2026-09-19T14:47:26Zhttps://dspace.mit.edu/server/oai/requestoai:dspace.mit.edu:1721.1/938002022-01-13T07:53:53Zcom_1721.1_7582com_1721.1_7581col_1721.1_131023
Kerri Cahoy.
Peters, Eric David
Massachusetts Institute of Technology. Department of Aeronautics and Astronautics.
Massachusetts Institute of Technology. Department of Aeronautics and Astronautics
2015-02-05T18:22:34Z
2015-02-05T18:22:34Z
2014
2014
http://hdl.handle.net/1721.1/93800
900610426
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).
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.
by Eric David Peters.
S.M.
87 pages
eng
Massachusetts Institute of Technology
M.I.T. theses are protected by copyright. They may be viewed from this source for any purpose, but reproduction or distribution in any format is prohibited without written permission. See provided URL for inquiries about permission.
http://dspace.mit.edu/handle/1721.1/7582
Aeronautics and Astronautics.
Dynamic instabilities imparted by CubeSat deployable solar panels
Thesis
application/pdf
Publication
unknown
unknown
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