[1]郝 峰,王鹏飞,张 栋.含落角约束打击运动目标偏置比例制导律设计[J].弹道学报,2018,(04):25.[doi:10.12115/j.issn.1004-499X(2018)04-005]
 HAO Feng,WANG Pengfei,ZHANG Dong.Guidance With Constrained Impact Angle Against MovingTarget Using Bias Proportional Guidance Law[J].Journal Of Ballistics,2018,(04):25.[doi:10.12115/j.issn.1004-499X(2018)04-005]
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含落角约束打击运动目标偏置比例制导律设计()
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《弹道学报》[ISSN:1004-499x/CN:32-1343/TJ]

卷:
期数:
2018年04期
页码:
25
栏目:
出版日期:
2018-12-31

文章信息/Info

Title:
Guidance With Constrained Impact Angle Against MovingTarget Using Bias Proportional Guidance Law
文章编号:
1004-499X(2018)04-0025-07
作者:
郝 峰13王鹏飞12张 栋12
1.西北工业大学 航天学院,陕西 西安 710072; 2.西北工业大学 陕西省空天飞行器设计实验室,陕西 西安 710072; 3.中国兵器工业第二○三研究所,陕西 西安 710065
Author(s):
HAO Feng13WANG Pengfei12ZHANG Dong12
1.School of Astronautics,Northwestern Polytechnical University,Xi’an 710072,China; 2. Aerospace Vehicle Laboratory,Northwestern Polytechnical University,Xi’an 710072,China; 3.No.203 Research Institute of Chinese Weaponry Industry,Xi’an 710065,China
关键词:
导弹 落角约束 运动目标 偏置比例
Keywords:
missile constrained impact angle moving target bias proportional navigation
分类号:
TJ765.3
DOI:
10.12115/j.issn.1004-499X(2018)04-005
文献标志码:
A
摘要:
以打击地面运动目标为研究对象,提出了一种带落角约束的偏置相对比例制导律。利用弹目相对运动关系,将运动目标视为一个虚拟静止目标。进而,实际的制导指令可转化为虚拟制导指令,即相对飞行轨迹角变化速率的设计问题。再依据相对关系,采用瞬时变化及小角度假设推导得到了偏置指令项。通过要求相对飞行轨迹角速率与视线角成比例并包含一个附加偏置项,实际弹道倾角的约束控制可通过间接控制相对飞行轨迹角实现。由于所提制导方案需要剩余时间,推导得到了一种针对运动目标并考虑比例项和偏置项的剩余时间估计方法。仿真结果表明,该制导律可以对运动目标实现全向打击,并具有良好的制导性能。
Abstract:
A bias proportional guidance law with constrained impact angle was proposed,which was used to attack moving target. According to the relative motion of missile and target,the moving target was considered as a stationary virtual target. The actual guidance instruction can be transformed into virtual guidance instruction,namely the design problem of the relative flight path angle rate. Based on the relative relation,the instantaneous variation and small angle hypothesis was used to deduce the bias instruction item. The relative flight-trajectory-angle rate is proportional to the LOS angle and contains an additional bias item,and the constraint control for the actual trajectory angle can be indirectly realized by controlling relative flight-trajectory-angle. Due to the time-to-go required for the guidance scheme,a time-to-go estimation method for moving targets was derived considering proportional and bias terms. The simulation results show that the moving target can be omnidirectionally striked by the guidance law,and the guidance law has good performance.

参考文献/References:

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备注/Memo

备注/Memo:
收稿日期:2018-04-19基金项目:国防基础科研项目(A0420132102)作者简介:郝峰(1978- ),男,研究员,硕士,研究方向为蜂群协同作战。E-mail:jackzhangd@163.com。通讯作者:张栋(1986- ),男,副教授,博士,研究方向为集群智能规划与自主控制。E-mail:zhangdong@nwpu.edu.cn。
更新日期/Last Update: 2018-12-30