Passive Precision Alignment for Thin-Panel Deployable Space Systems

Optical satellite performance improves with increased surface area, which enhances light capture and sensor input. Deployable mechanisms allow satellites to remain compact during launch and expand in orbit but the large relative motion during deployment makes it difficult to achieve precision alignment in the final deployed state. This study focuses on designing passive hinges in rigid-panel origami-based deployable satellites for optical applications. A novel kinematic coupling method is developed, incorporating magnets, compact Lamina Emergent Torsional (LET) joints, and principles from Maxwell couplings. This system autonomously achieves alignment without motorized actuation. The design process involved iterative testing of ten two-panel hinge prototypes to identify the most effective designs. These were integrated into a degree-four vertex pattern (“bird’s foot”) for further refinement and ultimately applied to a full origami flasher pattern with 26 panels. The coupling accommodates the flasher’s non-rigid foldable nature while ensuring precise alignment, essential for optical applications requiring rigid panels. Additionally, all prototype configurations maintained an 8mm thickness, optimizing the stowed-to-deployed ratio for space applications. This study highlights the feasibility of precise kinematic couplings for small origami-inspired satellites and provides a foundation for advancements in deployable optical systems.