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针对考虑交会角约束的导引律在可用过载不足时将导致大的交会角误差问题,推导一种考虑时变过载约束的制导形式,而该导引律在实现较大机动的同时会带来较大能量损失,进而提出一种考虑导弹机动效率的多约束导引律。首先,应用最优二次型原理推导出一种时变控制项权系数的闭环制导形式;其次,将导弹机动时刻阻力系数引入时变权系数,并通过迭代分别确定可用过载与机动效率约束边界;最后,将时变过载约束表示成剩余时间的函数,代入制导指令,并进行弹道仿真。结果表明:推导的2种导引律均能较好地实现末端弹道成型要求,考虑机动效率的制导指令分配更为合理,并有效降低了拦截末端速度损耗,提高了制导精度与毁伤效果;且考虑机动效率的导引律中时变权系数无须配平求解,在保证精度的同时极大提高了迭代速度。
The guidance law considering the intersection constraint can lead to large crossover angle error when the available overload is not enough, and derive a guidance form considering the time-varying overload constraint. The guidance law brings with it a large maneuver Large energy loss, and then proposed a multi-constraint guided law considering missile maneuver efficiency. Firstly, a closed-loop guidance form with time-varying control weight is deduced by using the optimal quadratic principle. Secondly, the resistance coefficient of missile maneuver moment is introduced into the time-varying weight coefficient, and the available overload and maneuver efficiency bounding boundaries Finally, the time-varying overload constraints are expressed as a function of the remaining time, substituted into the guidance instructions and ballistic simulation. The results show that both of the two guidance laws can achieve the requirements of the terminal ballistic forming better. The distribution of guidance commands considering the maneuver efficiency is more reasonable, and the speed loss at the end of interception is effectively reduced, and the guidance accuracy and damage effect are improved. The time-varying weight coefficients in the guidance law considering the maneuver efficiency do not need to be solved in a balanced way, which greatly improves the iteration speed while ensuring the accuracy.