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題 名 | 以模糊邏輯為基礎之飛彈導控系統設計=Design of Fuzzy Logic-Based Guidance and Control Systems |
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作 者 | 林俊良; 劉煥彩; 蘇懷文; | 書刊名 | 模糊系統學刊 |
卷 期 | 4:2 1998.12[民87.12] |
頁 次 | 頁1-14 |
分類號 | 595.95 |
關鍵詞 | 模糊邏輯; 導引律; 自動駕駛儀; 比例導引; 比例控制; Fuzzy logic; Guidance law; Autopilot; Proportional navigation guidance; Proportional control; |
語 文 | 中文(Chinese) |
中文摘要 | 傳統的飛彈導引控制系統在導引律部份大多採比例歸向導引,自動駕駛儀部份亦 為比例控制。這種過於簡化的設計相對於先進飛彈的複雜、非線性動態行為,並無法提供較 佳的擊敵性能和強健性。本研究提出一種嶄新的模糊控制架構設計導引律及自動駕駛儀。我 們以視角變化率、敵機逃逸加速度及相對距離作為模糊導引律之前件因素,推論適宜的加速 度命令,據此改良傳統比例導引的效能、節省能量消耗且提高對逃逸目標的擊殺率。至於自 動駕駛儀的加速度及速度迴路,我們以追蹤誤差及誤差信號變化率作為模糊控制法則的前件 因素,據此改良加速度命令至彈體橫向加速度反應的時間,有效、快速地控制飛彈姿態。 |
英文摘要 | Actual aerodynamically controlled missiles are nonlinear: their dynamics changes with the operating points and there may be essential nonlinearities in the plant. For the sack of simplification in designs, traditional aerodynamically controlled missiles are usually guided by the proportional navigation guidance law, and the flight control systems are some types of the proportional-integral-derivative ( PID ) control. However, such design approaches cannot cope with highly nonlinear behavior and provide satisfactory engagement performance and performance robustness. A fully fuzzy logic-based guidance and control design is proposed in this paper. Estimated line-of-sight angle rate, relative range and estimated target evasive acceleration are used to constitute the rule antecedent of the guidance law to improve engagement performance. The advanced design relaxes the interceptor acceleration requirements and also yields smaller miss distances. Tracking error and change of tracking error constitute the rule antecedent of the fuzzy autopilot to provide excellent tracking performance and robustness. |
本系統中英文摘要資訊取自各篇刊載內容。