SDRE Missile Guidance Law

淡江大學機構典藏 > 工學院 > 航空太空工程學系暨研究所 > 期刊論文 > Item 987654321/106309

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题名:	SDRE Missile Guidance Law
作者:	Tyan, Feng;Shen, Jeng-fu
关键词:	State dependent Riccati equation;guidance law
日期:	2010-06-09
上传时间:	2016-04-22 13:45:37 (UTC+8)
摘要:	In this work, a state dependent Riccati equation (SDRE) missile guidance is formulated and studied. With the aid of a line of sight (LOS) fixed coordinate, the order of the system equations describing the three dimensional missile guidance problem is reduced to three. In addtion, the computational effort of solving SDRE is less than the usual guidance formulations which often have the order greater than three. Three different state dependent coefficient forms are proposed and compared under the consideration of optimality and implementation. For more constructive design, a simple shift of variable is also introduced to achieve better performance. From the results of numerical experiments, we also find that the proposed SRRE guidance law outperforms the conventional PPN guidance (for navigation constant equals 5) in the sense of time but at the cost of energy.
關聯:	2010 8th IEEE International Conference on Control and Automation, pp.866-870
DOI:	10.1109/ICCA.2010.5524364
显示于类别:	[航空太空工程學系暨研究所] 期刊論文

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