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頁籤選單縮合
題 名 | Anti-Missile Guidance=反飛彈導引設計 |
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作 者 | 袁平甲; | 書刊名 | 新新科技年刊 |
卷 期 | 3 2007.01[民96.01] |
頁 次 | 頁279-284 |
分類號 | 595.95 |
關鍵詞 | 導引; 反飛彈; 直接命中; Guidance; Anti-missile; Direct-hit; |
語 文 | 英文(English) |
中文摘要 | 面對空防空飛彈系統攔截來襲高速飛彈目標之導引設計,已歷經長期之探討與研究。其特點為防空飛彈係以相對低速攔截高速飛彈目標,同時正迎頭攔截為達到直接命中(direct-hit)之最佳途徑。本文提出一積分式比例導航歸向導引律以達到上述正迎頭攔截而能直接命中目標。 |
英文摘要 | The guidance performance for a surface-to-air missile against a high-speed target has been studied and investigated for long time. The system is characterized by intercepting very high-speed targets with relatively low-speed missiles. From the result of previous study, it shows that the aspect angle between the missile and the target results in the intercept error. The exact head-on attack with zero miss upon interception will be the best way to achieve the direct-hit capability. The advanced midcourse guidance law has been proposed to obtain some improvement during midcourse phase. But the conventional proportional navigation is simply used in the terminal homing phase, in which the aspect angle is ignored to satisfy the final constraint. In this paper, integrated proportional navigation homing guidance law is proposed and studied, with which the exact head-on attack upon intercept can be easily achieved. |
本系統中英文摘要資訊取自各篇刊載內容。