Cartesian to circular orbital elements
[cir,jacob] = CL_oe_car2cir(pos,vel [,mu])
Converts cartesian orbital elements to orbital elements adapted to near-circular orbits.
The transformation jacobian is optionally computed.
See Orbital elements for more details.
Position vector [x;y;z] [m] (3xN)
Velocity vector [vx;vy;vz] [m/s] (3xN)
(optional) Gravitational constant. [m^3/s^2] (default value is %CL_mu)
Orbital elements adapted to near-circular orbits [sma;ex;ey;inc;gom;pso] [m,rad] (6xN)
(optional) Transformation jacobian (See Orbital elements for more details) (6x6xN)
CNES - DCT/SB
// Example 1 pos = [7000.e3; 1000.e3; -500.e3]; vel = [1.e3; 2.e3; 7e3]; cir = CL_oe_car2cir(pos, vel); // Example 2 pos = [7000.e3; 1000.e3; -500.e3]; vel = [1.e3; 2.e3; 7e3]; [cir, jacob1] = CL_oe_car2cir(pos, vel); [pos2, vel2, jacob2] = CL_oe_cir2car(cir); pos2 - pos // => zero vel2 - vel // => zero jacob2 * jacob1 // => identity |  |  |