A method for validating CubeSat satellite EPS through power budget analysis aligned with mission requirements

The use of commercial off-the-shelf (COTS) components in CubeSat design offers flexibility, scalability, reduced project costs, and reduced development time. For these reasons, many space missions have adopted COTS platforms, owing to their advantages and limitations. An electrical power system (EPS) is a critical subsystem of COTS platforms that must meet mission requirements for the satellite to operate and guarantee mission success, including support for the operation modes and meeting the required lifetime. However, EPS validation is necessary to identify EPS characteristics such as energy generation, storage, power consumption, and management modes. The power budget is a crucial aspect in the validation, design, and correct selection of an EPS, which can reduce costs and ensure compliance with EPS requirements. In this paper, a method is proposed to validate the EPS characteristics of COTS platforms by analyzing the power budget according to mission specifications. The approach determines the power and energy for the operational modes and scenarios and evaluates the battery depth of discharge (DoD) and charge/discharge cycles. The effectiveness of the proposed method is demonstrated through a case study of the LEOPAR mission, a 3U CubeSat satellite. The results show that the EPS can meet the power demands of the satellite subsystems during the mission. Our method provides a systematic and easy-to-follow process for validating CubeSat satellite EPS and can significantly enhance the development process for these satellites. It also contributes to the small-satellite community by providing a valuable tool to ensure the success of CubeSat missions.