固体火箭发动机喷管一体化粘接工艺研究  

Research on Integrative Bonding Process of Solid Rocket Motor Nozzle

作　　者：王纪霞[1] 包乐[1] 胡大宁 张崇耿[1] 张新航[1] 

机构地区：[1]西安长峰机电研究所,西安710065 [2]陆军驻天水地区军事代表室,天水740000

出　　处：《航天制造技术》2014年第1期26-29,共4页Aerospace Manufacturing Technology

摘　　要：为了满足固体火箭发动机喷管一体化的粘接要求,提高产品的粘接质量,分析了胶粘剂性能、粘接工艺、温度及内衬与壳体的配合间隙对喷管粘接质量的影响,结果表明,通过控制影响一体化喷管粘接的各种因素,得出了最佳的工艺生产条件,保证了发动机工作的可靠性。Influence factors on nozzle bonding property including temperature, adhesive, bonding process and gap between metal shell and insert were analyzed to satisfy integrative bonding process of some solid rocket nozzle. The result of the test indicated that the best bonding process was found through controlling the factors, and the reliability of solid rocket was protected.

关 键 词：喷管 一体化 粘接工艺 

分 类 号：V435[航空宇航科学与技术—航空宇航推进理论与工程]