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A composite material rotary structure and its forming method

A technology of rotating structure and composite material, applied in the field of structural composite material manufacturing, can solve the problems of unable to meet the requirements of lightweight components, reduce the overall bearing efficiency of components, increase the weight of components, etc., so as to avoid end frame reinforcement and weight increase, The effect of preventing distortion and improving mechanical bearing capacity

Active Publication Date: 2019-11-12
AEROSPACE RES INST OF MATERIAL & PROCESSING TECH +1
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0004] The aerospace field has an absolute requirement for lightweight. The segmented processing method introduces the butt end frame, which increases the weight of the component, and cannot meet the requirements of the aerospace field for lightweight components; The sudden change of stiffness in the end frame area requires local reinforcement for the end frame area of ​​the composite column-section rotary structure and the cone-section rotary structure, which reduces the overall load-carrying efficiency of the component

Method used

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  • A composite material rotary structure and its forming method
  • A composite material rotary structure and its forming method
  • A composite material rotary structure and its forming method

Examples

Experimental program
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Embodiment 1

[0059] This embodiment provides a mold for preparing a composite rotary member, such as figure 2 As shown, the mold includes a mandrel 40 and a mandrel 50, and the mandrel 50 includes a first extension section 54, a cylindrical mold section 51, a transition mold section 52, a truncated cone mold section 53 and a second extension section 55 connected in sequence, Cylindrical die section 51 is smoothly transitionally connected with truncated cone die section 53 through transition die section 52. First extension section 54 is a cylindrical structure with a diameter consistent with cylindrical die section 51. The end diameter is consistent with the diameter of the big end of the frustum die section 53; the diameter of the big end of the frustum die section 3 is Φ1500mm, the diameter of the cylindrical die section 51 is Φ1000mm, the height of the cylindrical die section 51 is 1500mm, and the height of the transition die section 52 The height of the frustum section 3 is 200mm, the ...

Embodiment 2

[0061] This embodiment provides a cone-column integrated composite material rotary member 60, and the preparation method includes:

[0062] Step 1, fixing the mandrel of the mold passed in embodiment 1 on the automatic silk laying equipment;

[0063] Step 2, coating release agent on the core mold surface that embodiment 1 provides, carry out laying, see Figure 4 , when laying layers, the first layer is [90 / -45 / 45 / 45 / -45 / 0]s, covering areas A, B, C, D, E and F; the second layer [0 / 45 / -45]s, covering area B; the third layer is [0 / 45 / -45]s, covering areas B, C, D, E and F; the fourth layer It is [90 / 60 / -60]s, and the length of each ply is different, among which the 90° ply covers D area, E area and F area, [60 / -60] covers E and F area, [-60 / 60 ] covers area F, where:

[0064] like Figure 5 As shown, the non-circular layup (the first non-circular layup) wire laying molding method comprises the following three steps:

[0065] In the first step, 16 tow prepregs are laid from ...

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Abstract

The invention provides a composite material rotation structure and a forming method thereof and belongs to the technical field of structural composite material manufacturing. The forming method comprises the steps that a core mould is manufactured, wherein the core mould comprises a cylindrical mould section, a transition mould section and a frustum mould section, the cylindrical mould section isconnected with the frustum mould section through the transition mould section, and the connection position is in smooth transition; the surface of the core mould is coated with a release agent, and then laying layers are laid, wherein the laying layers comprise the first annular laying layer, a first non-annular laying layer and an annular reinforcing layer, the first annular laying layer and theannular reinforcing layer are laid annularly around the core mould, the first annular laying layer covers the cylindrical mould section, the transition mould section and the frustum mould section, theannular reinforcing layer covers the transition mould section, the first non-annular laying layer is laid in the direction from one end of the core mould to the other end of the core mould and coversthe cylindrical mould section, the transition mould section and the frustum mould section; and after laying of the laying layers, curing and demoulding are conducted, and thus the composite materialrotation structure is obtained. According to the composite material rotation body member, the weight of the overall structure is decreased by 15% or above, and the manufacturing production period of the member is shortened by about 10%.

Description

technical field [0001] The invention provides a composite material rotary structure and a forming method thereof, belonging to the technical field of structural composite material manufacturing. Background technique [0002] Cone-column integrated rotary structural composite components are often used in the aerospace field. At present, the structural component is usually processed in segments. The segmented processing method specifically includes: [0003] Separately process the column-section rotary structure and the cone-section rotary structure. During processing, a metal end frame is set at the butt joint end of the two sections, and the two-section butt joint is realized by fixing the metal end frame with a fixing piece, so as to obtain a cone-column integrated rotary structure. Composite components. [0004] The aerospace field has an absolute requirement for lightweight. The segmented processing method introduces the butt end frame, which increases the weight of the ...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B29C70/34B29C70/54B29C70/22
CPCB29C70/226B29C70/34B29C70/54
Inventor 张建宝陈亮李忠王伟孙文文孙宏杰张蕾
Owner AEROSPACE RES INST OF MATERIAL & PROCESSING TECH
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