摘要
为了研究NEPE推进剂环境下HTPB衬层老化对松弛模量的影响,从75℃老化不同时间的NEPE推进剂/HTPB衬层粘接试件中取得衬层试样,进行了不同温度下衬层的拉伸应力松弛测试,并获得了相应的凝胶分数测试数据。根据时-温等效原理将不同老化时间的衬层的松弛模量数据制作成松弛模量主曲线,并分别用Prony级数进行拟合。结果显示,老化对松弛模量的弹性部分有显著影响,对粘性部分影响很小。忽略老化对粘性部分的影响,建立了含老化效应的衬层应力松弛模型。建立了修正的弹性模量-凝胶分数关系模型,并根据衬层实验数据验证了该模型。结合上述2个模型,得到了化学参量表征老化效应的衬层应力松弛模型。对该模型的应用进行了讨论,发现外推至常温,应力松弛与老化在不同的时间尺度起作用,松弛模量可用分段函数描述。
Effects of aging on stress relaxation of HTPB liner exposed on NEPE propellant have been investigated.Liner samples were taken from NEPE propellant-HTPB liner bonding specimens,which had been aged for different time at 75 ℃.Tensile stress relaxation were tested on the samples at different temperatures,and gel fractions of the samples also were measured.According to time-temperature superposition,master curves were made from relaxation modulus data measured at different temperatures.The master curves were fitted by Prony series.The results show that there are significant effects of aging on elastic part of relaxation modulus,and little effect of aging on visco part of relaxation modulus.A stress relaxation model with aging effects was obtained regardless of the effects on the visco part.A corrected model for relationship between elastic modulus and gel fraction was established,and verified by experimental data of the liner.Then a stress relaxation model with aging effects based on chemical parameters was achieved by combining above two models.Relaxation modulus predication was discussed with the model.It was found that at ambient temperature,the effects of stress relaxation and aging do not work on modulus in the same time scale,and relaxation modulus can be described as a subsection function.
出处
《固体火箭技术》
EI
CAS
CSCD
北大核心
2010年第4期435-439,444,共6页
Journal of Solid Rocket Technology
