Session
2025 Session 4
Location
Brigham Young University Engineering Building, Provo, UT
Start Date
5-5-2025 11:30 AM
Description
Optical satellite performance improves with increased surface area, which enhances light capture and sensor input. Deployable array mechanisms allow satellites to remain compact during launch and expand in orbit. 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 precise alignment without motorized actuation reducing complexity. 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. Alignment accuracy was evaluated using a Faro 3D scanning arm. 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.
Precision Hinges for Origami Space Arrays
Brigham Young University Engineering Building, Provo, UT
Optical satellite performance improves with increased surface area, which enhances light capture and sensor input. Deployable array mechanisms allow satellites to remain compact during launch and expand in orbit. 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 precise alignment without motorized actuation reducing complexity. 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. Alignment accuracy was evaluated using a Faro 3D scanning arm. 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.