Mechanism, ensuing dynamics and control of a polar low-earth orbit tethered nano-satellite

This paper describes the dynamics of a polar low earth orbit nano-satellite as a consequence of tether deployment; and the control system to counter its effect. The complete tether assembly, including the deployment mechanism, choice of material, length of the tether, preferred door axis for deployment of tether, have been explained in detail. A force sensor, to measure the forces associated with the tether deployment, has also been featured and explained. Analysis of the effect of deployment of the tether on the satellite has been described, along with the controller´s ability to stabilize the satellite thereafter. Also described are the satellite kinematics and dynamics model in space environment, to test and evaluate the performance of the controller to meet the desired stability. The results from these simulations, used to test the controller in space environment for attitude control have been analyzed and used to evaluate the performance of the controller. All graphs pertaining to the simulations have been analyzed and discussed.