Design and Analysis of Trajectory Calculation for Nano Satellite Orbiting in LEO

Raja Munusamy¹ , Manisha Kumari² , Jasmine Kaur³ , Utsav Nangalia⁴

Section:Research Paper, Product Type: Journal-Paper
Vol.5 , Issue.9 , pp.47-53, Sep-2019

Online published on Sep 30, 2019

Copyright © Raja Munusamy, Manisha Kumari, Jasmine Kaur, Utsav Nangalia . This is an open access article distributed under the Creative Commons Attribution License, which permits unrestricted use, distribution, and reproduction in any medium, provided the original work is properly cited.
 

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Abstract :
The space race introduced a phenomenal growth in the computation of the orbits of artificial satellites. The objective of this project is to derive an effective technique to estimate the orbital and trajectory data for the LEO Nano satellites. To design the accurate orbit and trajectory of a satellite information regarding the variables responsible for the deviation in the path of satellites. The variables that needs to be calculate to determine the position of the satellite. This can accomplished by making use of the orbit simulation software like GMAT, Orbitron and STK for acquiring the data and then incorporating the acquired data with MATLAB to get the result. The various effects on the satellite in space is slight deviation in the satellite from its orbit. To estimate the deflection from its actual coordinates to provide a relatively accurate method for the correction of the same. The purpose of research is consider three Indian Nano satellites are Jugnu, INS-1A and INS-1B. The selection of the satellite based on their efficiency and purpose of the mission. The Nano Satellites launched in space were the academic collaboration of the universities with their national space research centres for facilitation of research purpose with less expense.

Key-Words / Index Term :
Nano satellite, GMAT, Orbitron, STK, LEO

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