Chandrayaan-3 Propulsion Module Configuration

The demonstration of soft landing on lunar surface is a critical aspect for ISRO’s future inter-planetary missions. The second Indian mission to Moon, Chandrayaan-2 could not demonstrate soft landing in the final phases of its descent. Keeping this in mind, subsequently, as a follow on mission, Chandrayaan-3 was planned to achieve safe and soft landing on lunar surface, whose configuration was worked out considering the experience gained from Chandrayaan- 2 performance. The spacecraft was configured as a two-module concept; a Lander Module (LM) and a Propulsion Module (PM). Configuration of Propulsion Module was optimised with minimum essential functionality required for carrying the Lander Module to lunar orbit. This resulted in saving in mass of Propulsion Module and there by offering the saved mass to Lander for robustness building, while keeping the overall mass similar to Chandrayaan-2, thereby limiting within the LVM-3 capability. The main function of PM was to carry the LM from launch vehicle injection till LM separation. This paper brings out the overview of Propulsion Module along with the details pertaining to spacecraft configuration, brief specifications, spacecraft realisation, mission operations and mission accomplishments.