#TITLE_ALTERNATIVE#

• Main Author: PRATIWI (NIM : 10311014); Pembimbing : Prof. Dr. Suryadi Siregar dan Dr. Ridanto Eko Poetro, NINDHITA
• Format: Final Project
• Language: Indonesia
• Online Access: https://digilib.itb.ac.id/gdl/view/20351
• Institution: Institut Teknologi Bandung

Until now, Indonesia still using TLE (Two-Line Element) from NORAD (North American Aerospace Defense Command) to know orbital element of satellite especially for position and velocity of satellite. Orbital propagation can be used to calculate the vectors of orbital satellite. Models of propagation can be used to predict the perturbation effect caused by earth's shape, atmospheric drag, radiation, Sun and Moon’s gravitation effect. <br /> <br /> <br /> STK (System Tool Kit) is geometry machine that used to determine the position of satellite as function of time. Propagators that available in STK are Two Body, J2 <br /> <br /> <br /> Perturbation, J4 Perturbation, and SGP4 (Simplified General Perturbations 4). Using STK with that propagators, we can obtain comparison of orbital element, position, velocity, and error to NORAD's TLE, so we can determine the SGP4 propagation's duration that can still be used for some kind of accuracy. Based on result, we get the conclusion that for accuration limit 25 kilometers and 60 kilometers, SGP4 propagation can still be used for maximal duration 7 days and 77 days.