Numerical Investigation of the Jet Interference Characteristics of a Lateral-jet-controlled Spinning Missile

doi:10.12382/bgxb.2022.0379

Abstract

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

CLC Number:

V211.3

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.

Figures/Tables 27

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

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

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

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

Fig.4 CCF model and computational grid

Fig.5 Comparison of Cp computational results with experiments data

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

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

Fig.6 Comparison of CFD simulated results with experimental data

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

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%

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

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

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

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)

Fig.11 Variation of lateral force coefficient with non-dimensional spin rate for different pneumatic components(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)

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

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)

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

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

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)

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)

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)

Fig.20 Variation of lateral force coefficient CZ with non-dimensional spin rate ω ¯ at different angles of attack(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)

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)

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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