固体火箭发动机粘接界面湿热老化实验

推进技术 ›› 2013, Vol. 34 ›› Issue (4): 557-561.

固体火箭发动机粘接界面湿热老化实验

张晓军,常新龙

第二炮兵工程大学飞行器动力工程系,陕西西安 710025;第二炮兵工程大学飞行器动力工程系,陕西西安 710025

发布日期:2021-08-15
作者简介:张晓军(1979—),男,博士,讲师,研究领域为火箭发动机及失效物理与可靠性。 E-mail:zxj982003@163.com
基金资助:
装备预先研究项目(41328136032)。

Experimental Investigation for Hygrothermal Accelerated Aging on Adhesive Interface of Solid Rocket Motor

Department of Flight Vehicle Propulsion Engineering,The Second Artillery Engineering University,Xi’an 710025,China;Department of Flight Vehicle Propulsion Engineering,The Second Artillery Engineering University,Xi’an 710025,China

Published:2021-08-15

摘要/Abstract

摘要： 对固体火箭发动机粘接界面试验件进行了不同湿热条件下的加速老化试验,并测量了不同老化时间粘接界面的扯离强度,描述了湿热老化试验和性能测试中的试验现象,结合复合材料微粘接结构吸湿规律对试验现象和撤离强度随老化时间变化曲线进行了分析。研究结果表明:衬层-推进剂粘接界面是固体火箭发动机粘接结构中最薄弱环节,应予以重点考虑；湿热老化促进了环境水分从衬层–推进剂界面向推进剂内部的扩散和渗透,致使弱边界层向推进剂内部扩展,导致了衬层-推进剂界面粘接强度的降低。试验件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。 

关键词: 粘接界面;湿热老化;扯离强度 

Abstract: The hygrothermal accelerated aging experiments for adhesive interface specimens of solid rocket motor were carried out, and the tearing strength at different aging time was measured. The phenomena in the hygrothermal accelerated aging experiments and tearing strength measurment were described and explained, also including the rule of variation of the tearing strength with aging time by contrasting to the absorption law of composite. The results show that the lining-propellant interfaces are the weakest interfaces. Hygrothermal aging can promote the diffusion and permeability of water from lining-propellant interface to propellant internal and lead the tearing strength loss. The average tearing strength of adhesion interface varies downward with aging time, and there is a period in which the strength varies stably.

Key words: Adhesive interface; Hygrothermal aging; Tearing strength

张晓军,常新龙. 固体火箭发动机粘接界面湿热老化实验[J]. 推进技术, 2013, 34(4): 557-561.

ZHANG Xiao-jun, CHANG Xin-long. Experimental Investigation for Hygrothermal Accelerated Aging on Adhesive Interface of Solid Rocket Motor[J]. Journal of Propulsion Technology, 2013, 34(4): 557-561.