ETD

• circular restricted three-body problem
• lagrangian points
• leader follower
• Lissajous orbit
• Moon gravitational perturbation
• solar radiation pressure
• Spacecraft formations
• state-dependent Riccati equation control

Control of spacecraft formations around lagrangian points, particularly L2 point of the Sun-Earth system.
Classification of keywords and properties of formation paradigm are analysed, then dynamics are developed
in the circular restricted three-body problem. Formation adopt leader-follower paradigm with the leader is
positioned on a Lissajous orbit around L2 point. State-dependent Riccati equation control is applied on the
nonlinear dynamics including Moon's gravitational perturbation and solar radiation pressure disturbance.
Manoeuvres reported in simulations are relative the New Worlds Observer mission set to launch in 2020.