自適應PPN飛彈導引律

淡江大學機構典藏 > 工學院 > 航空太空工程學系暨研究所 > 研究報告 > Item 987654321/76218

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题名:	自適應PPN飛彈導引律
其它题名:	Adaptive Ppn Missile Guidance Law
作者:	田豐
贡献者:	淡江大學航空太空工程學系
关键词:	PPN missile guidance;Adaptive;State Dependent Riccati Equa- tion;timescale gap;.nite time Lyapunov exponent
日期:	2011-08
上传时间:	2012-05-03 20:28:41 (UTC+8)
摘要:	In the past few decades, designing homing guidance laws for tactical guided missiles has been an area of intense research owing to the stringent perfor- mance requirement. Although the classical (constant gain) pure proportional navigation (PPN) guidance law provides satisfactory performance, there exist situations such as the maneuvering target scenario where the simple PPN may not o er satisfactory performance. To this end, a 3-dimensional state depen- dent Riccati equation 3-dimensional nonlinear PPN guidance law for missiles to against maneuvering targets is proposed in this work. To have a simple equations of motion used for describing the relative dynamics between missile and target, a 3-dimensional line-of-sight xed coordinate system is adopted. This makes possible the real-time computation of the state dependent Riccati equation nonlinear guidance law for missiles to against maneuvering targets, then a nite time Lyapunov exponent is used to de ne the timescale gap for evaluating the performance of the guidance law. For completeness, both non- maneuvering and maneuvering target will be considered.
显示于类别:	[航空太空工程學系暨研究所] 研究報告

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