基于高温树脂传递模塑工艺的碳纤维/聚酰亚胺复合材料连接环制备与验证

doi:10.7527/S1000-6893.2021.25438

先进制造技术与装备专栏

本期目录 | 过刊浏览 | 高级检索

前一篇 |

基于高温树脂传递模塑工艺的碳纤维/聚酰亚胺复合材料连接环制备与验证

罗楚养^1,2, 江晟达¹, 陈梦熊¹, 张朋³, 夏旭峰², 蔡培培²

1. 东华大学民用航空复合材料协同创新中心, 上海 201620;
2. 中国空空导弹研究院, 洛阳 471009;
3. 航空工业复合材料技术中心先进复合材料重点实验室, 北京 101300

收稿日期:2021-03-02 修回日期:2021-04-06 发布日期:2021-04-29
通讯作者: 罗楚养 E-mail:cyluo@dhu.edu.cn
基金资助:
航空科学基金（20180112008）；青年人才托举工程（2016QNRC001）；上海市科技创新行动计划（19DZ1100300）

Preparation and evaluation of carbon fiber/polyimide composite attaching collars based on high temperature resin transfer mould process

LUO Chuyang^1,2, JIANG Shengda¹, CHEN Mengxiong¹, ZHANG Peng³, XIA Xufeng², CAI Peipei²

1. Collaborative Innovation Center for Civil Aviation Composites, Donghua University, Shanghai 201620, China;
2. China Airborne Missile Academy, Luoyang 471009, China;
3. Science and Technology on Advanced Composites Laboratory, AVIC Composite Technology Center, Beijing 101300, China

Received:2021-03-02 Revised:2021-04-06 Published:2021-04-29
Supported by:
Aeronautical Science Foundation of China (20180112008); Young Elite Scientist Sponsorship Program (2016QNRC001); Science and Technology Commission of Shanghai Municipality (19DZ1100300)

摘要/Abstract

摘要： 根据连接环的结构特点，结合复合材料的力学特性及成型工艺要求设计了一种隔热/承载一体的碳纤维增强聚酰亚胺复合材料连接环，采用高温树脂传递模塑成型（RTM）整体成型工艺制备了复合材料连接环样件。超声检测结果显示，连接环内部质量良好。常温静强试验结果表明，在150%使用载荷下，连接环能保持良好的结构完整性，其最大应变仅为-491.0 με，满足常温静强度设计要求。520℃严酷热载荷下的静热联合试验结果显示，连接环在118%使用载荷下发生根部连接螺钉断裂失效，连接环本体未出现明显残余变形和损伤，满足热强度设计要求。有限元分析结果显示，常温条件下复合材料连接环的应力危险点出现在孔边，破坏方式主要为孔边的挤压破坏和层间剪切失效，高温条件下复合材料连接环失效位置主要出现在其外侧隔热层及螺栓孔处，对结构承载能力影响较小。

关键词: 聚酰亚胺复合材料, 树脂传递模塑成型(RTM), 高速飞行器热结构, 静热联合试验, 有限元分析

Abstract: A carbon fiber/polyimide composite attaching collar was designed and manufactured by high temperature Resin Transfer Mould (RTM) process according to the structural characteristics of attaching collars and the mechanical properties and forming process requirements of composite materials. The ultrasonic inspection results showed the good internal quality of the composite attaching collar. The static strength test conducted at room temperature showed that the maximum strain of the composite attaching collar is -491.0 με, indicating that the composite attaching collar maintains structural integrity under 150% ot the design load and meets the static strength design requirements. The thermo-static mechanical coupling test results at the maximum service temperature of 520 ℃ revealed that the attaching collar failed under the limit load of 118% due to the rapture of the screws at the root. The finite element analysis showed that the maximum stress of the composite attaching collar at room temperature occurred at the edge of the holes, and the primary failure mode was crushing and interlaminar shear failure around the holes. In comparison, the primary damage of the composite attaching collar at high temperature appeared at the outer thermal protection layer and the holes, which has minor influence on the structure bearing.

Key words: polyimide composite, Resin Transfer Molding (RTM), thermal structure of high-speed aircraft, thermo-static mechanical coupling test, finite element analysis

中图分类号:

TB332
V214.8

罗楚养, 江晟达, 陈梦熊, 张朋, 夏旭峰, 蔡培培. 基于高温树脂传递模塑工艺的碳纤维/聚酰亚胺复合材料连接环制备与验证[J]. 航空学报, 2021, 42(7): 625438-625438.

LUO Chuyang, JIANG Shengda, CHEN Mengxiong, ZHANG Peng, XIA Xufeng, CAI Peipei. Preparation and evaluation of carbon fiber/polyimide composite attaching collars based on high temperature resin transfer mould process[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2021, 42(7): 625438-625438.

参考文献

[1] 张漠杰. 导弹天线罩连接方式的设计[J]. 上海航天, 1999, 16(3):33-35,44. ZHANG M J. Design of joining of missile's antenna housing[J]. Aerospace Shanghai, 1999, 16(3):33-35,44(in Chinese).
[2] 曹运红. 用于导弹雷达天线罩的材料、工艺现状及未来发展趋势[J]. 飞航导弹, 2005(5):59-64. CAO Y H. Status and future development trend of materials and processes used for missile's radome[J]. Winged Missiles Journal, 2005(5):59-64(in Chinese).
[3] 刘萝葳, 曹运红, 王蕾, 等. 导弹雷达天线罩用的工艺材料[J]. 战术导弹技术, 2004(1):23-28. LIU L W, CAO Y H, WANG L, et al. Material and technology used in missile radome[J]. Tactical Missile Technology, 2004(1):23-28(in Chinese).
[4] 宋银锁. 导弹天线罩连接结构的设计问题[J]. 航空兵器, 1997(3):28-33. SONG Y S. The design problems of connected structures used for missile radome[J]. Aero Weaponry, 1997(3):28-33(in Chinese).
[5] 刘萝威, 曹运红. 高温树脂基复合材料在超声速导弹弹体上的应用[J]. 宇航材料工艺, 2002, 32(5):15-19. LIU L W, CAO Y H. High-temperature resistant resin matrix composite applications to supersonic missile airframes[J]. Aerospace Materials & Technology, 2002, 32(5):15-19(in Chinese).
[6] 张学斌, 何利华, 张漠杰. 碳纤维复合材料在导弹天线罩连接环上的应用[J]. 制导与引信, 2012, 33(1):33-36,43. ZHANG X B, HE L H, ZHANG M J. The application of carbon fiber reinforced plastic on missile radome attachment[J]. Guidance & Fuze, 2012, 33(1):33-36,43(in Chinese).
[7] 罗楚养, 张朋, 李伟东, 等. 高温复合材料在空空导弹上的应用研究[J]. 航空科学技术, 2017, 28(1):19-24. LUO C Y, ZHANG P, LI W D, et al. Application research of high temperature composite on airborne missile[J]. Aeronautical Science & Technology, 2017, 28(1):19-24(in Chinese).
[8] 罗楚养, 孙毓凯, 王文博, 等. 空空导弹结构技术的研究进展[J]. 航空兵器, 2019, 26(5):1-10. LUO C Y, SUN Y K, WANG W B, et al. Research progress on structure technology of air-to-air missile[J]. Aero Weaponry, 2019, 26(5):1-10(in Chinese).
[9] 刘强, 王晓亮, 蒋蔚, 等. BMP系列热固性聚酰亚胺树脂基复合材料的应用进展[J]. 航空制造技术, 2009,52(增刊1):22-24. LIU Q, WANG X L, JIANG W, et al. Application progress of BMP thermosetting polyimide resin matrix composites[J]. Aeronautical Manufacturing Technology, 2009,52(Sup1):22-24(in Chinese).
[10] ZHU Y T, AKKERMAN R, XIONG J J, et al. Evaluation of insert design on the performance of repaired composite-Ti alloy joints[J]. Composite Structures, 2019, 230:111506.
[11] ZHU Y T, XIONG J J. High temperature effect on mechanical performance of screwed CFRPI-TC4 alloy joints repaired with metal inserts[J]. Journal of Composite Materials, 2020, 54(17):2245-2260.
[12] ZHU Y T, XIONG J J, LUO C Y, et al. Progressive damage characteristics of screwed single-lap CFRPI-metal joint subjected to tensile loading at RT and 350℃[J/OL]. Journal of Composite Materials, 55(15):2069-2086.
[13] XIONG J J, ZHU Y T, LUO C Y, et al. Fatigue-driven failure criterion for progressive damage modelling and fatigue life prediction of composite structures[J]. International Journal of Fatigue, 2021, 145:106110.
[14] 刘志真, 郭恩玉, 邢军, 等. "离位"增韧技术在碳纤维/RTM聚酰亚胺复合材料中的应用[J]. 复合材料学报, 2010, 27(6):1-8. LIU Z Z, GUO E Y, XING J, et al. Application of carbon fiber/RTMable polyimide composites by ex-situ toughness method[J]. Acta Materiae Compositae Sinica, 2010, 27(6):1-8(in Chinese).
[15] 余瑞莲, 汪明, 李弘瑜, 等. RTM成型聚酰亚胺复合材料研究[J]. 宇航材料工艺, 2008, 38(2):6-8. YU R L, WANG M, LI H Y, et al. Polyimide composite fabricated by RTM[J]. Aerospace Materials & Technology, 2008, 38(2):6-8(in Chinese).
[16] 刘志真, 李宏运, 邢军, 等. RTM聚酰亚胺树脂性能优化设计研究[J]. 材料工程, 2007, 35(增刊1):80-84. LIU Z Z, LI H Y, XING J, et al. Research on the optimization and design of resin transform moldable polyimides[J]. Journal of Materials Engineering, 2007, 35(Sup1):80-84(in Chinese).
[17] 罗楚养, 熊峻江, 益小苏, 等. 基于水溶性型芯的RTM成型的整体化复合材料翼盒研制[J]. 复合材料学报, 2011, 28(3):203-209. LUO C Y, XIONG J J, YI X S, et al. Design and manufacture of RTM-made composite wing box based on the water-soluble mandrel[J]. Acta Materiae Compositae Sinica, 2011, 28(3):203-209(in Chinese).
[18] 刘刚, 罗楚养, 张代军, 等. 基于NCF技术的RTM成型复合材料T型接头高效制造与验证[J]. 复合材料学报, 2012, 29(4):99-104. LIU G, LUO C Y, ZHANG D J, et al. Manufacture and testing of composite T-joint fabricated via RTM process based on NCF technology[J]. Acta Materiae Compositae Sinica, 2012, 29(4):99-104(in Chinese).
[19] 刘刚, 罗楚养, 李雪芹, 等. 复合材料厚壁连杆RTM成型工艺模拟及制造验证[J]. 复合材料学报, 2012, 29(4):105-112. LIU G, LUO C Y, LI X Q, et al. Process simulation and manufacture testing of composite thick-wall drag brace via RTM technology[J]. Acta Materiae Compositae Sinica, 2012, 29(4):105-112(in Chinese).
[20] 陈建升, 左红军, 杨海霞, 等. 适用于RTM成型聚酰亚胺树脂的合成与性能研究[J]. 航空材料学报, 2006, 26(3):183-186. CHEN J S, ZUO H J, YANG H X, et al. Synthesis and characterization of high temperature transfer molding polyimide resins[J]. Journal of Aeronautical Materials, 2006, 26(3):183-186(in Chinese).
[21] 刘志真, 李宏运, 邢军, 等. RTM聚酰亚胺复合材料力学性能研究[J]. 材料工程, 2007, 35(增刊1):98-101. LIU Z Z, LI H Y, XING J, et al. Study on the mechanical property of RTMable polyimide composite[J]. Journal of Materials Engineering, 2007, 35(Sup1):98-101(in Chinese).
[22] 江晟达, 罗楚养, 张朋, 等. 基于RTM技术的碳纤维/聚酰亚胺复合材料舵面一体化制备与验证[J]. 复合材料学报, 2020, 37(9):2152-2162. JIANG S D, LUO C Y, ZHANG P, et al. Integration manufacturing and testing verification for RTMable carbon fiber/polyimide composite rudder[J]. Acta Materiae Compositae Sinica, 2020, 37(9):2152-2162(in Chinese).
[23] 张朋, 周立正, 包建文, 等. 耐350℃ RTM聚酰亚胺树脂及其复合材料性能[J]. 复合材料学报, 2014, 31(2):345-352. ZHANG P, ZHOU L Z, BAO J W, et al. Properties of 350℃ temperature-resistant RTM polyimide matrix resin and its composites[J]. Acta Materiae Compositae Sinica, 2014, 31(2):345-352(in Chinese).
[24] 沈真. 复合材料飞机结构设计许用值及其确定原则[J]. 航空学报, 1998, 19(4):2-9. SHEN Z. Design allowables of composite aircraft structures and their determination principles[J]. Acta Aeronautica et Astronautica Sinica, 1998, 19(4):2-9(in Chinese).
[25] 曾照勇, 夏红娟, 沈艳, 等. 薄壁结构有机复合材料天线罩隔热涂层研究[J]. 制导与引信, 2016, 37(2):28-32. ZENG Z Y, XIA H J, SHEN Y, et al. Research of barrier coating on organic composite material radome with thin-walled structure[J]. Guidance & Fuze, 2016, 37(2):28-32(in Chinese).
[26] 王春奎, 黄晨光, 孙原龙, 等. 升温率和应变率对30CrMnSi拉伸强度的影响[J]. 金属学报, 1995, 31(10):475-478. WANG C K, HUANG C G, SUN Y L, et al. Influence of heating rate and strain rate on tensile strength of 30CrMnSi[J]. Acta Metallurgica Sinica, 1995, 31(10):475-478(in Chinese).
[27] DATOO M H. Mechanics of fibrous composites[M]. Dordrecht:Springer Netherlands, 1991:69-97.

E-mail：hkxb@buaa.edu.cn

关于我们

期刊社服务

专业学科

封面文章

友情链接

主管单位：中国科学技术协会主办单位：中国航空学会北京航空航天大学

基于高温树脂传递模塑工艺的碳纤维/聚酰亚胺复合材料连接环制备与验证

Preparation and evaluation of carbon fiber/polyimide composite attaching collars based on high temperature resin transfer mould process

RichHTML

PDF (PC)

可视化

摘要/Abstract

引用本文

使用本文

参考文献

相关文章 15

编辑推荐

Metrics

本文评价

[1]	余煜玺, 张伟彬, 孙轶, 丛明辉, 朱建, 宋经远. 动密封用Ni基合金斜圈弹簧的变形行为及回弹力模拟[J]. 航空学报, 2022, 43(7): 425527-425527.
[2]	曹勇, 张超. 薄层复合材料冲击损伤行为研究进展[J]. 航空学报, 2022, 43(6): 525323-525323.
[3]	于成月, 刘波, 李传政, 薛闯. 复合材料卫星承力筒连接结构分析[J]. 航空学报, 2022, 43(3): 225161-225161.
[4]	杨夏炜, 彭冲, 马铁军, 温国栋, 王艳莹, 柴小霞, 徐雅欣, 李文亚. 高温合金线性摩擦焊接头疲劳裂纹扩展有限元分析[J]. 航空学报, 2022, 43(2): 625004-625004.
[5]	彭锦峰, 吴东润, 崔为运, 蔡登安, 周光明. 3D打印夹芯复合材料模拟冰型设计与分析[J]. 航空学报, 2021, 42(9): 224536-224536.
[6]	赵波, 别文博, 王晓博, 常宝琪. 纵-扭复合超声钻削TC4钛合金振动系统设计与试验[J]. 航空学报, 2020, 41(1): 423207-423207.
[7]	刘存, 张磊, 杨卫平. 舰载机壁板剪切后屈曲承载能力预测与试验验证[J]. 航空学报, 2019, 40(4): 622300-622300.
[8]	冯振宇, 解江, 李恒晖, 程坤, 马骢瑶, 牟浩蕾. 大飞机货舱地板下部结构有限元建模与适坠性分析[J]. 航空学报, 2019, 40(2): 522394-522394.
[9]	段沐枫, 秦田亮, 沈裕峰, 徐吉峰. 自动铺丝最小间隙路径规划与复合材料锥壳结构制造[J]. 航空学报, 2019, 40(2): 522423-522423.
[10]	李斌斌, 徐宗真, 李鹏, 赵一昭, 刘马宝. 考虑钉头传载的阶梯搭接钉载分配特性[J]. 航空学报, 2018, 39(7): 221816-221816.
[11]	孙见忠, 刘信超, 刘若晨, 康远荣, 殷逸冰, 左洪福. 基于IDMS的航空发动机砂尘吸入物定量监测[J]. 航空学报, 2017, 38(8): 320977-320977.
[12]	刘凯, 曹毅, 周睿, 葛姝翌, 丁锐. 二自由度平板折展柔性铰链的分析及优化[J]. 航空学报, 2017, 38(2): 420317-420326.
[13]	朱琳, 余音, 汪海. 复合材料曲板缺陷及安装误差对屈曲性能的影响[J]. 航空学报, 2016, 37(7): 2180-2188.
[14]	宋丹龙, 张开富, 钟衡, 李原. 层合板干涉螺接分层损伤及其临界干涉量[J]. 航空学报, 2016, 37(5): 1677-1688.
[15]	李连升, 邓楼楼, 梅志武, 吕政欣, 刘继红, 左富昌. 基于Monte Carlo的聚焦型X射线脉冲星望远镜多物理场耦合分析方法[J]. 航空学报, 2016, 37(4): 1249-1260.