带末端落角约束的制导律

吴鹏; 杨明

带末端落角约束的制导律

吴鹏,
杨明^,

基金项目:

国家自然科学基金重点项目(60434010)

黑龙江杰出青年基金资助项目(JC200606)

详细信息

作者简介:
吴鹏(1980- ),男,博士研究生,研究方向为飞行器控制与制导、鲁棒控制,电话:13945035224,E-mail:myang@hit.edu.cn

通讯作者:
杨明(1963- ),男,教授,博士生导师,研究方向为现代飞行器控制、制导与仿真,E-mail: wppengjacob@163.com

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- 文章访问数: 1054
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- PDF下载量: 366
- 被引次数: 0
出版历程
- 收稿日期: 2007-07-24
- 刊出日期: 2008-06-25

Missile Guidance Law with Terminal Impact Angle Constraint

WU Peng,
YANG Ming^,

摘要

摘要: 为保证导弹攻击角度,分析了末端落角和期望视线角的关系.基于Lyapunov稳定性定理,通过对导弹飞行时间的估计,给出了具有末端落角约束的制导律.该制导律形式简单,且克服了被动寻的导弹不能测距的缺点.仿真结果证明,对于某些变加速机动的目标,该制导律能使导弹以尾追攻击或垂直攻击的形式命中目标.
- 导弹 /
- 制导律 /
- 末端落角 /
- 飞行时间
Abstract: The correlation between terminal impact angle and expected angle of sight was analyzed to ensure impact angle of a missile.A guidance law with a terminal impact angle constraint was proposed based on Lyapunov stability theorem and estimation about time-to-go.The proposed guidance law is simple and overcomes the limitation that a passive homing missile does not has a distance-measurement function.Numerical simulation results demonstrate that the proposed guidance law can guide the missile to hit some mobile targets with high maneuverability by stem chase impact or perpendicular impact.
- missile /
- guidance law /
- terminal angle /
- time-to-go

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参考文献(1)

KIM M,GRIDER K V.Terminal guidance for impact attitude angle constrained flight trajectories[J].IEEE Trans.on Aerospace and Electronic Systems,1973,9(6):852-859.[2] KIM B S,LEE J G,HAN H S.Biased PNG law for impact with angular constraint[J].IEEE Trans.on Aerospace and Electronic Systems,1998,34(1),277-288.[3] KIM B S,LEE J.Homing guidance with terminal angular against non-maneuvering and maneuvering target[C] ∥AIAA Guidance,Navigation and Control Conference,New Orleans:[s.n.] ,1997:189-199.[4] 曹邦武,姜长生,关世义,等.电视指令制导空地导弹垂直命中目标的末制导系统研究[J].宇航学报,2004,25(4):393-397.CAO Bangwu,JIANG Changsheng,GUAN Shiyi,et al.Research on the vertical intercept terminal guidance system of TV-command-guidance air-to-ground missile[J].Journal of Astronautics,2004,25(4):393-397.[5] RYOO C K,CHO H,TAHK M J.Time-to-go weighted optimal guidance with impact angle constraint[J].IEEE Trans.Control Systems Technology,2006,14(3):483-492.[6] TAHK M J,RYOO C K,CHO H.Recursive time-to-go estimation for homing guidance missiles[J].IEEE Trans.Aerospace and Electronic Systems,2002,38(1):13-24.[7] 钱杏芳,林瑞雄,赵亚男.导弹飞行力学[M].北京:北京理工大学出版社,2000.[8] JEON I S,LEE J I,TAHK M J.Guidance law to control impact time and angle[J].IEEE Trans.Aerospace and Electronic Systems,2007,43(1):301-310.[9] JEON I S,LEE J I,TAHK M J.Impact-time-control guidance law for anti-ship missiles[J].IEEE Trans on Control Systems Technology,2006,14(2):260-266,

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文章访问数: 1054
HTML全文浏览量: 92
PDF下载量: 366
被引次数: 0

带末端落角约束的制导律

作者简介: 吴鹏(1980- ),男,博士研究生,研究方向为飞行器控制与制导、鲁棒控制,电话:13945035224,E-mail:myang@hit.edu.cn

通讯作者: 杨明(1963- ),男,教授,博士生导师,研究方向为现代飞行器控制、制导与仿真,E-mail: wppengjacob@163.com

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出版历程

Missile Guidance Law with Terminal Impact Angle Constraint

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出版历程

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作者简介:
吴鹏(1980- ),男,博士研究生,研究方向为飞行器控制与制导、鲁棒控制,电话:13945035224,E-mail:myang@hit.edu.cn

通讯作者:
杨明(1963- ),男,教授,博士生导师,研究方向为现代飞行器控制、制导与仿真,E-mail: wppengjacob@163.com