滚转状态下卷弧翼火箭弹气动特性的数值模拟  

Numerical simulation on aerodynamic characteristics of rolling rocket with wraparound fins

作　　者：宋琦[1] 杨树兴[1] 徐勇[1] 王飞[1] 

机构地区：[1]北京理工大学,北京100081

出　　处：《固体火箭技术》2008年第6期552-554,560,共4页Journal of Solid Rocket Technology

摘　　要：采用滑移网格技术对卷弧翼火箭弹的滚转特性进行数值模拟,并对模拟所得的马格努斯力与风洞实验数据进行分析比较。误差分析证明了滑移网格技术模拟火箭弹滚转特性的准确性;模拟结果与风洞实验数据对比表明,采用细长体外形效果显著,升阻力系数受滚转特性影响较小,因而在本次模拟的火箭弹滚速下,可不考虑滚转来模拟火箭弹的升力系数和阻力系数,得出火箭弹滚转运动对气动参数的影响。The rolling characteristics of the rocket with wraparound fins were numerically simulated by means of the slide mesh technology of CFD. The Magnus force simulation results were analyzed and compared with wind tunnel test data. The error analysis results verify the accuracy of the slide mesh technology for simulating the rolling characteristics of rocket with wraparound fins. The comparison between simulation results and wind tunnel test data shows that rolling characteristics has less effect on lift coefficient and drag coefficient of the slender rocket with wraparound fins, so lift coefficient and drag coefficient of the non-rolling rocket can be used as simulated value under the certain rolling velocity condition. Finally aerodynamic parameters of the rocket under rolling movement can be obtained.

关 键 词：卷弧尾翼 火箭弹 滚转特性 滑移网格 数值模拟 

分 类 号：TJ765[兵器科学与技术—武器系统与运用工程]