姿態感測與控制系統（ADCS）是一個非常重要的次系統，用於穩定在軌立方體衛星並確保其能成功指向所需的方向。本文將主要設計及模擬鯨鯊號（SCIONX）立方衛星的姿態感測與控制次系統。鯨鯊號（SCIONX）立方衛星是一顆科學任務衛星，搭載小型電離層探測器，主要是探測500 公里太陽同步圓軌道電離層中F 層不規則體和電離層擾動；以及搭載高光譜成像儀主要是探測日測下380 到1020 納米波長之間的可見光和近紅外電磁光譜來分析台灣上空PM 2.5 濃度測量值2.5 濃度測量值；並搭載微小型太
陽極紫外線光度計，主要是探測軌道附近電漿與太陽紫外光所產生之光電流；以及搭載自動位置回報系統來接收與轉發以AX.25 形式的數據封包。為了使鯨鯊號能夠完成科學觀測並將珍貴的觀測。為了使鯨鯊號能夠完成科學觀測並將珍貴的觀測資料下傳至地面站，姿態感測與控制次系統需要在不同的指向需求中將鯨鯊號指向所需的方向並完成其任務，本文使用MATLAB 之Simulink 建立真實太空環境擾動、軌道以及衛星動力學模型來模擬不同軌道週期下，鯨鯊號使用反應輪、磁力計以及磁力矩器在Detumbling、Local Velocity Local Horizon (LVLH) Pointing、Sun Pointing、Surface Target Pointing 指向需求下的控制模擬，並成功完成指向控制模式切換使衛星達到穩定狀態。

The Attitude Determination and Control Subsystem (ADCS) is a very important subsystem used to stabilize an in-orbit CubeSat and ensure it can be successfully pointed in the required direction. This thesis will mainly design and simulate the Attitude Determination and Control Subsystem for the SCintillation and IONosphere eXtended (SCION-X) CubeSat. The SCIONX 12U CubeSat is a scientific mission satellite, equipped with a Compact Ionosphere Probe (CIP), mainly to detect F-layer plasma irregularities and ionospheric disturbances in the ionosphere along a 500-kilometer sun-synchronous circular orbit; and equipped with a Hyper-SCAN, a hyperspectral imager to measure the visible and near-infrared electromagnetic spectrum between 380 and 1020 nanometer wavelengths to analyze PM 2.5 concentration
measurements over Taiwan, a Solar Extreme Ultraviolet Probe(SEUV) to measure photoelectric current along a 500-kilometer sun-synchronous circular orbit, and a Automatic
Packet Report System(APRS) Digipeater to receive and forward data packets in the form of AX.25. In order to enable SCION-X to complete scientific observations and download precious observation data to the ground station, the attitude sensing and control subsystem needs to point the spacecraft in the required direction and complete its tasks in different pointing requirements. This thesis uses MATLAB Simulink to implement real space environment disturbance torques, orbit, and satellite dynamics model to simulate different orbit periods. The SCION-X spacecraft uses reaction wheels, magnetometers, and magnetic torquer devices to achieve the requirements of detumbling, local velocity local horizon (LVLH) Pointing, Sun Pointing, and Surface Target Pointing, and successfully completed the pointing control mode switching to control the satellite to be in stable state, satisfying pointing requirements.

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