Dynamic instabilities imparted by CubeSat deployable solar panels

[摘要] 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.

[发布机构] Massachusetts Institute of Technology