Dynamic instabilities imparted by CubeSat deployable solar panels
Name
900610426-MIT.pdf
Description
Full printable version
Size
9.88 MB
Format
Adobe PDF
Checksum (MD5)
4c8549f1a899801fbb0ca0217ca0861c
Author(s)
Peters, Eric David
Advisor(s)
Kerri Cahoy.
Date Issued
2014
Publisher
Massachusetts Institute of Technology
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).
Subjects
Aeronautics and Astronautics.
MIT Department
Massachusetts Institute of Technology. Department of Aeronautics and Astronautics
Terms of Use
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.
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