DocumentCode :
3253272
Title :
Research of guidance law of missile with terminal angular constraint
Author :
Xiaoli, Qin ; Xingli, Huang ; Pengyu, Zhang ; Ding, Yang
Author_Institution :
Sci. & Technol. on Space Phys. Lab., Beijing, China
fYear :
2012
fDate :
14-17 July 2012
Firstpage :
962
Lastpage :
966
Abstract :
At present, there is a more popular topic to do research about hard target and underground target. More and more precision weapons equip with penetration warhead. But to show the best penetration performance, there should be a strict terminal angular constraint. Thus, the research about trajectory and terminal guidance law of penetration missile will supply more theoretical basis for the design of penetration missile. The paper presents a guidance law and does research work about realizability in Engineering.
Keywords :
impact (mechanical); missile guidance; trajectory control; hard target; missile guidance law; penetration missile design; penetration performance; penetration warhead; precision weapons; terminal angular constraint; trajectory guidance law; underground target; Equations; Mathematical model; Military aircraft; Missiles; Real time systems; Trajectory; Penetration missile formatting; Terminal angular constraint; Trajectory shaping;
fLanguage :
English
Publisher :
ieee
Conference_Titel :
Computer Science & Education (ICCSE), 2012 7th International Conference on
Conference_Location :
Melbourne, VIC
Print_ISBN :
978-1-4673-0241-8
Type :
conf
DOI :
10.1109/ICCSE.2012.6295225
Filename :
6295225
Link To Document :
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