CL_oe_cirEqua2car — Circular equatorial adapted to cartesien orbital elements
[pos_car,vel_car[,jacob]]=CL_oe_cirEqua2car(cir_equa[,mu])
The transformation jacobian is also optionally computed.
circular equatorial adapted parameters [a,ex,ey,ix,iy,omega+w+M] [rad],[m] (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,ex,ey,ix,iy,omega+w+M) (6x6xN)