Computer Modeling Of Nanosatellite Trajectory In The Polar Coordinate System Using Matlab Interface

The present paper represents the analytical calculation and computer simulation of motion of nanosatellite that in polar system of coordinates are structured. In particular, the paper asks whether possible to simulate the problem gets the initial orbital altitude and eccentricity of trajectory. GUI in MATLAB designed to distinguish between these explanations are described. The results indicate that perigee distance, apogee distance, focal parameter, radius-vector, angle of true anomaly will change to describe trajectory of nanosatellite which is presented in 2D animation. These findings provide opportunity to calculate and model such type of problems using adapted user-friendly interface.