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

• DOI: 10.20948/prepr-2024-5
• Publication Date: 2024-01-31T12:44:45Z
• Authors: Uliana Vladimirov...
• Keywords: 0203 mechanical engineering; 02 engineering and technology

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