OPTIMIZED TRAJECTORIES FOR SATELLITE FORMATION FLYING USING DIFFERENTIAL DRAG MANEUVERS
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Author
Demoss, Andrew G.
Date
2023-09Advisor
Karpenko, Mark
Minelli, Giovanni
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The demand for space capabilities is growing rapidly, and one promising approach to increase the availability of space assets quickly and cost-effectively is by deploying large numbers of small satellites that can collaborate and combine their capabilities. CubeSats, whether operating as a distributed constellation or in close swarms, have the potential to unlock new possibilities for the United States. Leveraging differential drag techniques to manage satellite formations offers several advantages, including lower production and launch costs and the utilization of readily available technologies. Implementing differential drag maneuvers presents challenges as they require a delicate balance between formation management and satellite operations. Both aspects necessitate precise attitude determination and control, which can potentially conflict with one another. Optimization techniques, such as Pontryagin's Principle, can be employed to develop trajectories for satellites and automate constellation management which could enable new applications and enhance space capabilities and capacity. This thesis demonstrates that by optimizing orbit transfer and formation flying trajectories, the duration of differential drag maneuvers can be reduced while accommodating mission requirements. It also develops tools to generate commands for satellites that would allow them to achieve the desired formation. As a result, the overall efficiency and effectiveness of CubeSats can be enhanced.
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This publication is a work of the U.S. Government as defined in Title 17, United States Code, Section 101. Copyright protection is not available for this work in the United States.Related items
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