Abstract
Ensuring robust energy systems is essential for satellite missions. Within the on-board power subsystem, lithium-ion batteries act as secondary power sources when solar arrays are unavailable. This study presents the preliminary design and modal analysis of a 9S4P lithium-ion battery pack based on NCR18650B cells for small satellite applications. A finite element model (FEM) is developed to evaluate the dynamic behavior of the structure under launch-relevant mechanical conditions. The modeling assumptions, including material properties, contact conditions, and boundary constraints representative of the launch configuration, are defined to accurately simulate the mechanical environment. Natural frequencies and mode shapes are extracted to assess compliance with structural requirements. The results demonstrate that the battery structure exhibits adequate stiffness, with natural frequencies significantly higher than the typical excitation range of launch vehicles. This indicates a reduced risk of resonance and dynamic coupling. These results confirm the structural integrity, dynamic robustness, and suitability of the proposed battery preliminary design for small satellite applications under the adopted modeling assumptions.
Highlights
Design of a lithium-ion battery pack suitable for nano-satellite applications.
Modal analysis performed using finite element modeling to identify natural frequencies.
Mode shapes and structural response evaluated under launch vibration conditions.
Methodological improvements and reinforced literature review ensure clarity.
Contribution enhances the understanding of battery pack structural reliability in space systems.