高超声速滑翔飞行器轨迹预测分析
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摘要
针对轨迹预测在目标交接班和基于预测命中点拦截制导中的应用需求,分析了高超声速滑翔飞行器滑翔段轨迹预测的可行性。结合典型高超声速滑翔飞行器的运动轨迹,分析了其运动轨迹特性、机动模式、转弯半径、最大射程以及可达区域,提出了基于不变力预测法的轨迹预测思路。认为高超声速滑翔飞行器在滑翔段,运动轨迹几何特征明显、转弯半径大、保持大升阻比,便于实施中长期轨迹预测,但难以实现全程预测。
Aiming at the application requirements of trajectory prediction in early warning detection system target handover and interception guidance based on predictive hit point,the feasibility of trajectory prediction of hypersonic glide vehicle in gliding section is analyzed. Trajectory characteristics, maneuver mode, turning radius, maximum range and landing footprint area are analyzed based on the trajectory of typical hypersonic glide vehicle,and trajectory prediction method based on invariant force prediction method is proposed. The results show that the trajectory has obvious geometric characteristics,turning radius is greater than 200 km and it maintains high lift ratio in glide section,which contribute to implement the medium and long term trajectory prediction,but it is difficult to realize the whole forecast.
Aiming at the application requirements of trajectory prediction in early warning detection system target handover and interception guidance based on predictive hit point,the feasibility of trajectory prediction of hypersonic glide vehicle in gliding section is analyzed. Trajectory characteristics, maneuver mode, turning radius, maximum range and landing footprint area are analyzed based on the trajectory of typical hypersonic glide vehicle,and trajectory prediction method based on invariant force prediction method is proposed. The results show that the trajectory has obvious geometric characteristics,turning radius is greater than 200 km and it maintains high lift ratio in glide section,which contribute to implement the medium and long term trajectory prediction,but it is difficult to realize the whole forecast.
引文
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[2]PHILLIPS T H. A common aero vehicle(CAV)model,description,employment guide[R]. Schafer Corporation forAFRL and AF-SPC,2003.
[3]韩春耀,熊家军.高超声速飞行器弹道预测方法研究[J].飞航导弹,2016,46(2):24-27.
[4]万雨君,刘鲁华,陈克俊,等.基于预测命中点的机动目标最优制导方法[J].国防科技大学学报,2012,34(5):21-25.
[5]王路,邢清华,毛艺帆.助推-滑翔无动力跳跃飞行器轨迹预测[J].空军工程大学学报(自然科学版),2015,16(1):24-27.
[6]秦雷,李君龙,周荻.临近空间非弹道式目标HTV-2跟踪滤波与预报问题[J].航天控制,2015,33(2):56-61.
[7]翟岱亮,雷虎民,李炯,等.基于自适应IMM的高超声速飞行器轨迹预测[J].航空学报,2016,37(11):3466-3475.
[8]王路,邢清华,毛艺帆.基于升阻比变化规律的再入高超声速滑翔飞行器轨迹预测算法[J].系统工程与电子技术,2015,37(10):2335-2340.
[9]魏喜庆,王社阳,李瑞康.基于自适应IMM算法的高超声速飞行器轨迹预测[J].上海航天,2016,33(2):27-31.
[10]王还乡,李为民,上官强,等.高超声速飞行器巡航段拦截作战需求分析[J].战术导弹技术,2012,33(2):36-40.
[11]秦雷,李君龙,周荻.国外临近空间高速滑翔弹头运动特征研究[J].战术导弹技术,2015,36(1):16-20.
[12]李广华,张洪波,汤国建.高超声速滑翔飞行器典型弹道特性分析[J].宇航学报,2015,36(4):397-403.
[13]张科南,周浩,陈万春.高超声速飞行器多约束多种机动突防模式弹道规划[J].弹道学报,2012,24(3):86-91.
[14]谢愈,刘鲁华,汤国建,等.高超声速滑翔飞行器摆动式机动突防弹道设计[J].航空学报,2011,32(12):2174-2181.
[15]赵江,周锐.基于粒子群优化的再入可达区计算方法研究[J].兵工学报,2015,36(9):1680-1687.
[16]李柯,聂万胜,冯必鸣.助推-滑翔飞行器可达区域影响因素研究[J].现代防御技术,2013,41(3):42-47.
[17]徐浩,邢清华,黄兴.不确定信息下反导拦截效果评估[J].火力与指挥控制,2017,42(1):62-65.
[18]LU P,XUE S B. Rapid generation of accurate entry landingfootprints[C]//AIAA Guidance Navigation and ControlConference. Chicago,2009.
[19]肖翔,杨业,郭涛,等.升力式再入飞行器两种可达区域计算方法的探讨[J].航天控制,2015,33(2):39-43.