This paper proposes a method for continuous-thrust control of satellite formations in elliptic orbits. A previously calculated Lyapunov-Floquet transformation relates the linearized equations of relative motion for elliptic chief orbits to the Hill-Clohessy-Wiltshire equations describing circular chiefs. Using a control law based on Lyapunov-Floquet theory, a time-varying feedback gain is computed that drives a deputy satellite toward rendezvous with an elliptic chief. This control law stabilizes the relative motion across a wide range of chief eccentricities.
Lyapunov-Floquet control of satellite relative motion in elliptic orbits
IEEE Transactions on Aerospace and Electronic Systems ; 51 , 4 ; 2800-2810
2015-10-01
4110931 byte
Article (Journal)
Electronic Resource
English
Lyapunov-Floquet Transformation of Satellite Relative Motion in Elliptic Orbits (AAS 13-466)
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