多约束条件下制导系数可变的最优制导律研究
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摘要
针对大落角攻击要求,分析了终端落角约束制导律的解析解和脱靶量特性,提出了满足命中位置、落角、需用过载及目标跟踪要求的落角约束值装定设计方法;给出了终端落角约束制导律的推导过程,基于解析解分析了制导律的指令特性及飞行器速度、位置变化规律,并进行了仿真验证;利用伴随法分析了无量纲位置、角度脱靶量特性,确定了制导律收敛时间为至少15倍制导动力学时间;分析了制导律角度权系数变化对终端落角的影响,给出了装定落角约束值与精确落角约束之间的转换设计方法,并通过仿真验证了装定设计方法的正确性。
The guidance characteristics for terminal large impact angle attack have been researched.And a method is presented for impact angle design to satisfy terminal constraints. The derivation process of terminal impact angle constraint guidance law is given. Based on the close-form solution of terminal guidance law,the characteristics of guidance command,velocity and location are analyzed and verified.The non-dimensional miss distance and the impact angle error are analyzed by using the adjoint mathematical method,and the covergence time of the guidance law is determined to be at least 15 times of the guidance dynamic time. The effect of guidance weighted coefficients on impact angle is analyzed,and the conversion design method between constraint and actual impact angle value is proposed. The simulation results show that the conversion design method is valid.
The guidance characteristics for terminal large impact angle attack have been researched.And a method is presented for impact angle design to satisfy terminal constraints. The derivation process of terminal impact angle constraint guidance law is given. Based on the close-form solution of terminal guidance law,the characteristics of guidance command,velocity and location are analyzed and verified.The non-dimensional miss distance and the impact angle error are analyzed by using the adjoint mathematical method,and the covergence time of the guidance law is determined to be at least 15 times of the guidance dynamic time. The effect of guidance weighted coefficients on impact angle is analyzed,and the conversion design method between constraint and actual impact angle value is proposed. The simulation results show that the conversion design method is valid.
引文
[1]孙未蒙,骆振,郑志强.一种多约束条件下高超声速导弹对地攻击的三维最优变结构制导律[J].国防科技大学学报,2007,29(3):126-130.Sun Weimeng,Luo Zhen,Zheng Zhiqiang. Three-Dimensional Optimal Variable Structure Guidance Law with Multiple Constraints in Ground Strike of Hypersonic Air-toSurface Missiles[J]. Journal of National University of Defense Technology,2007,29(3):126-130.(in Chinese)
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[3]Gu Wenjin,Zhao Hongchao,Zhang Ruchuan. A ThreeDimensional Proportional Guidance Law Based on RBF Neural Network[C]∥Proceedings of the 7th World Congress on Intelligent Control and Automation,2008:6978-6982.
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[15]王辉,吕瑛杰,林德福,等.扩展弹道成型制导系统脱靶量特性分析[J].红外与激光工程,2013,42(5):1322-1329.Wang Hui,LüYingjie,Lin Defu,et al. Miss Distance Analysis of the Extended Trajectory Shaping Guided Systems[J]. Infrared and Laser Engineering,2013,42(5):1322-1329.(in Chinese)
[2]蔡洪,胡正东,曹渊.具有终端角度约束的导引律综述[J].宇航学报,2010,31(2):315-323.Cai Hong,Hu Zhengdong,Cao Yuan. A Survey of Guidance Law with Terminal Impact Angle Constrains[J].Journal of Astronautics,2010,31(2):315-323.(in Chinese)
[3]Gu Wenjin,Zhao Hongchao,Zhang Ruchuan. A ThreeDimensional Proportional Guidance Law Based on RBF Neural Network[C]∥Proceedings of the 7th World Congress on Intelligent Control and Automation,2008:6978-6982.
[4]Fleman E L. Tactical Missile Design[M]. Reston:AIAA,2001:124-135.
[5]Zarchan P. Tactical and Strategic Missile Guidance[M].4th ed. Reston:AIAA,2002.
[6]Glizer V Y. Optimal Planar Interception with Fixed End Conditions:Closed-Form Solution[J]. Journal of Optimization Theory and Applications,1996,88(3):503-539.
[7]Ryoo C K,Cho H,Tahk M J. Time-to-Go Weighted Optimal Guidance with Impact Angle Constraints[J]. IEEE Transactions on Control Systems Technology,2006,14(3):483-492.
[8]Ryoo C K,Cho H,Tahk M J. Optimal Guidance Laws with Terminal Impact Angle Constraint[J]. Journal of Guidance,Control,and Dynamics,2005,28(4):724-732.
[9]Song T L,Shin S J,Cho H. Impact Angle Control for Planar Engagements[J]. IEEE Transactions on Aerospace and Electronic Systems,1999,35(4):1439-1444.
[10]程国采.战术导弹导引方法[M].北京:国防工业出版社,1996.Cheng Guocai. Guidance Method for Tactical Missile[M]. Beijing:National Defense Industry Press,1996.(in Chinese)
[11]李强,卢宝刚,王晓辉,等.一种导弹终端侵彻多约束最优制导方法[J].兵工学报,2016,37(6):1131-1137.Li Qiang,Lu Baogang,Wang Xiaohui,et al. A Terminal Multi-Constraint Optimal Guidance Law for Missile[J].Acta Armamentarii,2016,37(6):1131-1137.(in Chinese)
[12]李强.高超声速滑翔飞行器再入制导控制技术研究[D].北京:北京理工大学,2015.Li Qiang. Study on Reentry Guidance and Control Method for Hypersonic Glide Vehicle[D]. Beijing:Beijing Institute of Technology,2015.(in Chinese)
[13]吴受章.应用最优控制[M].西安:西安交通大学出版社,1987.Wu Shouzhang. Application of Optimal Control[M]. Xi’an:Xi’an Jiaotong University Press,1987.(in Chinese)
[14]刘大卫.侵彻制导炸弹终端多约束最优制导律与弹道研究[D].北京:北京理工大学,2011.Liu Dawei. Research on Terminal Multi-Constraint Optimal Guidance Law and Trajectory for Penetrating Guided Bombs[D]. Beijing:Beijing Institute of Technology,2011.(in Chinese)
[15]王辉,吕瑛杰,林德福,等.扩展弹道成型制导系统脱靶量特性分析[J].红外与激光工程,2013,42(5):1322-1329.Wang Hui,LüYingjie,Lin Defu,et al. Miss Distance Analysis of the Extended Trajectory Shaping Guided Systems[J]. Infrared and Laser Engineering,2013,42(5):1322-1329.(in Chinese)
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