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Composite material reflector forming and assembling method

A technology of composite materials and assembly methods, which is applied to other household appliances, household appliances, household components, etc., to achieve the effects of ensuring accuracy, reducing manufacturing costs, and ensuring surface quality and surface accuracy

Active Publication Date: 2021-03-23
XIAN AIRCRAFT IND GROUP
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0005] The purpose of the present invention is to solve the problem of surface precision control of composite material reflectors and provide a molding and assembling method for composite material reflectors

Method used

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  • Composite material reflector forming and assembling method
  • Composite material reflector forming and assembling method

Examples

Experimental program
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Embodiment 1

[0027] Implementation example 1: a satellite main reflector

[0028] Main materials: carbon fiber unidirectional belt prepreg M40J, adhesive film REDUX 312UL, porous aluminum honeycomb core BC1.8-3 / 8P-15, foam adhesive FM410-1, structural adhesive EC2216B / A, dry glass cloth EW100, adhesive AO-3

[0029] 1) Upper and lower skin forming

[0030] Taking the forming mold of the reflective surface 1 as the model body, a composite material dummy for forming the upper skin 7 is manufactured using carbon fiber prepreg and NOMEX honeycomb core, and then the lower skin 6 is laid on the molding mold and the dummy respectively ( working surface) and upper skin 7 prepregs, the prepregs are paved with a 50mm narrow strip, and the narrow strips are butt spliced. The number of paving layers is 4 layers, and the angle is [0° / +45 ° / -45° / 90°] symmetrical. During the paving process, it is required that each layer must be vacuum compacted. After the last layer of the lower skin is paved, the ou...

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Abstract

The invention provides a composite material reflector forming and assembling method. Both the lower skin and the upper skin of the reflecting surface of a reflector are formed by narrow-band laying, the preforming of a porous aluminum honeycomb core is conducted before cementing and then the porous aluminum honeycomb core is subjected to secondary cementing with the upper skin and the lower skin,the cured reflecting surface is subjected to aging treatment, the reflecting surface and back ribs are assembled by adopting a forming and cementing integrated tool, the reflecting surface is uniformly pressurized by a method of calibrating embedded part positioning and manufacturing a vacuum bag in an edge margin area, the reflecting surface and the back ribs as well as the back ribs are bonded by using a room-temperature curing structural adhesive, and glass cloth reinforcing angle sheets are laid at adhesive joints by a wet method. According to the composite material reflector forming and assembling method provided by the invention, the molded surface precision control problem of the composite material reflector is solved, and the structural stability of the reflector is ensured.

Description

technical field [0001] The invention relates to the field of composite material molding and manufacturing, in particular to composite material reflector molding and assembly technology used in the aerospace field. Background technique [0002] In recent years, with the continuous advancement of science and technology, material technology has developed rapidly. As a new type of material, composite materials have unique properties such as high specific strength, high specific modulus, heat resistance, corrosion resistance, fatigue resistance, and good stealth. They are used in aviation, aerospace, automobiles, weapons, electronics, construction, medical and other fields has been widely used. After aluminum, steel, and titanium, advanced composite materials have rapidly developed into one of the four major structural materials, and their dosage has become one of the advanced symbols of aerospace structures. [0003] The lightweight of satellite structure is very important to ...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B29C70/34B29C70/44B29C70/70B29C70/88B29C70/54B29L31/30
CPCB29C70/342B29C70/44B29C70/70B29C70/887B29C70/54B29C70/541B29K2715/003B29L2031/3097
Inventor 张静郭俊刚徐小伟胡杰雄
Owner XIAN AIRCRAFT IND GROUP
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