本論文目的為開發皮、奈米衛星等級衛星於次軌道任務中使用的姿態控制系統，使用商業現成元件製成的動量輪為姿態致動器，並整合地磁計、陀螺儀及地弧感測器數據判定姿態。衛星預期以混合式火箭為載具，探測位於高空一百公里至三百公里處的電離層不規則體，於高空脫離後利用本模組減滾並提供儀器之指向。研究已開發完成系統之機構、驅動電路及控制軟體，並設計扭力測試量測動量輪之角動量容量、旋轉測試驗證衛星之減滾及姿態控制流程。;The purpose of this paper is to develop an attitude determination and control system (ADCS) for pico and nano-satellite at sub-orbital task. The actuator of this system is momentum wheel which made by commercial-off-the-shelf (COTS) components. And data of geomagnetic, gyroscope and earth sensor is integrated to determine the attitude. A hybrid rocket is expected to be the carrier of satellite, probing the irregularities of ionosphere at 100km to 300km altitude. After satellite detached form carrier, this module provides de-spin and instruments pointing ability. In this research, mechanical structure, circuit and control software have been developed. A torque test has performed to determine capacity of momentum wheel, and a rotation test has performed for validation of attitude control and de-spin process.
