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題 名 | 以模糊-比例微分混合應用為基礎之導引律設計=Design of a Fuzzy-Pd Based Guidance Law |
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作 者 | 劉煥彩; 林俊良; 蘇懷文; 薛立群; | 書刊名 | 技術學刊 |
卷 期 | 15:1 2000.03[民89.03] |
頁 次 | 頁113-121 |
分類號 | 595.95 |
關鍵詞 | 模糊邏輯; 導引律; 比例導引; Fuzzy logic; Guidance law; Proportional navigation guidance; |
語 文 | 中文(Chinese) |
中文摘要 | 由於比例歸向導引簡單、有效以及易於實現的優點因此成為傳統飛彈導引律設計 的主流。但相對於先進戰機的高機動能力,這種設計實無法提供較佳的擊敵性能和強健性。 本研究應用模糊邏輯高設計自由度及高彈性的特質提出一種嶄新的模糊終端導引律。此導引 律為三階段式,各階段應用視線角、視線角變化率和視線角加速度作為模糊導引律之前件因 素,推論適宜的擊敵飛行軌跡。導引律設計使用非對稱的歸屬函數和導引規則,據此提昇導 引效能、節省能量消耗並且提高強健性。 |
英文摘要 | The popularity of proportional navigation guidance laws in traditional aerodynamically controlled missiles is based on their simplicity, effectiveness, and ease of implementation. However, such a design approach cannot provide satisfactory engagement performance and performance robustness with respect to advanced fighters. Based on the high design freedom and flexibility of the fuzzy logic theory, a novel fuzzy logic-based terminal guidance law is proposed. The guidance is partitioned into three phases. Estimated line-of-sight angle, line-of-sight angle rate, line-of-sight angular acceleration and relative range are used to constitute the rule antecedents of the guidance law to shape appropriate flight trajectories for engagement. Asymmetric membership functions and guidance rules are used in the proposed design to provide satisfactory performance and robustness. |
本系統中英文摘要資訊取自各篇刊載內容。