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A method for forming a high-temperature-resistant composite cabin section with an end frame

A technology of composite materials and forming methods, which is applied in the field of forming high-temperature-resistant composite material compartments with end frames, can solve the problems of difficult forming of components, reduce the thickness of heat-resistant layers, and high volatile content, and achieve high-temperature bearing capacity and Effects of reliability, increased payload, and improved pass rate

Active Publication Date: 2018-02-09
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

[0005] The technical problem of the present invention is: to overcome the deficiencies of the prior art, to provide a molding method of a high-temperature-resistant composite material compartment with an end frame, which adopts low-temperature imidization, high-temperature imidization and curing stepwise heating and pressure The advanced molding process solves the problem of high resin viscosity and high volatile content in the curing process of polyimide composite materials, which leads to difficult forming and poor quality of components, reduces the defect rate of composite material components, and improves composite material components. The qualified rate saves manufacturing costs, effectively reduces the thickness of the heat-resistant layer, and achieves structural weight reduction

Method used

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  • A method for forming a high-temperature-resistant composite cabin section with an end frame
  • A method for forming a high-temperature-resistant composite cabin section with an end frame
  • A method for forming a high-temperature-resistant composite cabin section with an end frame

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Experimental program
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Effect test

Embodiment 1

[0050] Both the end frame and the skin material are laminated with MT300 / 904 unidirectional tape and fabric prepreg. The prepreg is prepared by solution method. The unidirectional tape prepreg has a glue content of 47±3% and an area density of 165± 5g / m 2 , thickness 0.15mm; MT300 / 904 fabric prepreg, glue content 47±3%, areal density 275±5g / m 2 , thickness 0.27mm.

[0051] After the automatic blanking machine is used for blanking according to the layup and size requirements, the multi-layer end frame and skin prepreg are laid layer by layer on the end frame imidization mold and the cabin integral molding mold according to the designed layup angle , where the end frame layer is [+45 / -45 / carbon cloth / 0 / carbon cloth / 0 2 / carbon cloth / 0]2s, the skin layer is [+45 / -45 / carbon cloth / 0 / carbon cloth]s (carbon cloth means fabric prepreg), and the composite material prepreg laminate is prepared, and the After lamination of composite material prepregs, auxiliary materials such as PTFE ...

Embodiment 2

[0054] Both the end frame and the skin material are laminated with MT300 / 904 unidirectional tape and fabric prepreg. The prepreg is prepared by solution method. The unidirectional tape prepreg has a glue content of 47±3% and an area density of 165± 5g / m 2 , thickness 0.15mm; MT300 / 904 fabric prepreg, glue content 47±3%, areal density 275±5g / m 2 , thickness 0.27mm.

[0055] After the automatic blanking machine is used for blanking according to the layup and size requirements, the multi-layer end frame and skin prepreg are laid layer by layer on the end frame imidization mold and the cabin integral molding mold according to the designed layup angle , where the end frame layer is [+45 / -45 / carbon cloth / 0 / carbon cloth / 0 2 / carbon cloth / 0]2s, the skin layer is [+45 / -45 / carbon cloth / 0 / carbon cloth]s (carbon cloth means fabric prepreg), and the composite material prepreg laminate is prepared, and the After lamination of composite material prepregs, auxiliary materials such as PTFE ...

Embodiment 3

[0058] Both the end frame and the skin material are laminated with MT300 / 904 unidirectional tape and fabric prepreg. The prepreg is prepared by solution method. The unidirectional tape prepreg has a glue content of 47±3% and an area density of 165± 5g / m 2 , thickness 0.15mm; MT300 / 904 fabric prepreg, glue content 47±3%, areal density 275±5g / m 2 , thickness 0.27mm.

[0059] After the automatic blanking machine is used for blanking according to the layup and size requirements, the multi-layer end frame and skin prepreg are laid layer by layer on the end frame imidization mold and the cabin integral molding mold according to the designed layup angle , where the end frame layer is [+45 / -45 / carbon cloth / 0 / carbon cloth / 0 2 / carbon cloth / 0]2s, the skin layer is [+45 / -45 / carbon cloth / 0 / carbon cloth]s (carbon cloth means fabric prepreg), and the composite material prepreg laminate is prepared, and the After lamination of composite material prepregs, auxiliary materials such as PTFE ...

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Abstract

The invention relates to an end-frame-carrying high temperature resistant composite material cabin forming method. Low-temperature imidization, high-temperature imidization and curing sublevel heating pressurizing forming process are adopted, and problems of large component forming difficulty and poor quality due to high viscosity of resin and high volatile content during the curing process of a polyimide composite material are solved, defect rate of composite components is reduced, qualification rate of composite components is raised, and manufacture cost is saved. By the end-frame and housing integral co-curing forming technology, quantity of fasteners is minimized, the purpose of structure weight reducing is realized, and effective load is enhanced. As long-term use temperature of a novel PMR-type thermosetting polyimide resin matrix reaches up to 420 DEG C, thickness of a heat shielding layer can be effectively reduced, and structure weight reducing can be realized.

Description

technical field [0001] The invention belongs to the technical field of high-temperature-resistant resin-based composite materials, and in particular relates to a method for forming a high-temperature-resistant composite cabin section with an end frame. Background technique [0002] In order to improve the survivability and attack capability of missiles, the flight Mach number of missiles has been continuously improved. High-speed missiles have fast response capabilities, strong penetration and high survivability, and can effectively strike high-value maneuvering targets and time-sensitive targets. They will play an important role in future wars. High-speed missiles maneuvering in a dense atmosphere will experience more complex environments such as aerodynamic heat and large overload. Among them, the important components of the missile, such as the instrument cabin, the final repair cabin, and the wings, are in a harsh environment with low heat flow and long-term heating, an...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B29C70/34
CPCB29C70/342
Inventor 潘玲英赵伟栋刘含洋崔超郭鸿俊
Owner AEROSPACE RES INST OF MATERIAL & PROCESSING TECH
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