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

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

• a) preparing an envelope material blank, wherein an overall profile of the envelope material blank is 1.0006 to 1.0009 times larger than that of an envelope of based on a three-dimensional mathematical model of a wing main body;
• b) performing forging and solid solution heat treatment on the envelope material blank, and performing rough milling on the envelope material blank to obtain a rough blank;
• c) performing rough machining on the rough blank to obtain a wing main body profile and process reference blocks 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;
• the 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 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 suspending holes are symmetrically formed in the first process reference block with respect to a centroid of the wing main body in a height direction of the envelope material blank;
• d) performing further rough machining, in a manner of reserving a machining allowance of 1 mm in one side, on the molded surface to obtain grooves with a width of greater than 30 mm and holes with 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 the two suspending holes in the first process reference block, and performing aging treatment on the wing main body;
• h) removing the first process reference block based on the three-dimensional mathematical model of the wing main body, such that the overall profile of the wing main body is identical to that of the three-dimensional mathematical model of the wing main body;
• and
• i) performing and deburring treatment on the wing main body,
• wherein the rough machining relating to obtaining the wing main body profile in step c), the further rough machining in step d) and the finish milling in step e) are performed based on the three-dimensional mathematical model of the wing main body, such that an overall profile of the wing main body obtained after step e) is 1.0006 to 1.0009 times larger than that of the three-dimensional mathematical model of the wing main body.