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《Journal of Projectiles,Rockets,Missiles and Guidance》 2010-04
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Research on the Optimal Terminal Guidance Law for Gliding Guidance Bombs

WANG Ying,SONG Long,ZHANG Yongjun (China Airborne Missile Academy,Henan Luoyang 471009,China)  
Based on a kind of gliding guidance bomb,an optimal terminal guidance law with constraint on terminal impact angle was deduced by using the optimal control theory and the method of state transition matrix.This method guarantees the minimum of miss distance and energy consumption.It is suitable for attacking the fixed ground target.The digital simulation was compared with the proportional guidance law of terminal angular constraint.The simulation results prove that the proposed optimal terminal guidance law can improve the terminal impact angle with precise guidance.
【CateGory Index】: TJ765.3
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1 JIANG Jin-zhe(College of Automation & Engineering,Nanjing University of Aeronautics & Astronautics,Nanjing 210016,China);Phenomenon and Control of Pendulum in Single Rotor Helicopter with Ducted Fan[J];Ordnance Industry Automation;2007-05
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1 Sun Weimeng,Zheng Zhiqiang College of Mechatronics Engineering and Automation,National University of Defense Technology,Changsha 410073,P.R.China;3D Variable Structure Guidance Law Based on Adaptive Model-following Control with Impact Angular Constraints[A];[C];2007
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8 RAO Weidong~(1,2) (1.Beijing Institute of Control Engineering,Beijing 100190,China; 2.Science and Technology on Space Intelligent Control Laboratory,Beijing 100190,China);Numerical solution for time optimal control of elastic satellites[A];[C];2013
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1 CHENG Jiang-tao WANG Chao-yong XIE Zhen-hua (Qingdao Branch of Navy Aviation Engineering College, Qingdao 266041);Study on the Damage Probability of Air-to-Ship Missile[J];Electronics Optics & Control;2001-01
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【Secondary References】
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