先进复合材料国防科技重点实验室的航空树脂基复合材料研发进展

李斌太; 邢丽英; 包建文; 安学锋; 张洋; 石峰晖; 李雪芹; 焦健; 陈祥宝

doi:10.11868/j.issn.1005-5053.2016.3.010

先进复合材料国防科技重点实验室的航空树脂基复合材料研发进展

doi: 10.11868/j.issn.1005-5053.2016.3.010

北京航空材料研究院先进复合材料国防科技重点实验室, 北京 100095

基金项目:

973计划项目 51311

详细信息

通讯作者:
陈祥宝(1956-),男,博士,研究员,主要从事树脂基复合材料研究,(E-mail)xiangbao.chen@biam.ac.cn。

中图分类号: TB332
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出版历程
- 收稿日期: 2016-03-19
- 修回日期: 2016-04-24
- 刊出日期: 2016-06-01

Research and Development Progress of National Key Laboratory of Advanced Composites on Advanced Aeronautical Resin Matrix Composites

National Key Laboratory of Advanced Composites, Beijing Institute of Aeronautical Materials, Beijing 100095, China

摘要

摘要: 归纳先进复合材料国防科技重点实验室在航空先进树脂基复合材料方面的应用和研究进展。研制出超薄热塑性无纺织物层间增韧技术以实现提高复合材料的CAI性能。设计出的多夹层结构具有多层吸收拓展频带的作用,使多夹层隐身复合材料的吸收频宽达1~18GHz。高韧性树脂基复合材料和耐高温复合材料技术得到发展,并形成预浸料-热压灌成型、液态成型和自动化制造技术体系。发展复合材料固化、树脂流动、固化变形等模拟优化技术,并建立复合材料数据库技术。建立先进复合材料国防科技重点实验室可在支撑航空装备研制,在航空复合材料创新引领、体系主导、基础支撑和保障应用方面发挥作用。
- 微波吸收材料 /
- 树脂基复合材料 /
- 航空复合材料 /
- 技术体系
Abstract: Applications and research progress in advanced aeronautical resin matrix composites by National Key Laboratory of Advanced Composites (LAC) were summarized. A novel interlaminar toughening technology employing ultra-thin TP non-woven fabric was developed in LAC, which significantly improved the compression after impact (CAI) performances of composite laminates.Newly designed multilayer sandwich stealth composite structures exhibited a good broadband radar absorbing properties at 1-18 GHz.There were remarkable developments in high toughness and high temperature resin matrix composites, covering major composite processing technologies such as prepreg-autoclave procedure, liquid composite molding and automation manufacture, etc. Finally, numerical simulation and optimization methods were deliberately utilized in the study of composites curing behavior, resin flow and curing deformation. A composite material database was also established.In conclusion, LAC has been a great support for the development of aeronautical equipment, playing such roles as innovation leading, system dominating, foundation supporting and application ensuring of aerocomposites.
- microware absorbing composite materials /
- polymer matrix composites /
- aerocomposites /
- technology system

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图 1 复合材料超声C扫描图像(a)未增韧复合材料；(b)增韧复合材料

Figure 1. Ultrasonic C-scan images of composites(a)un-toughened composites;(b)toughened composites

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图 2 150 ℃下耐高温结构吸波复合材料吸波性能

Figure 2. Properties of high temperature radar absorbing structure material at 150 ℃

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图 3 “陷阱式”层合结构吸波复合材料电性能

Figure 3. Microwave absorbing properties of the trap type composite materials

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图 4 梯度和均匀浸渍吸波蜂窝吸波性能比较

Figure 4. Reflection ratio vs frequency of honeycomb with an even and gradient application of absorber

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图 5 耐高温多夹层结构吸波复合材料电性能

Figure 5. Reflection ratio vs frequency of high temperature resistant multi-layer sandwich structure absorbing composite materials (a)1-2 GHz；(b)2-18 GHz

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图 6 HT-350RTM与PETI-330树脂流变性能比较^[5-6]

Figure 6. Rheological behavior of HT-350RTM and PETI-330 resins^[5-6]

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图 7 HT-350RTM与PETI-330树脂耐热性比较^[5-6]

Figure 7. Heat resistant properties of HT-350RTM and PETI-330 resins^[5-6]

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图 8 热熔法预浸料制造设备 (a)胶膜机；(b)预浸机

Figure 8. Hot melt prepreg preparation equipment (a)resin film coating equipment;(b)prepreg equipment

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图 9 Φ5 m×12 m热压罐

Figure 9. Autoclave with size of Φ5 m×12 m

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图 10 典型复合材料固化动力学模拟与实验结果比较 (a)5428双马树脂体系；(b)3234环氧树脂体系

Figure 10. Simulative and experimental results for cure kinetics of resins (a)5428 resins;(b)3234 resins

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图 11 3234/T300B复合材料不同位置温度模拟计算与验证结果比较 (a) 中心；(b)边缘

Figure 11. Simulative and experimental results of the temperature vs time at different positions of 3234/T300B composites (a)center;(b)edge

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图 12 工字孔二维平板注射模拟计算和实验结果比较 (a)模拟计算结果；(b)实验结果

Figure 12. Simulative and experimental results for filling panel with I-shaped hole (a)simulative results;(b)experimental results

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表 1 复合材料损伤面积和CAI

Table 1. Damage area and CAI of composites

Material	Damage area /mm²	CAI/MPa
Un-toughened compositess	2585	164
Toughened composites	382	359

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表 2 热塑性超细纤维无纺布层间增韧复合材料的CAI

Table 2. CAI of composites toughened with thermoplastic non-woven fabric interleaf

Material	CAI/MPa
5284RTM/U3160	257
3228RTM/U3160	280
HT-350/CCF300	295

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表 3 韧性树脂基复合材料主要性能

Table 3. Properties of toughened polymer matrix composites

Material	T_g/℃	CAI/MPa	Tensile strength/MPa	Tensile modulus/GPa	Flexural strength/MPa	Flexural modulus/GPa	Interlaminar shear strength/MPa
3238A/CCF300	154	243	1858	136	1269	117	80.4
5228A/CCF300	223	280	1654	146	1679	114	105
5428/T700	270	260	2150	125	1640	120	97
5429/ZT7H	240	280	2581	150	1970	138	108
AC531/CCF800	230	330	3002	170	2154	152	110
AC631/CCF800	260	297	3053	177	2432	153	107

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表 4 液态成型树脂体系主要性能

Table 4. Properties of the resin system for liquid composites moulding

Material	Shelf time/month		Injection temperature/℃	Injection window/h	Cure temperature/℃	Cure cycle/h	T_g/℃	Service temperature/℃
Material	RT	0℃	Injection temperature/℃	Injection window/h	Cure temperature/℃	Cure cycle/h	T_g/℃	Service temperature/℃
3228RTM	0.5	6	45	10	125	2	148	90
5284RTM	＞5	12	65	300	180	2	227	130-150
6421RTM	1	12	120	8	210	5	265	150-170
HT-350RTM	12	24	280	3	350	3	394	350

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表 5 SiC纤维(KD-II型)二维平纹布增强SiC基复合材料力学性能

Table 5. Mechanical properties of KD-II SiC/SiC composites

T/℃	Flexural strength /MPa	Flexural modulus /GPa	Interlaminar Shear strength /MPa	Tensile strength /MPa	Tensile modulus /GPa	Compressive strength/MPa	Compressive modulus/GPa
RT	642	98.0	33.6	300	158	543	251
1200	320	—	—	215	—	—	—

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表 6 本实验室研究成果

Table 6. Research work by National Key Laboratory of Advanced Composites

Description	Benefit and feature	Application
5228A,toughened epoxy system	· Excellent toughness · Good hot-wet performance	· Large aircraft primary structures
5428,toughened bismaleimide system	· Good processability · Excellent toughness	· Primary aircraft structures
5429,toughened bismaleimide system	· Good processability · Excellent toughness	· Primary aircraft structures
Radar absorbing structural composites	· Low radar cross section	· Stealth aircraft
RTMable materials,including 3266,	· Good processability	· Control rudder structures
5284 epoxy system	· Excellent toughness	· Composites propeller
Automated fiber placement	· High processing speed · Improved part-to-part uniformity · Suitability to complex shapes	· S-shaped composites inlet of unmanned aircraft vehicle

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参考文献(15)

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