CAJ | 학술논문

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。
위사재입비행기공격목표시획득최대훼상효과,기우탄목상대운동방정,병고필락각등다약속조건,용선성이차형（LQR）최우공제적려잡제방정,설계료일충신적최우말제도률,병급출료령계무시연계통적근사표체식。전형탄도화불동약속조건하적방진결과표명：해말제도률유교우적정학성、유효성화탄도성능。
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.