Скачать или смотреть Rigid-flexible coupled attitude dynamics in large reflectarray antenna on a slewing CubeSat

The structure shown is a 6U CubeSat with a 1 m^2 reflectarray antenna in a deployed configuration. The main reflectarray structure is made up of 4 booms. The flexing in those booms is modeled using a cantilever type damped oscillator model. The view is in a satellite body fixed frame. At t = 0:00, the satellite starts a 1 degree/second slewing maneuver about the [1 1 1] axis. This sets of transient oscillations in the boom like structures holding the reflectarray antenna sheet. Notice (in the top right plot) that there is a steady state bias deflection in the antenna boom locations, which indicate that the antenna is lagging behind the rigid body satellite as it slews. At t = 300 secs simulation time (0:48), the satellite slewing is hard stopped by the reaction wheels, and this sets off another set of transient oscillations in the antenna structure that settle over the next 200 seconds.