喉栓式变推力固体火箭发动机内弹道调节特性  

Internal ballistic regulating property of variable thrust pintle SRM

作　　者：武渊[1] 何国强[1] 孙立刚[2] 孙展鹏[2] 苏建河[2] 

机构地区：[1]西北工业大学航天学院,西安710072 [2]中国航天科技集团公司四院,西安710025

出　　处：《固体火箭技术》2009年第5期511-513,共3页Journal of Solid Rocket Technology

摘　　要：发展了一套电动伺服驱动的喉栓式变推力固体火箭发动机试验系统,研制了喉栓式变推力固体火箭发动机,进行了喉栓式变推力固体火箭发动机内弹道调节特性试验。试验研究表明,耐烧蚀喉栓的轴向运动可实时调节发动机内弹道特性,目前已实现压强的四级调节;发动机内弹道变化相对喉栓运动有一定延迟,但其延迟可为工程所接受。The variable thrust pintle motor test system driven by electrical servo was developed and internal ballistic property regulation experiments were carried out. The experimental results show that the pinfle axial movement is useful to control internal ballistic property simultaneously and four-level pressure regulation can be achieved. The changes of internal ballistic property delaying to the pintle moment are acceptable in engineering application.

关 键 词：喉栓式变推力固体火箭发动机 内弹道 电伺服系统 调节特性 

分 类 号：V435[航空宇航科学与技术—航空宇航推进理论与工程]