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

LUO Chuyang; JIANG Shengda; CHEN Mengxiong; ZHANG Peng; XIA Xufeng; CAI Peipei

doi:10.7527/S1000-6893.2021.25438

ACTA AERONAUTICAET ASTRONAUTICA SINICA >

2021 , Vol. 42 >Issue 7: 625438 - 625438

DOI: https://doi.org/10.7527/S1000-6893.2021.25438

Special Topic of Advanced Manufacturing Technology and Equipment

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

LUO Chuyang ,
JIANG Shengda ,
CHEN Mengxiong ,
ZHANG Peng ,
XIA Xufeng ,
CAI Peipei

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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 date: 2021-03-02

Revised date: 2021-04-06

Online 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)

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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

Cite this article

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 . DOI: 10.7527/S1000-6893.2021.25438

References

[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.

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