摘要
采用一维准定常方法 ,对整体式固体火箭冲压发动机的无喷管助推器内弹道进行了计算。计算结果表明 ,随着燃面的推移 ,燃烧室压强下降很快 ,而推力增大 ;助推器比冲偏低 ;对于高燃速固体推进剂 ,燃速沿通道降低 。
The purpose of the paper is to study the interior ballistics in nozzleless booster with solide propellant rocket ramjet engine with one dimension quasi steady equations. The result of calculation shows that the pressure in chamber decreases considerably and the thrust increases as the burn progresses. The impulse of nozzleless booster is low. The regression rate of propellant decreases along the grain, so the fuel first shrinks and then begins to expand.
出处
《导弹与航天运载技术》
北大核心
2004年第4期37-41,共5页
Missiles and Space Vehicles
关键词
整体式固体火箭冲压发动机
无喷管助推器
内弹道
Integral solide propellant rocket ramjet engine
Nozzleless booster
Interior ballistics
