A Rapid Design Method for Inner Panels of Aircraft Assembly Frames

Abstract

The invention relates to a rapid design method for an aircraft assembly mold inner panel, which belongs to the field of digital manufacturing of aircraft. Summarize and unify the sketch template of the boss of the inner type plate and extract the key parameters as a template for repeated design of the inner type plate; through the design drive button, import the sketch template into the modeling environment, and use the feature recognition technology to constrain and trim the specified features to form a closed Sketch, stretch the closed sketch to generate the boss of the inner plate; design a fast extraction algorithm and an automatic extension algorithm, extract the inner surface of the skin and automatically extend it, split the boss to generate the working surface of the inner plate; apply sketch template parameterization Technology Batch modeling of the inner panel groove; the rapid design method of the inner panel of the present invention shortens the design time, reduces the design labor intensity, and improves the design efficiency of the inner panel of the aircraft assembly frame.

Description

technical field [0001] The invention relates to a rapid design method for an aircraft assembly mold inner panel, which belongs to the field of digital manufacturing of aircraft. Background technique [0002] There are a large number of parts in the aircraft product structure, and most of them are thin-walled parts with low rigidity. The aircraft assembly jig is a process equipment with positioning requirements in the aircraft assembly process, which ensures the interchange coordination and geometric parameters of aircraft products. In aircraft manufacturing, the manufacture of assembly frames accounts for half of the total amount of tooling manufacturing. According to relevant statistics, more than 40% of the aircraft assembly work is completed in the assembly frame, and its design and manufacturing cycle greatly affects the aircraft manufacturing cycle. The frame is mainly composed of skeleton, shape positioning parts, joint positioning parts, clamping parts and auxiliary...

AI Technical Summary

Problems solved by technology

The current design still relies on manual interactive design on the common CAD / CAM platform. The operation is cumbersome, the design efficiency is low, the repetitive workload is large, and the standardization is insufficient. Mold an initial boss, the sketch of this initial boss is complex, each design of an inner panel needs to interactively draw this complex sketch, the amount of repetitive work is large; (2) the bonding surface of the inner panel and the inner surface of the skin It is obtained by extracting the inner surface of the skin and extending a section of curved surface along the upper and lower boundary lines, and then dividing the above-mentioned boss. The number of faces on the inner surface of the skin is large and the structure is complex, and the inner surface of the skin used to obtain the division is a Bottleneck problem; (3) There are supporting stringers inside the skin, and the inner panel needs to design grooves at the positions where the strings pass. There are a lot of strings. Manually drawing the sketches of the grooves passing through the strings consume time consuming

The above problems affect the design efficiency of the inner panel of the aircraft assembly tooling, and restrict the production preparation process of the aircraft manufacturing

At present, there is no exploration in the rapid design of the inner panel of the aircraft assembly frame in China, and no rapid design method has been formed.

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