Investigation on the Impact of Initial Velocity on Cold Separation Between the Missile and the Booster

doi:10.3969/j.issn.1009-086x.2025.02.006

Abstract

Abstract:

We investigate the impact of the initial separation velocity on the trajectory and aerodynamics of the missile and booster during cold separation. A numerical simulation method that couples unsteady computational fluid dynamics with a six degree-of-freedom solver is adopted. The paper analysis the separation processes between the missile and booster under various initial separation velocities. Simulation results reveal two distinct flow structures during the separation process： one characterized by recirculation and the other characterized by wake interaction. The paper analyzes the relationship between these typical flow structures and aerodynamics. A fitting curve tailored to the separation problem is established to predict the trajectory. In addition， the paper analyzes the pitching characteristics of the missile. The analysis in this paper provides a theoretical basis for the design of separation strategies. The fitting curve established in this paper provides a rapid prediction method for trajectory design.

Key words: stage separation, transonic, unsteady, simulation, trajectory prediction, attitude

摘要：

针对导弹与助推级间冷分离中初始分离速度对分离轨迹及气动力特性的影响问题，采用基于耦合六自由度运动方程的非定常流动数值模拟方法，模拟不同初始分离速度下导弹与助推的分离过程。模拟结果显示，分离过程可以分解为级间填充阶段和尾流冲击阶段，分离过程的气动力变化与流场特性相互耦合，提出初始分离速度影响导弹运动轨迹的拟合公式，得到分离后俯仰姿态受初始分离速度影响的运动学规律。初始分离速度对分离气动特性的影响研究能够为分离策略设计提供理论基础，为分离轨迹预测提供数学手段。

关键词: 级间分离, 跨声速, 非定常, 数值模拟, 轨迹预测, 姿态

CLC Number:

TJ760

Fei CAO, Yifei XUE, Chunfeng NIU, Hongxu HAO, Zhi QIAO, Ning DING. Investigation on the Impact of Initial Velocity on Cold Separation Between the Missile and the Booster[J]. Modern Defense Technology, 2025, 53(2): 55-65.

曹飞, 薛亦菲, 牛春峰, 郝宏旭, 乔治, 丁宁. 初始速度对导弹级间冷分离影响研究[J]. 现代防御技术, 2025, 53(2): 55-65.

Figures/Tables 23

Fig. 1 Schematic of wing/pylon/finned store model

Fig. 2 Comparison of simulation and experimental Euler angles

Fig. 3 Comparison of simulation and experimental position

Fig. 4 Schematic of the missile and booster

Table 1 Characteristic of missile and booster

参数名称

导弹

助推

质量/kg

质心/m

长度/m

直径/m

x向转动惯量/（kg·m²）

y向转动惯量/（kg·m²）

z向转动惯量/（kg·m²）

200

1.28

2.40

0.32

160

210

2.65

4.63

0.32

350

Fig. 5 Schematic of the overset grid

Fig. 6 Zoom-in grid at the leading edge of the missile

Fig.7 Trajectories of the missile

Fig. 8 Mach contour at the start of the separation

Fig. 9 Pressure contour at the start of the separation

Fig. 10 Flow of v0=10 m/s， at t=0 s

Fig. 11 Flow of v0=10 m/s， at t=0.02 s

Fig. 12 Flow of v0=10 m/s， at t=0.05 s

Fig. 13 Flow of v0=10 m/s， at t=0.1 s

Fig. 14 Trajectories for various initial velocities

Fig. 15 Velocity evolutions in x direction under various initial velocity

Fig. 16 Evolutions of total force on x direction

Fig. 17 Evolutions of the viscous drag and inviscid drag

Fig. 18 Trajectories of the booster

Fig. 19 Attitudes of missile and booster at t=0.6 s

Fig. 20 Evolution of the missile’s pitch angle

Fig. 21 Evolution of the missile’s pitch angular velocity

Fig. 22 Evolution of the missile’s pitching moment

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