用於微型衛星姿態控制之一體式反應輪設計

Abstract

反應輪係航太設備姿態控制器中重要的致動器，利用角動量守恆的原理，實現高效率且精確的姿態控制。本論文提出用於微型衛星姿態控制之反應輪系統化設計流程，基於三相永磁同步電動機 (PMSM) 架構下提出具有由內軛和外軛組成的雙層轉子結構，可以降低定子內軛與磁石之間於軸承上的交互作用磁力所產生的損失，轉子磁石設計中使用海爾貝克磁石陣列 (Halbach magnet array) 以提高轉矩密度並降低外轉子背鐵使用，本論文提出可應用於無定子槽式設計之繞線因素，透過樣機製造與實驗比較傳統實體繞組與軟性印刷電路板 (FPCB) 繞組特性差異，旨在提出一反應輪設計於需求體積與重量限制下提供更高的角動量的最佳化解決方案。本論文對於系統化磁路設計流程的設計原理、分析方法，以及最佳化演算法皆有詳盡的說明。針對本論文所提出之微型反應輪設計進行樣機製造並完成環境測試驗證，其中機構設計亦有考量靜磁場漏磁分析、機械形變量分析及機械振動分析，而太空環境實驗驗證包含振動測試、熱循環測試及熱真空測試，實驗結果表明，本論文所提出的反應輪設計可以滿足需求設計規格。

The reaction wheel is an essential satellite actuator for attitude control in spacecraft applications. The reaction wheel performs the attitude control of a miniaturized satellite based on the conservation of angular momentum to achieve high efficiency and precise attitude control. This dissertation proposes a systematic design process of reaction wheels for miniaturized satellite attitude control. The proposed reaction wheel is a three-phase SmCo permanent magnet synchronous motor (PMSM) with a dual-layer rotor composed of an inner and outer yoke. It can reduce the loss caused by the interaction of magnetic force between the inner stator yoke and the magnets on the bearing. A rotor design with a Halbach magnet array improves the torque density and reduces back iron usage. This dissertation proposed a slotless winding factor for slotless stator design. The reaction wheel with enameled copper windings and flexible printed circuit board (FPCB) windings is manufactured for feature comparison. This dissertation proposes an optimized solution for designing a reaction wheel to provide better angular momentum under the required volume and weight constraints. This dissertation explains design principles, analysis methods, and optimization algorithms used in the systematized magnetic property design process. The proposed miniaturized reaction wheel is fabricated, verified, and validated. The nominal angular momentum is 30 mNm-sec and the volume 50×50×40 mm3. The rated speed is 1400 rpm. The mechanical design considerations include static magnetic field leakage analysis, mechanical deformation analysis, and mechanical vibration analysis. The environmental experiments of the satellite facility include mechanical vibration tests, thermal vacuum operation tests, and thermal cycle operation tests. The experiment results conclude that the proposed design can meet design specification expectations.