DocumentCode :
2638945
Title :
Research for the effect of the saturated acceleration on the guidance precision in proportion navigation
Author :
Wang, Liguang ; Jing, Zhanrong ; Zhu, Anfu ; Chen, Weijun
Author_Institution :
Sch. of Electron. & Inf., Northwestern Polytech. Univ., Xian
fYear :
2008
fDate :
10-12 Dec. 2008
Firstpage :
1
Lastpage :
5
Abstract :
During the course of intercepting the fast target in proportion navigation law, the missilepsilas acceleration increases so quickly and even reaches its saturated value near the hitting spot that the guidance precision becomes worse. To analyse the effect of the saturated acceleration on the guidance precision in proportion law, an algorithm to calculate the missilepsilas miss distance within the limitation of different saturated acceleration is presented and the simulation in three-dimensional field is carried out. The simulation indicates that the saturated acceleration hardly influences on the guidance precision when the acceleration exceeds a certain critical value which is much less than the maximal acceleration. The algorithm can not only calculate the miss distance within the limitation of different saturated acceleration but also can get the minimum acceleration value insuring a certain guidance precision. The algorithm provides an effective way to guidance law designing, the missilepsilas performance evaluation, battle decision-making and so on.
Keywords :
acceleration control; missile guidance; guidance precision; missile acceleration; missile miss distance; proportion navigation; saturated acceleration; Acceleration; Algorithm design and analysis; Analytical models; Decision making; Navigation;
fLanguage :
English
Publisher :
ieee
Conference_Titel :
Systems and Control in Aerospace and Astronautics, 2008. ISSCAA 2008. 2nd International Symposium on
Conference_Location :
Shenzhen
Print_ISBN :
978-1-4244-3908-9
Electronic_ISBN :
978-1-4244-2386-6
Type :
conf
DOI :
10.1109/ISSCAA.2008.4776347
Filename :
4776347
Link To Document :
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