带末端落角约束的制导律  

Missile Guidance Law with Terminal Impact Angle Constraint

作　　者：吴鹏[1] 杨明[1] 

机构地区：[1]哈尔滨工业大学控制与仿真中心,黑龙江哈尔滨150001

出　　处：《西南交通大学学报》2008年第3期309-313,共5页Journal of Southwest Jiaotong University

基　　金：国家自然科学基金重点项目(60434010);黑龙江杰出青年基金资助项目(JC200606)

摘　　要：为保证导弹攻击角度,分析了末端落角和期望视线角的关系.基于Lyapunov稳定性定理,通过对导弹飞行时间的估计,给出了具有末端落角约束的制导律.该制导律形式简单,且克服了被动寻的导弹不能测距的缺点.仿真结果证明,对于某些变加速机动的目标,该制导律能使导弹以尾追攻击或垂直攻击的形式命中目标.The correlation between terminal impact angle and expected angle of sight was analyzed to ensure impact angle of a missile. A guidance law with a terminal impact angle constraint was proposed based on Lyapunov stability theorem and estimation about time-to-go. The proposed guidance law is simple and overcomes the limitation that a passive homing missile does not has a distance-measurement function. Numerical simulation results demonstrate that the proposed guidance law can guide the missile to hit some mobile targets with high maneuverability by stem chase impact or perpendicular impact.

关 键 词：导弹 制导律 末端落角 飞行时间 

分 类 号：TP183[自动化与计算机技术—控制理论与控制工程]