Date of Award
3-2024
Document Type
Thesis
Degree Name
Master of Science
Department
Department of Aeronautics and Astronautics
First Advisor
Robert A. Bettinger, PhD
Abstract
Imaging and inspecting Resident Space Objects (RSO) have gained increasing importance in Space Situational Awareness (SSA) missions. These missions are driven by the necessity to perform satellite repairs, refueling, de-orbiting, and orbital debris reduction. However, the challenging lighting conditions in space often hinder these tasks. To overcome this challenge, a novel concept has been proposed—deploying mirrors from servicer satellites. These mirrors would harness solar energy to illuminate dimly-lit RSOs, enabling imaging, inspection, repair, and refueling operations. In this context, servicer satellites play a pivotal role in controlling the reflected light beam and precisely positioning themselves to illuminate RSOs effectively. Notably, these servicer satellites are envisioned as either 12U or 27U CubeSats, compact and versatile spacecraft. To make this concept feasible, extensive research is required to explore the application of origami techniques for folding mirrors into a compact state. Specifically, cubic or rectangular origami flashers are under consideration for CubeSat applications.
The outcomes of this research not only showcase the design, construction, and testing of an operational origami mirror membrane, but also delve into the intricacies of control design. Maintaining a specific attitude throughout a natural motion circumnavigation (NMC) orbit for SSA missions was a focal point of interest in this research. Leveraging optimal control methods for a deputy spacecraft to execute maneuvers within a 2-by-1 ellipse NMC orbit about a chief satellite. This positioning facilitates the application of the mirror and its associated control system. To achieve this, the research incorporates well-established Hill-Clohessy-Wiltshire (HCW) equations for accurately positioning a servicer satellite around an RSO in geosynchronous Earth orbit (GEO). The space-based mirror, is engineered to reflect solar energy at a precise angle. In essence, the research into the attitude controller aims to enable the illumination of an RSO from multiple angles using a servicer satellite, thus ensuring comprehensive coverage of all six sides of the RSO at distinct times. This innovation promises to significantly enhance the effectiveness of satellite mission operations.
AFIT Designator
AFIT-ENY-MS-24-M-189
Recommended Citation
Garcia, David J., "Origami Application and Attitude Control Investigation of Space-Based Mirror System" (2024). Theses and Dissertations. 7886.
https://scholar.afit.edu/etd/7886
SF298 form for AFIT-ENY-MS-24-M-189 Garcia, D.
Comments
A 12-month embargo was observed for posting this work on AFIT Scholar.
Distribution Statement A, Approved for Public Release. PA case number on file.
The SF298 form for this work is included separately below in the additional files.
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