Control method for numerical control machining deformation of wall panel parts

A technology of deformation control and wall panels, applied in metal processing equipment, metal processing machinery parts, manufacturing tools, etc., can solve problems such as easy deformation, uneven removal amount, affecting aircraft manufacturing efficiency and quality, and achieve control of processing deformation Effect

Active Publication Date: 2009-04-22
XIAN AIRCRAFT IND GROUP
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  • Abstract
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Problems solved by technology

Most of these parts are machined from pre-stretched plates. Generally, large-scale panel parts for aircraft have structures such as theoretical shapes, mouth frames, slopes, and broken ribs. Due to the particularity of the structure of such parts, CNC machining In this case, the amount of material removed on the upper and lower sides of the part wool is not uniform, resulting in deformation during the processing of the part, and the size of the deformation of the wing panel often determines the forming quality of the subsequent panel, which in turn affects the manufacturing efficiency and quality of the entire aircraft.

Method used

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  • Control method for numerical control machining deformation of wall panel parts
  • Control method for numerical control machining deformation of wall panel parts

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Embodiment Construction

[0011] Referring to accompanying drawing, the panel part 1 among the embodiment is the panel part of an aircraft wing, and this part is long 12460MM, wide 2500MM, thick 17MM. For processing this part, the wall panel material 2 selected is a stretched plate to be processed, with a length of 13000MM, a width of 2600MM and a thickness of 19MM. The wallboard material 2 has an outer surface 5 and an inner surface 6. During numerical control machining, the theoretical shape of the wallboard part 1 is projected onto the wallboard material 2 to be processed, and the part outside the contour line 7 is the process margin during the processing material part. The processing of parts is to process the outer surface 5 of the wall panel material into a flat reference plane, that is, the outer surface of the wall panel part 1, and remove the remaining material from the inner surface 6 of the wall panel material according to the theoretical shape data of the wall panel part 1. In order to con...

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Abstract

The invention relates to a processing method for providing stress grooves at outside outline of the periphery of a large-sized wall plate part. The method effectively releases stress deformation generated by a wall plate material in a numerical control machining process, and achieves the aim of controlling processing deformation of the wall plate part.

Description

technical field [0001] The invention relates to the technical field of numerical control machining, in particular to a method for controlling the deformation of large wallboard parts in numerical control machining. Background technique [0002] At present, integral wing panels are the development trend of large aircraft wing structures. The aircraft wing siding part is a kind of siding part, and its design tends to be integrated, large-scale, and complex in structure. This development trend will help improve the overall performance of the aircraft. Large siding parts cover various frames, beams, joints and other parts of the aircraft, and are the main parts that constitute the shape of the aircraft fuselage and wings. Most of these parts are machined from pre-stretched plates. Generally, large-scale wall panels for aircraft have structures such as theoretical shapes, mouth frames, slopes, and broken ribs. Due to the particularity of the structure of such parts, CNC machinin...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B23Q3/00
Inventor 周文动王俊斌陈益峰田辉段雪峰龚斌
Owner XIAN AIRCRAFT IND GROUP
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