天基光学平台下弹头与气球诱饵中段观测运动差异分析

为了解决弹道导弹在中段释放气球诱饵伴飞,以干扰天基光学防御系统对导弹目标进行精确跟踪识别的问题,基于弹头和气球诱饵质阻比的差异,利用美国NRLMSISE-00(Naval Research Laboratory Mass Spectrometer and Incoherent Scatter radar Exosphere,海军研究实验室质谱仪和非相干散射雷达大气经验性模型)对气球诱饵进行相应动力学分析,得出气球诱饵在弹道中段的大气阻力模型.然后给出了J2摄动下,气球诱饵经过阻力修正后较精确的中段运动模型,并将结论引入到天基光学平台中,进行观测仿真实验.结果表明,在200 km以上的高空,大气阻力对于弹头和气球诱饵的影响微弱,可忽略不计,在观测像平面中表现为一块难以区分的亮斑;而在100～200 km高度范围内,气球诱饵受大气阻力影响剧烈,在观测像平面内的运动与弹头存在较大差别,具有较强的可区分性.

Analysis of Movement Difference Between Warhead and Balloon Decoy in Midcourse under Space-Based Optical Observation Platform

Throwing balloon decoy is a widely used and efficient way to affect the performance of tracking and recog-nizing ballistic missile targets for a space-based optical defense system. To solve this problem,a more precise mo-tion model conditioned to J 2 perturbation with rarefied atmosphere drag in midcourse was given after analyzing the dynamic characteristics based on the low mass-to-drag ratio of balloon decoy using the Unite States Naval Research Laboratory Mass Spectrometer and Incoherent Scatter radar Exosphere (NRLMSISE-00)atmosphere model. Simu-lation under a space-based optics observation system shows that the influence of rarefied atmosphere drag was small enough to ignore above 200 km high space,while the trajectory of warhead differed greatly with the trajectory of balloon decoy in image plane within 100～200 km high space,which can provide strong identifiability.