本文目的為介紹PEARL立方衛星的姿態判定與控制次系統。PEARL-1C實驗立方衛星裝載Ka波段通訊酬載與小型電離層探測儀，將進行高通量通訊實驗與電離層科學資料之蒐集；PEARL-1H實驗立方衛星裝載高通量通訊酬載與光電影像儀，將進行高通量通訊實驗。衛星姿態判定與控制次系統功能為調整衛星姿態，使其符合衛星任務目的之姿態需求，本文詳述姿態判定與控制次系統之測試方法與結果，確認其健康狀態並與衛星電腦、電源供應次系統等界面相容，可正確執行各指令之響應。姿態需求之驗證方法則透過電腦模擬環境與姿態判定與控制次系統電腦形成硬體迴路，進行姿態判定與控制之模擬，確認姿態控制結果能否符合預期之任務需求。;The purpose of this paper is to introduce the attitude determination and control subsystem of the PEARL cube satellite. The PEARL-1C experimental cube satellite is equipped with a Ka-band communication payload and a Compact Ionospheric Probe, CIP, and will conduct high-throughput communication experiments and ionospheric scientific data collection; the PEARL-1H experimental cube satellite is loaded with a high-throughput communication payload and a photoelectric imager. High-throughput communication experiments will be performed. The function of the satellite attitude determination and control subsystem is to adjust the satellite attitude to meet the attitude requirements of the satellite mission. The system and other interfaces are compatible, and the response of each command can be executed correctly. The verification method of attitude requirements is to form a hardware loop through the computer simulation environment and the attitude determination and control subsystem computer to conduct attitude determination and control simulations to confirm whether the attitude control results meet the expected mission requirements.
