摘要
叙述了固体推进剂火箭级间分离过程中，后向喷流流场的特征和影响反向喷流流场结 构的；因素．介绍了反向喷流风洞试验的模拟参数．分析了后体反向喷流对前体法向力系数、俯仰 力矩系数、阻力系数的影响以及喷流总压对前体气动特性的影响，打得出四点结论．
The flowfield feature of backward jet and the factor affecting flowfield structure of backward jet during stage separation are described. The simulation parameters of wind tunnel test of backward jet are presented. The influence of backward jet of the afterbody on normal force coefficient,pitching moment coefficient and drag coefficient of the forebody,and influence of jet total pressure on the aerodynamic characteristic of the forebody have been analyzed. The conclusions are given.
出处
《战术导弹技术》
2000年第1期63-68,共6页
Tactical Missile Technology
关键词
固体推进剂火箭
级间分离
喷流
流场
气动特性
solid propellant rocket
stage separation
jet
flowfield
interference
aerodynamic characteristic
