臺灣博碩士論文加值系統

本論文中，我們討論具有高操控性與高準確性的中低空反彈道飛彈之導控系統。假想來襲之彈道飛彈已進入大氣層內，且具有速度上絕對的優勢，反飛彈如何利用側噴流系統，加強氣動力操作所較不足的側向推力，改變彈體側向移動的位置與速度，提升彈體的機動性，以直接碰撞的方式摧毀彈道飛彈。就氣動力操作而言，最大的優點在於具有良好的操控性，且不會有燃料消耗與噴發次數等問題，但其缺點在於需要較長的反應時間。就側噴流系統而言，最大的優點在於可作即時加速的動作，可提升反飛彈的機動性，但其缺點在於側噴流系統有噴發次數的限制。本論文的重點在於如何將氣動力操作與側噴流系統相互結合，在相輔相成的原則下，完成攔截任務。整個導控流程是以比例導引律作為基礎，負責產生命令，交由自動駕駛儀系統與側噴流系統產生側向推力輸出。自動駕駛儀系統係我們利用彈體尾翼控制面以控制彈體的平移與轉動。而側噴流系統係以零推力誤差為基礎，根據觸發邏輯以決定側向推力輸出與否。最後，我們以數值模擬的方式來評估所研究之導控系統的性能。

This thesis discusses the guidance and control system design problem for missiles with high controllability and accuracy. Assume that there is a target ballistic missile (the target) moving very fast inside the atmosphere, and an anti-ballistic-missile missile (the missile) with a lateral jet system is to intercept the target by making a direct collision. The lateral jet system of the missile can produce large lateral force instantaneously so that the missile can make lateral motion quickly. However, the number of lateral jets in the system is limited, so the aerodynamic control system of the missile must be used in the first stage of the intercept mission to bring the missile close to the target. How to integrate these two systems so that they can work together with the guidance system of the missile is the main research subject of this thesis. Our results show that in the first stage, the proportional navigation guidance law can be integrated with the aerodynamic control system, which is based on the linear quadratic optimal control method, to generate proper commands for the control surfaces of the missile. Then, just before the proportional navigation guidance law diverges, the lateral jet system and a zero-effort-miss concept based intelligent guidance law can take over, and accomplish the direct collision intercept mission. Our works include many simulation results for evaluating the performance of the proposed guidance and control system.

第一章 緒論 …………………………………………………… 1
第一章 系統描述 ………………………………………………… 4
2.1 系統架構 ……………………………………………………4
2.2 飛彈模式 …………………………………………………….. 6
2.2.1 符號說明 ………………………………………………... 6
2.2.2 飛彈規格 ………………………………………………... 7
2.2.3 運動方程式 ……………………………………………… 9
2.2.4 座標轉換 ………………………………………………. 10
第三章 比例導引律設計 ………………………………………... 12
3.1 比例導引律的概念與公式推導 …………………………… 12
3.2 零推力誤差的觀點 (ZEM) ………………………………. 16
3.3 真比例導引律 (TPN) …………………………………….. 17
3.4 普通比例導引律 (GPN) …………………………………. 21
3.5 比例導引律的使用範圍 ………………………………….. 23
3.6 導引律常數K的選取 …………………………………….. 25
第四章 導控系統設計 …………………………………………… 26
4.1 反飛彈導控流程 …………………………………………… 26
4.2 控制器切換 ………………………………………………… 28
4.3 自動駕駛儀系統 …………………………………………… 31
4.4 側噴流控制系統 …………………………………………… 38
4.4.1 預測式的觸發邏輯設計 …………………………………. 38
4.4.2 控制噴嘴的定址與噴發方向的選擇 ………………... 45
第五章 模擬結果分析 …………………………………………… 49
5.1 基本接戰條件與模擬結果 ………………………………… 49
5.2 數值模擬比較與分析各種條件之影響 …………………… 55
第六章 結論 ……………………………………………………….. 65
參考文獻 ……………………………………………………………. 67

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