Real Time Measurement of High-temperature Shrinkage of Resin-based Materials under Constant Load

doi:10.12382/bgxb.2023.0158

Abstract

Abstract:

To study the high-temperature shrinkage of resin-based materials, a method for measuring the high-temperature shrinkage of composite materials under constant load is proposed, and a measuring device for the high-temperature shrinkage process of composite materials is designed. The high-temperature shrinkages of resin-based materials under constant load are test measured by taking different resin-based materials as the research objects. The changing curves of displacements at the hot surface of carbon plate and the cold surface of indenter were obtained, and the high-temperature shrinkages of resin-based materials and their shrinkages after cooling were measured. The results show that the measuring device can measure the high-temperature shrinkage of resin-based materials in real-time under constant load. The absolute maximum deformation of the test piece is no more than 0.37mm during heating or after cooling. During heating, the maximum deformation rate of braided quartz/ phenolic composite is no more than 6.43‰, and that of quartz-phenolic hybrid composite is no more than 3.76‰. After cooling, the maximum deformation rate of braided quartz/phenolic composite is no more than 4.57‰, and that of quartz-phenolic hybrid composite is not more than 6.87‰. The test results provide basic physical property data for the high-temperature shrinkage and matching analysis of such materials.

Key words: resin-based material, constant load, high temperature, shrinkage, test measurement

CLC Number:

V258

WANG Liyan, GAO Yang, CHEN Weihua, LIU Bo, XU Yun, ZHANG Liang. Real Time Measurement of High-temperature Shrinkage of Resin-based Materials under Constant Load[J]. Acta Armamentarii, 2024, 45(10): 3577-3584.

Figures/Tables 15

Fig.1 Test system

Fig.2 Test piece

Fig.3 Theoretically analyzed results of Ucp2_ftd-Ucp1_ftd

Table 1 Instrument precision and related parameters

仪器	量程范围	精度
位移计	-50~50mm	0.1%
游标卡尺	0~200mm	±0.02mm
K型热电偶	0~1200℃	0.4%

Fig.4 Surface temperature control

Fig.5 Displacement measurement curve of quartz-phenolic hybrid composite in typical test process

Fig.6 Temperature changing curves of quartz-phenolic hybrid composites

Fig.7 Displacement curves of quartz-phenolic hybrid composites

Fig.8 Comparison between the measured results of W2 and the hydraulic rod stroke calibration

Fig.9 Relative displacement curves of quartz-henolic hybrid composites

Fig.10 Temperature changing curves of braided quartz/phenolic composites

Fig.11 Displacement curves of braided quartz/phenolic composites

Fig.12 Comparison of travel calibration between braided quartz/phenolic composite W2 and hydraulic rod

Fig.13 Relative displacement curves of braided quartz/phenolic composites

Table 2 Comparison of product heights and weights before and after test

试验件	质量/g		失重率/ %	高度/mm		变形量/ mm	冷却后收缩率/‰
试验件	试验前	试验后	失重率/ %	试验前	试验后	变形量/ mm	冷却后收缩率/‰
石英杂化酚醛	147.0	144.9	1.43	48.34	48.01	0.33	6.87
编织石英酚醛	191.9	176.8	7.87	48.18	47.96	0.22	4.57

References 22

[1]	李仲平. 防热复合材料发展与展望[J]. 复合材料学报, 2011, 28(2): 1-9.
	LI Z P. Major advancement and development trends of TPS composites[J]. Acta Materiae Compositae Sinica, 2011, 28(2): 1-9. (in Chinese)
[2]	韩杰才, 洪长青, 张幸红, 等. 新型轻质热防护复合材料的研究进展[J]. 载人航天, 2015(4): 315-321.
	HAN J C, HONG C Q, ZHANG X H, et al. Research progress of novel lightweight thermal protection composites[J]. Manned Spaceflight, 2015(4): 315-321. (in Chinese)
[3]	冯志海, 李俊宁, 左小彪, 等. 航天复合材料研究进展[J]. 宇航材料工艺, 2021, 46(4): 23-28.
	FENG Z H, LI J N, ZUO X B, et al. Progress of composite materials for aerospace applications[J]. Aerospace Materials & Technology, 2021, 46(4): 23-28. (in Chinese)
[4]	董彦芝, 刘峰, 杨昌昊, 等. 探月工程三期月地高速再入返回飞行器防热系统设计与验证[J]. 中国科学:技术科学, 2015, 45(2): 151-159.
	DONG Y Z, LIU F, YANG C H, et al. Design and verification of the TPS of the circumlunar free return and reentry flight vehicle for the 3rd phase of Chinese lunar exploration program[J]. SCIENTIA SINICA Technologica, 2015, 45(2): 151-159. (in Chinese)
[5]	许孔力, 夏雨, 李丽英, 等. 树脂基烧蚀材料研究进展[J]. 复合材料科学与工程, 2021, 2(3): 123-127.
	XU K L, XIA Y, LI L Y, et al. Progress of resin-based ablative materials research[J]. Composites Science and Engineering, 2021, 2(3): 123-127. (in Chinese)
[6]	李玮洁. 变密度炭化复合材料的热防护模型及其数值模拟[D]. 北京: 北京交通大学, 2017.
	LI W J. Thermal protection models and numerical simulation for variable density charring materials[D]. Beijing: Beijing Jiaotong University, 2017. (in Chinese)
[7]	刘骁, 国义军, 刘伟, 等. 炭化材料三维烧蚀热响应有限元计算研究[J]. 宇航学报, 2016, 37(9): 1150-1156.
	LIU X, GUO Y J, LIU W, et al. Numerical simulation research on three-dimensional ablative thermal response of charring ablators[J]. Journal of Astronautics, 2016, 37(9): 1150-1156. (in Chinese)
[8]	SHI S B, LI L, LIANG J. Surface and volumetric ablation behaviors of SIFRP composites at high heating rates for thermal protection applications[J]. International Journal of Heat and Mass Transfer, 2016, 102: 1190-1198.
[9]	郭瑾, 黄海明. 热解气体燃烧对炭化复合材料烧蚀热响应影响规律[J]. 中国空间科学技术, 2020, 40(6): 41-47.
	GUO J, HUANG H M. Effect of pyrolysis gases combustion on surface ablation of charring material[J]. Chinese Space Science and Technology, 2020, 40(6): 41-47. (in Chinese)
[10]	柳云钊, 师建军, 王筠, 等. PICA中的酚醛树脂热分解机理[J]. 宇航材料工艺, 2016, 46(6): 68-73.
	LIU Y Z, SHI J J, WANG Y, et al. Pyrolysis mechanism of PICA phenolics[J]. Aerospace Materials & Technology, 2016, 46(6): 68-73. (in Chinese)
[11]	杨凯威, 张杨, 梁欢, 等. 高超声速飞行器热流密度/分层温度/炭化层研究[J]. 中国空间科学技术, 2018, 38(3): 33-39.
	YANG K W, ZHANG Y, LIANG H, et al. Study on heat flux density/stratified temperature/ carbonization layer of hypersonic vehicle[J]. Chinese Space Science and Technology, 2018, 38(3): 33-39. (in Chinese)
[12]	陈亚西. ZrB2对轻质碳/酚醛复合材料烧蚀、隔热及力学性能影响[D]. 大连: 大连理工大学, 2013.
	CHEN Y X. Effect of ZrB2 on ablation、thermal insulation and mechanical properties of light carbon/phenolic composites[D]. Dalian: Dalian University of Technology, 2013. (in Chinese)
[13]	程海明, 洪长青, 张幸红. 低密度烧蚀材料研究进展[J]. 哈尔滨工业大学学报, 2018, 50(5): 1-11.
	CHENG H M, HONG C Q, ZHANG X H, et al. An overview on low-density ablators[J]. Journal of Harbin Institute of Technology, 2018, 50(5): 1-11. (in Chinese)
[14]	冯志海, 师建军, 孔磊, 等. 航天飞行器热防护系统低密度烧蚀防热材料研究进展[J]. 材料工程, 2020, 48(8): 14-24. doi: 10.11868/j.issn.1001-4381.2020.000206
	FENG Z H, SHI J J, KONG L, et al. Research progress in low-desity ablative materials for thermal protection system of aerospace flight vehicles[J]. Journal of Materials Engineering, 2020, 48(8): 14-24. (in Chinese)
[15]	师建军, 孔磊, 左小彪, 等. 酚醛/SiO₂双体系凝胶网络结构杂化气凝胶的制备与性能[J]. 高分子学报, 2018(10): 58-65.
	SHI J J, KONG L, ZUO X B, et al. Facile preparation and study of the organic aerogel based on conventional phenolic resins[J]. Acta Polymerica Sinica, 2018(10): 58-65. (in Chinese)
[16]	国义军, 石卫波, 曾磊, 等. 高超声速飞行器烧蚀防热理论与应用[M]. 北京: 科学出版社, 2019.
	GUO Y J, SHI W B, ZENG L, et al. Mechanism of ablative thermal protection applied to hypersonic vehicles[M]. Beijing: Science Press, 2019. (in Chinese)
[17]	LI W J, HUANG H M, XU X L. A coupled thermal/ fluid/ chemical/ablation method on surface ablation of charring composite[J]. International Journal of Heat and Mass Transfer, 2017, 109: 725-736.
[18]	LI W, ZHANG J, FANG G D, et al. Evaluation of numerical ablation model for charring composites[J]. SCIENCE CHINA Technological Sciences, 2019, 62(8): 1322-1330. doi: 10.1007/s11431-018-9476-2
[19]	聂春生, 杨光, 聂亮, 等. 飞行器热解炭化材料烧蚀产物对等离子体流场的影响规律[J]. 兵工学报, 2022, 43(3): 513-523. doi: 10.12382/bgxb.2021.0161
	NIE C S, YANG G, NIE L, et al. Influence of ablation products of aircraft pyrolytic carbonized material on plasma flow field[J]. Acta Armamentarii, 2022, 43(3): 513-523. (in Chinese) doi: 10.12382/bgxb.2021.0161
[20]	袁野, 王丽燕, 曹占伟, 等. 碳纤维增强类复合材料烧蚀产物对等离子体流场特性影响的实验研究[J]. 兵工学报, 2020, 41(2): 298-304. doi: 10.3969/j.issn.1000-1093.2020.02.011
	YUAN Y, WANG L Y, CAO Z W, et al. Experimental research on the influence of ablation product of carbon fiber reinforced composite material on the plasma flow field characteristics[J]. Acta Armamentarii, 2020, 41(2): 298-304. (in Chinese) doi: 10.3969/j.issn.1000-1093.2020.02.011
[21]	聂春生, 袁野, 周禹, 等. 纯碳/碳材料烧蚀对飞行器等离子体流场的影响[J]. 兵工学报, 2021, 42(2): 320-326.
	NIE C S, YUAN Y, ZHOU Y, et al. The influence of ablated products of pure carbon/carbon materials on plasma flow field around aircraft[J]. Acta Armamentarii, 2021, 42(2): 320-326. (in Chinese)
[22]	于哲峰, 胥建宇, 罗跃, 等. 高超声速飞行器烧蚀后退量时序提取及基于神经网络的预测[J]. 兵工学报, 2021, 42(6): 1230-1237. doi: 10.3969/j.issn.1000-1093.2021.06.013
	YU Z F, XU J Y, LUO Y, et al. Time series extraction of ablation recession of hypersonic vehicle and its prediction based on LSTM neural network[J]. Acta Armamentarii, 2021, 42(6): 1230-1237. (in Chinese) doi: 10.3969/j.issn.1000-1093.2021.06.013