针对空射导弹拦截助推/上升段战术弹道导弹制导问题进行制导系统建模和数字仿真。选取4种基本制导律进行中、末制导研究,包括:比例制导律(PNG)、基于瞬时脫靶量的一种最优制导律(OGL)、视线角加速度制导律(AAG)、目标加速度补偿比例制导律(APN)。据此提出2种中、末制导组合方案,通过重力过补偿优化中制导得到另2种方案。4种方案仿真对比得到“OGL+APN(重力过补偿)”方案。该方案攻击区较大,发射条件约束较宽松,具有较好的制导性能。

For antimissile interception of the boosting/ascending tactical missile, guidance system model is built, and numeric simulation is carried out. First, 4 guidance laws, including proportion navigation guidance(PNG)、instantaneous miss-distance based forecasting optimal guidance law( OGL)、line of sight acceleration guidance(AAG) and target acceleration compensated proportion navigation(APN), are selected and applied to mid-course guidance to study the performance. According to the guidance performance analysis, 2 schemes are presented, and another two schemes are presented via exorbitant gravitation compensation (EGC). Finally, ‘OGL + APN( EGC)'is demonstrated to be the best one, which behaves better in attack zone, launching restrictions and guidance performance.