Designing Earth–observation campaigns that visit multiple ground sites from Low Earth Orbit is a balancing act between geometry, timing and propellant. This thesis proposes a practical framework to plan multi-target observations by coupling a realistic dynamical and sensing model with a multiobjective optimizer. The spacecraft motion is propagated with a secular J₂ model, observation feasibility is enforced through nadir-aligned line-of-sight and field-of-view rules with minimum observation time. Operational limits include altitude bounds, mass budget and propellant budget. Trajectory corrections are executed as high-thrust impulsive maneuvers in the RTN frame (tangential and normal components, radial set to zero by design), interspersed with coast phases.