Implementation of Attitude Determination and Control System into PACE Nanosatellite

• Main Authors: Hoang TheHuynh, 黄世兄
• Other Authors: Jiun-Jih Miau
• Format: Others
• Language: en_US
• Published: 2013
• Online Access: http://ndltd.ncl.edu.tw/handle/77308633372031690952

碩士 === 國立成功大學 === 航空太空工程學系碩博士班 === 101 === The thesis describes the implementation of an active attitude determination and control system (ADCS) for the PACE nanosatellite. PACE satellite is a 2U cubesat under developed at National Cheng Kung University (NCKU) with a mass less than 2 kg and dimension of 100 mm x 100 mm x 227 mm. Two main missions of PACE satellite are to conduct attitude control experiments and to demonstrate the technology to be used in future missions for small satellite. The ADCS sub-system aims to provide functions for active attitude control such as detumbling, determination and stabilization. More importantly, the operation of the PACE mission will allow users to upload ADCS algorithms so that the algorithm can be tested and verified in space. In order to fully verify the embedded ADCS software, a verification system and a Processor-in-the-loop (PIL) simulation are developed. The simulation models consisting of space environment, orbit dynamic, attitude dynamic, and sensor/actuator are modeled using Labview software. A CompactRIO real-time controller is adopted as a simulator to execute simulation models into Labview and also to provide real-time interface with ADCS board. For the results, algorithms and functions for ADCS software are both implemented and verified. The results are met the requirements for ADCS.