The Chandrayaan-3 mission, ISRO’s first successful lunar landing mission consisted of a Propulsion Module (PM) and a Lander Module (LM), with Rover accommodated inside Lander. Chandrayaan-3 Lander was a challenging mission considering the critical mission operations and stringent requirements on propulsion, structure and other bus systems of the spacecraft. The biggest challenge in this mission was to design and develop the entire satellite and conduct the sufficient ground tests within a minimal period to target the optimum launch opportunity. The configuration and panel layout design of the bus systems and the payloads posed a challenge in terms of mass optimization, thermal requirements, field of view clearances for sensors, payloads, Center of Gravity (CG) and Inertia control and the short time available for realization. The paper presents the details of the aspects considered by the Integration team for the configuration design, panel layout and development of this prestigious satellite and the strategies worked out to meet these challenges.