The effects of the main orbital disturbances on the attitude of a small spacecraft with two large flexible appendages are discussed. Different orbital configurations were simulated with a numerical multi-body code. The panels are discretized into a number of rigid bodies, connected to each other by rotational joints, while the spacecraft is thought as a single rigid body. The simulations are performed with variable panels thickness and including a distributed control action
Dynamic analysis of thin-film solar panels on small satellites
Bettiol, Laura
2014/2015
Abstract
The effects of the main orbital disturbances on the attitude of a small spacecraft with two large flexible appendages are discussed. Different orbital configurations were simulated with a numerical multi-body code. The panels are discretized into a number of rigid bodies, connected to each other by rotational joints, while the spacecraft is thought as a single rigid body. The simulations are performed with variable panels thickness and including a distributed control actionFile in questo prodotto:
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Utilizza questo identificativo per citare o creare un link a questo documento:
https://hdl.handle.net/20.500.12608/17922