针对旋翼巡飞末敏弹末制导段的命中精度受探测系统误差和姿态扰动共同影响的问题,分析了影响EFP毁伤元散布精度的动态特性,建立基于导引系统探测误差、弹体空间姿态扰动、毁伤元牵连运动偏差和系统时延的动态命中点模型,并引入末制导段的弹目交会轨迹与摆动姿态修正,从而在充分利用弹体姿态信息的情况下,利用实验飞行数据,分析各因素对弹着点的影响。仿真和分析结果表明:在一定随机干扰下,巡飞弹弹体姿态扰动和交会轨迹偏差是影响命中精度的主要因素,得出了满足打击典型装甲目标命中率的姿态角控制要求,为巡飞末敏弹的制导律和轨迹预测控制研究提供了理论依据。

To address the issue of hit accuracy of terminal guidance phase of a rotor loitering terminal sensitive projectile, that is jointly affected by detection system errors and attitude disturbances, this study focuses on the dynamic factors which affect the dispersion of EFP warhead destruction element. In the study, a dynamic impact point model is established based on the seeker system detection error, airframe's spatial attitude disturbances, implicated motion deviation of the warhead destruction element and system latency, meanwhile the trajectory of missile target rendezvous and swinging attitude correction in the final guidance phase are utilized. By taking full advantage of airframe's attitude information and with the help of experimental flight data, the model can be used to analyze the influence of each factor on the point of impact. Simulation and analysis results demonstrate that, under certain random disturbances, the primary factor causing aiming error is the airframe's attitude disturbances and rendezvous trajectory deviation, so that gain the attitude angle control requirements necessary to achieve a desired hit rate on a typical armored target. This study provides a theoretical basis for the research on guidance law and trajectory prediction control of loitering terminal sensitive projectile.