RECONSTRUCTION OF MARS ORBITER MISSION TRAJECTORY USING GENERAL MISSION ANALYSIS TOOL

• Main Author: Raihan Pratama, Rangga
• Format: Final Project
• Language: Indonesia
• Online Access: https://digilib.itb.ac.id/gdl/view/50047
• Institution: Institut Teknologi Bandung

Mars Orbiter Mission is a mission carried out by ISRO (India Space Research Organization) to collect atmospheric, morphological, topology, and minerals on Mars. This mission uses 6 times the Orbit Rising Maneuver before making an orbital transfer to Mars, the aim is to adjust to the ability of the thruster who is not able to at the same time encourage spacecraft to enter the hyperbolic escape path from Earth to Mars. Patched conic analysis divides the mission path into 3 phases, namely the geocentric phase includes the transfer process from the parking orbit to the hyperbolic loose cross through several times the orbit raising maneuver. The heliocentric phase starts from the time the spacecraft exits the sphere of influence of the Earth to enter the sphere of influence of Mars, assuming the Hohmann transfer. The Martian phase covers the cross of hyperbolic arrivals from spacecraft entering the sphere of influence of Mars to orbiting Mars after slowing maneuvers. In this paper, the authors conducted a study in the form of a reconstruction of the Mars Orbitter Mission trajectory using GMAT software. Furthermore, it is compared with the patched conic method and 4-body problem simulation using Simulink. The conclusion is that GMAT is a software suitable for reconstructing interplanetary missions. The cause of the error in the simulation results is that this simulation has not been able to model the entire mission properly, for example, thruster modeling, mission sequence and mission timing. GMAT provides a fuel count with an error of 7.2% and can reconstruct orbits with less than 1% error compared to mission data.