Abstract:
A technique for satellite formation flying modelling in LEO is applied at L2.
Analytical solutions to the equations of motion of a hub satellite relative to L2 are
used to define a halo reference orbit. An expression for the gravity gradient is
obtained at the hub and the linearised equations of motion of the mirror satellites
relative to the hub are derived. The relative motion model is implemented in
Matlab/Simulink and evaluated for different initial conditions. The analytical
solutions to the equations of relative motion are derived. These and other equations
of motion are compared to the Satellite Tool Kit numerical orbit propagator.
Description:
Paper given at Dynamics and Control of Systems and Structures in
Space (DCSSS), 6th conference, Riomaggiore, Italy, July 2004
