Differential Drag-Based Orbital Maneuvers using Origami-Inspired Drag Area Modulation

Abstract

Thesis (Master's)--University of Washington, 2025In recent years, a surge in demand for small satellites has generated interest in propulsion-less orbital control methods—differential drag, specifically—as a way to minimize propellant usage and cost. While successful in a number of missions, present implementations typically limit this technique to an On-Off mode, which can limit maneuver flexibility and interfere with other mission requirements. This research introduces a continuous drag control system employing origami-inspired foldable structures. Such foldable panels allow for continuous modulation of the spacecraft's projected area, thus enhancing maneuver accuracy without sacrificing solar power or any other pointing related requirements. Rendezvous maneuvers between two identical satellites are designed using linear equations, with battery State-of-Charge considerations. Results indicate that continuous control leads to a significant improvement over discrete On-Off control in terms of energy consumption for control inputs, while delivering equivalent performance. Additionally, incorporating additional degrees of freedom in origami design was proposed and evaluated, which significantly improved the power levels throughout the mission. A bar-and-hinge model is utilized to simulate dynamic unfolding behavior of the origami panels, and a proportional-integral-derivative control scheme is utilized for hinge actuation to achieve desired angles. Overall, this integrated approach not only optimizes differential drag control but is an efficient design for future small satellite missions with propellant-free orbital maneuvers