Orbital stabilization of dynamically elongated small satellite using active magnetic attitude control

The paper proposes an algorithm for angular motion control of a dynamically elongated spacecraft. The algorithm is based on the direct Lyapunov method using matrix control coefficients. The calculated mechanical torque is implemented using a magnetic attitude control system. Control parameters are selected using Floquet theory to ensure convergence of the motion trajectory to the required one. A numerical study of controlled motion to achieve gravitational attitude equilibrium of a 3U CubeSat is carried out.