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題 名 | 空戰模擬之飛彈三維尾隨法導引律以迴授線性化控制法實現--解析解與參數探討=Implementation of Three-Dimensional Missile Pursuit Guidance Law with Feedback Linearization Control for Air Combat Simulation--Exact Solution and Parameters Effect |
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作 者 | 孔健君; 吳啟郁; | 書刊名 | 航空太空及民航學刊. 系列B |
卷 期 | 43:1 2011.04[民100.04] |
頁 次 | 頁1-9 |
分類號 | 595.95 |
關鍵詞 | 迴授線性化控制; 時間延遲; 尾隨法導引律; Feedback linearization control; Time delay; Pursuit guidance law; |
語 文 | 中文(Chinese) |
中文摘要 | 本文以迴授線性化控制法推導了空戰模擬中,以三維尾隨法導引律設計之飛彈加速度解析解與相關參數影響之探討。本文首先介紹簡化之質點飛彈運動方程式與空間座標轉換關係;其次提出以三維極座標之XY平面及ZR平面上各一個二維導引律,擴展爲三維導引律的觀點。在此觀點下,吾人發現符合三維尾隨法導引律設計之飛彈俯仰加速度與法向加速度,可藉由迴授線性化及追蹤俯仰角及航向角控制之思維求出解析解,讓飛彈姿態角以一階線性動態穩定逼近目標與飛彈之視線角。爲了克服制動器延遲現象,本文更進一步推導俯仰加速度命令與法向加速度命令解析解,使得進入飛彈運動方程式之加速度最終能等同於三維尾隨法導引律。本文最後以模擬結果驗證推導之正確性,並針對所提出方法之參數進行調變,研究各參數對飛彈追擊目標之影響。 |
英文摘要 | In this paper, we derive the implementation exact solutions of missile accelerations designed by three-dimensional pursuit guidance law with feedback linearization control method for air combat simulation and study the effects of parameters. First, we introduce simplified equations of motion of a missile and the transformation from line-of-sight and base-line frame to inertial reference frame. Next, utilizing a 3-D polar coordinate frame, a three-dimensional guidance law can be formed by collecting two 2-D guidance laws in X-Y plane and Z-R plane respectively proposed in this paper. Pursuit guidance law is our highlight. We apply feedback linearization control method to obtain the exact acceleration solutions to implement pursuit guidance law. The solution makes warhead direction follow with line-of-sight. The acceleration commands to compensate the time delay of actuators are also demonstrated in this paper. Final, the simulation results show that the exact solution derived in this paper is correct and some factors, e.g. control gain, time delay, are important to implement pursuit guidance law. |
本系統中英文摘要資訊取自各篇刊載內容。