Mini satellite Bus is one of its kind for configuring various Micro and Mini satellites. Innovative thermal design of battery was evolved to meet the its space and power constrains of this bus. This design also aids in efficient thermo-vacuum performance of systems in the satellite. A modular thermal design for battery for this bus was evolved and presented in IHMTC-2021-623 [1]. This design has been flown in one of the latest missions of ISRO. This paper gives the thermo-vacuum performance and actual observed temperatures on-orbit for this satellite and its comparison with the estimated temperatures using thermal mathematical model for actual on-orbit condition.

This design now is validated and enables small satellites to handle larger dissipation without posing limitations from battery.