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    題名: 自適應PPN飛彈導引律
    其他題名: Adaptive Ppn Missile Guidance Law
    作者: 田豐
    貢獻者: 淡江大學航空太空工程學系
    關鍵詞: PPN missile guidance;Adaptive;State Dependent Riccati Equa- tion;timescale gap;.nite time Lyapunov exponent
    日期: 2011-08
    上傳時間: 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.
    顯示於類別:[航空太空工程學系暨研究所] 研究報告

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