微型固体脉冲推力器内弹道数值计算与分析  

Numerical Analysis on Interior Ballistics of the Micro-Impulsive Thruster

作　　者：周海清[1] 尤政[1] 张平[2] 

机构地区：[1]清华大学精密仪器与机械学系,北京100084 [2]北京理工大学机电工程学院,北京100081

出　　处：《弹箭与制导学报》2005年第4期89-91,共3页Journal of Projectiles,Rockets,Missiles and Guidance

摘　　要：为预示微型固体脉冲推力器内弹道特性,采用数值计算模拟了推力器内弹道全过程,模拟过程考虑了瞬态燃烧的影响,采用了不同压力范围的稳态燃速数据,对不同的计算方案进行了比较,分析结果表明瞬态燃烧对推力器内弹道特性影响较小,准确的推进剂高压力范围稳态燃速是影响微型固体脉冲推力器内弹道特性预示的主要影响因素。In order to figure out the interior ballistic characteristics of the micro- impulsive thruster, numerical calculation and simulation have been done, in which the effects of the transient burning were taken into consideration and steady burning rate under different pressure ranges were used. According to the comparison among the results of several calculation schemes, it shows that the accurate steady burning rate of the propellant in extended pressure range is the primary effect on the interior ballistic characteristics of the micro-impulsive thruster while transient burning places relatively less ones.

关 键 词：微型火箭发动机 脉冲推力器 内弹道 数值分析 推进剂 

分 类 号：TJ012.1[兵器科学与技术—兵器发射理论与技术]