固体火箭发动机快速升压过程的流固耦合分析  

Analysis on fluid-structural coupling of solid rocket motor during rapid pressurization

作　　者：于胜春[1] 赵汝岩[2] 许涛 谢丽宽 王广[4] 

机构地区：[1]海军航空工程学院飞行器工程系,烟台264001 [2]海军航空工程学院研究生管理大队,烟台264001 [3]海军驻西安地区导弹发动机专业军代室,西安710025 [4]第二炮兵工程学院,西安710025

出　　处：《固体火箭技术》2008年第3期232-235,共4页Journal of Solid Rocket Technology

摘　　要：固体火箭发动机快速升压过程是一个非常典型的非稳态流固耦合问题。通过流固耦合软件MPCC I将FLUENT和ABAQUS连接,对气流流动与药柱结构完整性进行了耦合分析,确定了该过程中药柱的应力、应变情况及燃烧室的流场变化情况。仿真结果表明,在气流进入燃烧室时,可看到压力峰由前向后的传播过程,药柱随之变形,但同一时刻流场压力的最大处与药柱应变的最大处并不在同一位置。The rapid pressurization process of SRM belongs to a kind of trpical non-steady fluid-structural coupling problem. The FLUENT was linked with the ABAQUS by means of the fluid-structural coupling software to analyze gas flow and structural integrity of the grain. The change of stress, strain of the propellant and flow-field in motor chamber were determined. The simulation results show that pressure peak spreads from fore part to aft part when gas flow enters into the chamber, then the grain starts to distort; however, the maximum pressure in the flow-field isnt located in the same position of the maximum strain of the propellant.

关 键 词：固体火箭发动机 快速升压 流固耦合分析 

分 类 号：V435[航空宇航科学与技术—航空宇航推进理论与工程]