Session
2026 Session 1
Location
Orem, UT
Start Date
5-4-2026 9:10 AM
Description
Deployable arrays for space-based optical instruments, such as LiDAR, demand large apertures that can be compactly packaged within launch vehicle volume constraints. This work details the design, fabrication, and experimental validation of a full-scale deploy-able optical array derived from the origami flasher pattern, featuring passive precision kinematic couplings for repeatable panel alignment upon deployment. The flasher configuration (�� = 5, ℎ = 2, �� = 1, ���� = 0.1) was chosen to maximize deployed circularity and minimize hinge strain, with a target aperture of 0.6 m sized for an ESPA-class payload envelope. A hybrid hinge strategy addressed non-rigid fold kinematics and finite panel thickness: compliant flexure hinges at five interfaces accommodate out-of-plane motion, while rigid offset hinges govern the remainder. Four iterations were produced and tested, progressing from FDM-printed PLA to a machined Al6061-T6 prototype. The Extended Arm kinematic coupling interface represented the most significant advancement, enlarging the stability triangle and measurably improving global array alignment. Results confirm a consistent reduction in best-fit plane deviation across iterations, with the aluminum prototype achieving a global flatness of 0.37 mm under ideal boundary conditions
Design and Test of Deployable Origami Array
Orem, UT
Deployable arrays for space-based optical instruments, such as LiDAR, demand large apertures that can be compactly packaged within launch vehicle volume constraints. This work details the design, fabrication, and experimental validation of a full-scale deploy-able optical array derived from the origami flasher pattern, featuring passive precision kinematic couplings for repeatable panel alignment upon deployment. The flasher configuration (�� = 5, ℎ = 2, �� = 1, ���� = 0.1) was chosen to maximize deployed circularity and minimize hinge strain, with a target aperture of 0.6 m sized for an ESPA-class payload envelope. A hybrid hinge strategy addressed non-rigid fold kinematics and finite panel thickness: compliant flexure hinges at five interfaces accommodate out-of-plane motion, while rigid offset hinges govern the remainder. Four iterations were produced and tested, progressing from FDM-printed PLA to a machined Al6061-T6 prototype. The Extended Arm kinematic coupling interface represented the most significant advancement, enlarging the stability triangle and measurably improving global array alignment. Results confirm a consistent reduction in best-fit plane deviation across iterations, with the aluminum prototype achieving a global flatness of 0.37 mm under ideal boundary conditions