Control system design to counter the effect of tether ejection system on a nano-satellite

This paper describes the nominal control system design to counter the effect of deployment of an electro-dynamic tether on a polar low-earth orbit nano-satellite. 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. Analysis of the effect of deployment of the tether on the satellite has been described along with the controller´s ability to stabilise the satellite there after. Also described, is 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 analysed and used to evaluate the performance of the controller. All graphs pertaining to the simulations have been analysed and discussed.