A processing method for aircraft complex joint parts

Abstract

A method for processing a complex joint part of an aircraft comprises the steps of first milling a hexagonal part on a prepared blank to obtain a preliminary part, performing rough milling on the front and reverse side of the preliminary part with a drilled process hole to obtain a roughly processed part; performing heat treatment on the roughly processed part and then forming a plane, and then perform half finish-milling processing to obtain a processed half finish-milling part; after fine plane processing is performed on the processed half finish-milling part, performing finish-milling on the front and the reverse side, adopting a phi12R3 cutter to perform high-speed hole milling on the part, performing hole processing on the surface of a finish-milling lug piece and a recession, and processing a lug groove in two steps to obtain a processed finish-milling part; metering the appearance of the processed finish-milling part, and selecting the qualified processed finish-milling part toremove a process supplementing block to obtain a joint part. By reasonable selection of the cutter and optimized processing of process parameters, high-speed and high-efficiency processing of the joint part is achieved; meanwhile, a lug groove front and reverse side verification edge and verification hole process is added, and the front and reverse side butt joint errors are effectively reduced.

Description

technical field [0001] The invention relates to the technical field of part processing, in particular to a processing method for aircraft complex joint parts. Background technique [0002] Aircraft joint parts are key parts, and the key elements in the processing process are the hole distance A (G1) and the lug width BH9 (such as figure 1 and figure 2 As shown), the material of joint parts is LC9CGS3 (Dm). Because the thickness of the material is > 80, the parts need to undergo heat treatment in the middle process during the processing, and the parts are easily deformed after heat treatment, and the part hole D is processed by a desktop drilling machine. The hole distance A (G1), the key element of processing, is difficult to guarantee, especially the processing of the ear groove width due to improper selection of processing parameters, which makes it difficult to guarantee the ear groove width BH9 size. Contents of the invention [0003] The technical problem to be sol...

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Problems solved by technology

[0002] Aircraft joint parts are key parts, and the key elements in the processing process are the hole distance A (G1) and the lug width BH9 (such as figure 1 and figure 2 As shown), the material of joint parts is LC9CGS3 (Dm). Because the thickness of the material is > 80, the parts need to undergo heat treatment in the middle process during the processing, and the parts are easily deformed after heat treatment, and the part hole D is processed by a desktop drilling machine. The hole distance A (G1), the key element of processing, is difficult to guarantee, especially the processing of the lug width due to improper selection of processing parameters, which makes it difficult to guarantee the lug width BH9 dimension

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