摘要
为了模拟适配器与弹体分离的真实过程,以某箱式导弹垂直发射过程为背景,开展了对利用数值模拟风洞建立完备且准确的适配器气动数据库的方法的研究。仿真过程中采用批处理技术提高了计算效率。研究表明,以风速为10 m/s时得到的气动参数为基准,所有的气动参数误差均可以控制在1.5%以内,计算效率提高了50倍;通过数值模拟风洞得出的气动数据库,仿真得到的适配器脱离导弹的过程与试验结果一致。
In order to simulate the actual progress of the separation between the missile body and the adapter, the method of building complete and accurate aerodynamic database of adapter utilizing numerical wind tunnel was researched with the coffin-type vertical launch of missile as the background. During the simulation, calculating efficiency was improved with the use of batch processing technology. The research show that with the aerodynamic parameters gain got when the velocity of wind is 10 m/s as reference, the error of all the aerodynamic parameters could be controlled within 1.5 %, which means the calculating efficiency is improved by 50 times. The process of the adapter breaking away from the missile is obtained by simulating the aerodynamic database through numerical wind tunnel, which is in consistent with the experiment result.
作者
陶倩楠
姜毅
史少岩
唐垚
倪小川
TAO Qian-nan JIANG Yi SHI Shao-yan TANG Yao NI Xiao-chuan(School of Aerospace Engineering, Beijing Institute of Technology, Beijing 100081, China)
出处
《飞行力学》
CSCD
北大核心
2017年第5期92-96,共5页
Flight Dynamics
