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A SIMPLIFIED MODEL FOR VIBRATING MASS CONTROL MOMENT GYROSCOPE
Date
2017-02-09
Author
Akbulut, Burak
Arberkli, Ferhat
Azgın, Kıvanç
Tekinalp, Ozan
Metadata
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This work is licensed under a
Creative Commons Attribution-NonCommercial-NoDerivatives 4.0 International License
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A novel satellite attitude actuator based on vibrating masses was previously proposed. Its governing equations were obtained and simulated. In this study, the resulting mathematical model is validated via energy as well as the conservation of angular momentum methods. Additionally, the mathematical model for the complete system was too complicated for analysis. In this work, a representative simplified set of equations describing vibrating mass control moment gyroscope (vCMG) dynamics in high fidelity are also obtained . It is shown that the simplified model may be used to simulate the complex vCMG dynamics under certain conditions.
Subject Keywords
Spacecraft
URI
https://hdl.handle.net/11511/55729
Conference Name
27th AAS/AIAA Space Flight Mechanics Meeting
Collections
Department of Mechanical Engineering, Conference / Seminar
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BibTeX
B. Akbulut, F. Arberkli, K. Azgın, and O. Tekinalp, “A SIMPLIFIED MODEL FOR VIBRATING MASS CONTROL MOMENT GYROSCOPE,” San Antonio, TX, 2017, vol. 160, Accessed: 00, 2020. [Online]. Available: https://hdl.handle.net/11511/55729.