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.