頁籤選單縮合
題 名 | Design of Advanced Guidance Law Against High Speed Attacking Target=反制高速進襲目標之新式導引律研究 |
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作 者 | 林俊良; 陳永裕; | 書刊名 | Proceedings of the National Science Council : Part A, Physical Science and Engineering |
卷 期 | 23:1 1999.01[民88.01] |
頁 次 | 頁60-74 |
分類號 | 595.95 |
關鍵詞 | 反制高速進襲目標; 地對空飛彈導引律; Explicit guidance law; Optimal guidance law; Guided missile; Ballistic target; Neural network; |
語 文 | 英文(English) |
英文摘要 | An advanced guidance law is developed such that anti-air surface-to-air tactical missiles can effectively defend against very high speed targets, such as ballistic targets. Preliminary studies have shown that the aspect angle of the interceptor at lock-on near 180 degrees is a fundamental requirement for an aerodynamically controlled missile to achieve a small miss distance against a faster target. To meet this geometric constraint, an advanced midcourse guidance law based on optimal trajectory shaping and a neural network correction guidance algorithm is explored. It is shown that the proposed guidance law can offer a near head-on homing condition before the guided missile enters the terminal phase. It is also found that the neural network incorporated with conventional proportional navigation in the terminal phase can significantly extend the defensible region. Results of a simulation study show the effectiveness of our proposed guidance scheme. |
本系統中英文摘要資訊取自各篇刊載內容。