Classical Keplerian to cartesian orbital elements
[pos, vel, jacob] = CL_oe_kep2car(kep [, mu])
Converts classical Keplerian orbital elements to cartesian orbital elements.
The transformation jacobian is optionally computed.
See Orbital elements for more details.
Classical Keplerian orbital elements [sma;ecc;inc;pom;gom;anm] [m,rad] (6xN)
(optional) Gravitational constant. [m^3/s^2] (default value is %CL_mu)
Position vector [x;y;z] [m] (3xN)
Velocity vector [vx;vy;vz] [m/s] (3xN)
(optional) Transformation jacobian (See Orbital elements for more details) (6x6xN)
CNES - DCT/SB
// // Example 1 kep = [7000.e3; 0.1; 0.5; 1; 2; 3]; [pos, vel] = CL_oe_kep2car(kep); // Example 2 kep = [7000.e3; 0.1; 0.5; 1; 2; 3]; [pos, vel, jacob1] = CL_oe_kep2car(kep); [kep2, jacob2] = CL_oe_car2kep(pos, vel); kep2 - kep // => zero jacob2 * jacob1 // => identity |  |  |