CL_oe_car2cirEqua — Cartesien to circular equatorial adapted orbital elements
[cir_equa[,jacob]]=CL_oe_car2cirEqua(pos_car,vel_car[,mu])
The transformation jacobian is optionally computed.
satellite's cartesien position [rx,ry,rz] [m] (3xN)
satellite's cartesien velocity [vx,vy,vz] [m/s] (3xN)
(optionnal) geocentric gravitational constant [m^3/s^2] (default value is %CL_mu)
circular equatorial adapted parameters [a,ex,ey,ix,iy,omega+w+M] [rad],[m] (6xN)
(optional) transformation jacobian d(rx,ry,rz,vx,vy,vz)/d(a,ex,ey,ix,iy,omega+w+M) (6x6xN)