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 ren-dezvous trajectory deviation,so that gain the attitude angle control requirements necessary to achieve a desired hit rate on a typ-ical armored target. This study provides a theoretical basis for the research on guidance law and trajectory prediction control of loitering terminal sensitive projectile.
关键词
旋翼巡飞末敏弹/EFP毁伤元/命中点仿真/弹目交会
Key words
rotor loitering terminal sensitive projectile/EFP destruction element/striking point simulation/missile-target rendezvous
维普
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