尾翼通槽对弹箭气动特性影响研究

Study on the Influence of Tail Hole on Aerodynamic Characteristics of Missile

摘要

为适应弹箭运输与发射需求，尾翼通常采用折叠式设计，折叠舱未完全密封时会在弹身表面形成上下贯通的槽状结构，进而改变全弹气动性能。针对该问题，建立了不同通槽宽度正常式布局导弹的三维数值模型，并与风洞试验数据对比，验证了计算方法的准确性。采用 CFD 方法计算轴向力系数、法向力系数和俯仰力矩系数，研究通槽宽度、攻角和马赫数对导弹气动力特性及局部流场的影响。结果表明，有通槽导弹的轴向力系数、法向力系数和俯仰力矩系数绝对值总体均大于无通槽导弹；随着通槽宽度增大，轴向力系数整体增大，法向力系数和俯仰力矩系数绝对值先增大后减小。在 Ma＝０.３ 且 α ＝１５°工况下，通槽宽度为 ４ｍｍ 时法向力系数最大，较无通槽构型提高 ４.２％，俯仰力矩系数绝对值提高 ４.６％，导弹俯仰操纵性能较好。流场分析表明，通槽改变了尾舵前方的速度与压力分布，通槽末端高低压区作用面积变化是气动力非单调变化的主要原因。随着攻角增大，通槽内流速提高，尾舵前方低压涡增强，使法向力系数和俯仰力矩系数绝对值进一步增大。

Abstract

To facilitate missile transportation and launch, tail fins are commonly designed to be foldable. When the folding compartment cannot be completely sealed, a hole-like structure connecting the upper and lower surfaces of the missile body may be formed, thereby altering the aerodynamic characteristics of the entire missile. To investigate this issue, a three-dimensional numerical model of conventional-configuration missiles with different hole-widths was established, and the accuracy of the numerical method was validated through comparison with wind-tunnel test data. The axial force coefficient, normal force coefficient, and pitching moment coefficient were calculated using CFD method, and the effects of different hole-widths, angle of attack, and Mach number on the aerodynamic characteristics and local flow-field of the missile were studied. The results show that the axial force coefficient, normal force coefficient, and absolute pitching moment coefficient of the missile with holes are generally greater than those of the missile without holes. As the hole width increases, the axial force coefficient generally increases, whereas the normal force coefficient and the absolute pitching moment coefficient first increase and then decrease. At Ma ＝０.３ and α ＝１５°, the missile with a hole width of ４mm exhibits the maximum normal force coefficient, which is ４.２％ higher than that of the configuration without holes. Meanwhile, the absolute pitching moment coefficient increases by ４.６％, indicating improved pitch maneuverability. Flow-field analysis shows that the holes alter the velocity and pressure distribution upstream of the tail fins, and that variations in the effective areas of the high-and low-pressure regions near the hole exits are primarily responsible for the non-monotonic variation in aerodynamic forces. As the angle of attack increases, the flow velocity within the holes rises, and the low-pressure vortices upstream of the tail fins intensify, further increasing the normal force coefficient and the absolute pitching moment coefficient.

关键词

弹箭 / 尾部通槽 / 气动特性 / 正常式布局 / 数值模拟

Key words

missile / tail hole / aerodynamic characteristics / normal layout / numerical simulation

参考文献

[1] 谷良贤. 导弹总体设计原理[M]. 西安: 西北工业大学出版社, 2004.

[2] 钱杏芳. 导弹飞行力学[M]. 北京: 北京理工大学出版社, 2006.

[3] 岑梦希, 张瑞民. 某型导弹动导数风洞试验和 CFD 数值模拟[J]. 航空工程进展, 2019, 10(3): 371-375.

[4] CEN Mengxi, ZHANG Ruimin. Wind tunnel test and CFD numerical simulation of dynamic derivative for a certain type of missile[J]. Advances in Aeronautical Science and Engineering, 2019, 10(3): 371-375. (in Chinese)

[5] MENG Y, YAN L, HUANG W, et al. Numerical investigation of the aerodynamic characteristics of a missile[J]. IOP Conference Series: Materials Science and Engineering, 2020, 887: 012001.

[6] ŞUMNU A, GÜZELBEY İ. The effects of different wing configurations on missile aerodynamics[J]. Journal of Thermal Engineering, 2023, 9(5): 1260-1271.

[7] 孙宁, 陈少松, 徐一航, 等. 侧滑角对大长细比鸭式布局弹箭俯仰操纵性的影响[J]. 弹道学报, 2023, 35(4): 70-79.

[8] SUN Ning, CHEN Shaosong, XU Yihang, et al. Influence of sideslip angle on pitching maneuverability of canard configuration missiles with large length to diameter ratio[J]. Journal of Ballistics, 2023, 35(4): 70-79. (in Chinese)

[9] WEI K, CHEN S, TANG D, et al. The influence of roll angles on unsteady aerodynamics in a canard-configured missile[J]. International Journal of Mechanical System Dynamics, 2024, 4(2): 213-225.

[10] WEI K, CHEN S, TANG D, et al. Evolution and influence of multivortex structure on the head of canard-controlled missile at high angle of attack[J]. International Journal of Aerospace Engineering, 2024, 2024: 6074417.

[11] 秦帆, 支豪林, 肖天航, 等 . 舵面控制下的导弹俯仰与滚转特性研究[C]// 第七届中国航空科学技术大会论文集. 北京: 北京航空航天大学出版社, 2024: 672-679.

[12] GAO Y, LEI J, YIN J. Magnus effect over aerodynamic components of spinning missile[J]. International Journal of Aeronautical and Space Sciences, 2022, 23(3): 447-460.

[13] MEHDI G, ADAM J, POONEH A, et al. Computational aerodynamic investigation of long strake-tail missile configurations[J]. Aerospace Science and Technology, 2022, 127: 107704.

[14] 王锌晨, 王学德. 超音速鸭式布局导弹舵面偏转气动特性研究[J]. 兵器装备工程学报, 2020, 41(9): 99-104.

[15] WANG Xinch en, WANG Xuede. Aerodynamic analysis of a missile with dithering canards in supersonic[J]. Journal of Ordnance Equipment Engineering, 2020, 41(9): 99-104. (in Chinese)

[16] 姚鹏, 陈少松. 旋转体制下鸭式布局弹箭正弦打舵气动特性分析[J]. 弹道学报, 2021, 33(3): 19-24.

[17] YAO Peng, CHEN Shaosong. Analysis on aerodynamic characteristics of canard-configuration missile with sinusoidal rudder under rotating system[J]. Journal of Ballistics, 2021, 33(3): 19-24. (in Chinese)

[18] 陈海鹏, 顾祥玉, 王鑫蔚, 等. 基于高阶浸入边界法的变构型非定常气动仿真方法研究[J]. 宇航学报, 2025, 46(3): 473-484.

[19] CHEN Haipeng, GU Xiangyu, WANG Xinwei, et al. Research on aerodynamic characteristics of flight vehicle folding deformation based on high-order immersion boundary method[J]. Journal of Astronautics, 2025, 46(3): 473-484. (in Chinese)

[20] 陈军, 王瑶, 余长浩, 等. 变后掠翼制导火箭弹气动特性分析与弹道优化[J]. 中国惯性技术学报, 2023, 31(12): 1228-1235.

[21] CHEN Jun, WANG Yao, YU Changhao, et al. Analysis of aerodynamic characteristics and trajectory optimization of variable-sweep wing guided rockets[J]. Journal of Chinese Inertial Technology, 2023, 31(12): 1228-1235. (in Chinese)

[22] 王明亮. 变体飞行弹箭的气动特性与飞行弹道研究[D]. 南京: 南京理工大学, 2022.

[23] 王颖, 李裕, 刘力, 等. 大长径比变后掠翼导弹的颤振特性分析[J]. 计算机仿真, 2024, 41(4): 55-58,493.

[24] WANG Ying, LI Yu, LIU Li, et al. Flutter characteristics analysis of variable sweep wing missile with large aspect ratio[J]. Computer Simulation, 2024, 41(4): 55-58, 493. (in Chinese)

[25] GEVA A, ABRAMOVICH H, ARIELI R. Investigation of a morphing wing capable of airfoil and span adjustment using a retractable folding mechanism[J]. Aerospace, 2019, 6(8): 85.

[26] XIE C, CHEN Z, AN C. Aeroelastic response of a Z-shaped folding wing during the morphing process[J]. AIAA Journal, 2022, 60(5): 3166-3179.

[27] 白剑锋, 孟军辉, 张莉丽, 等. 考虑流固耦合效应的弹翼展开动力学性能研究[J/OL]. 北京航空航天大学学报, 2024. DOI: 10.13700/j.bh.1001-5965.2024.0645.

[28] BAI Jianfeng, MENG Junhui, ZHANG Lili, et al. Dynamic performances research of the wing deployment considering fluid structure interaction[J /OL]. Journal of Beijing University of Aeronautics and Astronautics, 2024. DOI: 10.13700/j.bh.1001-5965.2024.0645.(in Chinese)

[29] 马国亮, 张猛, 韩桂元, 等. 刀片动能导弹跨声速气动特性研究[J]. 现代防御技术, 2025, 53(5): 99-110.

[30] MA Guoliang, ZHANG Meng, HAN Guiyuan, et al. Research of characteristics aerodynamic of blade kinetic energy missile[J]. Modern Defence Technology, 2025, 53(5): 99-110. (in Chinese)

[31] 张猛. 刀片动能导弹的建模和数值模拟研究[D]. 西安: 西安工业大学, 2024.

[32] ANDERSON JD. Fundamentals of aerodynamics[M]. New York: McGraw-Hill Education 2014.

[33] 闫超. 计算流体力学方法及应用[M]. 北京: 北京航空航天大学出版社, 2006.

[34] MENTER FR. Zonal two-equation k -ω turbulence models for aerodynamic flows: AIAA 93-2906[R]. 1993.

[35] MENTER FR. Two-equation eddy-viscosity turbulence models for engineering applications[J]. AIAA Journal, 1994, 32(8): 1598-1605.

[36] HONKANEN T, TUISKU T, PANKKKONEN A. CFD simulations and wind tunnel experiments of a generic split-canard air-to-air missile at high angles of attack in turbulent subsonic flow: AIAA 2011-6335[R]. 2011.

[37] 钱翼稷. 空气动力学[M]. 北京: 北京航空航天大学出版社, 2004.