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The increase in the application of the satellite has skyrocketed the numberof satellites, especially in the low earth orbit. The major concern today isafter the end of life, these satellites become debris which negatively affectsthe space environment. As per the international guidelines of the EuropeanSpace Agency, it is mandatory to deorbit the satellite within 25 years of theend of life. StudSat1, which was successfully launched on 12th July 2010, isthe first Pico satellite developed in India by undergraduate students fromseven different engineering colleges across South India. Now, the team isdeveloping StudSat2, which is India's first twin satellite mission having twonanosatellites whose overall mass is less than 10kg. This paper is aimed todesign the propulsion system, cold gas thruster, to deorbit StudSat2 from itsoriginal orbit i.e. 600 km to lower orbit i.e. 400km. The propulsion systemmainly consists of a storage tank, pipes, Convergent Divergent nozzle, andelectronic actuators. The paper also gives information about the components ofcold gas thruster, which have been designed in the CATIA V5, and the structuraland flow analysis of the same has been done in ANSYS. The concept of Hohmanntransfer has been used to deorbit the satellite and STK has been used tosimulate it.

Design of the Propulsion System of Nano satellite: StudSat2