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

Abstract:

Article Preview

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.

Info:

Periodical:

Edited by:

Wu Fan

Pages:

4537-4543

DOI:

10.4028/www.scientific.net/AMM.110-116.4537

Citation:

H. Zhang et al., "Active Stabilization of a Two-Satellite Tether in Elliptic Orbits Using Coulomb Forces", Applied Mechanics and Materials, Vols. 110-116, pp. 4537-4543, 2012

Online since:

October 2011

Export:

Price:

$35.00

In order to see related information, you need to Login.

In order to see related information, you need to Login.