<p>Operating a spacecraft in an elliptical geo transfer orbit throughout its mission life presents multiple constraints and unique operational challenges. Long-term operation at low perigee altitudes in the presence of atmospheric drag leads to sustained momentum build-up and requires carefully optimised reaction wheel momentum desaturation cycles. If perigee altitude is not maintained, atmospheric drag degrades apogee height, affecting payload visibility and mission lifetime. Reaction wheel speeds vary significantly with each perigee passage and due to external disturbances, necessitating periodic thruster operations to keep wheel speeds within design limits and ensure stable attitude. To address these complexities, operational strategies evolved from initial manual ground commands to a highly automated concept of operations with effective utilisation of onboard features. The core element is an on-board timer-driven sequence of events framework that handles key tasks such as solar array positioning at perigee, eclipse operations, automatic momentum dumping during non-visibility periods, perigee-raising maneuver and payload operations. Attitude pointing switches efficiently between inertial sun-safe mode and earth-pointed payload mode to satisfy the requirements of power, thermal, attitude and payload subsystems amidst time-varying visibility windows and frequent eclipses. Quantitative gains include reduced ground commanding, improved wheel momentum margins and preserved battery margins. The experience provides practical lessons for future satellite missions operating under non-ideal conditions and prolonged orbit raising, including missions using electric propulsion.</p>