卷弧尾翼滚转特性研究  

Research on rolling characteristics of curly tail

作　　者：张志倩 李真 吴晶 王彦超 董玉立 李文武 熊国松 ZHANG Zhiqian;LI Zhen;WU Jing;WANG Yanchao;DONG Yuli;LI Wenwu;XIONG Guosong(Chongqing Hongyu Precision Industry Corporation Co.,Ltd.,Chongqing 400000,China)

机构地区：[1]重庆红宇精密工业集团有限公司,重庆400000

出　　处：《兵器装备工程学报》2024年第S01期129-134,共6页Journal of Ordnance Equipment Engineering

摘　　要：为研究卷弧尾翼滚转特性,利用流体计算软件Fluent进行数值模拟。在验证网格无关性的基础上,对卷弧尾翼火箭弹在不同滚转角、转速及攻角下的气动参数进行了计算分析,结果表明:不同滚转角、转速对全弹的阻力、升力影响较小,变化范围在5%以内;主要对侧向力和滚转力矩产生影响,在计算工况下滚转角越大,全弹侧向力(滚转角22.5°除外)、滚转力矩系数(滚转角67.5°除外)的换向马赫数越小;转速越高全弹滚转力矩系数越大;在小攻角范围内(-2°~6°),攻角绝对值越大,滚转力矩系数的换向马赫越小。In order to study the rolling characteristics of roll-tail rocket,Fluent in computational fluid dynamics(CFD)was used for numerical simulation.On the basis of verifying the effectiveness of the algorithm,unsteady calculation of different roll angle,rotational speed and attack angle of the roll-tail rocket is carried out to obtain the aerodynamic parameters of the rocket,and the calculated results are compared.The results show that different rolling angles and rotational speeds have little effect on the resistance and lift of the projectile,and the variation range is less than 5%,and the lateral force and rolling moment are mainly affected.Different rolling angle and attack angle affect the commutation Mach number of rolling torque.

关 键 词：卷弧尾翼 滚转特性 数值模拟 

分 类 号：TJ410[兵器科学与技术—火炮、自动武器与弹药工程]