鸭式布局卷弧尾翼导弹气动特性数值分析  

NUMERICAL ANALYSIS OF AERODYNAMIC CHARACTERISTICS OF CANARD WRAPAROUND FINS MISSILE

作　　者：罗中琦 张涪 郑磊 杨鹏 付豪 王立峰[1] LUO Zhongqi;ZHANG Fu;Zheng Lei;YANG Peng;FU Hao;WANG Lifeng(State Key Laboratory of Mechanics and Control for Aerospace Structures,Nanjing University of Aeronautics and Astronautics,Nanjing 210016,China;The 210th Institute of the Sixth Academy of CASIC,Xi’an 710065,China)

机构地区：[1]南京航空航天大学航空航天结构力学及控制全国重点实验室,南京210016 [2]中国航天科工集团六院二一〇所,西安710065

出　　处：《力学与实践》2025年第2期295-305,共11页Mechanics in Engineering

基　　金：国家自然科学基金项目(U2341230)资助。

摘　　要：主要研究鸭式布局卷弧尾翼导弹的气动特性。采用格心有限体积法与滑移网格技术对鸭式布局卷弧尾翼导弹进行了定常与非定常数值模拟。结果表明:在相同滚转舵偏角度下,正负打舵时尾翼上的滚转力矩大小不等;在相同滚转舵偏角度下,正向打舵比负向打舵尾翼诱导的反操纵力矩大;同方向打舵时舵偏角越大反操纵影响程度越小。导弹旋转时马格努斯力系数随滚转角呈周期性变化,不同旋转方向时马格努斯力的波动方向相反,且反转的马格努斯力小于正转;当尾翼与弹体固联旋转时马格努斯力主要由后体提供,且前后体马格努斯力方向相反;当尾翼与弹体解耦旋转时,马格努斯力比固联旋转时更小。以上结论可为导弹控制系统设计提供依据。In order to investigate the aerodynamic characteristics of a canard missile with wraparound fins,steady-state and unsteady-state numerical simulations were conducted using the grid-centered finite volume method and slip-grid technique.The results indicate that the roll moments on the tail are not equal when the same roll deflection angle is applied in opposite directions.Specifically,under the same roll deflection angle,a positive deflection of the canard generates a larger anti-control moment on the tail than a negative deflection.When the deflection are in same direction,the anti-control effectiveness decreases as the deflection angle increases.Additionally,as the missile rotates,the Magnus force coefficient varies periodically with the roll angle.The fluctuation direction of the Magnus force is opposite for different rotation directions,and the Magnus force during reverse rotation is smaller than during forward rotation.When the tail is rigidly coupled and rotating with the missile body,the Magnus force is primarily contributed by the afterbody,with the Magnus forces on the fore and after bodies having opposite directions.Conversely,when the tail is decoupled from the missile body,the Magnus force is smaller compared to the case of rigid coupling rotation.These conclusions can serve as a foundation for the design of missile control systems.

关 键 词：鸭式布局 卷弧翼 反操纵 马格努斯力 气动特性 

分 类 号：TJ011.3[兵器科学与技术—兵器发射理论与技术]