| dc.description.abstract | 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. | en_US |