57 resultados

The SGP4 model to calculate orbital state vectors of near-Earth satellites

Precise modeling of satellite's perturbed motion (special perturbations approach)

Solves any Lambert-problem robustly. Can be compiled to increase efficiency.

Satellite Orbits: Models, Methods and Applications

Precise modeling of satellite's perturbed motion (special perturbations approach)

Model, simulate, analyze, and visualize CubeSats using Aerospace Blockset

A program for computation an orbit of a satellite by third Kepler law.

Simulink model for Quaternion based Satellite Attitude dynamics and control

Real-Time Orbit Determination based on GPS Navigation Data

An orbit and attitude propagator for small satellites with models for control and environmental torques

Matlab based application to predict the orbit and track the geostationary satellites in real time.

Propagation of perturbed and unperturbed orbital trajectories from initial states

Lunar High precision Orbit Propagator

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

Satellite Gravity Field Missions: Simulation Scenarios

This code calculates for a given inputs the necessary DeltaV and wait time for different rendezvous which is necessary for several analysis.

How to interpret TLE and convert its unperturbed orbit into various coordinate systems.

Computation of GPS receiver position based on navigation and observation files

Angles-only approach applying the Least Squares method

Initial orbit determination applying the Extended Kalman Filter

Seven MATLAB scripts for modeling impulsive and finite-burn orbital maneuvers

Converts classical orbital elements ( Keplerian Elements ) to position and velocity elements in cartesian coordinates (Oxyz).

Satellite Propagation with Runge-Kutta 4th Order Numerical Integration Method

MATLAB script that solves the non-spherical gravity-perturbed two impulse Hohmann orbit transfer problem.

MATLAB script named satplot.m that demonstrates how to graphically display satellite ground tracks and orbits.

Initial orbit determination applying the Least Squares method

MATLAB script for the solution of the one and two impulse orbit transfer between two Earth orbits.

Computation of state transition matrix for desired degree and order of gravity field of the Earth.

OTB/fsolve version of the lambert4.m MATLAB script which solves the gravity-perturbed Lambert problem

Orbit Determination from Tracking and Data Relay Satellite Measurements

A function to create an animation of the GPS constellation and working principle (pedagogic purpose).

Optimization Toolbox version of the tlto_matlab script used to design preliminary lunar missions from Earth park orbit to B-plane encounter.

Function designed to be used by Mat-lab's ode45 for gravity simulation of a projectile being affected by the Earth and the Moon's gravity

The NASA Calipso model is converted here to wavefront obj format and displayed using trisurf and materials.

Satellite Orbits: Models, Methods and Applications

Computation of GPS broadcast orbits from RINEX navigation file

A Matlab code for Multispectral Satellite Image Mapping using K Means

Optimization Toolbox version of a MATLAB script that can be used to model finite-burn interplanetary injection from a circular Earth orbit.

Optimal two impulse transfer subject to non-spherical gravity perturbations - Optimization Toolbox version

Graphical User Interface (GUI) for simulating and visualizing Keplerian satellite orbits.

Makes use of Runge-Kutta 4 method and J2 Earth Model

Optimization Toolbox version of the lambert4.m MATLAB script which solves the gravity-perturbed Lambert problem

Optimization Toolbox version of the deorbit.m MATLAB script which determines optimal de-orbit maneuvers.

Simulation of projectile motion using orbital mechanics. Note: must also be used with earth_moon_orbit_ode45.

The program calculates magnetic field over satellite orbit. It uses orbit parameters as input and gives out magnetic field components.

Simulation of projectile motion and orbital mechanics using both the Classical 4th Order Runge-Kutta method and Euler's Method

Real time simulator for visibility prediction of GPS satellites

Matlab can be used to plot the orbits designed for Satellite trajectory using Kepler Initial Conditions ....distance, angle, velocity

Gives an overview of the time spend in- and outside the SAA given a certain orbit.

3D GDOP, Visibility and Constellation

This function provides a quick calculation of a satellite LLA from Kepler elements

Initial orbit determination (two sets of range and angle measurements of a satellite)

optimal impulsive maneuver required to de-orbit a spacecraft in a circular or elliptical Earth orbit

Trade-off analysis of an antenna repointing system for computing accurate time budgets during fly-by.

Optimization Toolbox version of the hyper2.m MATLAB script which determines the characteristics of hyperbolic injection.

A back-of-envelop (K14 education) model of the Microsat-R debris is presented with Gabbard Diagram of TLE and model orbital properties.

Satellite Constellation of 31 Satellites for time duration of 24 hours.