Machining method for ultra-high strength steel high-aspect-ratio wind tunnel test model part

A machining method for an ultra-high strength steel high-aspect-ratio wind tunnel test model part, comprising the following steps:

• a) preparing an envelope material blank, wherein the envelope material blank is based on a three-dimensional mathematical model of a wing main body, and the overall profile is enlarged by 1.0006 to 1.0009 times;
• b) performing forging and solid solution heat treatment on the envelope material blank, and performing rough milling on the length, width, and height of a forged material to obtain a rough blank size;
• c) performing rough milling on the forged material to obtain a wing main body profile and process reference blocks reserved on the wing main body, wherein the wing main body profile comprises a wing root profile, a wing front edge profile, a wing rear edge inner aileron profile, and a wing rear edge outer aileron profile;
• these process reference blocks comprise a first process reference block arranged on the wing root profile, a second process reference block, a third process reference block, a fourth process reference block, a fifth process reference block, and a sixth process reference block arranged along the wing front edge profile, a seventh process reference block and an eighth process reference block arranged along the wing rear edge inner aileron profile, a ninth process reference block, a tenth process reference block, and an eleventh process reference block arranged along the wing rear edge outer aileron profile, and a twelfth process reference block arranged in a manner of extending a molded surface of the wing main body and used for connecting the seventh process reference block, the eighth process reference block, the ninth process reference block, the tenth process reference block, and the eleventh process reference block integrally;
• and two lifting holes taking a centroid of the wing main body as a symmetry center are formed in the first process reference block;
• d) performing rough machining, in a manner of reserving a machining allowance of 1 mm in one side, on the molded surface to obtain grooves with the width of greater than 30 mm and holes with the diameters of greater than 16 mm;
• e) performing finish milling on all features on the molded surface of the wing main body in step d);
• f) removing all process reference blocks except the first process reference block;
• g) freely suspending the wing main body through two lifting holes in the first process reference block, and performing aging strengthening treatment on the wing main body;
• h) removing the first process reference block by using 1:1 machining data;
• and
• i) performing shaping treatment and deburring treatment on the wing main body.