MATLAB files and Simulink models for the course of Spacecraft Dynamics and Control, Sharif University of Technology.
This repository includes the following MATLAB script functions:
1- Fourth-order Runge-Kutta integration: "rk4.m"
2- Obtaining the inertial position and velocity vectors from classical orbital elements: "oe2rv.m"
3- Obtaining the classical orbital elements from inertial position and velocity vectors: "rv2oe.m"
4- Two-body problem (TBP) unactuated state-space model: "dyn.m"
5- Solving Kepler problem using Newton-Raphson method: "Kepler.m"
6- Simulation of unperturbed TBP: "tbp_unp.m"
7- Simulation of perturbed TBP under J2 (zonal sphere harmonics): "tbp_per1.m"
8- Simulation of perturbed TBP under J2 (zonal sphere harmonics) using approximated secular motion: "tbp_per2.m"
9- Calculation of geodetic latitude and logitude from ECEF position vector: "r2gd.m"