The Global Carbon Dioxide Monitoring Microsatellite Mission Design and Analysis
- Paper number
GLOC-2023,T,IP,x75092
- Author
Mr. Ahmad Zammir Ribah, Beihang University (BUAA), China
- Year
2023
- Abstract
The carbon-detection satellite technology has been established as one of the solutions to provide the carbon dioxide (CO2) data such as TanSat by China, and Copernicus by The European Union (UE). The concept of CO2 measurement by satellite’s payload is detecting the gas, when the atmosphere is irradiated by sunlight, the gas molecules will show spectral absorption characteristics. Hence, in this research, the mission design and analysis are conducted to determine the feasibility of the remote sensing microsatellite system that can provide CO2 data globally to support environmental monitoring and contribute to ecological sustainability. The mission would provide academic, scientific, policy, and industry benefits. To support the mission, the satellite system design contains the hyperspectral camera as the primary payload by operating the Short-Wave Infrared (SWIR) camera, in a band region of 1-2 µm. The satellite is designed to orbit in a sun-synchronous orbit (SSO), and 10:30 Local Time of Descending Node (LTDN). The preliminary analysis and calculation are conducted in the design of the communication satellite sub-system, structure and mechanism sub-system, electrical power sub-system (EPS), attitude determination and control sub-system (ADCS), and thermal control and protection sub-system. In the communication aspect, the satellite uses the X-Band for data transmission. Based on the link budget analysis, it shows a good result of link margin in 24.52 dB of Uplink and 11.94 of Downlink. As required, the satellite needed to have a mass below 100 kg, and implement both body-mounted and deploy mechanisms for solar panel configuration. Then, the ADCS should capable to support the satellite in several attitude control modes such as nadir pointing, target pointing, and inertial pointing. Then, EPS is designed to operate in normal mode, and safety mode. For thermal protection, the satellite will implement both active and passive thermal control system. The overall operation range for the satellite is summarized as approximately -10.00 to 45.00 °C to ensure all satellite components working properly. Current mission design and analysis result shows the key points of the satellite system design as the preliminary step. Then, the overall result shows that global CO2 monitoring mission is possible to be implemented in microsatellite system design.
- Abstract document
- Manuscript document
(absent)