细长体自旋与锥动耦合运动作用下的流动结构研究

利用刚性网格运动技术和计算流体力学数值模拟相结合的方法，分析了带鸭舵细长体锥形运动和自转运动耦合作用下的空气动力学特性。研究了带鸭舵细长体耦合运动下的气动力系数随旋转角变化情况，对相同转速、不同攻角下的鸭舵诱导涡系结构和尾翼流场结构进行了对比分析。研究结果表明：耦合运动状态下，细长体的流场结构兼顾锥形运动和自转运动的特点，但又互相干扰、相互融合，涡系发展情况更为复杂，气动力曲线呈现周期性且有规律的振荡；攻角的增加将加剧涡系结构的破坏程度，并改变尾翼附近环状压力等值线的分布形状。

Research on Flow Field Structure of Slender Spinning Missile under Coupling of Conical and Spinning Motions

The aerodynamic characteristics of slender spinning missile with canard rudders under the coupling of conical and rotational motions are studied by using CFD numerical simulation and rigid moving grid technique.The aerodynamic coefficients of slender spinning missile are analyzed,and the changing curves of aerodynamic coefficients with spinning angle are given.The evolutionary trend of rudder-induced vortex is studied,and the tail flow fields at different times are compared.The result shows that the characteristics of conical and spinning motions are taken into account in the flow field structure of slender spinning missile,and these two kinds of motions not only interfere but also blend with each other.The evolution of vortices is more complex,and the aerodynamic curves are periodically and regularly oscillating.The destructiveness of vortex structure is aggravated with the increase in angle of attack,and the pressure around the fins is also changed.