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題 名 | 微衛星姿態翻滾強健控制使用脈寬脈頻調變推力器之分析與設計=Analysis and Design of Robust Attitude Detumbling Control Using Pulse-Width Pulse-Frequency Modulation for Micro-Satellite |
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作 者 | 壽鶴年; 霍立珍; 柳復華; 林麗鳳; | 書刊名 | 航空技術學院學報 |
卷 期 | 10:1 2011.08[民100.08] |
頁 次 | 頁115-130 |
分類號 | 448.942 |
關鍵詞 | 微衛星姿態翻滾強健控制; 軟體迴路; 處理器迴路; Attitude detumbling control; Software-in-the-loop; Processor-in-the-loop; |
語 文 | 中文(Chinese) |
中文摘要 | 小(微)衛星進行的任務的能力從早期的軍事用途發展至氣象預測、資源探勘、通訊及科學實驗等方面。小(微)衛星擁有機械結構簡單、可靠性高、價格低廉、研究人員與設備精簡等優點。所以設計成本低、製作時間短、及高精度的微小衛星便成為各大學及小型科技機構主要研究之領域。我國第二期太空計畫預計以自主發展微衛星為主要里程碑,並期望使用自主載具進行發射。本文目的為探討微衛星脫離載具初入軌道之姿態控制問題。主要將藉由推力進行抑制衛星轉動及姿態穩定控制,並使用軟體迴路(Software-in-the-Loop, SIL)與處理器迴路(Processor-in-the-Loop, PIL)來實現。 |
英文摘要 | The objective of the project is to analysis and design of micro-satellite detumbling control. As the satellite was separates from the launch vehicle into orbit around the earth, an initial high angular rate is generated. The project focuses on robust attitude detumbling control to decrease the high three axis angle rate. Nonlinear spacecraft containing mismatched: thruster canted inaccuracy angle, the function of center of mass offset dependent on the thrusters are mounted a distance, the disturbing on the spacecraft may be attributed to gravity gradient, solar pressure, atmospheric drag and so on. The nonlinear controller is designed to achieve disturbance attenuation and to resist parameter uncertainty varying as well as asymptotically stability. The nonlinear controller is composite of pulse-width pulse-frequency modulated (PWPF) thrusters based on state feedback attitude control law. The solution of the nonlinear robust control problem is known to be related to the existence of solution to a Hamilton-Jacobi inequality. In the project, a solution for spacecraft attitude control is conjectured and shown to satisfy the robust criterion. The simulations show that the use of PWPF thrusters state feedback provides several important advantages over conventional bang-bang thruster control, including less thruster activity, smoother control action, and closed to linear actuation. The method is applied to the microsatellite orbit launched control problem to verify its effectiveness. |
本系統中英文摘要資訊取自各篇刊載內容。