CAJ | 학술논문

　　针对舰空导弹超视距拦截低空飞行目标问题，在复合制导的中制导段，建立了导弹拦截目标的相对运动模型，依据制导平台无线电指令修正信息，考虑舰空导弹拦截低空目标时的飞行速度特性，给出了预测遭遇点的实时解算模型，并确定了利于中末制导交班的中制导终端约束条件。基于拦截预测遭遇点，引入伪控制量的概念，应用线性二次型最优控制理论，设计了一种基于拦截预测遭遇点的利于制导交班的最优中制导律，仿真结果验证了预测遭遇点实时解算模型和最优中制导律的正确性与有效性。
　　침대함공도탄초시거란절저공비행목표문제，재복합제도적중제도단，건립료도탄란절목표적상대운동모형，의거제도평태무선전지령수정신식，고필함공도탄란절저공목표시적비행속도특성，급출료예측조우점적실시해산모형，병학정료리우중말제도교반적중제도종단약속조건。기우란절예측조우점，인입위공제량적개념，응용선성이차형최우공제이론，설계료일충기우란절예측조우점적리우제도교반적최우중제도률，방진결과험증료예측조우점실시해산모형화최우중제도률적정학성여유효성。
For the case of ship-to-air missile intercepting the low target, the relative motion model between the missile and the target was firstly established at the midcourse guidance segment. Considering the velocity charac?teristics of the ship-to-air missile, the solution model of the prediction encounter point was presented based on the radio information of the guidance platform,and the dynamic constraint condition at the end of the mid?course guidance was determined. Based on the solution model of the interception point, an optimal midcourse guidance law was designed by applying the concept of the pseudo control variable and the theory of optimal con?trol. The simulation results validated the correctness and effectiveness of the solution model of the interception point and the designed optimal midcourse guidance law.