助推滑翔飞行器远程拦截发射方位角设计
发布时间：2018-12-12 12:58
【摘要】：针对高超声速助推滑翔飞行器远程拦截问题,结合球面三角形,提出在临近空间远程拦截目标飞行器时拦截发射诸元的求解思路。选取经典飞行器控制程序角模型,以时间与射程为控制目标合理设计了拦截器助推段弹道,并提出用平衡滑翔假设解析方程快速预报射程从而求解飞行器的拦截发射方位角的方法。仿真结果表明,所提出的拦截发射诸元设计方法可以成功将拦截器送到目标飞行器周围。
[Abstract]:Aiming at the problem of long-range interception of hypersonic gliding vehicle, a solution of intercepting launching data is proposed in the near space remote intercepting target by combining spherical triangle. The angle model of the classical aircraft control program is selected and the trajectory of the interceptor booster section is reasonably designed with time and range as the control target. An analytical equation of equilibrium gliding hypothesis is proposed to predict the range quickly and to solve the intercepting and launching azimuth angle of the aircraft. The simulation results show that the proposed design method can successfully deliver the interceptor around the target vehicle.
【作者单位】： 国防科学技术大学航天科学与工程学院;北京宇航系统工程研究所;
【基金】：国家重点基础研究发展计划(973计划)(批准号:2013CB733100)资助
【分类号】：V249.1
本文编号：2374597
[Abstract]:Aiming at the problem of long-range interception of hypersonic gliding vehicle, a solution of intercepting launching data is proposed in the near space remote intercepting target by combining spherical triangle. The angle model of the classical aircraft control program is selected and the trajectory of the interceptor booster section is reasonably designed with time and range as the control target. An analytical equation of equilibrium gliding hypothesis is proposed to predict the range quickly and to solve the intercepting and launching azimuth angle of the aircraft. The simulation results show that the proposed design method can successfully deliver the interceptor around the target vehicle.
【作者单位】： 国防科学技术大学航天科学与工程学院;北京宇航系统工程研究所;
【基金】：国家重点基础研究发展计划(973计划)(批准号:2013CB733100)资助
【分类号】：V249.1
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