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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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