摘要
为研究导弹发射过程中的燃气流场和导弹运动规律 ,采用计算流体力学方法和动网格技术 ,对导弹发射过程进行数值模拟 .将安置在发射筒中的导弹作为运动实体 ,随着导弹运动 ,相应的流场计算边界发生变化 .计算过程根据当前时刻喷管内流场及燃气流场计算导弹受力 ,确定导弹在任意计算时刻的运动速度 ,并由相应的运动边界更新网格 ,计算新网格下的流场参数分布 .计算结果与实验结果相符 。
The thesis simulates the missile launch p ro cess by the method of the computational fluid dynamics and the technology of dyn amic mesh, in order to study the jet flow during the missile launch and the rule s of missile movement. The missile, laid in the launch canister, is regarded as movement entity in the study. With the missile moving, the boundary of the corre sponding flow field will change. On the base of the nozzle flow and the jet flow , we can calculate the force of missile, by which we can obtain the velocity of the missile at current time. Then according to the new boundary, we can update m esh and compute the flow field of the next time. Compared emulational results wi th practical experiments, the two results are consistency. As a result, the stud y by the method of the computational fluid dynamics and the technology of dynami c mesh during the process of missile launch, can be regards as references and gi st.
出处
《弹道学报》
CSCD
北大核心
2004年第3期11-16,共6页
Journal of Ballistics
关键词
计算流体力学
动网格
燃气流
computational fluid dynamics, dynamic mesh, jet flow
