Please use this identifier to cite or link to this item: http://hdl.handle.net/11455/8527
標題: 中高層飛彈導引律設計與分析
Design and Analysis of Medium and Higher-Tier Missile Guidance Law
作者: 李雲皓
Li, Yun-Hao
關鍵字: Ballistic Target;彈道目標;Guidance Law;Control;Performance;導引律;控制;性能
出版社: 電機工程學系所
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摘要: 
本論文主要目的在分析與設計中高層反戰術彈道飛彈導引律,針對彈道飛彈返回大氣層尚未具突防能力前予以擊殺。研究中採用的飛彈系統具有雙節燃料,各節皆具備可動式噴嘴以產生固定推力並控制飛彈行進角度。
此導引律設計由第一節中途導引為初期導引律,採用直接飛行路徑角控制法則,將可動式噴嘴與彈體軸向之夾角設限,避免推力力矩破壞第一、二節連接處之結構。第一節結構在該節燃料燃燒完畢後,便從飛彈上脫落,飛彈進入巡航階段,以等待第二節燃料點燃。第二節飛彈在尋標器穩定作用之前,依據地面雷達估測之角速度,以傳統比例導引律控制飛彈往目標行進。待尋標器鎖定目標並估測出終端導引所需之參數後,導引系統改用可因應飛彈為加速或變加速度的3D改良式比例導引律,以側向加速度命令導引飛彈攔截彈道目標。
為了有效擊殺彈道目標,其中初期及中途導引控制法則導引律設計上,希望飛彈於中途導引結束時飛行路徑角滿足終端條件;終端導引律的設計除了考慮飛彈本身的軸向加速度也考慮目標具等加速度的情況,以強化飛彈導引律的擊敵性能強健性。最後,針對全系統導控性能進行模擬分析,進行誤失距離分析並評估攔截空間大小。

The research issue regarding missile guidance law design of a medium and higher-tier anti-ballistic missile to intercept ballistic targets during their early reentry phase has been a major concern in the defense technology. The defense missile possessing two solid rocket stages with both stages based on thrust vector control is used as a reference model for developing the guidance law.
For the guidance law design, the missile trajectory is first shaped by directly controlling its flight path toward the incoming target. When the first-stage rocket burns out, the missile coasts toward to the target with inertia force until the second-stage rocket activates. After the second-stage rocket activates, the missile is guided by proportional navigation guidance law that the angular rates are provided by the ground control center. The modified proportional navigation guidance law, works after the seeker starts, is designed to account the missile's axial acceleration and target acceleration variation. The lateral acceleration command is applied to guide the missile engaging the ballistic target.
The guidance law is developed with the aim to increase the interception performance by incorporating a thrust vector control mechanism to enhance lateral maneuverability and the second stage of the missile fitted with small control fins to stabilize the missile body. The effect of the proposed design is verified via extensive numerical simulation to examine its engagement performance. Miss distance analysis is conducted and characterization of the 3-dimenaional defensible volume is constructed to verify the proposed design.
URI: http://hdl.handle.net/11455/8527
其他識別: U0005-1708200919581000
Appears in Collections:電機工程學系所

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