长期贮存固体火箭发动机界面脱粘安全性研究  

Research on the Safety of Long Term Storage Solid Rocket Motor with Debonded Layer

作　　者：贾卫东 周建[2] 刘亚冰[2] 朱凯[2] 

机构地区：[1]海军驻北京地区电子设备军事代表室,北京100070 [2]北京动力机械研究所,北京100074

出　　处：《战术导弹技术》2013年第5期101-106,共6页Tactical Missile Technology

摘　　要：研究了长期贮存的两型固体发动机的工作安全性。将两型固体发动机在CT探伤中发现的装药界面脱粘情况进行了统计分类,将其归结为"非贯通性"和"贯通性"两类脱粘情况。对两类脱粘情况分别开展了工作状态下的装药结构有限元计算及脱粘缝隙流场仿真,并将计算结果与发动机地面试验情况进行了对比。认为"非贯通性"的界面脱粘基本不会影响发动机工作安全性,而存在"贯通性"的界面脱粘的发动机则危险性较大。The safety of two types of SRM long term storage has been analyzed. The surface debonding phenomenon of them founded in CT detecting was counted and classified as ＂un-penetration＂ style and ＂penetration＂ style. Finite element grain structure analysis and fluid simulation inner grain crack has been conducted to figure the safety of two surface debonding styles. The simulation result was compared with the ground tests result of two types SRM. The results show that the ＂un-penetration＂ layer debonding style doesn＇t damage the safety during the SRM combustion, in the meanwhile the ＂penetration＂ style is quiet dangerous.

关 键 词：固体火箭发动机 脱粘裂痕 地面试验 安全性 

分 类 号：V435[航空宇航科学与技术—航空宇航推进理论与工程]