Design and Evaluation of Deployable Perovskite Solar Arrays Aboard Small Spacecraft

A self-deployable membrane structure with integrated perovskite solar arrays was developed for installation aboard OrigamiSat-2, a 3U CubeSat (10 cm × 10 cm × 34 cm) selected by the Japan Aerospace Exploration Agency’s Innovative Satellite Technology Demonstration-4 program. The textile membrane (50 cm × 50 cm), inspired by the origami flasher model, is stowed within a volume of 1U (10 cm × 10 cm × 8 cm) and deployed in orbit using composite booms. Two solar arrays, each consisting of two flexible perovskite solar cells (35.4 mm × 75 mm × 315 μm), are attached to the surface of the membrane. This paper will describe the following development activities in detail: (i) Structural prototypes of the membrane solar arrays were fabricated with dummy solar cells and cables. To ensure high packing efficiency and reliable deployment, the prototypes were subjected to a series of stowage and deployment tests. Design modifications were made based on the test results; (ii) The performance of the perovskite solar cells was evaluated by measuring their current-voltage characteristics under a solar simulator; (iii) Potential degradation in solar cell performance due to extreme space temperatures was assessed through thermal modeling and simulation. The design challenges and solutions, as well as compromises that were necessary to meet satellite requirements, may provide insights for future development of deployable power systems on small satellites.