导弹助推器级间分离非定常数值模拟研究  

Numerical Simulation and Study of Unsteady Separation of Missile Booster

作　　者：伍彬 王韦钰 钟永建 王磊 朱梦杰 WU Bin;WANG Weiyu;ZHONG Yongjian;WANG Lei;ZHU Mengjie(Shanghai Electro-mechanical Engineering Institute,Shanghai 201109,China)

机构地区：[1]上海机电工程研究所

出　　处：《空天防御》2019年第4期7-12,共6页Air & Space Defense

摘　　要：采用数值方法对不同分离攻角状态下的非定常分离过程进行了研究,给出了分离轨迹和姿态等随时间变化的规律,并结合非定常气动力和流场结构对分离结果进行了分析。研究结果表明,为了实现快速安全分离,需要适当的分离攻角。此外,助推器负加速度绝对值大于主级负加速度绝对值是成功分离的基础,实际工程应用中可以采用增大助推器过渡段倾斜角或者施加初始反作用力的方法来提高其可靠性。研究结果对前后级串联的防空导弹助推器分离状态的选取和分离安全性评估具有指导价值。Unsteady booster separation process at different separation angles of attack is studied by using numerical method in this paper.Separation trajectories and attitudes of booster versus time are given,and separation analyses are conducted based on unsteady aerodynamic forces and flow structures.The study shows that a proper large angle of attack must be chosen to achieve fast and safe separation.Besides,the absolute value of negative acceleration of booster is larger than that of upper stage,which is the foundation of successful separation.In actual engineering application,the reliability of separation can be improved by increasing a large transition slope or applying an initial reverse force.The results in this paper are valuable to choose separation condition and evaluate separation safety of the tandem booster-upper stage of surface-to-air missile.

关 键 词：防空导弹 助推器级间分离 数值模拟 非定常 

分 类 号：V412.4[航空宇航科学与技术—航空宇航推进理论与工程]