远程火箭末敏弹弹道特性仿真  

Simulation of Ballistic Characteristics of Long-Range-Rocket Target-Sensitivity-Projectile

作　　者：王国平[1] 芮筱亭[1] 张驰[1] 辛松[1] 

机构地区：[1]南京理工大学发射动力学研究所,南京210094

出　　处：《弹道学报》2011年第4期1-4,共4页Journal of Ballistics

基　　金：国家自然科学基金项目(11102089);新世纪优秀人才支持计划基金项目(NCET-10-0075);南京理工大学自主科研专项计划基金项目(2011ZDJH11)

摘　　要：为研究远程火箭末敏弹弹道特性,应用弹道理论和控制理论,建立了远程火箭末敏弹母弹弹道方程;引入多体系统动力学理论,分析了末敏弹系统伞、伞盘、弹等刚体间的力学关系,考虑了系统的连接方式和约束,分析了伞绳弹性,建立了末敏弹在减速运动和稳态扫描段的完整运动模型.编制了远程火箭末敏弹弹道仿真软件,进行了末敏弹全弹道数字仿真,并得到了部分试验验证,分析了末敏弹弹道特性.为远程火箭末敏弹射击精度仿真和减少精度试验用弹量奠定了基础.To study the ballistic characteristics of long-range-rocket target-sensitivity-projectile,the ballistic equations of long-range-rocket target-sensitivity-projectile were established.Considering the jointing mode and binding,the dynamic relations of rigid bodies among parachute,plate and projectile were studied.The elasticity of the parachute rope was analyzed.The integrated motion model in decelerating and stable scanning period was established.The simulation software for long-range-rocket target-sensitivity-projectile was compiled,and the numerical simulation was carried out.The simulation results were validated by some experiment results.The ballistic characteristics of target-sensitivity-projectile were analyzed.The study lays foundation for simulation of firing precision and decreasing rockets consuming in test of long-range-rocket target-sensitivity-projectile.

关 键 词：远程火箭 末敏弹 弹道特性 仿真 

分 类 号：TJ393[兵器科学与技术—火炮、自动武器与弹药工程]