适用于攻击机动目标的制导律实现与仿真

Realization and Simulation of Guidance Laws Applicable to Maneuvering Target Attacking

为了使导弹在较短的末制导时间内获得很小的脱靶量,同时对机动过载的需求满足导弹实际过载能力,研究了适用于攻击蛇形机动目标的最优制导律和蛇形机动补偿制导律,并分析了具体实现方法,设计目标状态估计器,建立导引回路数学模型。仿真验证了测量越精确,可知信息越多,估计性能就越好;最后研究了导弹过载限制、测量误差、目标状态估计精度及制导律的选择等因素对制导精度的影响。

To make the missile obtain minimum miss distance at the limited time of terminal guidance while keeping the maneuvering acceleration within the missile＇s realistic acceleration capability, we studied the optimum guidance law suitable for attacking sinusoidal maneuvering targets and compensation guidance law for sinusoidal maneuvering. The realization method was analyzed, a Kalman filter was designed for estimating the target state information, and the homing guidance loop model was established. Simulation results indicated that the more accurate the measurement and the more information known, the better the estimate performance. The influence of the following factors on guidance precision was also studied： missile overload limit, measurement error, target state estimation precision and selection of guidance law.