CubeSat Unfolding Solar Sail

P18101, from left to right:Eric Pareis, Michael Berezny,Victor Braescu and Andrew Lewis

The final design, when attached to a control unit, could be used forcases including studying the effects of propulsion on the sail due tophoton impact, altitude control, or attaching to space debris anddeorbiting it. In the future, this control unit, which could collectdata and control sail orientation, can be added when themechanism is integrated into a 3U CubeSat. In addition, while thefunctional prototype utilizes common materials like tape measuresand mylar blankets, the final mechanism could instead use moreexotic materials like TRAC booms and specially crafted mylarsheets, enabling scaling the design to a larger area sail as desired.

Rotating Mounting PlateThe gyroscopic mounting plate allows for

implementation of sail orientation

Geneva CamPrevents unwanted rotation in the

deployment mechanism

Simplified Frame DesignFewer individual designs and less

complicated assembly

This project aimed to create a deployable solar sailwithin a 2U CubeSat frame. This collaborative effortwith RIT’s Space Exploration team allows forreorientation of the sail after deployment, as wellas partial retraction of the sail.

Acknowledgments & Thanks:Thanks go out to Chris Leibfried, Elizabeth DeBartolo, the RIT MECE Machine Shop, as well as James Parkus, and RIT Space Exploration for their continued support of this project.

Funding provided by RIT Multidisciplinary Senior Design, RIT Space Exploration, and Boeing.

Space background image courtesy of Nova Next (PBS.org):https://www-tc.pbs.org/wgbh/nova/next/wp-content/uploads/2017/06/quantum-entanglement_2048x1152.jpg

For more in-depth information about

this project, visit the team’s Edge page

using the QR code:

Multiple test designs were constructed via 3D printing and traditionalmanufacturing methods, while the final model was constructed from 6061aluminum. Rigorous testing was done on numerous aspects of the design such assail folding patterns, boom marking methods, sail attachment points, andfunctionality of the other crucial subsystems listed below. The final frame design,which was designed in cooperation with the RIT Space Exploration team, hadwaterjet cut components, and the internal components were manufactured vianumerous methods within the RIT MECE Machine Shop.

Use Cases and Future Work

Prototyping and Testing

Performance Requirements and Concept Generation

Faculty Advisor: Mihail Barbosu | MSD Guide: Arthur North

Performance criteria included:• Sail deployment time• Ease of assembly• Manufacturing complexity• Moment generation• Volume less than 20x10x10 cm3

• Mass less than 2.66 kg

Multiple concepts were generatedfrom performance criteria, some moreexotic than others. From left to right:• Geared deployment mechanism• Spiral unfolding motorized drive• Telescoping boom design• Memory metal mesh-enforced sail

Deployment Mechanism Concept Drawings

3D Printed Deployment Mechanism Prototype Construction Process of Large Sail Quadrant

CAD Model of Final Design

Major Components of Final Design