The charged relative-motion dynamics and control of a two-craft system is investigated if one vehicle is performing a low-thrust orbit correction using inertial thrusters. The nominal motion is an along-track configuration where active electrostatic charge control is maintaining an attractive force between the two vehicles. In this study the charging is held fixed and the inertial thruster of the tugging vehicle is controlled to stabilize the relative motion to a nominal fixed separation distance. Using a candidate Lyapunov function, the relative orbit control law is shown to be asymptotically stable. Analysis of the control system gains is performed in order to achieve a desired settling time and damping ratio. The effects of uncertainties in the vehicle charges are also examined. Using numerical simulation, the performance of the proposed control system is investigated for a formation in geosynchronous earth orbit.
Relative Motion Control For Two-Spacecraft Electrostatic Orbit Corrections
Journal of Guidance, Control, and Dynamics ; 36 , 1 ; 240-249
2012-11-27
10 pages
Article (Journal)
Electronic Resource
English
Relative Motion Control for Two-Spacecraft Electrostatic Orbit Corrections (AAS 11-466)
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