Deployment Methods for an Origami-Inspired Rigid-Foldable Array

The purpose of this work is to evaluate several deployment methods for an origami-inspired solar array at two size scales: 25-meter array and CubeSat array. The array enables rigid panel deployment and introduces new concepts for actuating CubeSat deployables. The design for the array was inspired by the origami flasher model (Lang, 1997; Shafer, 2001). Figure 1 shows the array prototyped from Garolite and Kapton film at the CubeSat scale. Prior work demonstrated that rigid panels like solar cells could successfully be folded into the final stowed configuration without requiring the panels to flex (Zirbel, Lang, Thomson, & al., 2013). The design of the array is novel and enables efficient use of space. The array can be wrapped around the central bus of the spacecraft in the case of the large array, or can accommodate storage of a small instrument payload in the case of the CubeSat array. The radial symmetry of this array around the spacecraft is ideally suited for spacecraft that need to spin. This work focuses on several actuation methods for a one-time deployment of the array. The array is launched in its stowed configuration and it will be deployed when it is in space. Concepts for both passive and active actuation were considered

Design parameters for the bistable mechanism prototypes.

<p>Design parameters for the bistable mechanism prototypes.</p

Design iterations of the compliant bistable mechanism.

<p>Design iterations of the compliant bistable mechanism.</p

Bistable Mechanisms for Space Applications - Fig 12

<p>(a) Initial position of the finite element model. (b) Position where highest stress occurs during deflection. (c) Second stable position of the model.</p

Predicted energy curve of the metallic glass bistable mechanism from the PRBM.

<p>Predicted energy curve of the metallic glass bistable mechanism from the PRBM.</p

Design parameters for the bistable mechanism prototypes.

<p>Design parameters for the bistable mechanism prototypes.</p

Comparing geometry of compliant segments.

<p>The thicker segments increase the force slightly.</p

An example of the finite element mesh for the bistable mechanism.

<p>An example of the finite element mesh for the bistable mechanism.</p

Conceptual illustration of the cable cutting mechanism being employed as an antennae release mechanism on a cube-sat.

<p>Conceptual illustration of the cable cutting mechanism being employed as an antennae release mechanism on a cube-sat.</p