Dynamic instabilities imparted by CubeSat deployable solar panels

Author(s)
Peters, Eric David
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Massachusetts Institute of Technology. Department of Aeronautics and Astronautics.
Advisor
Kerri Cahoy.
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Abstract
In this work, multibody dynamics simulation was used to investigate the effects of solar panel deployment on CubeSat attitude dynamics. Nominal and partial/asymmetric deployments were simulated for four different solar panel assemblies. Trend lines were obtained for the evolution of the angular velocities and accelerations of the CubeSat about its center of mass for the duration of the deployment. The partial deployment simulations shed insight into the motions that an attitude control system may need to mitigate in the event of a deployment anomaly.
Description
Thesis: S.M., Massachusetts Institute of Technology, Department of Aeronautics and Astronautics, 2014.
 
Cataloged from PDF version of thesis.
 
Includes bibliographical references (pages 85-87).
 
Date issued
2014
URI
http://hdl.handle.net/1721.1/93800
Department
Massachusetts Institute of Technology. Department of Aeronautics and Astronautics
Publisher
Massachusetts Institute of Technology
Keywords
Aeronautics and Astronautics.
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