CL_oe_kep2car — Keplerian to cartesian orbital elements
[pos_car,vel_car[,jacob]] = CL_oe_kep2car(kep[,mu])
The transformation jacobian is optionally computed.
keplerien parameters [a,e,i,w,omega,M] [m],[rad] (6xN)
(optional) geocentric gravitational constant. [m^3/s^2] (default value is %CL_mu)
satellite's cartesien position [rx,ry,rz] [m] (3xN)
satellite's cartesien velocity [vx,vy,vz] [m/s] (3xN)
(optional) transformation jacobian d(rx,ry,rz,vx,vy,vz)/d(a,e,i,w,omega,M) (6x6xN)