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Method for milling and processing carbon fiber sacrifice layer of connecting plane

A processing method and a technology for connecting planes, which are applied in metal processing equipment, workpieces, milling machine equipment, etc., can solve the problems of difficult to control the thickness of parts, large deformation, and it is difficult to ensure the requirement of 0.25 contour, so as to improve the surface quality and improve the The effect of airworthiness satisfaction

Active Publication Date: 2017-02-22
AVIC SAC COMML AIRCRAFT
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Problems solved by technology

Due to the large deformation of carbon fiber composite parts after forming, the thickness of the parts is not easy to control, and the thickness tolerance is ±5%.

Method used

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  • Method for milling and processing carbon fiber sacrifice layer of connecting plane
  • Method for milling and processing carbon fiber sacrifice layer of connecting plane
  • Method for milling and processing carbon fiber sacrifice layer of connecting plane

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Embodiment Construction

[0028] Such as Figure 1-2 As shown, the connection between the front section of the rear fuselage of the aircraft and the vertical tail adopts the method of plane docking and bolt fastening. The docking plane 6 is located on the upper surface of the upper wall plate 7 of the front section of the rear fuselage. There is a pressure frame 8 on the front side of the upper wall plate 7, and the rear There are 79 frames 9 on the side, the right side is a right wall plate 10, and the left side is a left wall plate 11. The material of the docking plane 6 is carbon fiber composite material, and the project requires that the profile of the docking plane 6 be 0.25. In order to ensure the profile requirements and ensure the smooth docking of the front section of the rear fuselage and the vertical tail, a 2mm sacrificial layer is reserved for the docking plane 6 of the project. Since the contour tolerance is only 0.25mm, and the milling area is 2 meters long and 0.6 meters wide, milling i...

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Abstract

The invention discloses a method for milling and processing a carbon fiber sacrifice layer of a connecting plane, which is applied to milling and processing the carbon fiber sacrifice layer of a butting plane for connecting a composite material afterbody and a vertical tail of an aircraft. The method comprises the following steps: (1) positioning an assembly part of the front section of the afterbody, i.e., maintaining a product of the front section of the afterbody after assembly, and positioning the front section of the afterbody and an assembly tooling together in a processing area of plane milling equipment; (2) selecting a processing tool for the plane milling, wherein the tool is a disc type milling tool, and is made of hard alloy; (3) determining a processing technology, aligning the tool by the milling equipment, determining the allowance of milling, and determining the feeding direction of the tool processing; (4) determining parameters of the processing technology; (5) milling the butting plane by the milling equipment. The method has the advantages that the contour of the butting plane is checked by a laser tracking instrument; the contour requirement of the connecting plane of the front section of the afterbody and the vertical tail is guaranteed, and the front section of the afterbody and the vertical tail can be smoothly butted.

Description

technical field [0001] The invention belongs to the field of aviation milling and processing, and in particular relates to a milling and processing method for connecting plane carbon fiber sacrificial layers. Background technique [0002] The connection between the front section of the rear fuselage and the vertical tail adopts the method of plane docking and bolt fastening. The docking plane is located on the upper surface of the upper wall plate of the front section of the rear fuselage, and the material is carbon fiber composite material. Due to the large deformation of carbon fiber composite parts after forming, the thickness of the parts is not easy to control, and the thickness tolerance is ±5%. In order to ensure the profile requirements and ensure the smooth docking of the front section of the rear fuselage and the vertical tail, a 2mm sacrificial layer is reserved for the docking plane of the project, and the process of finishing milling and cutting the docking plan...

Claims

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Application Information

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IPC IPC(8): B23C3/00
CPCB23C3/00B23C2215/04
Inventor 刘振山贾晓亮金加奇王超李论李艳军
Owner AVIC SAC COMML AIRCRAFT
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