攔截飛彈的中途導引與控制

Abstract

本論文討論攔截飛彈在三維空間的中途導引與控制。飛彈進入中途導引階段時先預測剩餘飛行時間(time-to-go)，透過剩餘飛行時間來估計預測攔截點(Predicted Interception Point，PIP)。中途導引律則根據預測攔截點的位置算出飛彈飛往預測攔截點所需的速度改變。由於中途導引階段的導引加速度由推力向量控制(Thrust Vector Control，TVC)系統來達成，因此設計雙迴路飛行控制系統來穩定姿態並且使推力向量達到導引律的需求。我們所使用的中途導引方法能節省運算量且容易實現並降低對估計誤差的敏感度，有效地導引飛彈。本文模擬三維飛彈攔截目標的狀況，分析飛彈以不同方向角發射造成零力誤失(Zero Effort Miss，ZEM)的變化，討論推力向量控制系統的致動器(actuator)時間常數對飛彈控制的影響。

The thesis investigates three-dimensional midcourse guidance and control for missile interceptor. When missile enter the midcourse phase we makes the time-to-go prediction first, then estimates the predicted interception point (PIP) in use of the time-to-go prediction. According to the estimation of the PIP, midcourse guidance law computes the variation of velocity that missile required. Since the commanded guidance acceleration is achieved by thrust vector control (TVC) system in midcourse phase, we design two loops flight control system to stabilize the attitude and achieve the guidance command by TVC system. The midcourse guidance we used can reduce the amount of computation and the sensitivity of estimation error, be implemented easily and guide missile effectively. We simulate three-dimensional missile and target engagement, analyze zero effort miss (ZEM) caused by various yaw angle at launch and discuss the actuator time constant effects on control system.