摘要
为使再入飞行器攻击目标时获得最大毁伤效果,基于弹目相对运动方程,并考虑落角等多约束条件,用线性二次型(LQR)最优控制的黎卡提方程,设计了一种新的最优末制导律,并给出了零阶无时延系统的近似表达式。典型弹道和不同约束条件下的仿真结果表明:该末制导律有较优的精确性、有效性和弹道性能。
To achieve the maximum damage effect when a reentry vehicle attacked the target,a new optimal terminal guidance law according to the missile-target relative equation was designed in this paper,in which the falling angle and other multi-restraint conditions were considered,and the LQR optimal control Riccati equation was utilized.The approximate expression of the zero-order non-time lag system was given out.The simulation results of the typical trajectory with the different constraint conditions showed that the law proposed had the advantages of accuracy,effectiveness and better trajectory performance.
出处
《上海航天》
2012年第2期1-6,17,共7页
Aerospace Shanghai
关键词
再入飞行器
零阶无时延
最优末制导律
约束条件
有效性
Reentry vehicle
Zero-order non-time lag system
Optimal terminal guidance law
Restraint condition
Effectiveness
