初始速度对导弹级间冷分离影响研究  

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

作　　者：曹飞 薛亦菲 牛春峰 郝宏旭 乔治 丁宁 CAO Fei;XUE Yifei;NIU Chunfeng;HAO Hongxu;QIAO Zhi;DING Ning(Navigation and Control Technology Research Institute of Norinco Group,Beijing 100089,China;Chinese Aeronautical Establishment,Beijing 100029,China)

机构地区：[1]中国兵器工业导航与控制技术研究所,北京100089 [2]中国航空研究院,北京100029

出　　处：《现代防御技术》2025年第2期55-65,共11页Modern Defence Technology

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。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.

关 键 词：级间分离 跨声速 非定常 数值模拟 轨迹预测 姿态 

分 类 号：TJ760[兵器科学与技术—武器系统与运用工程]