摘要
为计算带约束流场的固体火箭发动机推力特性，建立了一维准定常变截面的内弹道计算和约束流场流动的数学模型。计算结果表明，约束流场使推力增加１４％，冲波进入喷管扩张段。与试验结果很接近，表明计算模型正确，可用于其它型号带约束流场的推力特性计算。
n order to compute the thrust characteristics of solid rocket motorwith the restrained flow, this paper establishes an internal ballistic mathematicalmodel by use of the steady one-dimensional flow equations in passage withchangable cross-sections in restrained flow fields. The results show that the thrustincreases by 14%, shock waves have entered the nozzle and the models developedare correct. The method is suitable for other solid rocket motors.
出处
《推进技术》
EI
CAS
CSCD
北大核心
1995年第1期33-40,共8页
Journal of Propulsion Technology
关键词
固体推进剂
火箭发动机
内弹道
计算
流动分布
Solid propellant rocket engine, Interior ballistic calculation, Gassolid interaction, Flow distribution
