19 results

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

The SGP8 model to calculate orbital state vectors of near-Earth satellites

SGP is the first orbit propagator. It has been developed by Hilton and Kuhlman in 1966 thanks to one of Kozai's research work made in 1959. It is made for satellites orbiting near the Earth which

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

Wrapper functions to run AER codes

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

SGP4 and SDP4 orbit propagators

Propagation of the satellite's state vector using SGP4 and checking its visibility for future

Maximum-likelihood analysis of univariate isotropic Matérn random fields

MATLAB + Arduino I2C SGP30 sensor support

Support for the SGP30 eCO2 and TVOC sensorCreate an arduino object with I2C. serialDevices = serialportlist; a = arduino(serialDevices(end),'Nano3','Libraries',{'I2C'});Connecting to the

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

MATLAB scripts that can be used to calculate an a Two Line Element (TLE) from a user-provided osculating state vector or orbital elements.

be modeled using the NORAD SGP4 algorithm. Includes PDF users guide.

This repo stores the CubeSat Thermal Power Toolbox installers for MATLAB file exchange

tool currently provides options for Earth or Moon orbits.Earth orbitsPropagator options: two-body-keplerian and SGP4.Moon orbitsPropagator options: Kepler and Numerical (high precision).The Numerical

This code gives you the date vector for a given epoch of Two Line Element (TLE)data.

Some optimization algorithms for mining gradual patterns.

as sgp1. GRAdual rANKing Algorithm for GPs (GRAANK)This is the classical approach (initially proposed by Anne Laurent) for mining gradual patterns. All the remaining algorithms are variants of this

Fast particle tracking and ray-triangle intersection queries on triangular meshes of a unit sphere

coordinates', In Proceedings of the 4th Eurographics Symposium on Geometry Processing (SGP 2006), pp.81–88.LicenseMIT © 2021 Anton Semechko (a.semechko@gmail.com)

Create shadows of your data on the sides of an Axes.

details.Compute shadow projections on all 3 walls of the axes, and animate the light throughthe scene.[tri, lz] = ps2stereographicsphere(hexgrid); H=triMeshShadow3(tri, [0 0 lz

Initial orbit determination applying the Extended Kalman Filter

Angles-only approach applying the Least Squares method

Initial orbit determination applying the Least Squares method