助推器对巡飞弹气动特性和静稳定性的影响

Influence of Booster on Aerodynamic Characteristics and Stability of Cruise Missile

针对助推分离舱外形对巡飞弹气动特性和静稳定性的影响,通过对船尾收缩比和分离舱外形设计的研究,分析了船尾收缩比和曲线过渡对改善气动特性和稳定性的机理,形成了“增大船尾收缩比-改善曲线过渡”的设计思想。结果表明:船尾收缩比是影响流动特性和气动特性的主要因素。增大船尾收缩比可以有效减小局部分离的面积,改善流动状况,改进后的零阻减小了1.5%~2%,静稳定度提高了1%~3%;在特定的船尾收缩比下,船尾与助推分离舱曲线过渡对阻力特性和静稳定性有一定改善效果。

In response to the influence of the shape of the booster separation chamber on the aerodynamic characteristics and static stability of cruise missiles,this article analyzes the mechanism of improving aerodynamic characteristics and stability by studying the stern contraction ratio and the shape design of the separation chamber,and forms the design concept of"increasing the stern contraction ratio and refine the curvature".The results indicate that the stern contraction ratio is the main factor affecting flow and aerodynamic characteristics.Increasing the stern contraction ratio can effectively reduce the area of local separation and improve flow conditions,which can reduce 1.5%~2%zero lift drag coefficient and improve 1%~3%longitude static stability.Under a specific stern contraction ratio,the curve transition between the stern and the propulsion separation chamber has a certain improvement effect on resistance characteristics and static stability.