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基于碰撞航线的动能拦截器滑模制导律设计

杨旭 张皎 刘源翔

杨旭, 张皎, 刘源翔等 . 基于碰撞航线的动能拦截器滑模制导律设计[J]. 北京航空航天大学学报, 2015, 41(11): 2095-2102. doi: 10.13700/j.bh.1001-5965.2014.0728
引用本文: 杨旭, 张皎, 刘源翔等 . 基于碰撞航线的动能拦截器滑模制导律设计[J]. 北京航空航天大学学报, 2015, 41(11): 2095-2102. doi: 10.13700/j.bh.1001-5965.2014.0728
YANG Xu, ZHANG Jiao, LIU Yuanxianget al. Sliding mode guidance law for KKV based on collision course[J]. Journal of Beijing University of Aeronautics and Astronautics, 2015, 41(11): 2095-2102. doi: 10.13700/j.bh.1001-5965.2014.0728(in Chinese)
Citation: YANG Xu, ZHANG Jiao, LIU Yuanxianget al. Sliding mode guidance law for KKV based on collision course[J]. Journal of Beijing University of Aeronautics and Astronautics, 2015, 41(11): 2095-2102. doi: 10.13700/j.bh.1001-5965.2014.0728(in Chinese)

基于碰撞航线的动能拦截器滑模制导律设计

doi: 10.13700/j.bh.1001-5965.2014.0728
基金项目: 国家"863"计划(2011AA7043024);"985工程"三期重点建设项目
详细信息
    通讯作者:

    杨旭(1986-),男,黑龙江安达人,博士研究生,yangxu@bit.edu.cn,主要研究方向为飞行器动力学与控制.

  • 中图分类号: V488.13

Sliding mode guidance law for KKV based on collision course

  • 摘要: 针对大气层外用于拦截目标动能拦截器(KKV)的制导律设计问题,采用非线性干扰观测器(NDO)及滑模变结构控制思想设计了一种基于碰撞航线的制导律.通过控制导弹攻角,使导弹的速度方向始终指向预期碰撞点,并利用NDO对目标加速度进行有效估计及动态补偿,降低了导弹所需的过载,并提高了命中时的速度.同时,分别从拦截轨迹、可拦截目标区域及拦截目标速度范围对机动目标进行拦截仿真,并与以零化视线角速率为目标设计的有限时间收敛制导律对比,仿真结果表明对于动能拦截器采用基于碰撞航线的滑模制导律具有更好的制导性能.

     

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出版历程
  • 收稿日期:  2014-11-20
  • 修回日期:  2015-01-06
  • 刊出日期:  2015-11-20

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