Preparation method of composite material missile wing

A technology of composite materials and wings, which is applied in the preparation of wings and the field of preparation of wings made of composite materials. It can solve problems such as the quality index of wings exceeding the standard, and achieve high precision, good internal bonding, and high fiber strength. Effect

Active Publication Date: 2013-07-24
湖北三江航天江北机械工程有限公司
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

The traditional molding process of the wing adopts the aluminum alloy skeleton + metal skin structure. Therefore, when the strength and stiffness indicators are met, the quality index of the wing is seriously exceeded.

Method used

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  • Preparation method of composite material missile wing
  • Preparation method of composite material missile wing
  • Preparation method of composite material missile wing

Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0027] Working conditions and requirements:

[0028] Tensile strength / MPa

≥400

Tensile modulus / GPa

≥20

Bending strength / MPa

≥400

Flexural modulus / GPa

≥20

150℃bending strength / MPa

≥320

Mass / Kg

≤15

Product length / m

2.4

[0029] 1) According to the product quality and external dimensions, through the analysis and calculation of ANSYS finite element software, the best lay-up angle is set to 0°, ±30°, ±45°, ±60°, ±80°, 90°, a total of 11 layers , the ply angle as figure 2 shown.

[0030] 2) Cut 11 pieces of T300 carbon fiber cloth according to 0°, 0°, ±30°, ±45°, ±60°, ±80°, and 90° respectively. According to the product size requirements, the size of the carbon fiber cloth is required to be 2600mm*1000mm.

[0031] 3) Embed two pieces of aluminum metal parts 11 in the polymethacrylimide foam material so as to facilitate the matching and load bearing of the product and the engine, and the two pi...

Embodiment 2

[0038] Working conditions and requirements:

[0039] Tensile strength / MPa

≥350

Tensile modulus / GPa

≥20

Bending strength / MPa

≥350

Flexural modulus / GPa

≥20

Weight / Kg

≤10

Product length / m

2.4

[0040] 1) According to the requirements of product quality and external dimensions, through the analysis and calculation of ANSYS finite element software, set the layup angle to 0°, ±45°, ±80°, ±90°, a total of 8 layers, the layup angle is as follows figure 2 shown.

[0041] 2) Cut 8 pieces of T300 carbon fiber cloth according to 0°, 0°, ±45°, ±80°, and ±90° respectively, and the size of the carbon fiber cloth is 2600mm*1000mm.

[0042] 3) Embed two pieces of aluminum metal parts 11 in the polymethacrylimide foam material, so as to facilitate the assembly and load bearing of the product and the engine, and the two pieces of aluminum metal parts can be the same or different.

[0043] 4) Lay 8 pieces of T300 carbon...

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Abstract

The invention discloses a preparation method of a composite material missile wing. The method comprises the following steps: setting the best laying angle and laying thickness, calculating the quantity of fiber cloth at each angle, cutting the fiber cloth according to the set laying angle and the calculated quantity of the fiber cloth, embedding at least two metal pieces into foam material, gradually laying the cut fiber cloth on upper and lower surfaces of the foam material according to the designed laying angle and sequence so as to obtain a premolded body, installing the premolded body in a rigid forming die, and performing solidification forming through a resin transfer molding technology, so as to obtain the composite material missile wing. The missile wing prepared by the method has the characteristics of low weight, high rigidity, uniform apparent color and good uniformity of external dimensions.

Description

technical field [0001] The invention belongs to the technical field of weapon preparation, and in particular relates to a method for preparing a wing, in particular to a method for preparing a wing made of composite materials. Background technique [0002] The wings installed under the tail of the UAV booster have a large-scale structural feature, and its function is to increase the stability of the UAV and provide a certain lift. The traditional forming process of the wing adopts aluminum alloy skeleton + metal skin structure. Therefore, when the strength and stiffness indicators are met, the quality index of the wing is seriously exceeded. [0003] Polymethacrylimide foam material was first successfully developed in Germany and started industrial production. It has the characteristics of low density, high temperature resistance, compression resistance and high specific strength, and has excellent secondary processing performance. Processing and molding, it has good compre...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B29C70/48
Inventor 张国喜邓德凤刘聿成霍文静曾甜甜
Owner 湖北三江航天江北机械工程有限公司
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