Low-deformation processing method for thin-wall large-area special-shaped composite case

A composite material and processing method technology, applied in metal processing equipment, metal processing machinery parts, manufacturing tools, etc., can solve problems such as deformation and difficult measurement, and achieve the effect of optimizing tool position algorithm, controlling thickness, and optimizing processing process

Active Publication Date: 2018-11-27
AEROSPACE RES INST OF MATERIAL & PROCESSING TECH +1
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  • Application Information

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Problems solved by technology

[0011] The technology of the present invention solves the problem: overcomes the deficiencies of the prior art, proposes a low-deformation processing method for thin-walled and large-area special-shaped composite material shells, designs a set of internal support tooling, and proposes the use of stress division grooves and optimized tool paths The process method of trajectory planning to release residual str

Method used

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  • Low-deformation processing method for thin-wall large-area special-shaped composite case
  • Low-deformation processing method for thin-wall large-area special-shaped composite case
  • Low-deformation processing method for thin-wall large-area special-shaped composite case

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[0062] Example:

[0063] Taking a large-area thin-walled special-shaped heat-resistant shell as an example, the small end of the shell is lip-shaped, the large end is round, and the middle is a free-form surface transition. The specific process implementation is as follows:

[0064] Step 1. The processing equipment is a three-axis or more multi-axis CNC machine tool. Lift the product with the big end facing upwards, lift the product, place the product stably on the machine table, and adjust the axis of the product to roughly coincide with the axis of rotation of the workbench. The main shaft is clamped to align the meter, and the meter is used to measure the four symmetrical points of the metal inner hole at the big end, and the axis of the product is adjusted and aligned to coincide with the axis of rotation of the worktable. Based on the inner center of the metal shell, a symmetrical four-point milling datum plane is made on the composite material layer on the side of the b...

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Abstract

The invention relates to a low-deformation processing method for a thin-wall large-area special-shaped composite case, provides a measuring method of the thin-wall large-area special-shaped compositecase, designs an internal supporting tool, provides a technology method that residual stress is released by using a stress segmentation groove and optimizing tool path planning, and solves the problems that the thin-wall large-area special-shaped composite case is difficult to measure and large in deformation. Through practical application and testing, it is shown that when the method is applied,low-deformation processing of the thin-wall large-area special-shaped composite case can be achieved, and fundamental research experience is provided for low-deformation processing of other similar thin-wall cases.

Description

technical field [0001] The invention relates to a processing method for a thin-walled large-area special-shaped composite material shell. Background technique [0002] With the development of new missile technology, the traditional heat-resistant structure of the conical cabin is also developing in the direction of special-shaped and light-weight design. The light-weight requirements of weight reduction and range increase make the wall thickness of structural parts have thin-wall characteristics. There are new requirements for processing technology. The heat-proof section can be divided into three layers from the structure: the inner layer is a metal shell with a finely processed outer surface, the outer layer is a composite material heat-proof layer, and the middle layer is an adhesive layer for buffering and bonding; Or manual pasting and other craft methods, the outer heat-proof layer is formed on the outer surface of the metal shell. After forming, the heat-resistant l...

Claims

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Application Information

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IPC IPC(8): B23P15/00B23Q3/06B23Q17/20
CPCB23P15/00B23Q3/062B23Q17/20
Inventor 王琦雷建华李杰凌丽郭安儒赵建设
Owner AEROSPACE RES INST OF MATERIAL & PROCESSING TECH
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