimum volume V min of a tool blank is obtained, and designing and obtaining tool number of dies based on the reference planes and the tool height. Aiming at the complex curvature skin clamp of the aircraft, the application constructs an accurate model, traverses the processing characteristics of the whole model, determines the most suitable tool datum plane, minimizes the volume of the tool blank on the premise of meeting the travel of the machine tool, solves the problems that the tool datum plane is determined by the existing model in the industry, the manufacturing cost of the tool is high and the overtravel of the machine tool is caused by improper selection of the tool datum plane.

Inventors

CHEN HONG
WANG RUIRUI
ZHANG YE
GAO TAO
ZHONG JIAN
LUO PAN
Duan Jukun
CAO ZEPING
ZHANG BOXIN
YANG ZHICHAO

Assignees

成都飞机工业（集团）有限责任公司

Dates

Publication Date: 20260512
Application Date: 20260119

Claims (10)

1. The design method of the aircraft complex curvature skin clamp is characterized by comprising the following steps of: Acquiring the number model of the skin part and hole site information, and performing data sampling; Based on sampling information obtained by data sampling, generating different reference planes; Performing simulation calculation on all sampling information under different reference planes to obtain a reference plane and a tool height when the minimum volume V min of the tool blank is obtained; And designing and obtaining a tooling digital model based on the reference plane and the tooling height when the minimum volume V min of the tooling blank is smaller.
2. The method for designing an aircraft complex curvature skin jig according to claim 1, wherein the acquiring skin part number model and hole site information and performing data sampling comprises: importing three-dimensional model and skin hole site normal vector information of the skin part from a model database; and (3) carrying out manual data sampling on the surface to be processed, the outline and all the positions to be processed of the skin so as to obtain sampling information of each target item.
3. The method for designing the aircraft complex curvature skin jig according to claim 2, wherein the sampling information includes the surface to be machined of the skin part, the profile, the coordinates (x, y, z) of all holes to be machined in the fuselage coordinate system, and the normal vectors (i, j, k).
4. The method for designing the aircraft complex curvature skin clamp according to claim 2, wherein the principle of sampling the manual data on the surface to be processed of the skin is that sampling points are uniformly distributed and spread over the surface of the skin in a grid shape, and the sampling points are added at the complex curvature.
5. The method for designing the aircraft complex curvature skin clamp according to claim 2, wherein the sampling principle of manual data sampling on the skin contour is that sampling is carried out in a fixed step length, and sampling points are added at the sharp corners of parts.
6. The method for designing an aircraft complex curvature skin jig according to claim 1, wherein generating different reference planes based on the sampling information obtained by the data sampling comprises: and traversing sampling points of the surface to be processed of the skin part, and generating an initial reference plane P0 by combining every three points, so that the initial reference plane P0 is tangential to the part and is positioned below the part, thereby obtaining the reference plane P.
7. The method for designing the aircraft complex curvature skin clamp according to claim 1, wherein the step of performing simulation calculation on all sampling information under different reference planes to obtain the reference plane and the tool height when the minimum volume V min of the tool blank comprises the steps of: Calculating a machine tool Z-axis stroke minimum value M of the part based on a machine tool Z-axis stroke relation during part machining under a certain reference plane; based on the minimum value M of the Z-axis stroke of the machine tool of the part, comparing the magnitude relation with the minimum stroke K of the Z-axis of the machine tool to obtain the tool height H; calculating the volume V of the tool woolen according to the obtained tool height H; And returning to the position of the workpiece on a certain reference plane, and calculating a minimum value M of the Z-axis stroke of the workpiece on the basis of the Z-axis stroke relation of the workpiece during machining of the workpiece so as to obtain the tool blank volume V under all the reference planes and obtain a minimum value V min of the tool blank volume, wherein the reference plane corresponding to V min is the reference plane for minimizing the tool blank volume.
8. The method of claim 7, wherein the minimum value M of machine Z-axis travel of the part is the minimum value of Z-axis travel of the skin part when all features are machined.
9. The method for designing the aircraft complex curvature skin jig according to claim 7, wherein the step of comparing the magnitude relation with the minimum stroke K of the machine tool Z axis based on the minimum stroke M of the machine tool Z axis of the part to obtain the tooling height H comprises: If the minimum value M of the Z-axis stroke of the machine tool of the part is larger than the minimum stroke K of the Z-axis of the machine tool, the tool height meets the machining requirement, at the moment, the tool consists of a tool main body and a tool base, wherein the height H of the tool main body is the distance from the highest point of the part to a reference plane, meanwhile, in order to meet the requirement of the supporting strength of the tool, the tool base with the thickness a is arranged below the tool main body for supporting, wherein a is a determined constant, and the final tool height H=the height H of the tool main body+the height a of the tool base; if the minimum value M of the Z-axis stroke of the machine tool of the part is smaller than the minimum stroke K of the Z-axis of the machine tool, the tool height is insufficient to cause the Z-axis of the machine tool to exceed the minimum stroke, the tool body height H is compensated, the compensation height is K-M, the tool body height is h+K-M at the moment, and the final tool height is H= (h+K-M) +a.
10. The method for designing an aircraft complex curvature skin jig according to claim 7, wherein the length L width W of the tooling is set as a determined parameter according to the skin size, and the tooling blank volume v=h×l×w.

Description

Design method of aircraft complex curvature skin clamp Technical Field The application relates to the technical field of tooling design, in particular to a design method of a complex curvature skin clamp of an airplane. Background Carbon fiber skins are widely used in the modern aerospace industry for their good properties of high strength, low density, shock absorption, sound absorption, corrosion resistance, and the like. The carbon fiber skin needs to be subjected to machining for trimming and hole making so as to ensure the dimensional accuracy. Skin vacuum milling machine jigs (hereinafter referred to as tooling) are now widely used in the machining of skins. However, skin tooling is costly to manufacture, and each tooling is typically only adapted to one skin part, with poor versatility. In this context, a reasonable reduction in tooling blank volume is an important goal in controlling tooling manufacturing costs. At present, the volume of the tooling woolen is reduced by simplifying the structural design, the modularized design and other ways of the tooling in the industry. Aiming at the complex curvature skin clamp of an airplane, no accurate model is available in the current industry to determine a tool reference plane, so that the volume of a tool blank cannot be minimized, and the problems of high tool manufacturing cost and over-travel of a machine tool caused by improper setting of the tool height are caused. Disclosure of Invention The application mainly aims to provide a design method of an aircraft complex curvature skin clamp, which aims to solve the problems that a tool datum plane is determined by an inaccurate model in the current industry, the tool manufacturing cost is high due to improper selection of the tool datum plane, and the tool overtravel is caused by improper setting of the tool height. The technical scheme adopted by the application is as follows: a design method of an aircraft complex curvature skin clamp comprises the following steps: Acquiring the number model of the skin part and hole site information, and performing data sampling; Based on sampling information obtained by data sampling, generating different reference planes; Performing simulation calculation on all sampling information under different reference planes to obtain a reference plane and a tool height when the minimum volume V min of the tool blank is obtained; And designing and obtaining a tooling digital model based on the reference plane and the tooling height when the minimum volume V min of the tooling blank is smaller. Further, the obtaining the skin part number model and the hole site information, and performing data sampling includes: importing three-dimensional model and skin hole site normal vector information of the skin part from a model database; and (3) carrying out manual data sampling on the surface to be processed, the outline and all the positions to be processed of the skin so as to obtain sampling information of each target item. Further, the sampling information comprises the surface to be processed of the skin part, the profile, the coordinates (x, y, z) of all holes to be made in the machine body coordinate system and the normal vectors (i, j, k). Furthermore, the sampling principle of the manual data sampling on the surface to be processed of the skin is that sampling points are uniformly distributed and spread on the surface of the skin in a grid shape, and the sampling points are added at the complex curvature. Furthermore, the sampling principle of the manual data sampling on the skin contour is that sampling is carried out in a fixed step length, and sampling points are added at the sharp corners of the parts. Further, the generating different reference planes based on the sampling information acquired by the data sampling includes: and traversing sampling points of the surface to be processed of the skin part, and generating an initial reference plane P0 by combining every three points, so that the initial reference plane P0 is tangential to the part and is positioned below the part, thereby obtaining the reference plane P. Further, the performing simulation calculation on all sampling information under different reference planes to obtain the reference plane and the tool height when the minimum volume V min of the tool blank comprises: Calculating a machine tool Z-axis stroke minimum value M of the part based on a machine tool Z-axis stroke relation during part machining under a certain reference plane; based on the minimum value M of the Z-axis stroke of the machine tool of the part, comparing the magnitude relation with the minimum stroke K of the Z-axis of the machine tool to obtain the tool height H; calculating the volume V of the tool woolen according to the obtained tool height H; And returning to the position of the workpiece on a certain reference plane, and calculating a minimum value M of the Z-axis stroke of the workpiece on the basis of the Z-axis stroke relation of