The SGP4 model to calculate orbital state vectors of near-Earth satellites
Simplified perturbations models are a set of five mathematical models (SGP, SGP4, SDP4, SGP8 and SDP8) used to calculate orbital state vectors of satellites and space debris relative to the
Determines visibility times from observer location for specified period. LLA and KML output.
file the user may have. 2. Mapping toolbox and external program needed to execute distance, elevation, reckon, and azimuth functions; and plot LLA ground tracks. This script runs the SGP4 propagator
Modified SGP4 code for GPS interface
A modified version of the SGP4 code used for standard satellite orbit computation using two-line elements (TLE). The modified code outputs satellite positions and velocity in ECF coordinates and
Matlab based application to predict the orbit and track the geostationary satellites in real time.
satellites orbit are predicted/propagated using Simplified perturbations models codes (SGP4) from “Revisiting Spacetrack Report #3” and The results of the orbit prediction are displayed in different types of