旋转导弹横向喷流干扰特性数值模拟

doi:10.12382/bgxb.2022.0379

摘要/Abstract

摘要：

为研究超声速来流条件下旋转导弹横向喷流干扰流场结构及喷流干扰对导弹气动特性的影响和机理,使用基于雷诺平均非定常N-S方程和滑移网格技术的非定常数值方法对旋转导弹横向喷流干扰流场进行模拟。研究旋转对导弹横向喷流控制效果的影响,给出不同条件下导弹的气动特性变化规律,分析了横向喷流对旋转导弹气动特性的影响。研究结果表明:旋转会导致导弹横向喷流控制力发生偏转,偏转方向与旋转方向相反,偏转角度随着转速增加而增加;在小攻角下,喷流干扰效应产生的附加侧向力和偏航力矩系数的瞬时值比旋转马格努斯效应产生的侧向力和偏航力矩系数的瞬时值大一个数量级,随着攻角增大,旋转马格努斯效应引起的侧向力和偏航力矩系数占全弹的比例增大,喷流引起的附加侧向力和偏航力矩量值减小;旋转导弹横向喷流控制扇面内气动系数随滚转角变化具有很强的非定常性,当喷流控制扇面角度不大时,时均侧向气动特性与对称面处滚转角下的瞬时值侧向气动特性比较接近,不同扇面角度内有喷流的时均侧向力系数和偏航力矩系数远大于无喷流时。

关键词: 旋转导弹, 横向喷流, 喷流干扰, 侧向力, 数值模拟

Abstract:

In this study, a supersonic jet issued from a spinning missile into a supersonic freestream is numerically simulated. The 3D compressible unsteady Navier-Stokes equations and the sliding mesh method are utilized to simulate the flow field numerically. The effect of spinning motion on missile lateral jet control efficiency is studied, and the variation rules of aerodynamic characteristics of spinning missile under different conditions are given. The influence of lateral jet on the aerodynamic characteristics of spinning missile was analyzed. The results show that the spinning leads to the deflection of jet interference force and control force, and the deflection angle increases with the increase of spin rate. At small angle of attack, the additional lateral force and yaw moment coefficient caused by jet interference effect are one order of magnitude larger than those caused by Magnus effect. With the increase of angle of attack, the proportion of lateral force and yaw moment coefficient caused by Magnus effect in the whole missile increases, and the additional lateral force and yaw moment coefficient caused by jet decreases. The aerodynamic coefficients in the lateral jet control sector of the spinning missile vary with the rolling angle with strong unsteady characteristics. When the angle of the jet control sector is small, the time-averaged lateral aerodynamic characteristics are close to the transient lateral aerodynamic characteristics at the rolling angle of the symmetric surface. The time-averaged lateral force coefficient and time-averaged yaw moment coefficient with jet at different sector angles are much larger than those without jet.

Key words: spinning missile, lateral jet, jet interference, lateral force, numerical simulation

中图分类号:

V211.3

雷娟棉, 高毅, 勇政. 旋转导弹横向喷流干扰特性数值模拟[J]. 兵工学报, 2024, 45(1): 105-121.

LEI Juanmian, GAO Yi, YONG Zheng. Numerical Investigation of the Jet Interference Characteristics of a Lateral-jet-controlled Spinning Missile[J]. Acta Armamentarii, 2024, 45(1): 105-121.

图/表 27

图1 AFF导弹尺寸与坐标系定义

Fig.1 Shape of AFF missile and definition of coordinate system

图2 角度定义及喷流工作扇面角度示意图

Fig.2 Definition of angles and schematic diagram of jet working sector

图3 旋转导弹喷流干扰流场计算网格示意图

Fig.3 Schematic diagram of computational grid of jet interference flow field

表1 喷流验证计算条件

Table 1 Computational conditions of lateral jet verification

α/(°)	Ma	p_∞/Pa	Ma_j	δ_PR
0	2.8	20793.2	1.0	100
T_∞/K	T_0j/K	Re
108.96	279.81	2.06×10⁶

图4 CCF模型及计算网格示意图

Fig.4 CCF model and computational grid

图5 压力系数数值模拟结果与文献[20]试验值对比曲线

Fig.5 Comparison of Cp computational results with experiments data

表2 数值模拟条件

Table 2 Computational conditions of AFF

α/(°)	Ma	p_∞/Pa	T_∞/K	$ω ¯$	ρ/(kg·m^-3)
4~30.3	2.5	3624.5	137.66	0.025	0.092

表2 数值模拟条件

Table 2 Computational conditions of AFF

α/(°)	Ma	p_∞/Pa	T_∞/K	$ω ¯$	ρ/(kg·m^-3)
4~30.3	2.5	3624.5	137.66	0.025	0.092

图6 AFF数值模拟结果与文献[21]试验值对比

Fig.6 Comparison of CFD simulated results with experimental data

表3 网格参数

Table 3 Grid parameters

参数	网格A	网格B	网格C
轴向(弹身)	240	290	352
翼展	26	36	50
周向	92	120	156
总量(百万)	4.25	6.31	10.06

表4 时均气动力系数和量值差

Table 4 Time-averaged aerodynamic coefficient and value difference

网格	法向力系数C_N	侧向力系数C_Z	俯仰力矩系数C_m_z	偏航力矩系数C_m_y
网格A	1.3315	-0.0091	-0.0699	-0.0081
网格B	1.3222	-0.0097	-0.0652	-0.0086
网格C	1.3225	-0.0101	-0.0669	-0.0090
网格B-网格C	-0.03%	-4.47%	-2.57%	-4.76%
网格A-网格B	0.70%	-6.18%	7.21%	-5.81%

图7 一个旋转周期内法向力系数CN和侧向力系数CZ随滚转角φ变化曲线(Ma=2.5,α=10°,δPR=150, ω ¯=0.025)

Fig.7 Variation of aerodynamic coefficients with rolling angles φ (Ma=2.5,α=10°,δPR=150, ω ¯=0.025)

图8 不同转速下喷流干扰法向力系数CN和喷流干扰侧向力系数CZ随无量纲转速 ω ¯变化曲线图(Ma=2.5, α=0°,δPR=150)

Fig.8 Variation of jet interference force coefficient with non-dimensional spin rate ω ¯(Ma=2.5, α=0°, δPR=150)

图9 旋转导弹横向喷流控制力及喷流干扰力示意图(前视)

Fig.9 Schematic diagram of forces and deflection angles(front view)

图10 喷流干扰附加力系数 F ¯ i和控制力系数 F ¯ C,喷流干扰力偏转角度ζ和喷流控制力偏转角度γ随无量纲转速 ω ¯的变化曲线(Ma=2.5,α=0°,δPR=150)

Fig.10 Variation of deflection angles and coefficients of jet interference force and jet control force with non-dimensional spin rate (Ma=2.5,α=0°,δPR=150)

图11 不同部件侧向力系数CZ随无量纲转速 ω ¯的变化曲线(Ma=2.5,α=0°,δPR=150)

Fig.11 Variation of lateral force coefficient with non-dimensional spin rate for different pneumatic components(Ma=2.5,α=0°,δPR=150)

图12 不同截面侧向分布力系数C'Z沿轴向分布曲线(Ma=2.5,α=0°,δPR=150)

Fig.12 Distribution of lateral force coefficient at different cross sections(Ma=2.5,α=0°,δPR=150)

图13 不同横截面内弹体周围涡量云图(Ma=2.5,α=0°,δPR=150)

Fig.13 Vorticity contours at different cross-sections (Ma=2.5,α=0°,δPR=150)

图14 不同转速下x/L=0.59截面内马赫数云图和流线图(Ma=2.5,α=0°,δPR=150,前视)

Fig.14 Mach number contours and streamlines on the section of x/L=0.59 at different spin rates (Ma=2.5,α=0°,δPR=150,view from head)

图15 压力系数分布云图和极限流线示意图(Ma=2.5,α=0°,δPR=150, ω ¯=0.025)

Fig.15 Pressure coefficient contour and limit streamlines (Ma=2.5,α=0°,δPR=150, ω ¯=0.025)

图16 不同转速下弹体表面压力系数分布云图和极限流线图(α=0°,δPR=150)

Fig.16 Pressure coefficient contours and limit streamlines at different spin rates (α=0°,δPR=150)

图17 旋转导弹有无喷流情况下瞬态侧向力系数CZ随滚转角φ变化对比曲线(Ma=2.5, ω ¯=0.025)

Fig.17 Variation of transient lateral force coefficient CZ with rolling angles φ under the condition of spinning missile with or without jet(Ma=2.5, ω ¯=0.025)

图18 旋转导弹有无喷流情况下瞬态偏航力矩系数Cmy随滚转角φ变化对比曲线(Ma=2.5, ω ¯=0.025)

Fig.18 Variation of transient yaw moment coefficient Cmy with rolling angle φ under the condition of spinning missile with or without jet(Ma=2.5, ω ¯=0.025)

图19 旋转导弹有无喷流情况下瞬态法向力系数CN随滚转角φ变化对比曲线(Ma=2.5, ω ¯=0.025)

Fig.19 Variation of transient normal force coefficient CN with rolling angles φ under the condition of spinning missile with or without jet(Ma=2.5, ω ¯=0.025)

图20 不同攻角下侧向力系数CZ随无量纲转速 ω ¯变化曲线(Ma=2.5,δPR=150)

Fig.20 Variation of lateral force coefficient CZ with non-dimensional spin rate ω ¯ at different angles of attack(Ma=2.5,δPR=150)

图21 不同攻角下偏航力矩系数Cmy随无量纲转速 ω ¯变化曲线(Ma=2.5,δPR=150)

Fig.21 Variation of yaw moment coefficient Cmy with non-dimensional spin rate ω ¯ at different angles of attack(Ma=2.5, δPR=150)

图22 不同攻角下全弹侧向力系数CZ和偏航力矩系数Cmy随无量纲转速 ω ¯变化曲线图(Ma=2.5,δPR=150)

Fig.22 Variation of lateral force coefficient CZ and yaw moment coefficient Cmy with non-dimensional spin rate ω ¯ at different angles of attack(Ma=2.5,δPR=150)

图23 不同扇面角度内全弹时均侧向力系数CZ和时均偏航力矩系数Cmy随攻角变化曲线图(Ma=2.5,δPR=150, ω ¯=0.025)

Fig.23 Variation of time-averaged lateral force coefficient and time-averaged yaw moment coefficient with angle of attack under different jet working sectors(Ma=2.5,δPR=150, ω ¯=0.025)

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