Cartesian to circular equatorial adapted orbital elements - DEPRECATED
[cir_equa,jacob] = CL_oe_car2cirEqua(pos_car,vel_car [,mu])
This function is deprecated.
Replacement function: CL__oe_car2cireq
"cirEqua" orbital elements are identical to "cireq" orbital elements except that ix=2*sin(i/2)*cos(raan) and iy=2*sin(i/2)*sin(raan)
Converts position and velocity to orbital elements adapted to near-circular near-equatorial orbits. (elliptic orbit only)
The transformation jacobian is optionally computed.
See Orbital elements for more details
position [X;Y;Z] [m] (3xN)
velocity [Vx;Vy;Vz] [m/s] (3xN)
(optional) gravitational constant [m^3/s^2] (default value is %CL_mu)
orbital elements adapted to near-circular near-equatorial orbits. [sma;ex;ey;ix;iy;pom+raan+anm] [m,rad] (6xN)
(optional) transformation jacobian (See Orbital elements for more details) (6x6xN)
1) CNES - MSLIB FORTRAN 90, Volume V (mv_car_cir_equa)
CNES - DCT/SB