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This paper describes a case study of a workload and development-time reduction method to enhance the benefits of using small satellites. The method consists of (1) a simplified satellite system design and requirement for attitude determination and control system (ADCS); (2) a simplified fault detection, isolation, and recovery (FDIR) system; and (3) a simplified software design that allows the software architecture to be reused. For the system analyses, this study proposes to select and focus on the most important parameters, especially system or mission survivability. The bus-system safety analysis is related to power generation, and the mission survivability analyses are related to the possibility of solar radiation incidences to the imaging sensor. The control algorithm and proposed system feasibilities are verified by model-based simulation. The results show high survivability of the designed system.

ADCS Design with Effective FDIR Considering Mission Constraints for a Small Satellite