高燃温喉栓式变推力固体火箭发动机试验  

High Burning Temperature Experiment on Pintle Controlled Solid Motor

作　　者：王佳兴[1] 魏志军[1] 王宁飞[1] 

机构地区：[1]北京理工大学宇航学院,北京100081

出　　处：《推进技术》2012年第1期89-92,共4页Journal of Propulsion Technology

摘　　要：为研究高燃温推进剂下喉栓式固体火箭发动机推力控制,设计同轴式变推力固体火箭发动机试验系统,以混合式直线步进电机作为喉栓驱动系统,采用组合动密封方式,利用高燃温高压强指数推进剂进行点火试验,实现了燃烧室压强从12.1～2MPa的调节。试验结果发现喉栓头部烧蚀严重,对压强调节影响较大,针对喉栓烧蚀问题提出了减轻烧蚀思路,通过闭环控制方式控制喉栓运动,增加喉栓直径以及合理选择推进剂等可降低喉栓烧蚀,提高压强控制精度。In order to investigate the performance of piutle controlled solid rocket motor under the condition of high burning temperature, a coaxial pintle solid motor system was designed, with a linear motor as pintle actuator. Under this system, an experiment was carried out using modified double base propellant with high burning temperature and high pressure expo- nent. The chamber pressure was changed from 12. 1 ~ 2MPa. It was found that pintle head was eroded seriously, and it re- duced interior ballistics precision greatly. Relevant solutions were recommended to reduce this detrimental influence, such as adopting close loop control, increasing pintle diameter, choosing appropriate propellant and so on. This could provide some experience and foundation for pintle controlled solid motor design in future.

关 键 词：固体火箭发动机 喉栓 变推力 高燃温 

分 类 号：V435[航空宇航科学与技术—航空宇航推进理论与工程]