低温高应变率条件下HTPB推进剂拉伸力学性能研究

推进技术 ›› 2015, Vol. 36 ›› Issue (9): 1426-1432.

低温高应变率条件下HTPB推进剂拉伸力学性能研究

王哲君¹,强洪夫¹,王广¹,刘小川²,黄拳章¹

第二炮兵工程大学动力工程系，陕西西安 710025,第二炮兵工程大学动力工程系，陕西西安 710025,第二炮兵工程大学动力工程系，陕西西安 710025,中国飞机强度研究所，陕西西安 710065,第二炮兵工程大学动力工程系，陕西西安 710025

发布日期:2021-08-15
作者简介:王哲君(1988—)，男，博士生，研究领域为飞行器结构完整性分析与技术。

Tensile Mechanical Properties of HTPB Propellant at Low Temperature and High Strain Rate

Power Engineering Department，Xi’an Hi-Tech Institute，Xi’an 710025，China,Power Engineering Department，Xi’an Hi-Tech Institute，Xi’an 710025，China,Power Engineering Department，Xi’an Hi-Tech Institute，Xi’an 710025，China,Aircraft Strength Research Institute，Xi’an 710065，China and Power Engineering Department，Xi’an Hi-Tech Institute，Xi’an 710025，China

Published:2021-08-15

摘要/Abstract

摘要： 为研究固体推进剂在低温高应变率条件下的力学性能，通过单轴拉伸实验和扫描电镜(SEM)断面观察，分别获取了HTPB推进剂在温度范围为-40～25℃及0. 4～14.29s-1应变率下的应力-应变曲线和拉伸断面形貌。结果表明，HTPB推进剂的力学性能具有明显的温度和应变率效应。随温度降低和应变率升高，应力-应变曲线特性变得更加复杂，断面形貌基本上呈现“脱湿”越困难、颗粒断裂越明显的规律，低温和高应变率的“耦合”作用使得推进剂的损伤变得更加严重。初始弹性模量[E]和最大拉伸应力[σm]随温度的降低和应变率的升高而逐渐增加，且均与应变率具有相对较好的线性对数关系。低温和高应变率的“耦合”作用，使得-40℃及14.29s-1条件下的初始弹性模量和最大拉伸应力分别为25℃及0.4s-1条件下数值的1.6倍和3.2倍。与模量和强度相比，应变的规律性较复杂，其值随温度的升高而增加，且在常温下随应变率的升高而增加，但在低温下随应变率的升高而降低。通过双因素方差分析表明，低温高应变率条件下，温度和应变率均对最大拉伸应力有更显著的影响，同时温度较应变率对最大拉伸应力影响更加明显，而对模量则较弱。基于时温等效原理，得到了低温高应变率条件下HTPB推进剂的拉伸力学性能主曲线，该主曲线较大地拓宽了对推进剂力学性能的预测范围。

关键词: HTPB推进剂；低温；高应变率；拉伸力学性能

Abstract: To investigate the mechanical properties of solid propellant at low temperature and high strain rate，stress-strain curves and tensile fracture surfaces of HTPB propellant were obtained in a wide range of temperature(-40～25℃)and strain rates(0.4～14.29s-1)，respectively，by means of uniaxial tensile tests and electron microscopy scanning on the fracture cross section. The results indicate that mechanical properties of HTPB propellant were influenced distinctly by temperature and strain rate. With decreasing temperature and increasing strain rate，the characteristics of stress-strain curves are more complex. At the same time，the dewetting between particles and matrix is more difficult to occur in propellant，but the particle brittle fracture is easier. With the coupled effects of low temperature and high strain rate，the damage for HTPB propellant is more serious. Secondly，the initial elastic modulus [E] and maximum tensile stress [σm] increase gradually with decreasing temperature and increasing strain rate，and well present linear-log function relation with strain rate. In addition，with the coupled effects of low temperature and high strain rate，the values of the initial elastic modulus [E] and maximum tensile stress [σm] at -40℃ and 14.29s-1 are 1.6 and 3.2 times of their values at 25℃ and 0.4s-1，respectively. But comparing with them，the relationships of the corresponding strain with temperature and strain rate are more complex. With increasing temperature，this strain increases. At room temperature，this parameter increases with increasing strain rate，while it decreases with increasing strain rate at low temperature. The results of variance analysis indicate that low temperature and high strain rate have more significant effects on maximum tensile stress [σm]. In addition，the low temperature has greater influence on this parameter than high strain rate，but there is an opposite law for the initial elastic modulus [E]. Finally，mechanical properties master curves for HTPB propellant at low temperature and high strain rate were calculated by means of time-temperature superposition principle，which widen the prediction range for the mechanical properties of HTPB propellant.

Key words: HTPB propellant；Low temperature；High strain rate；Tensile mechanical properties

王哲君,强洪夫,王广,刘小川,黄拳章. 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): 1426-1432.

WANG Zhe-jun¹,QIANG Hong-fu¹,WANG Guang¹,LIU Xiao-chuan²,HUANG Quan-zhang¹. Tensile Mechanical Properties of HTPB Propellant at Low Temperature and High Strain Rate[J]. Journal of Propulsion Technology, 2015, 36(9): 1426-1432.

参考文献

[1] 侯林法. 复合固体推进剂[M]. 北京:中国宇航出版社, 1994.
[2] Zimmerman G A, Kispersky J P, Nahlovsky B D, et al. Embrittlement of Propellants Containing Nitrate Ester Plasticizers[R]. AIAA 82-1099.
[3] Nevière R, Tixier L. Fracture of Case Bonded Grains in Cold Pressurization Motors Tests[R]. AIAA 2009-5171.
[4] Shekhar H. Effect of Temperature on Mechanical Properties of Solid Rocket Propellants[J]. Defence Science Journal, 2011, 61(6): 529-533.
[5] Zalewski R, Wolszakiewicz T. Analysis of Uniaxial Tensile Tests for Homogeneous Solid Propellants under Various Loading Conditions[J]. Central European Journal of Energetic Materials, 2011, 8(4): 223-231.
[6] 赖建伟, 常新龙, 龙兵, 等. HTPB推进剂的低温力学性能[J]. 火炸药学报, 2012, 35(3): 80-83.
[7] 龙兵, 常新龙, 刘万雷, 等. HTPB 推进剂低温断裂性能试验研究[J]. 推进技术, 2014, 35(9): 1278-1282. (LONG Bing, CHANG Xin-long, LIU Wan-lei, et al. Experimental Study on Low Temperature Fracture Properties of HTPB Propellant[J]. Journal of Propulsion Technology, 2014, 35(9): 1278-1282.)
[8] Ho S Y,Fong C W.Temperature Dependence of High Strain-Rate Impact Fracture Behaviour in Highly Filled Polymeric Composite and Plasticized Thermoplastic Propellants[J].Journal of Material Science,1987,22: 3023-3031.
[9] 王蓬勃, 王政时, 鞠玉涛, 等. 双基推进剂高应变率型本构模型的实验研究[J]. 固体火箭技术, 2012, 35(1): 69-72.
[10] 常新龙, 赖建伟, 张晓军, 等. HTPB推进剂高应变率粘弹性本构模型研究[J]. 推进技术, 2014, 35(1): 123-127. (CHANG Xin-long, LAI Jian-wei, ZHANG Xiao-jun, et al. High Strain-Rate Viscoelastic Constitutive Model for HTPB Propellant[J]. Journal of Propulsion Technology, 2014, 35(1): 123-127.)
[11] 强洪夫. 固体火箭发动机药柱结构完整性数值仿真与实验研究[D]. 西安:西安交通大学, 1998.
[12] 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(3): 771-774.
[13] 强洪夫, 王广, 武文明, 等. 一种用于非金属材料力学试验的单轴高速拉伸试验夹具[P]. 中国专利: ZL 2013 2 0012760.5, 2013-07-13.
[14] 颜红, 唐承志. 提高高燃速丁羟推进剂低温伸长率研究[J]. 推进技术, 2003, 24(6): 563-566. (YAN Hong, TANG Cheng-zhi. Improvement of Low Temperature Elongation Ratio of High-Burning Rate HTPB Propellant[J]. Journal of Propulsion Technology, 2003, 24(6): 563-566.)
[15] Nevière R. An Extension of the Time-Temperature Superposition Principle Applied for Predicting Mechanical Properties of Solid Rocket Propellants[J]. Propellants,Explosives, Pyrotechnics, 1999, 24: 221-223.
[16] Williams M L, Landel R F, Ferry J D. The Temperature Dependence of Relaxation Mechanisms in Amorphous Polymers and Other Glass-Forming Liquids[J]. Journal of the American Chemical Society, 1955, 77: 3701-3705.(编辑:张荣莉)　　　　　　　　　　　　　*　收稿日期:2014-11-05；修订日期:2014-12-31。作者简介:王哲君(1988—),男,博士生,研究领域为飞行器结构完整性分析与技术。E-mail: qiulongzaitian@126.com