Design and Implementation of Electrical Power System for 2U Cubesat

• Main Authors: LAI, YI-CHEN, 賴易琛
• Other Authors: CHEN, YU-KAI
• Format: Others
• Language: zh-TW
• Published: 2019
• Online Access: http://ndltd.ncl.edu.tw/handle/wx2mpw

碩士 === 國立虎尾科技大學 === 飛機工程系航空與電子科技碩士班 === 107 === This thesis presents the design and implementation of Electrical Power System for 2U Cubesat. Using Sepic Converter with Perturb & Observe method to do maximum power tracking, we add the latching relay in the system, when the battery voltage is lower than the setting voltage, then we will close the maximum power tracking and let the solar panel charge batteries directly. The main mission is received the ADS-B data of the Civil aircraft and drone then downlink to the ground station to analysis or application. The EPS system has battery over-charged, over-discharged, over-current and short protect, and we add a temperature detect to avoid the battery charge at the negative temperature, three mechanical switches are add between the battery and the subsystem to avoid discharge or wrong working, and add a switch before the subsystem to control the power status. When the battery voltage is lower than the setting voltage, then we will force to close the subsystem. EPS module communities with the OBC module by UART, then the OBC module will downlink the cubesat’s health condition by the UHF module. The space environment is vacuum, big temperature variation and high electromagnetic radiation, so the cubesat need to do vacuum thermal cycle test, radiation test, solar panel large temperature variation test, and because the li-on batter is one of the dangerous goods transport, so we need to pass the UN38.3 and a 1.2m falling test, then we ship the cubesat