摘要
介绍了单室双推力固体火箭发动机轴向分段装药工艺研究.结果采用结构新颖的转板阀,二次装配式芯模,以及刮涂绝热层和自动称量浇注药量技术,使装药达到了设计要求.
A study on axially segmented prpellant loading technology for a solid rocket motor with dual thrust in a single chamber is performed. The results indicate that a rotable plate valve with a novel structure, a secondary demountable mandrel and techniques of both scraping and coating of insulation and automatic weighing of propellant slurry to be loaded are adopted so that the design requirements for propellant loading can be met.
出处
《固体火箭技术》
EI
CAS
CSCD
1993年第2期87-89,共3页
Journal of Solid Rocket Technology
关键词
火箭发动机
固体推进剂
浇注
装药
Solid rocket engine Dual thrust rocket engine Solid rocket propellant Propellant casting Grain
