姿控发动机喷管内流场的DSMC并行算法  

Parallel algorithm for simulation of altitude-control thruster nozzle flow with DSMC method

作　　者：黄琳[1] 陈伟芳[1] 吴其芬[1] 

机构地区：[1]国防科技大学航天与材料工程学院,湖南长沙410073

出　　处：《推进技术》2001年第5期373-375,共3页Journal of Propulsion Technology

摘　　要：在分析了直接仿真Monte carlo (DSMC)方法内在并行度的基础上 ,针对工作站群机并行系统 (NOWS)分布主存的特点 ,构造了适合于DSMC仿真的并行算法模型 ,在PVM环境下将其应用于姿控发动机喷管内流场的DSMC仿真 ,结合并行算法效率评价准则对如何提高并行计算效率进行研究。仿真结果表明了实施DSMC并行计算的必要性与有效性。After analyzing the inner parallel character of DSMC method, a parallel algorithm for DSMC suited to distributed memory parallel system was constructed . Based on efficiency evaluation principle, some modifying techniques was also brought out. With above parallel algorithm, the simulation of attitude control thruster nozzle interior flowfield is finally realized with DSMC method using NOWS system. Some factors affecting parallel efficiency were also discussed. Computation results show the necessity and effctiveness of parallization of DSMC method.

关 键 词：姿控火箭发动机 喷管气流 流动分布 蒙特卡罗法 并行算法 数值仿真 

分 类 号：V231.3[航空宇航科学与技术—航空宇航推进理论与工程]