一種嶄新之模糊導引律設計

A Novel Design Approach for Fuzzy Guidance Law

林俊良(Chun-Liang Lin) ； 劉煥彩(Van-Tsai Liu) ； 蘇懷文(Huai-Wen SU)

《中國航空太空學會學刊》 31卷2期 (1999/06) Pp. 107-115

https://doi.org/10.6124/TAASRC.199906_31(2).05

摘要

傳統氣動控制飛彈導引律於終端階段大多採比例歸向導引。這種設計，彈性較小，相對於先進飛彈的複雜、非線性動態行爲，並無法提供較佳的擊敵佳能和強健性。本研究提出一種以Takagi-Sugeno模糊邏輯爲基礎，具有增益排程(gain scheduling)特徵增益導引律設計。相較於傳統模糊導引律，這種方法具有以下優點：首先，它提供了設計通則，減少設計過程的試誤次數，其次，利用Takagi-Sugeno模糊邏輯快速推論及計算簡易的特性，減少運算時間，更適於即時操作。此法以視角變化率、敵機逃逸加速度及相對距離作爲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。

關鍵字

Takagi-Sugeno模糊邏輯 ； 增益排程 ； 導引律 ； 比例導引

並列摘要

Traditional aerodynamically controlled missiles are usually guided by the proportional navigation guidance law in the terminal phase. Such design approaches possess little design flexibility on the improvement of engagement performance and robustness. A new approach using Takagi-Sugeno fuzzy logic and gain scheduling is presented to design the terminal guidance law. The proposed method has two major advantages over the existing fuzzy logic design. First, it provides a general and formally motivated method for the guidance rule design. Second, the method for determining the guidance command is general and computationally efficient In this method, estimated line-of-sight angle rate, relative range and estimated target evasive acceleration are used to constitute the rule antecedent of the fuzzy guidance law to improve engagement performance The design relaxes the interceptor acceleration requirements and yields smaller miss distances.

並列關鍵字

Takagi-Sugeno Fuzzy Logic ； gain scheduling ； guidance law ； proportional navigation guidance