Autonomous Control of Small Satellite Formations using
Differential Drag
Author(s)
Groesbeck, Daniel
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Abstract
This study develops a methodology for the autonomous control of multiple small satellites, to
include CubeSats, designed to operate in a formation or constellation in Low Earth Orbit (LEO).
The satellites are assumed to have no onboard propellant and will rely solely on changing the
orientations of the satellites, creating a differential drag force that will be the control mechanism.
The control systems that were developed account for the reduction of inter-satellite distance
drift and maneuver controls such that two satellites could change the mean relative distance
between them while not imparting an additional drift rate. These systems were developed
on the assumption of identical satellites operating in similar, near circular coplanar orbits.
Simulations were run to validate the functionality of the control systems developed and to find
optimal user defined parameters. The final simulations achieved both distance drift reduction
and inter-satellite relative distance changes
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Date
2019-05-01
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Resource Type
Text
Resource Subtype
Masters Project
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