46 results

SGP4

version 1.0.0.0

by Meysam Mahooti

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

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

Useful functions for geometry processing, constrainted optimization and image processing.

Wrapper functions to run AER codes