战术弹道导弹再入段机动弹道仿真研究  

Simulation of Reentry Maneuvering Trajectory of Tactical Ballistic Missile

作　　者：祝庆国[1] 刘刚[1] 鲜勇[1] 

机构地区：[1]第二炮兵工程学院,西安710025

出　　处：《战术导弹技术》2008年第1期79-82,共4页Tactical Missile Technology

摘　　要：战术弹道导弹(TBM)再入机动减速是末制导系统的设计需求,为了分析机动减速对突防的影响,在现有导弹突防系统的基础上,利用目标控制法给定了升力的变化规律,建立了再入机动弹道数学模型,编制了再入段机动弹道仿真软件.仿真结果表明,系统能完成多弹道并行仿真,该机动程序满足突防仿真的要求.The missile is required to decelerate in reentry maneuvering phase in order to meet the requirement for terminal guidance system of tactical ballistic missile. Based on the existing missile penetration system, the influence of deceleration on penetration is analyzed, and the mathematical model of reentry maneuvering trajectory is established by means of aim-control method. Simulation software of reentry maneuvering trajectory is programmed. The simulation result shows that this system can be used to accomplish multi-trajectory parallel computation, and the maneuvering model can be used for penetration simulation.

关 键 词：战术弹道导弹 减速 再入段机动 仿真 

分 类 号：TJ761.3[兵器科学与技术—武器系统与运用工程]