Active Stabilization of a Two-Satellite Tether in Elliptic Orbits Using Coulomb Forces

Abstract:

This paper investigates the dynamics and control of a charged two-craft tether formation in elliptical orbit. Due to the fact that the inter-spacecraft Coulomb forces are not sufficient to stabilize the tether, a method of hybrid control is proposed which uses conventional thrusts and Coulomb forces. A feedback control law is developed which could asymptotically stabilize the tether size and attitude while mitigating plume impingement issues. The equations governing this system are periodic in time, thus a feedback control using constant gains can not work. A periodic control law is suggested basing on Floquet theory. The control law consists of two main parts. First Floquet transformation is utilized to transform the system into a new linear system with a constant state matrix but a periodic control matrix. Then a feedback control is used to stabilize the new system. Numerical examples are provided to demonstrate the performance of the control law.

• Periodical: Applied Mechanics and Materials (Volumes 110-116)
• Pages: 4537-4543
• DOI: https://doi.org/10.4028/www.scientific.net/AMM.110-116.4537
• Online since: October 2011
• Authors: Hao Zhang, Yu Shan Zhao, Peng Shi
• Keywords: Coulomb Tethers, Elliptical Orbits, Formation Flying, Hybrid Control

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