Finite element models for Self-Deployable Miura-folded origami

TL;DR

This work develops finite-element frameworks to model self-deployable Miura-fold origami via two mechanisms: elastic energy release using energy-equivalent tape-spring hinges and thermally activated shape-memory polymer actuation. An explicit-dynamics ABAQUS model with a derived equivalent hinge thickness accurately reproduces folding and deployment timings, and parametric studies reveal how hinge stiffness and damping tune performance. For SMP actuation, a two-temperature viscoelastic constitutive model captures programming, freezing, and recovery in PLA columns, predicting a qualitative 34.5% shape-recovery and thermomechanical trends. Together, the results offer predictive guidance for designing origami-based deployable structures in aerospace applications and highlight practical challenges in hinge modelling, damping effects, and multiphysics actuation.

Abstract

Origami-inspired self-deployable structures offer lightweight, compact, and autonomous deployment capabilities, making them highly attractive for aerospace and defence applications, such as solar panels, antennas, and reflector systems. This paper presents finite element frameworks for simulating Miura-origami units in ABAQUS, focusing on two deployment mechanisms: elastic strain energy release and thermally activated shape-memory polymers (SMPs). Validation against experimental data for elastic deployment demonstrates that the model accurately captures fold trajectories and overall kinematics. Parametric studies reveal the influence of hinge stiffness and damping on deployment efficiency. SMP-based simulations qualitatively reproduce stress-strain-temperature behaviour and realistic shape recovery ratios. The study establishes that predictive numerical models can effectively guide the design of origami-based deployable structures for aerospace and defence applications, while highlighting the challenges associated with hinge modelling, damping effects, and thermomechanical actuation.

Figures (7)

• Figure 1: ABAQUS model of the 4-panel Miura unit in pre-folded, folded, and deployed states.
• Figure 2: Variation of fold angles between panels with time during folding (A-B), during release of stresses (B-C), and deployment stage (C-D).
• Figure 3: Comparison of deployment fold angles between simulation and experiment (fulton2022deployment).
• Figure 4: Effect of tape-spring equivalent thickness on deployment trajectory.
• Figure 5: Influence of mass-damping coefficient $\alpha$ on deployment trajectory.