攔截飛彈的導引與姿態控制

Abstract

本論文的主旨是探討攔截飛彈中途與終端三維導引律以及轉向與姿態控制系統的設計。因為在中途及終端階段的導引加速度均須由彈體側向的推力器來達成，而在終端階段紅外線尋標器必須一直鎖定目標，真比例導引律似為最恰當的選擇。本文推導三維真比例導引律的公式，並以模擬分析系統參數如雷達量測誤差大小、紅外線尋標器的鎖定距離、飛行控制系統的頻寬等對攔截效能的影響。攔截飛彈的轉向與姿態控制均以開關式推力器為致動器。轉向控制系統是單純以脈衝寬度調變的方式來達到導引加速度的需求。維持三軸穩定的姿態控制系統是以線性化的模式進行線性設計，採姿態角及角速度回授，並以脈衝寬度調變的方式合成。數值模擬以標準飛彈三型為藍本。模擬結果可提供未來硬體發展的參考。

The thesis investigates three-dimensional midcourse and terminal guidance laws for missile interceptor and the associated divert and attitude control system design. Since the commanded guidance acceleration, in both the midcourse phase and terminal phase, is achieved using divert thrusters and in the terminal phase the infrared seeker needs to continuously lock-on to the target, true proportional navigation guidance law seems to be the most appropriate choice among the various guidance laws. We derive the three-dimensional true proportional navigation guidance law and analyze, via simulations, various system parameters such as radar measurement errors, seeker lock-on range, and flight control system bandwidth, have on the performance of the interceptor. Divert and attitude control system use on-off thrusters as actuators. Divert control achieves the command guidance acceleration using pulse width modulation (PWM), in which the pulse duration is proportional to the magnitude of acceleration command. Attitude control system is linear and designed using linearized model, it uses angle and rate feedback, achieves three-axis stabilization and is implemented using PWM. Simulations for both guidance and control use Standard Missile III as a prototype. Results from this research should be useful for future system and hardware development.