In celestial mechanics numerical methods are widely used to solve differential equations. In this code, Runge-Kutta 4th Order method is used for numerical integration of equation of orbital motion according to Newton's law of gravitation to simulate object's trajectory around the Earth.

Inputs: Position and Velocity vector (x,y,z,vx,vy,vz)
OR
Keplerian Elements (a, e, i, Omega, w, M)
h = Step Size
steps = Number of Step
Output: Propagated Satellite PV Vector in ECI Frame of Reference

Call: [X_RK] = RK_4(X,h,steps)