旋转弹体及减旋片滚转阻尼数值模拟  

Roll Damping Simulation of Missile Body and Anti-rotation Flaps

作　　者：赵养正[1] 蒋胜矩[1] 党明利[1] 朱中根 

机构地区：[1]西安现代控制技术研究所,陕西西安710065

出　　处：《兵工学报》2015年第7期1176-1180,共5页Acta Armamentarii

摘　　要：滚转阻尼力矩导数是影响减旋效果的重要参数。采用求解定常流场的计算流体力学方法,对亚跨声速阶段带减旋片翼翼身组合体的滚转阻尼特性进行数值模拟。滚转阻尼力矩导数数值模拟的结果与试验值一致性较好。通过数值结果分析解释了由于滚转引起的弹翼气流攻角的变化,表面压力的变化,以及附加升力导致的滚转阻尼力矩的形成原因,展示了薄翼片弯折的位置,同时从流场的角度展示了滚转对弹体附近气体流动的影响,以及滚转引起的表面流线的弯曲,螺旋状尾迹。Roll damping derivative is an important aerodynamic parameter which affects the despinning effect of a missile. Steady CFD simulations are used to predict the roll damping characteristics of the missile with anti-rotation flaps at subsonic and transonic speeds. The predicted roll damping derivatives are in good agreement with the experimental data. The variation of the angle of attack and the surface pressure of wings due to rolling and the roll damping moment induced by additional wing lift are explained through numerical analysis. The bending location of the thin wings is shown. From the view of flow field,the influence of spinning on gas flow nearby the body of missile,the bending of surface streamline and the helical-like streamline pattern in the wake are demonstrated.

关 键 词：兵器科学与技术 滚转阻尼导数 弹体 减旋片 数值模拟 

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]