考虑弹体动态特性的机动效率约束导引律

针对考虑交会角和过载约束导引律在大机动时能量损失大的问题,提出一种考虑导弹机动效率的多约束制导律。应用最优二次型原理推导出考虑一阶弹体延迟的时变导引系数闭环次优制导形式,将导弹机动时刻阻力系数引入时变权系数,并通过迭代确定机动效率约束边界。将时变约束表示成剩余时间与弹体延迟时间的函数,代入制导指令,进行弹道仿真。结果表明,对于常值与机动目标,文中制导律与过载约束导引律同只考虑交会角约束的导引律相比,对目标均能实现末端弹道成型要求,而考虑机动效率的制导指令分配更为合理,在避免指令加速度饱和的同时有效降低了拦截末端速度损耗,提高制导精度与毁伤效果。且该制导律中时变权系数无须配平求解,在保证精度的同时极大地提高了迭代速度。

Guidance Law with Maneuvering Efficiency Constraint Considering Missile Dynamic Characteristics

Due to the guidance law with terminal intercept angle and payload constraints causing big engorge loss, a guidance law considering maneuvering efficiency constraint has been elicited. Elicit a closed-loop sub-optimum guidance law with time-varying control weight coefficient considering first-order missile dynamic characteristics according to optimal quadratic theory; introduce drag coefficient when maneuvering into time-varying control weight coefficient, and obtain the constraint boundary of maneuvering efficiency through iterations; change time-varying weight coefficient into function of time-to-go and delay time, and emulate the trajectories with guidance law considering maneuvering efficiency. The emulation results indicate that, for constant velocity and maneuvering target, compared with the guidance law with intercept angle, the new guidance law and the guidance law with payload constraint can meet the requirement of trajectory shaping, and the acceleration command of guidance law with constraint considering maneuvering is more reasonable. And the new guidance law would reduce the velocity loss effectively and avoid the payload saturation at the same time, and enhance the guidance accuracy and damage effect. Moreover, balance solutions of time-varying weight coefficient is not necessary with this method, so iteration speed will be highly improved when accuracy is guaranteed.