三维直角网格自适应DSMC数值模拟  

DSMC Numerical Simulation of Three Dimensional Cartesian Adaptive Grid

作　　者：朱荣丽[1] 曹义华[1] 李栋[1] 

机构地区：[1]北京航空航天大学航空科学与工程学院,北京100083

出　　处：《导弹与航天运载技术》2007年第3期50-54,共5页Missiles and Space Vehicles

基　　金：自然科学基金资助,项目编号：60541001

摘　　要：利用物面网格和流场网格耦合处理的方法,编制了三维再入飞行器稀薄高超声速绕流流场通用的DSMC计算程序,发展了一种高效、小存贮自适应多级直角网格技术,计算了圆球自由分子绕流和稀薄过渡区球双锥体绕流流场结构特征和气动力热特性,并将圆球自由分子绕流的计算结果、理论解以及超热力学解进行了了比较,利用直角网格自适应技术模拟了头双锥外形再入飞行器流场结构和气动力系数,验证了流场网格和物面网格处理方案和计算程序的可靠性。A general computer program for DSMC numerical simulation of reentry spacecraft in the ultrasonic three dimensional rarefied gas flow field with low density has been worked out. In this simulation, A new coupling process for the surface position elements and the space cells by the DSMC method are used. Based on adaptive grid technology, a numerical simulation of supersonic rarefied gas flow passing a spherical double-conic is obtained. The simulation results are in excellent agreement with the theoretical data in the entire Knudsen region, and the accuracy, generality and reliability of the coupling process and the computer program are verified.

关 键 词：直接模拟蒙特卡罗方法 过渡区 再入飞行器 热流 

分 类 号：V211.3[航空宇航科学与技术—航空宇航推进理论与工程]