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.
出处
《西南交通大学学报》
EI
CSCD
北大核心
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)
关键词
导弹
制导律
末端落角
飞行时间
missile
guidance law
terminal angle
time-to-go
