  The increase in the application of the satellite has skyrocketed the number
of satellites, especially in the low earth orbit. The major concern today is
after the end of life, these satellites become debris which negatively affects
the space environment. As per the international guidelines of the European
Space Agency, it is mandatory to deorbit the satellite within 25 years of the
end of life. StudSat1, which was successfully launched on 12th July 2010, is
the first Pico satellite developed in India by undergraduate students from
seven different engineering colleges across South India. Now, the team is
developing StudSat2, which is India's first twin satellite mission having two
nanosatellites whose overall mass is less than 10kg. This paper is aimed to
design the propulsion system, cold gas thruster, to deorbit StudSat2 from its
original orbit i.e. 600 km to lower orbit i.e. 400km. The propulsion system
mainly consists of a storage tank, pipes, Convergent Divergent nozzle, and
electronic actuators. The paper also gives information about the components of
cold gas thruster, which have been designed in the CATIA V5, and the structural
and flow analysis of the same has been done in ANSYS. The concept of Hohmann
transfer has been used to deorbit the satellite and STK has been used to
simulate it.
