Auday

Phi = keplerSTM(x0,dt,mu) will return the state transition matrix Phi for a set of objects described by initial positions and velocities (x0) with gravitational parameters mu, propogated along Keplerian orbits for time dt. The positions and velocities at time dt is then given by Phi*x0. x0 must... Platforms: Matlab

NBODYVECT - Fully vectorized n-body equationnbodyVect(x0,dx0,mus,t) integrates the n-body equations of motion using either a symplectic second order integrator, or any of the standard built-in or user supplied first order integrators. x0 - 3n x 1 stacked initial position vectors:... Platforms: Matlab