Numerical-control processing method for aircraft wall plate part with complex structure

A technology of complex structure and processing method, applied in aircraft parts, transportation and packaging, etc., can solve the problems of complex structure, stress deformation of parts, tight delivery time of parts, etc., and achieve the effect of fast and efficient process flow

Inactive Publication Date: 2016-06-29
XIAN AIRCRAFT BRANCH OF XIAN AIRCRAFT INT
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  • Abstract
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  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

The structure of such wallboard parts is complex, the amount of material removal is uneven in various parts during CNC machining, the cutting conditions of the tool are complicated, the parts are prone to stress deformation, the actual cutting speed is difficult to increase, and the processing cycle of the

Method used

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  • Numerical-control processing method for aircraft wall plate part with complex structure
  • Numerical-control processing method for aircraft wall plate part with complex structure
  • Numerical-control processing method for aircraft wall plate part with complex structure

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Embodiment Construction

[0017] Referring to the accompanying drawings, based on the above-mentioned content of the invention, the present invention is implemented and verified on an integral wing panel of a certain type of aircraft.

[0018] When the present invention is implemented, the overall structure of the target part is firstly analyzed. One side of the panel part 2 is a complex cavity surface with T-shaped rib structure, and the other side is a theoretical shape surface. The maximum profile of the part is 10845mmX470mmX74mm, the corner radius of the cavity is R10, and the wool size is 11200mmX670mmX80mm.

[0019] According to the principle that the radius of the tool is twice the radius of the corner of the cavity, a Φ40 tool is selected for rough machining of the cavity. The first step is to process the test knife boss 1 in the safe area of ​​the wool end process frame 3, such as figure 1 As shown in the figure, the tool calibration is performed on the test tool boss at the beginning of eac...

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Abstract

A numerical control machining method for a panel part with a complex structure of an aircraft. One side of the part is a multi-slot cavity surface and the other side is an outer profile surface. First, a tool is selected according to the corner radius of the groove cavity, and a trial tool convex is processed in the process frame area of ​​the wool end. Then, a sufficient number of stress grooves are machined on the process frame outside the part outline, and a sufficient number of supporting process bosses are reserved on the upper surface of the part. When processing the theoretical shape surface, the part and the wool frame are turned over and clamped together. Ensure the thickness of the web of the part, keep a sufficient number of connection points between the part and the process frame when machining the outer contour of the part, and finally remove all supporting process bosses and connection points to separate the part from the process frame.

Description

technical field [0001] The application relates to aircraft manufacturing technology, in particular to the numerical control machining of aircraft parts, and in particular to an efficient numerical control machining method for aircraft complex structural panel parts. Background technique [0002] In aircraft assembly, large panel parts cover various frames, beams, joints and other parts of the aircraft, and are the main parts that constitute the shape of the aircraft wing. At present, the structure of large-scale aircraft wing panels generally tends to be integrated, large-scale, and complex, and there are high requirements for CNC machining equipment, clamping methods, tool performance, and programming technology. One side of this type of panel part usually has a complex groove structure and T-shaped rib structure, and the other side is mainly composed of a theoretical shape surface, which is generally formed by direct milling of pre-stretched plates. The structure of such ...

Claims

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Application Information

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IPC IPC(8): B23P15/00
CPCB23P15/00B23P2700/01
Inventor 杨智敏闻虎臣黄茹郑小伟
Owner XIAN AIRCRAFT BRANCH OF XIAN AIRCRAFT INT
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