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Design of Chemical Propellant Thruster to Deorbit Nano satellite: StudSat II

Prabin SherpailiRoshan SahSandesh HegdeBir Bahadur Chaudhary
Dec 2022
摘要
An increase in satellite application has skyrocketed the number ofsatellites, especially in the low earth orbit (LEO). The major concern today isthat these satellites become debris after the end of life, negatively affectingthe space environment. As per the International Guidelines of the EuropeanSpace Agency, it is mandatory to deorbit the satellite within 25 years of itsend of life. This paper is aimed to design the solid chemical propellantthruster to deorbit the StudSat II from its original orbit to the lower orbit.StudSat II carries the heritage of StudSat I, successfully launched on 12thJuly 2010 AD, and is the first Pico Satellite in India by the undergraduatestudents of seven engineering colleges. This paper explains how a solidmonopropellant thruster could be used to deorbit the satellite after the end oflife with the least difficulty compared to other active and passive methods ofdeorbiting. The deorbiting mechanism consists of a solid propellant, ConvergentDivergent nozzle, ignition system, and electronic actuators. The components ofthe thruster were designed in the CATIA V5, and the combustion studies and flowanalysis were done in ANSYS. The concept of Hohmann transfer was used todeorbit the satellite, and STK was used to simulate it.
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