Date of Award

3-2025

Document Type

Thesis

Degree Name

Master of Science in Astronautical Engineering

Department

Department of Aeronautics and Astronautics

First Advisor

Robert A. Bettinger, PhD

Abstract

The space environment’s suboptimal lighting conditions and eclipse periods impede inspection and on-orbit servicing missions. To abate this problem, the Air Force Institute of Technology (AFIT) launched the Mirror Illumination for Reconnaissance and Rendezvous of Orbital Resident Systems (MIRRORS) initiative. This initiative provides augmented illumination to resident space objects (RSOs) by reflecting the sun’s rays from a mirror satellite. Leveraging origami-inspired designs for compact packaging, AFIT developed a cube origami flasher mirror constructed from aluminum panels that unfolds passively via Nitinol hinges. This research investigates the necessary deployment and panning mechanisms for a dynamic, space-based origami mirror to advance the MIRRORS initiative. Considering the stringent volume constraints of small satellites, the deployment mechanism was restricted to a 2U (2000 cm3 ) volume within a 6U CubeSat. This research presents a hinge deployment mechanism developed through iterative design to satisfy mission requirements and comply with NASA’s General Environmental Verification Standards (GEVS), which stipulate that resonant modes must exceed 70 Hz to prevent damage during launch. Computer-aided design (CAD) and finite element analysis (FEA) confirmed a first resonant frequency of 194.74 Hz, demonstrating the mechanism’s structural integrity. Event tree analysis was conducted to identify potential failure modes and critical components, thereby informing risk mitigation strategies for effective illumination of RSOs. Functional prototype tests demonstrated successful deployment from a CubeSat chassis and a panning range of up to 13◦ to direct reflected sunlight toward an RSO at distances up to 4 m. Furthermore, torque and power draw estimates were performed to inform future mission planning. Finally, mission simulations with RSO-to-MIRRORS CubeSat distances ranging from 12 to 22 meters confirmed that the RSO’s irradiance is adequate for detection by the onboard visible light camera. The results also identified scenarios where the MIRRORS CubeSat should mitigate overexposure to prevent potential damage to the optical system. Overall, this research provides a compelling proof of concept for a hinge deployment mechanism, advancing the capability for on-orbit servicing and inspection of RSOs through augmented illumination.

AFIT Designator

AFIT-ENY-MS-25-M-145

DTIC Accession Number

AD1356376

Comments

An embargo was observed for posting this thesis.

Distribution A: Approved for Public Release, Distribution Unlimited.

PA clearance case 88ABW-2025-0559

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