摘要
高装填小型固体发动机在研制初期遇到的问题之一是点火后存在过高的初始压强峰。通过对流场的数值模拟 ,找出了造成初始压强峰的原因是由于燃烧室尾部结构不匹配而导致初始时刻燃气流动不畅。修改尾部药型后 ,消除了初始压强峰。
In the preliminary stage of research and development of a high loading fraction small scale solid rocket motor, one of problems is that there exists super high initial pressure peak after ignition Through the numerical simulation of the inner flow field, it is found that the initial pressure peak is formed by the unmatched tail grain configuration, resulting in combustion gas choke After modification of the tail grain configuration, the initial pressure peak is removed
出处
《固体火箭技术》
EI
CAS
CSCD
北大核心
2002年第3期21-22,25,共3页
Journal of Solid Rocket Technology
关键词
药型
点火
影响
固体推进剂火箭发动机
压力
small scale solid motor
grain cofiguration
flow field simulation
