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Laminating manufacture method for symmetric laminated plate

A manufacturing method and laminated board technology, which is applied in special data processing applications, instruments, electrical digital data processing, etc., can solve the problems of few layup forms, no consideration of asymmetric deformation, and failure to meet the requirements for active control of CFPR mirrors, etc.

Inactive Publication Date: 2012-06-27
SUZHOU UNIV
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

This document only carried out finite element static analysis on the 13 kinds of layup methods listed, and found out the layup with the smallest gravity deformation as the carbon fiber composite mirror panel. It is a trial algorithm, which is relatively blind. Not suitable for industrial applications
Second, the actual symmetrical ply laying method with an angular step length of 15° and a total of 24 layers can theoretically reach infinite variety. For a set of ply angles, the ply sequence is fully arranged, The layer way can have 12! = 479001600 species, this does not include other ply forms (6! = 720, 4! = 24, 3! = 6) which do not include the number of directional single layers less than 12. Therefore, there are too few ply forms considered in the literature, and it is difficult to find best result
Third, the literature only analyzes the gravitational deformation of the entire mirror surface using PV and RMS values, without considering asymmetric deformation, that is, it does not analyze and judge the quasi-uniformity of bending stiffness. For active control of CFRP Composite material reflector, to improve surface shape accuracy, there are obvious deficiencies in this method
The key consideration of this technical solution is to meet the requirement of a certain stiffness, which does not involve the quasi-uniformity of bending stiffness, and cannot meet the requirements for active control of CFPR mirrors.
At the same time, this technical solution has clear regulations on the number of directional single layers, which can only be three, and the layering form is relatively simple; for actively controlled CFPR mirrors, in order to achieve the best quasi-uniformity of bending stiffness, more considerations may be needed The number of directional monolayers
[0006] At present, there is no report on the layup design and fabrication method of carbon fiber reinforced polymer composite mirrors suitable for active control

Method used

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  • Laminating manufacture method for symmetric laminated plate
  • Laminating manufacture method for symmetric laminated plate
  • Laminating manufacture method for symmetric laminated plate

Examples

Experimental program
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Embodiment 1

[0072] 1. In this embodiment, the carbon fiber reinforced polymer composite material adopts M40 / epoxy 648, and the engineering elastic constant of the one-way plate of this material is: E 1 =206GPa,E 2 =9.02GPa, v 1 =0.3, G 12 = 4.7 GPa. In addition, the fiber volume content v f =0.578, the total number of layers of the laminated board is 24 layers, the total thickness is 3mm, and the thickness of the single layer is the same; the laminated board adopts the form of symmetrical lay-up.

[0073] The specific implementation steps are as follows:

[0074] (1) On the premise that the number of single-layer groups is the largest, according to the total number of layers, determine the lay-up structure of several directional single-layers.

[0075]In order to verify the regularized stiffness coefficient method for the design of quasi-uniform laminates with bending stiffness, the following is a specific example to compare the uniformity of bending stiffness of symmetrical laminate...

Embodiment 2

[0113] Select the same carbon fiber reinforced polymer composite material as in Example 1, the same single-layer engineering elastic constant, the same lay-up form, and the same single-layer thickness, and set a 0° in the lay-up angle. For a symmetrical laminate with a total number of 30 layers, the number of single-layer groups m should be 15, and the number of oriented single layers p can be 3, 5, or 15. The quasi-isotropic and quasi-uniform symmetrical laminates are calculated using the regularized stiffness coefficient method The best ply sequence of p = 3 and 5, the exhaustive method is used, and the random sampling calculation method is used when p = 15. The calculation results are shown in Table 8.

[0114] Table 8 The optimal layup sequence under different directional single-ply numbers p

[0115] p

[0116] It can be seen from Table 8 that the target value Δ of the optimal ply sequence when p=15 is smaller than the target value of p=12 ply in Table 1, indi...

Embodiment 4

[0118] With reference to the conditions of Example 2, the optimal ply sequence of quasi-isotropic and quasi-uniform symmetrical laminates with a total number of layers of 36 layers of symmetrical laminates was calculated with the regularized stiffness coefficient method. For a symmetrical laminate with a total number of 36 layers, the number of single-layer groups m should be 18, and the number of directional single-layer p can be 3, 6, 9, 18, where p = 3, 6 and 9 use the exhaustive method, p =18, the random sampling calculation method is adopted, and the calculation results are shown in Table 9.

[0119] Table 9 The optimal layup sequence under different directional single-layer numbers p

[0120] p

[0121] It can be seen from Table 9 that the target value Δ of the optimal ply sequence when p=18 is smaller than the target value of p=15 ply in Table 8, indicating that when p increases, after the optimization calculation of the regularized stiffness coefficient met...

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Abstract

The invention relates to a laminating manufacture method for a symmetric laminated plate. The laminating manufacture method comprises the following steps of: under the condition of quasi-uniform quasi-isotropy, setting up a relational expression between a regularization in-plane stiffness coefficient formula (shown as a drawing) and a flexural stiffness coefficient formula (shown as a drawing) according to the geometric model of the symmetric laminated plate; with appointed number p of directional single layers, adopting a regularization stiffness coefficient method to carry out optimized adjustment on a laminating sequence by taking the quadratic sum of a formula (shown as a drawing) as an evaluation function; and obtaining the symmetric laminated plate with quasi-uniform quasi-isotropy.According to the laminating manufacture method, the theoretical-equation-based regularization stiffness coefficient method is adopted to design and optimize the laminating sequence, and the optimal laminating sequence under a certain number of directional single layers is directly obtained through calculation, so that the obtained symmetric laminated plate has optimal quasi-isotropy for in-plane stiffness, and the quasi-isotropy for the flexural stiffness of the obtained symmetric laminated plate is optimal with the appointed number of directional single layers. A carbon fiber reinforced polymer composite reflecting mirror formed by using the laminating sequence has less asymmetric deformation under active deformation, and thus, the surface shape accuracy of the reflecting mirror after being actively controlled is improved.

Description

technical field [0001] The invention relates to a layer-laying manufacturing method of a composite material, in particular to a layer-laying manufacturing method of a carbon fiber reinforced polymer composite reflector. Background technique [0002] The development of next-generation space telescopes is constrained by the sharp increase in weight brought about by the increase in the aperture of the main mirror. Among the several light-weight mirrors currently under development, the thin carbon fiber reinforced polymer (Carbon Fiber Reinforced Polymer, referred to as CFRP) composite mirror has excellent physical and thermal properties, and is less than 5Kg / m 2 The surface density, simple forming method, designable performance, no need for polishing, reproducible, and bendable mirror surfaces are expected to become the next generation of light-weight telescope mirrors for large-aperture space. One of the main problems in the current research on carbon fiber reinforced polymer...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G06F17/50
Inventor 曾春梅夏瑜郭培基
Owner SUZHOU UNIV
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