热老化改性双基推进剂延伸率主曲线研究

刘家铭; 邓恒; 杨春庆; 朱文革; 杨保雨

doi:10.15892/j.cnki.djzdxb.2025.05.020

弹箭与制导学报 >

2025 , Vol. 45 >Issue 5: 761 - 768

DOI: https://doi.org/10.15892/j.cnki.djzdxb.2025.05.020

学术文章

热老化改性双基推进剂延伸率主曲线研究

刘家铭 ,
邓恒 ^,^* ,
杨春庆 ,
朱文革 ,
杨保雨

展开

西安现代控制技术研究所, 陕西西安 710065

邓恒(1979—),男,正高级工程师,博士,DengHeng163@163.com

刘家铭(1994—),男,工程师,博士,liujiaming@njust.edu.cn

收稿日期: 2025-01-20

网络出版日期: 2025-11-28

收起

Research on the Master Curve of Elongation for Thermally Aged Modified Double-Base Propellant

LIU Jiaming ,
DENG Heng ^,^* ,
YANG Chunqing ,
ZHU Wenge ,
YANG Baoyu

Expand

Xi’an Modern Control Technology Research Institute, Xi’an 710065, China

Received date: 2025-01-20

Online published: 2025-11-28

Fold

摘要

为建立考虑老化效应的改性双基(CMDB)推进剂延伸率主曲线,开展了不同测试温度(233.15K、253.15K、273.15K、283.15K、298.15K、323.15K)和应变率(3.3×10^-4s^-1、3.3×10^-3s^-1和3.3×10^-2s^-1)下不同高温加速老化时间后改性双基推进剂单轴拉伸试验,根据实验结果获得了最大延伸率,结合扫描电子显微镜实验分析了老化对最大延伸率的影响,基于现有理论建立了考虑老化效应的延伸率主曲线模型。研究结果表明:随着老化时间的延长,改性双基推进剂最大延伸率单调递减,拉伸断面内细观损伤逐渐加重,老化时间对材料的温度特性和率相关特性影响较小,考虑老化效应的延伸率主曲线模型可以较好地描述不同老化时间下延伸率主曲线。研究结果可为不同老化时间下固体火箭发动机药柱结构完整性分析奠定基础。

关键词： 改性双基推进剂; 老化; 最大延伸率; 主曲线; 影响机理

本文引用格式

刘家铭 , 邓恒 , 杨春庆 , 朱文革 , 杨保雨 . 热老化改性双基推进剂延伸率主曲线研究[J]. 弹箭与制导学报, 2025 , 45(5) : 761 -768 . DOI: 10.15892/j.cnki.djzdxb.2025.05.020

Abstract

In order to establish the elongation criterion of composite modified double-base (CMDB) propellant considering aging effect,uniaxial tensile tests of CMDB propellant were carried out under different test temperatures (233.15K,253.15K,273.15K,283.15K,293.15K,323.15K) and strain rates (3.3×10^-4s^-1,3.3×10^-3s^-1,3.3×10^-2s^-1).According to the experimental results,the maximum elongation was obtained,and the mechanism of the effect of aging on the maximum elongation was analyzed by scanning electron microscope (SEM).Based on the existing theory,the master curve model of elongation considering aging effect was established.The results show that with the increase of aging time,the maximum elongation of CMDB propellant decreases monotonously,the meso-damage in the tensile section was gradually aggravated,and the aging time has little effect on the temperature and rate-dependent properties of the material.the master curve model of elongation considering aging effect can well describe the master curve of elongation under different aging time.The research results can lay a foundation for the structural integrity analysis of solid rocket motor grain under different aging time.

Key words： modified double-base propellant; aging; maximum elongation; master curve; influence mechanism

[an error occurred while processing this directive]

参考文献

原文顺序 | 文献年度倒序 | 文中引用次数倒序

[1]	Dong L, Wu Y, Yang K, et al. Investigation of high rate mechanical flow followed by ignition for high-energy propellant under dynamic extrusion loading[J]. Defence Technology, 2024, 32(2):336-347. DOI

[2]	DU Y Q, ZHENG J, YU G B. Storage life prediction under pre-strained thermally-accelerated aging of HTPB coating using the change of crosslinking density[J]. Defence Technology, 2021, 17(4):1387-1394. DOI

[3]	程吉明. 预应变作用下复合固体推进剂损伤本构及应用研究[D]. 西北工业大学, 2019. CHENG J M. Damage Constitutive Model of Composite Solid Propellant Under Prestrain and Its Application[D]. Xi’an: Northwestern Polytechnical University, 2019.

[4]	张兴高. HTPB推进剂贮存老化特性及寿命预估研究[D]. 国防科学技术大学, 2009. ZHANG X G. Study on the Aging Properties and Storage Life Prediction of HTPB Propellant[D]. Changsha: National University of Defense Technology, 2009.

[5]	张兴高, 张炜, 王春华, 等. 定应变作用下NEPE推进剂老化特性及寿命预估研究[J]. 国防科技大学学报, 2009, 31(3):5. ZHANG X G, ZHANG W, WANG C H, et al. The Aging Property and Life Prediction of NEPE Propellant under Constant Strain[J]. Journal of National University of Defense Technology, 2009, 31(3):5.

[6]	LYTTON R L, UZAN J, FERNANDO E G, et al. Development and validation of performance prediction models and specifications for asphalt binders and paving mixes[J]. asphalt mixtures,1993.

[7]	JONES R M. Stress-strain relations for materials with different moduli in tension and compression[J]. Aiaa Journal, 2012, 15(1):16-23. DOI

[8]	张晓军, 常新龙, 赖建伟, 等. HTPB推进剂低温拉伸/压缩力学性能对比[J]. 固体火箭技术, 2013, 36(6):4. ZHANG X J, CANG X L, LAI J W, et al. Comparative research of tensile and compressive mechanical properties of HTPB propellant at low temperature[J]. Journal of Solid Rocket Technology, 2013, 36(6):4.

[9]	王鸿丽. 改性双基推进剂含损伤粘弹塑性本构模型及应用研究[D]. 南京理工大学, 2019. WANG H L. Research on Visco-Elastic-plastic Constitutive Model with damage of Modified Double-Base Propellant and its Application[D]. Nanjing: Nanjing University of Science and Technology, 2011.

[10]	Chen G Q, Pan T L, Hui W W, et al. Numerical and experimental study on the curing process of NEPE solid rocket propellant considering multi-physical field effects[J]. Case Studies in Thermal Engineering, 2024,61,105124.

[11]	Zhou D M, Wang H, Hui B Q, et al. Effect of confining pressure on the structural integrity of NEPE solid propellant grain[J]. International Journal of Pressure Vessels and Piping, 2022, 200(4):241-255.

[12]	Zhang Y, Wang N, Ma W, et al. Investigations of the mechanical response of dummy HTPB propellant grain under ultrahigh acceleration overload conditions using onboard flight-test measurements[J]. Defence Technology, 2024.

[13]	张建彬, 鞠玉涛, 周长省. 双基固体推进剂的特性研究[J]. 固体火箭技术, 2013(1):4. ZHANG J B, JU Y T, ZHOU C S. Study on the characteristics of the double-base solid propellant[J]. Journal of Solid Rocket Technology, 2013(1):4.

[14]	刘家铭, 许进升, 陈雄, 等. 热老化改性双基推进剂拉伸力学性能及强度主曲线[J]. 含能材料, 2021, 29(9):9. LIU J M, XU J S, CHEN X, et al. Tensile Mechanical Properties and Strength Master Curve of thermal aged CMDB propellant[J]. Chinese Journal of Energetic Materials, 2021, 29(9):9.

[15]	LIU J, LI H, CHEN X, et al. A one-dimensional model for the aging and damage effects on the response of composite double-base propellants[J]. Mechanics of Time-Dependent Materials, 2022:1-17.

[16]	LIU J, TONG X, LUO X, et al. The relaxation behavior of composite double-base propellants with various stabilizer content under thermal aging[J]. Mechanics of Time-Dependent Materials, 2022:1-13.

[17]	刘畅, 强洪夫, 王哲君, 等. 低温动态加载下老化HTPB推进剂强度准则研究[J]. 推进技术, 2018, 39(11):7. LIU C, QIANG H F, WANG Z J, et al. Strength Criterion of Aged HTPB Propellant at Low Temperature under Dynamic Loading[J]. Journal of Propulsion technology, 2018, 39(11):7.

[18]	WANG Z, QIANG H, WANG T, et al. Tensile behaviors of thermal aged HTPB propellant at low temperatures under dynamic loading[J]. Mechanics of time-dependent materials, 2020(2):24.

[19]	GJB 770B-2005[S],火药试验方法:200-204,262-266. GJB 770B-2005[S],Test method of propellant:200-204,262-266.

[20]	孙朝翔. 宽泛应变率和温度下改性双基推进剂本构模型及应用研究[D]. 南京理工大学, 2018. SUN C X. A Constitutive Model for Modified Double-Base Propellant over A Wide Range of Strain Rates and Temperatures and Its Application[D]. Nanjing: Nanjing University of Science and Technology, 2018.

[21]	刘子如, 张腊莹, 衡淑云, 等. 双基推进剂的玻璃化温度[J]. 火炸药学报, 2009, 32(2):4. LIU Z R, ZHANG L Y, HENG S Y, et al. The Glass Transition Temperature for Double Base Propellant[J]. Chinese Journal of Explosives and Propellants, 2009, 32(2):4.

[22]	贾展宁. 改性双基推进剂力学性能特点分析[J]. 兵工学报, 1989. JIA Z N. Analysis of Mechanical Properties of CMDB Propellants[J]. Acta Armamentarii, 1989.

[23]	XU C, LENG S, ZHOU Z, et al. Accurate and straightforward symplectic approach for fracture analysis of fractional viscoelastic media[J]. Applied Mathematics and Mechanics, 2022, 43(3):403-416. DOI

[24]	SUN C, XU J, CHEN X, et al. Strain rate and temperature dependence of the compressive behavior of a composite modified double-base propellant[J]. Mechanics of Materials, 2015,89(oct.):35-46.

[25]	YAN Q L, ZHAO F Q, KUO K K, et al. Catalytic effects of nano additives on decomposition and combustion of RDX-,HMX-,and AP-based energetic compositions[J]. Progress in Energy and Combustion Science, 2016,57(nov.):75-136.

[26]	LI Y, YUAN J M, ZHAO W, et al. Application and Development of 3,4-Bis (3-nitrofurazan-4-yl) furoxan (DNTF)[J]. Russian Journal of General Chemistry, 2021, 91(3):445-455. DOI

[27]	王哲君, 强洪夫, 广王, 等. 低温高应变率条件下HTPB推进剂拉伸力学性能研究[J]. 推进技术, 2015, 36(9):7. WANG Z J, QIANG H F, GUANG W, et al. Tensile Mechanical Properties of HTPB Propellant at Low Temperature and High Strain Rate[J]. Journal of Propulsion technology, 2015, 36(9):7.

[28]	XU J S, JU Y T, et al. Research on relaxation modulus of viscoelastic materials under unsteady temperature states based on TTSP[J]. Mechanics of Time Dependent Materials, 2013.

[29]	唐国金, 周建平. 自由装填药柱的结构完整性分析[J]. 固体火箭技术, 1994(2):13-20. TANG G J, ZHOU J P. The Structural Integrity Analysis of Free Loading Solid Rocket Grains[J]. Journal of Solid Rocket Technology, 1994(2):13-20.

[30]	LANDEL R F, NIELSEN L E. Mechanical Properties of Polymers and Composites[M]. Mechanical Properties of Polymers and Composites, 1993.

[31]

李科, 郑坚, 支建庄, 等. 丁羟包覆层老化宏微观特性相关性及贮存寿命预估[J]. 复合材料学报, 2019, 36(05):1327-1334.

, Zheng

, Zhi

, Du

, Chen

. Correlation between macroscopic microscopic aging properties and lifetime prediction of hydroxyl-terminated polybutadiene inhibitor[J]. Acta Mater Compositae Sinica, 2019, 36(05):1327-1334.

Options

文章导航