摘要
研究反导弹武器的制导优化问题,针对弹道导弹助推段飞行加速度大、变化快以及拦截反应时间短的特点,掌握拦截时机,研究最优拦截制导律。分析了战术弹道导弹助推段飞行特点,指出了助推段拦截的优势与难点;建立了弹道导弹目标与拦截弹的相对运动方程;以能量最省为性能指标,设计了空基反导导弹在助推段拦截弹道导弹目标的最优制导律;给出了剩余飞行时间的计算方法。仿真结果表明所设计的制导律满足设计指标,达到了直接碰撞杀伤目标的目的。结果验证了所设计制导律的正确性和有效性,可为设计提供依据。
Aiming at the characteristics of high acceleration,rapid flight velocity and short reaction time for interception ballistic missile during the boost phase,optimal guidance law of interception is studied.Flight characteristic of tactical ballistic missile is analyzed during the boost phase.Advantages and challenges of interception are pointed out during the boost phase.Relative motion equation of interception missile and ballistic missile is founded,and performance index is designed based on energy minimum.Optimal guidance law of defense missile launched by airplane is designed for interception ballistic missile during the boost phase.Calculating method of time-to-go is put forwarded.Simulation shows that guidance law designed satisfies the required index,and reaches the aim to direct hit the target.The correctness and effectiveness of the optimal guidance law are proved.
出处
《计算机仿真》
CSCD
北大核心
2011年第7期87-89,99,共4页
Computer Simulation
关键词
弹道导弹
助推段拦截
最优制导律
剩余时间
Ballistic missile
Interception during the boost phase
Optimal guidance law
Time-to-go
