滑翔弹头末段俯冲导引律设计与仿真  

Design and Simulation of Diving Guidance Law for Terminal Phase Trajectory of Glide-warhead

作　　者：刘开封 陈颖[2] 梁立威[2] 孟海东[2] 

机构地区：[1]第二炮兵工程大学,西安710025 [2]第二炮兵装备研究院,北京100085

出　　处：《弹箭与制导学报》2014年第3期25-28,共4页Journal of Projectiles,Rockets,Missiles and Guidance

摘　　要：滑翔弹头长期飞行在气动环境较为复杂的临近空间,再入精度难以保证。为实现滑翔弹头精确打击并考虑攻击角度的战术使用需求,文中在目标坐标系中建立了滑翔弹头质心运动方程,推导了基于扩展比例导引的带落速方向控制的末段俯冲导引规律。仿真结果表明,在合理的俯冲起点参数要求范围内,采用文中制导规律,能够实现对落点和攻击角度的精确控制。Glide-warhead long flies in near space where aerodynamic environment is complicated, so the entry precision can not be guaran- teed. In order to realize accurate attack and considering the demand for attack angle control, the motion equation of glide warhead at termi- nal phase was built in target coordinates, the dive guidance law based on expanded proportion guidance with terminal-velocity direction con- trol was derived. Simulation results show that when parameters at the dive beginning point are reasonable, method in this paper performs ef- ficiently to control the precision of attack angle.

关 键 词：滑翔弹头 俯冲 扩展比例导引 落速方向控制 

分 类 号：TJ765[兵器科学与技术—武器系统与运用工程]