Missile Guidance Law with Terminal Impact Angle Constraint
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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.Abstract: 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.
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Key words:
- missile /
- guidance law /
- terminal angle /
- time-to-go
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