固体火箭发动机粘接界面湿热老化与寿命评估

摘要

By ways of the hygrothermal accelerated aging experiments for adhesion interface of solid rocket motor,and by measuring tearing strength at different aging time,the variation rule of the tearing strength with aging time was analyzed in different aging conditon. By integrating the Eyring model and the Arrhenius model, hygrothermal aging life model for adhesion interface was developed ,and the life in normal storage condition was predicted. The results show that the average tearing strength of adhesion interface decreases with aging time,and there is a period in which the strength varies stably. The storage life of fluorine rubber at 20℃ is 12. 8 years.%通过对固体火箭发动机衬层-推进剂粘接界面的湿热加速老化试验以及不同老化时间下粘接界面的扯离强度测量,分析了不同湿热老化条件下试验件扯离强度随老化时间的变化规律.综合运用Eyring模型与Arrhenius模型,建立了粘接界面湿热老化寿命模型,预测了正常贮存条件下发动机的贮存寿命.研究结果表明,粘接界面平均扯离强度随老化时间呈下降趋势,中间有一个强度趋于稳定的平台期；在温度为20℃,湿度为65％ RH条件下,粘接界面的强度半衰期寿命为12.8a.